A report on the 2014 outfield variety tests

USDA-ARS?s Scientific Manuscript database

Outfield variety tests are conducted each year on grower farms that represent different regions and soils of the Louisiana sugarcane industry. These tests are carried out during the final three years of a 12 year Louisiana sugarcane variety development program and include recommended commercial vari...

Preflight transient dynamic analyses of B-52 aircraft carrying Space Shuttle solid rocket booster drop-test vehicle

NASA Technical Reports Server (NTRS)

Ko, W. L.; Schuster, L. S.

1984-01-01

This paper concerns the transient dynamic analysis of the B-52 aircraft carrying the Space Shuttle solid rocket booster drop test vehicle (SRB/DTV). The NASA structural analysis (NASTRAN) finite element computer program was used in the analysis. The B-52 operating conditions considered for analysis were (1) landing and (2) braking on aborted takeoff runs. The transient loads for the B-52 pylon front and rear hooks were calculated. The results can be used to establish the safe maneuver envelopes for the B-52 carrying the SRB/DTV in landings and brakings.

Pre-flight transient dynamic analysis of B-52 carrying Space Shuttle solid rocket booster drop-test vehicle

NASA Technical Reports Server (NTRS)

Ko, W. L.; Schuster, L. S.

1983-01-01

This paper concerns the transient dynamic analysis of the B-52 aircraft carrying the Space Shuttle solid-rocket booster drop-test vehicle (SRB/DTV). The NASA structural analysis (NASTRAN) finite-element computer program was used in the analysis. The B-52 operating conditions considered for analysis were (1) landing and (2) braking on aborted takeoff runs. The transient loads for the B-52 pylon front and rear hooks were calculated. The results can be used to establish the safe maneuver envelopes for the B-52 carrying the SRB/DTV in landings and brakings.

Introduction of the 2007-2008 JOGMEC/NRCan/Aurora Mallik Gas Hydrate Production Research Program, NWT, Canada

NASA Astrophysics Data System (ADS)

Yamamoto, K.; Dallimore, S. R.; Numasawa, M.; Yasuda, M.; Fujii, T.; Fujii, K.; Wright, J.; Nixon, F.

2007-12-01

Japan Oil, Gas and Metals National Corporation (JOGMEC) and Natural Resource Canada (NRCan) have embarked on a new research program to study the production potential of gas hydrates. The program is being carried out at the Mallik gas hydrate field in the Mackenzie Delta, a location where two previous scientific investigations have been carried in 1998 and 2002. In the 2002 program that was undertaken by seven partners from five countries, 468m3 of gas flow was measured during 124 hours of thermal stimulation using hot warm fluid. Small-scale pressure drawdown tests were also carried out using Schlumberger's Modular Dynamics Tester (MDT) wireline tool, gas flow was observed and the inferred formation permeabilities suggested the possible effectiveness of the simple depressurization method. While the testing undertaken in 2002 can be cited as the first well constrained gas production from a gas hydrate deposit, the results fell short of that required to fully calibrate reservoir simulation models or indeed establish the technical viability of long term production from gas hydrates. The objectives of the current JOGMEC/NRCan/Aurora Mallik production research program are to undertake longer term production testing to further constrain the scientific unknowns and to demonstrate the technical feasibility of sustained gas hydrate production using the depressurization method. A key priority is to accurately measure water and gas production using state-of-art production technologies. The primary production test well was established during the 2007 field season with the re-entry and deepening of JAPEX/JNOC/GSC Mallik 2L-38 well, originally drilled in 1998. Production testing was carried out in April of 2007 under a relatively low drawdown pressure condition. Flow of methane gas was measured from a 12m perforated interval of gas-hydrate-saturated sands from 1093 to 1105m. The results establish the potential of the depressurization method and provide a basis for future prolonged testing planned in the near future. The authors acknowledge the Research Consortium for Methane Hydrate Resources in Japan (MH21), the Ministry of Economy, Trade and Industry (METI) and NRCan for the support and funding. The Mallik 2002 program was undertaken jointly by JNOC, NRCan, GeoForschungsZentrum Potsdam (GFZ), the United State Geological Survey (USGS), the United States Department of Energy (USDOE), the India Ministry of Petroleum and Natural Gas (MOPNG)-Gas Authority of India (GAIL), and the BP-Chevron Texaco Mackenzie Delta Joint Venture.

Commerical Crew Program - SpaceX

NASA Image and Video Library

2014-05-21

A SpaceX SuperDraco engine is hot-fired at the company's test facility in McGregor, Texas. SpaceX is developing its Crew Dragon spacecraft and Falcon 9 rocket in partnership with NASA’s Commercial Crew Program to carry astronauts to and from the International Space Station.

The General Aviation Propulsion (GAP) Program

NASA Technical Reports Server (NTRS)

2008-01-01

The General Aviation Propulsion (GAP) Program Turbine Engine Element focused on the development of an advanced small turbofan engine. Goals were good fuel consumption and thrust-to-weight ratio, and very low production cost. The resulting FJX-2 turbofan engine showed the potential to meet all of these goals. The development of the engine was carried through to proof of concept testing of a complete engine system. The proof of concept engine was ground tested at sea level and in altitude test chambers. A turboprop derivative was also sea-level tested.

EVALUATION REPORT SCIENCE APPLICATIONS INTERNATIONAL CORPORATION S-CAD CHEMICAL AGENT DETECTION SYSTEM

EPA Science Inventory

The USEPA's National Homeland Security Research Center (NHSRC)Technology Testing and Evaluation Program (TTEP) is carrying out performance tests on homeland security technologies. Under TTEP, Battelle recently evaluated the performance of the Science Applications International Co...

A Comprehensive Well Testing Implementation during Exploration Phase in Rantau Dedap, Indonesia

NASA Astrophysics Data System (ADS)

Humaedi, M. T.; Alfiady; Putra, A. P.; Martikno, R.; Situmorang, J.

2016-09-01

This paper describes the implementation of comprehensive well testing programs during the 2014-2015 exploration drilling in Rantau Dedap Geothermal Field. The well testing programs were designed to provide reliable data as foundation for resource assessment as well as useful information for decision making during drilling. A series of well testing survey consisting of SFTT, completion test, heating-up downhole logging, discharge test, chemistry sampling was conducted to understand individual wells characteristics such as thermodynamic state of the reservoir fluid, permeability distribution, well output and fluid chemistry. Furthermore, interference test was carried out to investigate the response of reservoir to exploitation.

1980-1981 Evaluation Findings.

ERIC Educational Resources Information Center

Austin Independent School District, TX. Office of Research and Evaluation.

This volume summarizes the results of evaluation and testing activities carried out in the Austin, Texas, Independent School District (AISD) during the 1980-81 school year. The text consists of five parts: Section one highlights important findings in the areas of Title I Schoolwide Projects, compensatory programs, early childhood programs,…

Commerical Crew Program - SpaceX

NASA Image and Video Library

2018-01-02

A SpaceX Merlin engine is on a test stand at the company's facility in McGregor, Texas. SpaceX is developing its Crew Dragon spacecraft and Falcon 9 rocket in partnership with NASA’s Commercial Crew Program to carry astronauts to and from the International Space Station.

Environmental impact studies for gas hydrate production test in the Ulleung Basin, East Sea of Korea

NASA Astrophysics Data System (ADS)

Ryu, Byong-Jae

2017-04-01

To develop potential future energy resources, the Korean National Gas Hydrate Program has been carried out since 2005. The program has been supported by the Ministry of Trade, Industry and Energy (MOTIE), and carried out by the Korea Institute of Geoscience and Mineral Resources (KIGAM), the Korea Gas Corporation (KOGAS) and the Korea National Oil Corporation (KNOC) under the management of Gas Hydrate R&D Organization (GHDO). As a part of this national program, geophysical surveys, geological studies on gas hydrates and two deep drilling expeditions were performed. Gas hydrate-bearing sand layers suitable for production using current technologies were found during the Second Ulleung Basin Gas Hydrate Drilling Expedition (UBGH2) in 2010. Environmental impact studies (EIS) also have been carried out since 2012 by KIGAM in cooperation with domestic and foreign universities and research organizations to ensure safe production test that will be performed in near future. The schedule of production test is being planned. The EIS includes assessment of environmental risks, examination on domestic environmental laws related with production test, collection of basic oceanographic information, and baseline and monitoring surveys. Oceanographic information and domestic environmental laws are already collected and analyzed. Baseline survey has been performed using the in-house developed system, KIGAM Seafloor Observation System (KISOS) since 2013. It will also be performed. R/V TAMHAE II of KIGAM used for KISOS operation. As a part of this EIS, pseudo-3D Chirp survey also was carried out in 2014 to determine the development of fault near the potential testing site. Using KIGAM Seafloor Monitoring System (KIMOS), monitoring survey is planned to be performed from three month before production test to three months after production test. The geophysical survey for determining the change of gas hydrate reservoirs and production-efficiency around the production well would also be conducted before and after the production test. KIMOS will be developed as the planning that was drawn up already. A period for monitoring survey and geophysical survey type, such as AUV or EM surveys will be decided according to the budget.

Safety and Abuse Testing of Energizer LiFeS2 AA Cells

NASA Technical Reports Server (NTRS)

Jeevarajan, Judith A.; Baldwin, Laura; Bragg, Bobby J.

2003-01-01

The LiFeS2 test program was part of the study on state-of-the-art batteries/cells available in the commercial market. It was carried out in an effort to replace alkaline AA cells for Shuttle and Station applications. A large number of alkaline cells are used for numerous Shuttle and Station applications as loose cells. Other government agencies reported good performance and abuse tolerance of the AA LiFeS2 cells. In this study, only abuse testing was performed on the cells to determine their tolerance. The tests carried out were over-discharge, external short circuit, heat-to-vent, vibration and drop.

MLP-1 on Crawler Transporter 2 (CT-2)

NASA Image and Video Library

2017-03-22

NASA's upgraded crawler-transporter 2 (CT-2), carrying mobile launcher platform 1, moves slowly along the crawlerway toward the Vehicle Assembly Building at the agency's Kennedy Space Center in Florida. The crawler's upgrades and modifications were monitored and tested during a loaded test to the crawlerway Pad A/B split. CT-2 will return to the crawler yard. The crawler is being tested to confirm it is ready to support the load of the mobile launcher carrying the Space Launch System with Orion atop for the first test flight, Exploration Mission 1. The Ground Systems Development and Operations Program at Kennedy is managing upgrades to the crawler.

Eighteenth Space Simulation Conference: Space Mission Success Through Testing

NASA Technical Reports Server (NTRS)

Stecher, Joseph L., III (Compiler)

1994-01-01

The Institute of Environmental Sciences' Eighteenth Space Simulation Conference, 'Space Mission Success Through Testing' provided participants with a forum to acquire and exchange information on the state-of-the-art in space simulation, test technology, atomic oxygen, program/system testing, dynamics testing, contamination, and materials. The papers presented at this conference and the resulting discussions carried out the conference theme 'Space Mission Success Through Testing.'

20th Space Simulation Conference: The Changing Testing Paradigm

NASA Technical Reports Server (NTRS)

Stecher, Joseph L., III (Compiler)

1998-01-01

The Institute of Environmental Sciences' Twentieth Space Simulation Conference, "The Changing Testing Paradigm" provided participants with a forum to acquire and exchange information on the state-of-the-art in space simulation, test technology, atomic oxygen, program/system testing, dynamics testing, contamination, and materials. The papers presented at this conference and the resulting discussions carried out the conference theme "The Changing Testing Paradigm."

20th Space Simulation Conference: The Changing Testing Paradigm

NASA Technical Reports Server (NTRS)

Stecher, Joseph L., III (Compiler)

1999-01-01

The Institute of Environmental Sciences and Technology's Twentieth Space Simulation Conference, "The Changing Testing Paradigm" provided participants with a forum to acquire and exchange information on the state-of-the-art in space simulation, test technology, atomic oxygen, program/system testing, dynamics testing, contamination, and materials. The papers presented at this conference and the resulting discussions carried out the conference theme "The Changing Testing Paradigm."

Cryo-Vacuum Testing of the JWST Integrated Science Instrument Module

NASA Technical Reports Server (NTRS)

Kimble, Randy A.; Vila, M. Begona; Van Campen, Julie M.; Birkmann, Stephen M.; Comber, Brian J.; Fatig, Curtis C.; Glasse, Alistair C. H.; Glazer, Stuart D.; Kelly, Douglas M.; Mann, Steven D.;

Results of the 1980 NASA/JPL balloon flight solar cell calibration program

NASA Technical Reports Server (NTRS)

Seaman, C. H.; Weiss, R. S.

1981-01-01

Thirty-eight modules were carried to an altitude of about 36 kilometers. In addition to the cell calibration program, an experiment to evaluate the calibration error versus altitude was performed. The calibrated cells can be used as reference standards in simulator testing of cells and arrays.

76 FR 21422 - Reports, Forms, and Record Keeping Requirements

Federal Register 2010, 2011, 2012, 2013, 2014

2011-04-15

...-occurring event), the interviews will follow a test- control design where they are administered during the... multiple locations designed to reduce impaired motorcycle riding. NHTSA anticipates that the programs will... in up to 4 program sites, and in up to 2 control sites not carrying out an intervention. Motorcycle...

Research in Language Assessment

ERIC Educational Resources Information Center

Knoch, Ute

2017-01-01

Since its inception in 1990, the Language Testing Research Centre (LTRC) at the University of Melbourne has earned an international reputation for its work in the areas of language assessment and testing as well as program evaluation. The mission of the centre is: (1) to carry out and promote research and development in language testing; (2) to…

PHENIX Muon Piston Calorimeter (MPC) APD and Prototype MPC Extension (MPC-EX) Tests

DOE Office of Scientific and Technical Information (OSTI.GOV)

Lajoie, John

2013-06-20

This is a technical scope of work (TSW) between the Fermi National Accelerator Laboratory (Fermilab) and the experimenters of Muon Piston Calorimeter Extension (MPC-EX) Collaboration who have committed to participate in beam tests to be carried out during the 2013- 2014 Fermilab Test Beam Facility program.

NASA mobile satellite program

NASA Technical Reports Server (NTRS)

Knouse, G.; Weber, W.

1985-01-01

A three phase development program for ground and space segment technologies which will enhance and enable the second and third generation mobile satellite systems (MSS) is outlined. Phase 1, called the Mobile Satellite Experiment (MSAT-X), is directed toward the development of ground segment technology needed for future MSS generations. Technology validation and preoperational experiments with other government agencies will be carried out during the two year period following launch. The satellite channel capacity needed to carry out these experiments will be obtained from industry under a barter type agreement in exchange for NASA provided launch services. Phase 2 will develop and flight test the multibeam spacecraft antenna technology needed to obtain substantial frequency reuse for second generation commercial systems. Industry will provide the antenna, and NASA will fly it on the Shuttle and test it in orbit. Phase 3 is similar to Phase 2 but will develop an even larger multibeam antenna and test it on the space station.

NASA mobile satellite program

NASA Astrophysics Data System (ADS)

Knouse, G.; Weber, W.

1985-04-01

A three phase development program for ground and space segment technologies which will enhance and enable the second and third generation mobile satellite systems (MSS) is outlined. Phase 1, called the Mobile Satellite Experiment (MSAT-X), is directed toward the development of ground segment technology needed for future MSS generations. Technology validation and preoperational experiments with other government agencies will be carried out during the two year period following launch. The satellite channel capacity needed to carry out these experiments will be obtained from industry under a barter type agreement in exchange for NASA provided launch services. Phase 2 will develop and flight test the multibeam spacecraft antenna technology needed to obtain substantial frequency reuse for second generation commercial systems. Industry will provide the antenna, and NASA will fly it on the Shuttle and test it in orbit. Phase 3 is similar to Phase 2 but will develop an even larger multibeam antenna and test it on the space station.

Multipactor Physics, Acceleration, and Breakdown in Dielectric-Loaded Accelerating Structures

DOE Office of Scientific and Technical Information (OSTI.GOV)

Fischer, Richard P.; Gold, Steven H.

2016-07-01

The objective of this 3-year program is to study the physics issues associated with rf acceleration in dielectric-loaded accelerating (DLA) structures, with a focus on the key issue of multipactor loading, which has been found to cause very significant rf power loss in DLA structures whenever the rf pulsewidth exceeds the multipactor risetime (~10 ns). The experiments are carried out in the X-band magnicon laboratory at the Naval Research Laboratory (NRL) in collaboration with Argonne National Laboratory (ANL) and Euclid Techlabs LLC, who develop the test structures with support from the DoE SBIR program. There are two main elements inmore » the research program: (1) high-power tests of DLA structures using the magnicon output (20 MW @11.4 GHz), and (2) tests of electron acceleration in DLA structures using relativistic electrons from a compact X-band accelerator. The work during this period has focused on a study of the use of an axial magnetic field to suppress multipactor in DLA structures, with several new high power tests carried out at NRL, and on preparation of the accelerator for the electron acceleration experiments.« less

TECHNOLOGY EVALUATION REPORT CEREX ENVIRONMENTAL SERVICES UV HOUND POINT SAMPLE AIR MONITOR

EPA Science Inventory

The USEPA's National Homeland Security Research Center (NHSRC) Technology Testing and Evaluation Program (TTEP) is carrying out performance tests on homeland security technologies. Under TTEP, Battelle evaluated the performance of the Cerex UV Hound point sample air monitor in de...

Investigation of the applicability of intrusion technology to estimate the resilient modulus of subgrade soil.

DOT National Transportation Integrated Search

2000-04-01

An innovative and simple approach is presented for estimation of the resilient modulus of subgrade soils utilizing the cone penetration test. Field and laboratory testing programs were carried out at seven sites that comprise three common soil types ...

Orion EFT-1 Heat Shield Move from LASF to VAB Highbay 2

NASA Image and Video Library

2017-04-26

A flatbed truck carrying the Orion heat shield from Exploration Flight Test-1, prepares to back into High Bay 2 in the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. The heat shield was moved from the Launch Abort System Facility. The heat shield is being transferred from the Orion Program to the Ground Systems Development and Operations Program, Landing and Recovery Operations. In the VAB, the heat shield will be integrated with the Orion ground test article and used for future underway recovery testing.

Orion EFT-1 Heat Shield Move from LASF to VAB Highbay 2

NASA Image and Video Library

2017-04-26

A flatbed truck carrying the Orion heat shield from Exploration Flight Test-1, backs into High Bay 2 in the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. The heat shield was moved from the Launch Abort System Facility. The heat shield is being transferred from the Orion Program to the Ground Systems Development and Operations Program, Landing and Recovery Operations. In the VAB, the heat shield will be integrated with the Orion ground test article and used for future underway recovery testing.

The Secrets of Taking Any Test: Learn the Techniques Successful Test-Takers Know. The Basics Made Easy...in 20 Minutes a Day.

ERIC Educational Resources Information Center

Meyers, Judith N.

The test-preparation program in this guide covers all forms of test taking to help students deal with real-world problems like test anxiety and insufficient preparation time. The chapters are: (1) "Finding Out about the Tests You Must Take"; (2) "Making a Study Plan"; (3) "Carrying Out Your Study Plan"; (4) "Learning Strategies"; (5) "Coping with…

Log-normal spray drop distribution...analyzed by two new computer programs

Treesearch

Gerald S. Walton

1968-01-01

Results of U.S. Forest Service research on chemical insecticides suggest that large drops are not as effective as small drops in carrying insecticides to target insects. Two new computer programs have been written to analyze size distribution properties of drops from spray nozzles. Coded in Fortran IV, the programs have been tested on both the CDC 6400 and the IBM 7094...

M2-F2 Lifting Body being Carried Aloft by B-52 Mothership

NASA Technical Reports Server (NTRS)

1966-01-01

The M2-F2 Lifting Body is shown here being carried aloft by the Air Force's B-52 (tail number 003) prior to a research launch. The success of Dryden's 'homebuilt' M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies--the M2-F2 and the HL-10, both built by the Northrop Corporation. The 'M' refers to 'manned' and 'F' refers to 'flight' version. 'HL' comes from 'horizontal landing.' The first flight of the M2-F2--which looked much like the 'F1'--was on July 12, 1966. Milt Thompson was the pilot. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During the X-15 and Lifting-Body programs, another B-52, tail number 003, also served as a launch aircraft. During those programs, both B-52s were operated by the Air Force, NASA's partner in both programs. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

ATLAS Large Scale Thin Gap Chambers

DOE Office of Scientific and Technical Information (OSTI.GOV)

Soha, Aria

This is a technical scope of work (TSW) between the Fermi National Accelerator Laboratory (Fermilab) and the experimenters of the ATLAS sTGC New Small Wheel collaboration who have committed to participate in beam tests to be carried out during the FY2014 Fermilab Test Beam Facility program.

Cryo-vacuum testing of the JWST Integrated Science Instrument Module (SPIE)

NASA Technical Reports Server (NTRS)

Kimble, Randy A.; Vila, M. Begona; Van Campen, Julie; Birkmann, Stephan M.; Comber, Brian J.; Fatig, Curtis C.; Glasse, Alistair C. H.; Glazer, Stuart D.; Kelly, Douglas M.; Mann, Steven D.;

Results of the 1984 NASA/JPL balloon flight solar cell calibration program

NASA Technical Reports Server (NTRS)

Downing, R. G.; Weiss, R. S.

1984-01-01

The 1984 solar cell calibration balloon flight was successfully completed on July 19, meeting all objectives of the program. Thirty-six modules were carried to an altitude of 36.0 kilometers. The calibrated cells can now be used as reference standards in simulator testing of cells and arrays.

Results of the 1986 NASA/JPL Balloon Flight Solar Calibration Program

NASA Technical Reports Server (NTRS)

Anspaugh, B. E.; Weiss, R. S.

1986-01-01

The 1986 solar cell calibration balloon flight was successfully completed on July 15, 1986, meeting all objectives of the program. Thirty modules were carried to an altitude of 118,000 ft (36.0 km). The calibrated cells can now be used as reference standards in simulator testing of cells and arrays.

Results of the 1982 NASA/JPL balloon flight solar cell calibration program

NASA Technical Reports Server (NTRS)

Downing, R. G.; Weiss, R. S.

1983-01-01

The 1982 solar cell calibration balloon flight was successfully completed on July 21, meeting all objectives of the program. Twenty-eight modules were carried to an altitude of 36.0 kilometers. The calibrated cells can now be used as reference standards in simulator testing of cells and arrays.

Proton Exchange Membrane Fuel Cell Engineering Model Powerplant. Test Report: Benchmark Tests in Three Spatial Orientations

NASA Technical Reports Server (NTRS)

Loyselle, Patricia; Prokopius, Kevin

2011-01-01

Proton exchange membrane (PEM) fuel cell technology is the leading candidate to replace the aging alkaline fuel cell technology, currently used on the Shuttle, for future space missions. This test effort marks the final phase of a 5-yr development program that began under the Second Generation Reusable Launch Vehicle (RLV) Program, transitioned into the Next Generation Launch Technologies (NGLT) Program, and continued under Constellation Systems in the Exploration Technology Development Program. Initially, the engineering model (EM) powerplant was evaluated with respect to its performance as compared to acceptance tests carried out at the manufacturer. This was to determine the sensitivity of the powerplant performance to changes in test environment. In addition, a series of tests were performed with the powerplant in the original standard orientation. This report details the continuing EM benchmark test results in three spatial orientations as well as extended duration testing in the mission profile test. The results from these tests verify the applicability of PEM fuel cells for future NASA missions. The specifics of these different tests are described in the following sections.

Test devices for aeronautical research and technology

NASA Technical Reports Server (NTRS)

1985-01-01

The objectives of the DFVLR in six areas are described: (1) transportation and communication systems; (2) aircraft, space technology, (4) remote sensing, (5) energy and propulsion technology; and (6) research and development. A detailed description of testing devices and other facilities required to carry out the research program is given.

Testing and development of electric vehicle batteries for EPRI Electric Transportation Program

NASA Astrophysics Data System (ADS)

1985-11-01

Argonne National Laboratory conducted an electric-vehicle battery testing and development program for the Electric Power Research Institute. As part of this program, eighteen battery modules previously developed by Johnson Controls, Inc. were tested. This type of battery (EV-2300 - an improved state-of-the-art lead-acid battery) was designed specifically for improved performance, range, and life in electric vehicles. In order to obtain necessary performance data, the batteries were tested under various duty cycles typical of normal service. This program, supported by the Electric Power Research Institute, consisted of three tasks: determination of the effect of cycle life vs peak power and rest period, determination of the impact of charge method on cycle life, and evaluation of the EV-2300 battery system. Two supporting studies were also carried out: one on thermal management of electric-vehicle batteries and one on enhanced utilization of active material in lead-acid batteries.

Space simulation techniques and facilities for SAX STM test campaign

NASA Technical Reports Server (NTRS)

Giordano, Pietro; Raimondo, Giacomo; Messidoro, Piero

1994-01-01

SAX is a satellite for X-Ray astronomy. It is a major element of the overall basic Science Program of the Italian Space Agency (ASI) and is being developed with the contribution of the Netherlands Agency for Aerospace Programs (NIVR). The scientific objectives of SAX are to carry out systematic and comprehensive observations of celestial X-Ray sources over the 0.1 - 300 KeV energy range with special emphasis on spectral and timing measurements. The satellite will also monitor the X-Ray sky to investigate long-term source variability and to permit localization and study of X-Ray transients. Alenia Spazio is developing the satellite that is intended for launch in the second half of 1995 in a low, near-equatorial Earth orbit. At system level a Structural Thermal Model (STM) has been conceived to verify the environmental requirements by validating the mechanical and thermal analytical models and qualifying satellite structure and thermal control. In particular, the following tests have been carried out in Alenia Spazio, CEA/CESTA and ESTEC facilities: Modal Survey, Centrifuge, Acoustic, Sinusoidal/Random Vibration and Thermal Balance. The paper, after a short introduction of the SAX satellite, summarizes the environmental qualification program performed on the SAX STM. It presents test objectives, methodologies and relevant test configurations. Peculiar aspects of the test campaign are highlighted. Problems encountered and solutions adopted in performing the tests are described as well. Furthermore, test results are presented and assessed.

[Validation of three screening tests used for early detection of cervical cancer].

PubMed

Rodriguez-Reyes, Esperanza Rosalba; Cerda-Flores, Ricardo M; Quiñones-Pérez, Juan M; Cortés-Gutiérrez, Elva I

2008-01-01

to evaluate the validity (sensitivity, specificity, and accuracy) of three screening methods used in the early detection of the cervical carcinoma versus the histopathology diagnosis. a selected sample of 107 women attended in the Opportune Detection of Cervicouterine Cancer Program in the Hospital de Zona 46, Instituto Mexicano del Seguro Social in Durango, during the 2003 was included. The application of Papa-nicolaou, acetic acid test, and molecular detection of human papillomavirus, and histopatholgy diagnosis were performed in all the patients at the time of the gynecological exam. The detection and tipification of the human papillomavirus was performed by polymerase chain reaction (PCR) and analysis of polymorphisms of length of restriction fragments (RFLP). Histopathology diagnosis was considered the gold standard. The evaluation of the validity was carried out by the Bayesian method for diagnosis test. the positive cases for acetic acid test, Papanicolaou, and PCR were 47, 22, and 19. The accuracy values were 0.70, 0.80 and 0.99, respectively. since the molecular method showed a greater validity in the early detection of the cervical carcinoma we considered of vital importance its implementation in suitable programs of Opportune Detection of Cervicouterino Cancer Program in Mexico. However, in order to validate this conclusion, cross-sectional studies in different region of country must be carried out.

Research of advanced techniques for X-ray detectors and telescopes with applications to rockets and the LAMAR facility

NASA Technical Reports Server (NTRS)

Gorenstein, P.

1985-01-01

A program for the development of high throughput instrumentation for X-ray astronomy based upon focusing optics is being carried out by the Smithsonian Astrophysical Observatory. The instrumentation is applicable to investigations requiring large area focusing optics for direct imaging or dispersive spectroscopy. The long range goals of this program are the development of telescopes and gratings for future major X-ray astronomy facilities, including additions to the LAMAR OSS-2/SHEAL experiment after the initial flights. Tests of the devices and their more immediate utilization in scientific investigations can be carried out with SPARTAN payloads deployed and retrieved by the Space Shuttle. However, the present backlog of approved SPARTAN missions is longer than the three-year duration of the program described in this program. Laboratory studies and breadboarding of instrumentation are discussed.

Results of the 1987 NASA/JPL balloon flight solar cell calibration program

NASA Technical Reports Server (NTRS)

Anspaugh, B. E.; Weiss, R. S.

1987-01-01

The 1987 solar cell calibration balloon flight was successfully completed on August 23, 1987, meeting all objectives of the program. Forty-eight modules were carried to an altitude of 120,000 ft (36.0 km). The cells calibrated can now be used as reference standards in simulator testing of cells and arrays.

Results of the 1988 NASA/JPL balloon flight solar cell calibration program

NASA Technical Reports Server (NTRS)

Anspaugh, B. E.; Weiss, R. S.

1988-01-01

The 1988 solar cell calibration balloon flight was successfully completed on August 7, 1988, meeting all objectives of the program. Forty-eight modules were carried to an altitude of 118,000 ft (36.0 km). The calibrated cells can now be used as reference standards in simulator testing of cells and arrays.

Results of the 1989 NASA/JPL balloon flight solar cell calibration program

NASA Technical Reports Server (NTRS)

Anspaugh, B. E.; Weiss, R. S.

1989-01-01

The 1989 solar cell calibration balloon flight was successfully completed on August 9, 1989, meeting all objectives of the program. Forty-two modules were carried to an altitude of 118,000 ft (36.0 km). The calibrated cells can now be used as reference standards in simulator testing of cells and arrays.

Results of the 1985 NASA/JPL balloon flight solar cell calibration program

NASA Technical Reports Server (NTRS)

Anspaugh, B. E.; Weiss, R. S.

1986-01-01

The 1985 solar cell calibration balloon flight was successfully completed on July 12, 1985, meeting all objectives of the program. Fifty-seven modules were carried to an altitude of 115,000 ft (35.0 km). The calibrated cells can now be used as reference standards in simulator testing of cells and arrays.

34 CFR 350.15 - What must a grantee do in carrying out a demonstration activity?

Code of Federal Regulations, 2011 CFR

2011-07-01

... REHABILITATION RESEARCH PROJECTS AND CENTERS PROGRAM What Projects Does the Secretary Assist? § 350.15 What must... under this program, a grantee shall apply results derived from previous research, testing, or practice to determine the effectiveness of a new strategy or approach. (Authority: Sec. 202; 29 U.S.C. 761a) ...

34 CFR 350.15 - What must a grantee do in carrying out a demonstration activity?

Code of Federal Regulations, 2010 CFR

2010-07-01

... REHABILITATION RESEARCH PROJECTS AND CENTERS PROGRAM What Projects Does the Secretary Assist? § 350.15 What must... under this program, a grantee shall apply results derived from previous research, testing, or practice to determine the effectiveness of a new strategy or approach. (Authority: Sec. 202; 29 U.S.C. 761a) ...

["Soiuz-Apollo" experimental flight. Preliminary results of medicobiological studies, carried out during the flight of "Soiuz-19" spaceship].

PubMed

Vorob'ev, E I; Gazenko, O G; Gurovskiĭ, N N; Nefedov, Iu G; Egorov, B B

1976-01-01

The paper presents brief information on the Apollo-Soyuz test mission, its program biomedical investigations to be carried out in flight and specific medical aspects. It discusses the main tasks of the joint US-USSR experiments and Soviet experiments. It gives and analyzes preliminary results of medical monitoring and postflight examinations of the crew members.

Airflow reduction during cold weather operation of residential heat recovery ventilators

DOE Office of Scientific and Technical Information (OSTI.GOV)

McGugan, C.A.; Edwards, P.F.; Riley, M.A.

1987-06-01

Laboratory measurements of the performance of residential heat recovery ventilators have been carried out for the R-2000 Energy Efficient Home Program. This work was based on a preliminary test procedure developed by the Canadian Standards Association, part of which calls for testing the HRV under cold weather conditions. An environmental chamber was used to simulate outdoor conditions. Initial tests were carried out with an outdoor temperature of -20/sup 0/C; subsequent tests were carried out at a temperature of -25/sup 0/C. During the tests, airflows, temperatures, and relative humidities of airstreams entering and leaving the HRV, along with electric power inputs,more » were monitored. Frost buildup in the heat exchangers and defrost mechanisms, such as fan shutoff or recirculation, led to reductions in airflows. The magnitude of the reductions is dependent on the design of the heat exchanger and the defrost mechanism used. This paper presents the results of tests performed on a number of HRVs commercially available in Canada at the time of the testing. The flow reductions for the various defrost mechanisms are discussed.« less

Randomization in cancer clinical trials: permutation test and development of a computer program.

PubMed Central

Ohashi, Y

1990-01-01

When analyzing cancer clinical trial data where the treatment allocation is done using dynamic balancing methods such as the minimization method for balancing the distribution of important prognostic factors in each arm, conservativeness occurs if such a randomization scheme is ignored and a simple unstratified analysis is carried out. In this paper, the above conservativeness is demonstrated by computer simulation, and the development of a computer program that carries out permutation tests of the log-rank statistics for clinical trial data where the allocation is done by the minimization method or a stratified permuted block design is introduced. We are planning to use this program in practice to supplement a usual stratified analysis and model-based methods such as the Cox regression. The most serious problem in cancer clinical trials in Japan is how to carry out the quality control or data management in trials that are initiated and conducted by researchers without support from pharmaceutical companies. In the final section of this paper, one international collaborative work for developing international guidelines on data management in clinical trials of bladder cancer is briefly introduced, and the differences between the system adopted in US/European statistical centers and the Japanese system is described. PMID:2269216

NASA electronic message experiment and study: Detailed test plans

NASA Technical Reports Server (NTRS)

1979-01-01

A methodology for evaluating the utility of high speed digital facsimile as a component of the projected NASA-wide electronic message network is presented. Equipment checkout, operator familiarization, pretest calibration, and the development of procedures are addressed. An experimental test program of the facsimile message service which will carry duplicates of the actual messages sent by other means is highlighted. Also, an operational test program during which messages will be sent on a regular basis in order to accumulate the information that will be used to evaluate system performance and project future growth is described.

Evaluation of materials and design modifications for aircraft brakes

NASA Technical Reports Server (NTRS)

Ho, T. L.; Kennedy, F. E.; Peterson, M. B.

1975-01-01

A test program is described which was carried out to evaluate several proposed design modifications and several high-temperature friction materials for use in aircraft disk brakes. The evaluation program was carried out on a specially built test apparatus utilizing a disk brake and wheel half from a small het aircraft. The apparatus enabled control of brake pressure, velocity, and braking time. Tests were run under both constant and variable velocity conditions and covered a kinetic energy range similar to that encountered in aircraft brake service. The results of the design evaluation program showed that some improvement in brake performance can be realized by making design changes in the components of the brake containing friction material. The materials evaluation showed that two friction materials show potential for use in aircraft disk brakes. One of the materials is a nickel-based sintered composite, while the other is a molybdenum-based material. Both materials show much lower wear rates than conventional copper-based materials and are better able to withstand the high temperatures encountered during braking. Additional materials improvement is necessary since both materials show a significant negative slope of the friction-velocity curve at low velocities.

A-3 First Tree Cutting

NASA Technical Reports Server (NTRS)

2007-01-01

Tree clearing for the site of the new A-3 Test Stand at Stennis Space center began June 13. NASA's first new large rocket engine test stand to be built since the site's inception, A-3 construction begins a historic era for America's largest rocket engine test complex. The 300-foot-tall structure is scheduled for completion in August 2010. A-3 will perform altitude tests on the Constellation's J-2X engine that will power the upper stage of the Ares I crew launch vehicle and earth departure stage of the Ares V cargo launch vehicle. The Constellation Program, NASA's plan for carrying out the nation's Vision for Space Exploration, will return humans to the moon and eventually carry them to Mars and beyond.

A-3 First Tree Cutting

NASA Image and Video Library

2007-06-13

Tree clearing for the site of the new A-3 Test Stand at Stennis Space center began June 13. NASA's first new large rocket engine test stand to be built since the site's inception, A-3 construction begins a historic era for America's largest rocket engine test complex. The 300-foot-tall structure is scheduled for completion in August 2010. A-3 will perform altitude tests on the Constellation's J-2X engine that will power the upper stage of the Ares I crew launch vehicle and earth departure stage of the Ares V cargo launch vehicle. The Constellation Program, NASA's plan for carrying out the nation's Vision for Space Exploration, will return humans to the moon and eventually carry them to Mars and beyond.

X-43A Vehicle During Ground Testing

NASA Technical Reports Server (NTRS)

1999-01-01

The X-43A Hypersonic Experimental Vehicle, or 'Hyper-X' is seen here undergoing ground testing at NASA's Dryden Flight Research Center, Edwards, California. The X-43A was developed to research a dual-mode ramjet/scramjet propulsion system at speeds from Mach 7 up to Mach 10 (7 to 10 times the speed of sound, which varies with temperature and altitude). Hyper-X, the flight vehicle for which is designated as X-43A, is an experimental flight-research program seeking to demonstrate airframe-integrated, 'air-breathing' engine technologies that promise to increase payload capacity for future vehicles, including hypersonic aircraft (faster than Mach 5) and reusable space launchers. This multiyear program is currently underway at NASA Dryden Flight Research Center, Edwards, California. The Hyper-X schedule calls for its first flight later this year (2000). Hyper-X is a joint program, with Dryden sharing responsibility with NASA's Langley Research Center, Hampton, Virginia. Dryden's primary role is to fly three unpiloted X-43A research vehicles to validate engine technologies and hypersonic design tools as well as the hypersonic test facility at Langley. Langley manages the program and leads the technology development effort. The Hyper-X Program seeks to significantly expand the speed boundaries of air-breathing propulsion by being the first aircraft to demonstrate an airframe-integrated, scramjet-powered free flight. Scramjets (supersonic-combustion ramjets) are ramjet engines in which the airflow through the whole engine remains supersonic. Scramjet technology is challenging because only limited testing can be performed in ground facilities. Long duration, full-scale testing requires flight research. Scramjet engines are air-breathing, capturing their oxygen from the atmosphere. Current spacecraft, such as the Space Shuttle, are rocket powered, so they must carry both fuel and oxygen for propulsion. Scramjet technology-based vehicles need to carry only fuel. By eliminating the need to carry oxygen, future hypersonic vehicles will be able to carry heavier payloads. Another unique aspect of the X-43A vehicle is the airframe integration. The body of the vehicle itself forms critical elements of the engine. The forebody acts as part of the intake for airflow and the aft section serves as the nozzle. The X-43A vehicles were manufactured by Micro Craft, Inc., Tullahoma, Tennessee. Orbital Sciences Corporation, Chandler, Arizona, built the Pegasus rocket booster used to launch the X-43 vehicles. For the Dryden research flights, the Pegasus rocket booster and attached X-43 will be air launched by Dryden's B-52 'Mothership.' After release from the B-52, the booster will accelerate the X-43A vehicle to the established test conditions (Mach 7 to 10) at an altitude of approximately 100,000 feet where the X-43 will separate from the booster and fly under its own power and preprogrammed control.

X-43A Undergoing Controlled Radio Frequency Testing in the Benefield Anechoic Facility at Edwards Ai

NASA Technical Reports Server (NTRS)

2000-01-01

The X-43A Hypersonic Experimental (Hyper-X) Vehicle hangs suspended in the cavernous Benefield Aenechoic Facility at Edwards Air Force Base during radio frequency tests in January 2000. Hyper-X, the flight vehicle for which is designated as X-43A, is an experimental flight-research program seeking to demonstrate airframe-integrated, 'air-breathing' engine technologies that promise to increase payload capacity for future vehicles, including hypersonic aircraft (faster than Mach 5) and reusable space launchers. This multiyear program is currently underway at NASA Dryden Flight Research Center, Edwards, California. The Hyper-X schedule calls for its first flight later this year (2000). Hyper-X is a joint program, with Dryden sharing responsibility with NASA's Langley Research Center, Hampton, Virginia. Dryden's primary role is to fly three unpiloted X-43A research vehicles to validate engine technologies and hypersonic design tools as well as the hypersonic test facility at Langley. Langley manages the program and leads the technology development effort. The Hyper-X Program seeks to significantly expand the speed boundaries of air-breathing propulsion by being the first aircraft to demonstrate an airframe-integrated, scramjet-powered free flight. Scramjets (supersonic-combustion ramjets) are ramjet engines in which the airflow through the whole engine remains supersonic. Scramjet technology is challenging because only limited testing can be performed in ground facilities. Long duration, full-scale testing requires flight research. Scramjet engines are air-breathing, capturing their oxygen from the atmosphere. Current spacecraft, such as the Space Shuttle, are rocket powered, so they must carry both fuel and oxygen for propulsion. Scramjet technology-based vehicles need to carry only fuel. By eliminating the need to carry oxygen, future hypersonic vehicles will be able to carry heavier payloads. Another unique aspect of the X-43A vehicle is the airframe integration. The body of the vehicle itself forms critical elements of the engine. The forebody acts as part of the intake for airflow and the aft section serves as the nozzle. The X-43A vehicles were manufactured by Micro Craft, Inc., Tullahoma, Tennessee. Orbital Sciences Corporation, Chandler, Arizona, built the Pegasus rocket booster used to launch the X-43 vehicles. For the Dryden research flights, the Pegasus rocket booster and attached X-43 will be air launched by Dryden's B-52 'Mothership.' After release from the B-52, the booster will accelerate the X-43A vehicle to the established test conditions (Mach 7 to 10) at an altitude of approximately 100,000 feet where the X-43 will separate from the booster and fly under its own power and preprogrammed control.

Last SSME test on A-1

NASA Image and Video Library

2006-09-29

The Stennis Space Center conducted the final space shuttle main engine test on its A-1 Test Stand Friday. The A-1 Test Stand was the site of the first test on a shuttle main engine in 1975. Stennis will continue testing shuttle main engines on its A-2 Test Stand through the end of the Space Shuttle Program in 2010. The A-1 stand begins a new chapter in its operational history in October. It will be temporarily decommissioned to convert it for testing the J-2X engine, which will power the upper stage of NASA's new crew launch vehicle, the Ares I. Although this ends the stand's work on the Space Shuttle Program, it will soon be used for the rocket that will carry America's next generation human spacecraft, Orion.

X-15 Mated to B-52 Captive Flight

NASA Technical Reports Server (NTRS)

1960-01-01

High-altitude contrails frame the B-52 mothership as it carries the X-15 aloft for a research flight on 13 April 1960 on Air Force Maj. Robert M. White's first X-15 flight. The X-15s were air-launched so that they would have enough rocket fuel to reach their high speed and altitude test points. For this early research flight, the X-15 was equipped with a pair of XLR-11 rocket engines until the XLR-99 was available. The X-15s made a total of 199 flights over a period of nearly 10 years--1959 to 1968--and set unofficial world speed and altitude records of 4,520 mph (Mach 6.7) and 354,200 feet. Information gained from the highly successful X-15 program contributed to the development of the Mercury, Gemini, and Apollo piloted spaceflight programs, and also the Space Shuttle program. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

Satellite triangulation in Europe from WEST and ISAGEX data. [computer programs

NASA Technical Reports Server (NTRS)

Leick, A.; Arur, M.

1975-01-01

Observational data that was acquired during the West European Satellite Triangulation (WEST) program and the International Satellite Geodesy Experiment (ISAGEX) campaign was obtained for the purpose of performing a geometric solution to improve the present values of coordinates of the European stations in the OSU WN14 solutions, adding some new stations and assessing the quality of the WN14 solution with the help of the additional data available. The status of the data as received, the preprocessing required and the preliminary tests carried out for the initial screening of the data are described. The adjustment computations carried out and the results of the adjustments are discussed.

Design of a CO2 Twin Rotary Compressor for a Heat Pump Water Heater

NASA Astrophysics Data System (ADS)

Ahn, Jong Min; Kim, Woo Young; Kim, Hyun Jin; Cho, Sung Oug; Seo, Jong Cheun

2010-06-01

For a CO2 heat pump water heater, one-stage twin rotary compressor has been designed. As a design tool, computer simulation program for the compressor performance has been made. Validation of the simulation program has been carried out for a bench model compressor in a compressor calorimeter. Cooling capacity and the compressor input power were reasonably well compared between the simulation and the calorimeter test. Good agreement on P-V diagram between the simulation and the test was also obtained. With this validated compressor simulation program, parametric study has been performed to arrive at optimum dimensions for the compression chamber.

MLP-1 on Crawler Transporter 2 (CT-2)

NASA Image and Video Library

2017-03-22

NASA's upgraded crawler-transporter 2 (CT-2), carrying mobile launcher platform 1, moves slowly along the crawlerway at the agency's Kennedy Space Center in Florida. The crawler's upgrades and modifications will be monitored and tested under loaded conditions during its travel to the crawlerway Pad A/B split and back to the crawler yard to confirm it is ready to support the load of the mobile launcher carrying the Space Launch System with Orion atop for the first test flight, Exploration Mission 1. The Ground Systems Development and Operations Program at Kennedy is managing upgrades to the crawler.

Investigation of the hydrochlorination of SiCl4

NASA Technical Reports Server (NTRS)

Mui, J. Y. P.

1982-01-01

A research and development program on the hydrochlorination of silicon tetrachloride and metallurgical grade (m.g.) silicon metal to trichlorosilane was carried out as scheduled. Effects of pressure and temperature on this reaction are reported. The presence of HCl in the reaction product mixture was successfully analyzed. Approximately 0.1% to 0.5% HCl based on total chlorosilanes were produced by the hydrochlorination reaction. Experiments on the corrosion study were carried out to evaluate a variety of metals and alloys as the material of construction for the hydrochlorination reactor. Material includes carbon steel, nickel, copper, Alloy 400 (Monel), stainless steel (Type 304), Incoloy 800H and Hastelloy B-2. The corrosion test was carried out at reaction temperature of 500 C, pressure of 300 psig and H2/SiCl4 feed ratio of 2.0 for a total of 87 hours. Results of the corrosion test show that all the test samples achieved a weigh gain.

DOE Office of Scientific and Technical Information (OSTI.GOV)

Grigg, Reid; McPherson, Brian; Lee, Rober

The Southwest Regional Partnership on Carbon Sequestration (SWP) one of seven regional partnerships sponsored by the U.S. Department of Energy (USDOE) carried out five field pilot tests in its Phase II Carbon Sequestration Demonstration effort, to validate the most promising sequestration technologies and infrastructure concepts, including three geologic pilot tests and two terrestrial pilot programs. This field testing demonstrated the efficacy of proposed sequestration technologies to reduce or offset greenhouse gas emissions in the region. Risk mitigation, optimization of monitoring, verification, and accounting (MVA) protocols, and effective outreach and communication were additional critical goals of these field validation tests. Themore » program included geologic pilot tests located in Utah, New Mexico, Texas, and a region-wide terrestrial analysis. Each geologic sequestration test site was intended to include injection of a minimum of ~75,000 tons/year CO{sub 2}, with minimum injection duration of one year. These pilots represent medium- scale validation tests in sinks that host capacity for possible larger-scale sequestration operations in the future. These validation tests also demonstrated a broad variety of carbon sink targets and multiple value-added benefits, including testing of enhanced oil recovery and sequestration, enhanced coalbed methane production and a geologic sequestration test combined with a local terrestrial sequestration pilot. A regional terrestrial sequestration demonstration was also carried out, with a focus on improved terrestrial MVA methods and reporting approaches specific for the Southwest region.« less

The NASA research and technology program on batteries

NASA Technical Reports Server (NTRS)

Bennett, Gary L.

1990-01-01

The NASA research and technology program on batteries is being carried out within the Propulsion, Power and Energy Division (Code RP) of NASA's Office of Aeronautics, Exploration and Technology (OAET). The program includes development of high-performance, long-life, cost-effective primary and secondary (rechargeable) batteries. The NASA OAET battery program is being carried out at Lewis Research Center (LeRC) and the Jet Propulsion Laboratory (JPL). LeRC is focusing primarily on nickel-hydrogen batteries (both individual pressure vessel or IPV and bipolar). LeRC is also involved in a planned flight experiment to test a sodium-sulfur battery design. JPL is focusing primarily on lithium rechargeable batteries, having successfully transferred its lithium primary battery technology to the U.S. Air Force for use on the Centaur upper stage. Both LeRC and JPL are studying advanced battery concepts that offer even higher specific energies. The long-term goal is to achieve 100 Wh/kg.

21st Space Simulation Conference: The Future of Space Simulation Testing in the 21st Century

NASA Technical Reports Server (NTRS)

Stecher, Joseph L., III (Compiler)

2000-01-01

The Institute of Environmental Sciences and Technology's Twenty-first Space Simulation Conference, "The Future of Space Testing in the 21st Century" provided participants with a forum to acquire and exchange information on the state-of-the-art in space simulation, test technology, atomic oxygen, programs/system testing, dynamics testing, contamination, and materials. The papers presented at this conference and the resulting discussions carried out the conference theme "The Future of Space Testing in the 21st Century."

Mars Mission Surface Operation Simulation Testing of Lithium-Ion Batteries

NASA Technical Reports Server (NTRS)

Smart, M. C.; Bugga, R.; Whitcanack, L. D.; Chin, K. B.; Davies, E. D.; Surampudi, S.

2003-01-01

The objectives of this program are to 1) Assess viability of using lithium-ion technology for future NASA applications, with emphasis upon Mars landers and rovers which will operate on the planetary surface; 2) Support the JPL 2003 Mars Exploration Rover program to assist in the delivery and testing of a 8 AHr Lithium-Ion battery (Lithion/Yardney) which will power the rover; 3) Demonstrate applicability of using lithium-ion technologyfor future Mars applications: Mars 09 Science Laboratory (Smart Lander) and Future Mars Surface Operations (General). Mission simulation testing was carried out for cells and batteries on the Mars Surveyor 2001 Lander and the 2003 Mars Exploration Rover.

Future X Pathfinder: Quick, Low Cost Flight Testing for Tomorrow's Launch Vehicles

NASA Technical Reports Server (NTRS)

London, John, III; Sumrall, Phil

1999-01-01

The DC-X and DC-XA Single Stage Technology flight program demonstrated the value of low cost rapid prototyping and flight testing of launch vehicle technology testbeds. NASA is continuing this important legacy through a program referred to as Future-X Pathfinder. This program is designed to field flight vehicle projects that cost around $100M each, with a new vehicle flying about every two years. Each vehicle project will develop and extensively flight test a launch vehicle technology testbed that will advance the state of the art in technologies directly relevant to future space transportation systems. There are currently two experimental, or "X" vehicle projects in the Pathfinder program, with additional projects expected to follow in the near future. The first Pathfinder project is X-34. X-34 is a suborbital rocket plane capable of flights to Mach 8 and 75 kilometers altitude. There are a number of reusable launch vehicle technologies embedded in the X-34 vehicle design, such as composite structures and propellant tanks, and advanced reusable thermal protection systems. In addition, X-34 is designed to carry experiments applicable to both the launch vehicle and hypersonic aeronautics community. X-34 is scheduled to fly later this year. The second Pathfinder project is the X-37. X-37 is an orbital space plane that is carried into orbit either by the Space Shuttle or by an expendable launch vehicle. X-37 provides NASA access to the orbital and orbital reentry flight regimes with an experimental testbed vehicle. The vehicle will expose embedded and carry-on advanced space transportation technologies to the extreme environments of orbit and reentry. Early atmospheric approach and landing tests of an unpowered version of the X-37 will begin next year, with orbital flights beginning in late 2001. Future-X Pathfinder is charting a course for the future with its growing fleet of low-cost X- vehicles. X-34 and X-37 are leading the assault on high launch costs and enabling the flight testing of technologies that will lead to affordable access to space.

X-15 on Lakebed after Landing with B-52 Mothership Flyover

NASA Technical Reports Server (NTRS)

1961-01-01

As crew members secure the X-15 rocket-powered aircraft after a research flight, the B-52 mothership used for launching this unique aircraft does a low fly-by overhead. The X-15s made a total of 199 flights over a period of nearly 10 years -- 1959 to 1968 -- and set unofficial world speed and altitude records of 4,520 mph (Mach 6.7) and 354,200. Information gained from the highly successful X-15 program contributed to the development of the Mercury, Gemini, and Apollo piloted spaceflight programs, and also the Space Shuttle program. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet.. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

Flight tests of Viking parachute system in three Mach number regimes. 1: Vehicle description, test operations, and performance

NASA Technical Reports Server (NTRS)

Lundstrom, R. R.; Raper, J. L.; Bendura, R. J.; Shields, E. W.

1974-01-01

Flight qualifications for parachutes were tested on full-scale simulated Viking spacecraft at entry conditions for the Viking 1975 mission to Mars. The vehicle was carried to an altitude of 36.6 km for the supersonic and transonic tests by a 980.000 cu m balloon. The vehicles were released and propelled to test conditions with rocket engines. A 117,940 cu m balloon carried the test vehicle to an altitude of 27.5 km and the conditions for the subsonic tests were achieved in free fall. Aeroshell separation occurred on all test vehicles from 8 to 14 seconds after parachute deployment. This report describes: (1) the test vehicle; (2) methods used to insure that the test conditions were achieved; and (3) the balloon system design and operations. The report also presents the performance data from onboard and ground based instruments and the results from a statistical trajectory program which gives a continuous history of test-vehicle motions.

Advanced Turbine Technology Applications Project (ATTAP)

NASA Technical Reports Server (NTRS)

1992-01-01

This report is the fourth in a series of Annual Technical Summary Reports for the Advanced Turbine Technology Applications Project (ATTAP). This report covers plans and progress on ceramics development for commercial automotive applications over the period 1 Jan. - 31 Dec. 1991. Project effort conducted under this contract is part of the DOE Gas Turbine Highway Vehicle System program. This program is directed to provide the U.S. automotive industry the high-risk, long-range technology necessary to produce gas turbine engines for automobiles with reduced fuel consumption, reduced environmental impact, and a decreased reliance on scarce materials and resources. The program is oriented toward developing the high-risk technology of ceramic structural component design and fabrication, such that industry can carry this technology forward to production in the 1990s. The ATTAP test bed engine, carried over from the previous AGT101 project, is being used for verification testing of the durability of next-generation ceramic components, and their suitability for service at Reference Powertrain Design conditions. This document reports the technical effort conducted by GAPD and the ATTAP subcontractors during the fourth year of the project. Topics covered include ceramic processing definition and refinement, design improvements to the ATTAP test bed engine and test rigs and the methodology development of ceramic impact and fracture mechanisms. Appendices include reports by ATTAP subcontractors in the development of silicon nitride and silicon carbide families of materials and processes.

Use of GEOGRID for Strengthening and Reducing the Roadway Structural Sections

DOT National Transportation Integrated Search

2016-01-01

An experimental laboratory program to assess the effectiveness of biaxial and triaxial geogrid-reinforced flexible pavements to reduce roadway section was carried out. Six laboratory tests were conducted using a steel cylindrical mold with dimensions...

A computer program for helicopter rotor noise using Lowson's formula in the time domain

NASA Technical Reports Server (NTRS)

Parks, C. L.

1975-01-01

A computer program (D3910) was developed to calculate both the far field and near field acoustic pressure signature of a tilted rotor in hover or uniform forward speed. The analysis, carried out in the time domain, is based on Lowson's formulation of the acoustic field of a moving force. The digital computer program is described, including methods used in the calculations, a flow chart, program D3910 source listing, instructions for the user, and two test cases with input and output listings and output plots.

Test and evaluation of the heat recovery incinerator system at Naval Station, Mayport, Florida

NASA Astrophysics Data System (ADS)

1981-05-01

This report describes test and evaluation of the two-ton/hr heat recovery incinerator (HRI) facility located at Mayport Naval Station, Fla., carried out during November and December 1980. The tests included: (1) Solid Waste: characterization, heating value, and ultimate analysis, (2) Ash: moisture, combustibles, and heating values of both bottom and cyclone ashes; Extraction Procedure toxicity tests on leachates from both bottom and cyclone ashes; trace metals in cyclone particulates, (3) Stack Emissions: particulates (quantity and size distribution), chlorides, oxygen, carbon dioxide, carbon monoxide, and trace elements, and (4) Heat and Mass Balance: all measurements required to carry out complete heat and mass balance calculations over the test period. The overall thermal efficiency of the HRI facility while operating at approximately 1.0 ton/hr was found to be 49% when the primary Btu equivalent of the electrical energy consumed during the test program was included.

The Effectiveness of Using Learning Management Systems and Collaborative Tool in Web-Based Teaching of Programming Languages

ERIC Educational Resources Information Center

Cavus, Nadire; Uzunboylu, Huseyin; Ibrahim, Dogan

2006-01-01

This paper is about a pilot study which has been carried out at the Near East University during the 2004/5 Fall Semester using the Moodle LMS [learning management system] together with GREWPtool collaborative editor. The system has been tested with 36 students taking the Java and the Pascal programming courses. The results of the pilot study…

Development of advanced blanket performance under irradiation and system integration through JUPITER-II project

DOE Office of Scientific and Technical Information (OSTI.GOV)

Abe, Katsunori; Kohyama, Akira; Tanaka, Satoru

This report describes an outline of the activities of the JUPITER-II collaboration (japan-USA program of Irradiation/Integration test for Fusion Research-II), Which has bee carried out through six years (2001-2006) under Phase 4 of the collabroation implemented by Amendment 4 of Annex 1 to the DOE (United States Department of Energy)-MEXT (Ministry of Education ,Culture,Sports,Science and Technology) Cooperation. This program followed the RTNS-II Program (Phase1:1982-4986), the FFTF/MOTA Program (Phase2:1987-1994) and the JUPITER Program (Phase 3: 1995-2000) [1].

Close-up of Wing Fit Check of Pylon to Carry the X-38 on B-52 Launch Aircraft

NASA Technical Reports Server (NTRS)

1997-01-01

Dryden Experimental Fabrication Shop's Andy Blua and Jeff Doughty make sure the new pylon for the X-38 fits precisely during a fit-check on NASA's B-52 at the Dryden Flight Research Center, Edwards, California in 1997. The 1,200-pound steel pylon, fabricated at Dryden, was an 'adapter' to allow the X-38 research vehicle to be carried aloft and launched from the bomber. The X-38 was a designed as a technology demonstrator to help develop an emergency Crew Return Vehicle for the International Space Station. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

Close-up of Wing Fit Check of Pylon to Carry the X-38 on B-52 Launch Aircraft

NASA Technical Reports Server (NTRS)

1997-01-01

The new pylon for the X-38 following a fit-check on NASA's B-52 at the Dryden Flight Research Center, Edwards, California, in 1997. The fit-check was the first time the 1,200-pound steel pylon was mated to the B-52 following fabrication at Dryden by the Center's Experimental Fabrication Shop. The pylon was built as an 'adapter' to allow the X-38 research vehicle to be carried aloft and launched from the B-52. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

Hyper-X Vehicle Model - Side View

NASA Technical Reports Server (NTRS)

1996-01-01

A side-view of an early desk-top model of NASA's X-43A 'Hyper-X,' or Hypersonic Experimental Vehicle, which has been developed to flight test a dual-mode ramjet/scramjet propulsion system at speeds from Mach 7 up to Mach 10 (7 to 10 times the speed of sound, which varies with temperature and altitude). Hyper-X, the flight vehicle for which is designated as X-43A, is an experimental flight-research program seeking to demonstrate airframe-integrated, 'air-breathing' engine technologies that promise to increase payload capacity for future vehicles, including hypersonic aircraft (faster than Mach 5) and reusable space launchers. This multiyear program is currently underway at NASA Dryden Flight Research Center, Edwards, California. The Hyper-X schedule calls for its first flight later this year (2000). Hyper-X is a joint program, with Dryden sharing responsibility with NASA's Langley Research Center, Hampton, Virginia. Dryden's primary role is to fly three unpiloted X-43A research vehicles to validate engine technologies and hypersonic design tools as well as the hypersonic test facility at Langley. Langley manages the program and leads the technology development effort. The Hyper-X Program seeks to significantly expand the speed boundaries of air-breathing propulsion by being the first aircraft to demonstrate an airframe-integrated, scramjet-powered free flight. Scramjets (supersonic-combustion ramjets) are ramjet engines in which the airflow through the whole engine remains supersonic. Scramjet technology is challenging because only limited testing can be performed in ground facilities. Long duration, full-scale testing requires flight research. Scramjet engines are air-breathing, capturing their oxygen from the atmosphere. Current spacecraft, such as the Space Shuttle, are rocket powered, so they must carry both fuel and oxygen for propulsion. Scramjet technology-based vehicles need to carry only fuel. By eliminating the need to carry oxygen, future hypersonic vehicles will be able to carry heavier payloads. Another unique aspect of the X-43A vehicle is the airframe integration. The body of the vehicle itself forms critical elements of the engine. The forebody acts as part of the intake for airflow and the aft section serves as the nozzle. The X-43A vehicles were manufactured by Micro Craft, Inc., Tullahoma, Tennessee. Orbital Sciences Corporation, Chandler, Arizona, built the Pegasus rocket booster used to launch the X-43 vehicles. For the Dryden research flights, the Pegasus rocket booster and attached X-43 will be air launched by Dryden's B-52 'Mothership.' After release from the B-52, the booster will accelerate the X-43A vehicle to the established test conditions (Mach 7 to 10) at an altitude of approximately 100,000 feet where the X-43 will separate from the booster and fly under its own power and preprogrammed control.

X-43A Hypersonic Experimental Vehicle - Artist Concept in Flight

NASA Technical Reports Server (NTRS)

1999-01-01

An artist's conception of the X-43A Hypersonic Experimental Vehicle, or 'Hyper-X' in flight. The X-43A was developed to flight test a dual-mode ramjet/scramjet propulsion system at speeds from Mach 7 up to Mach 10 (7 to 10 times the speed of sound, which varies with temperature and altitude). Hyper-X, the flight vehicle for which is designated as X-43A, is an experimental flight-research program seeking to demonstrate airframe-integrated, 'air-breathing' engine technologies that promise to increase payload capacity for future vehicles, including hypersonic aircraft (faster than Mach 5) and reusable space launchers. This multiyear program is currently underway at NASA Dryden Flight Research Center, Edwards, California. The Hyper-X schedule calls for its first flight later this year (2000). Hyper-X is a joint program, with Dryden sharing responsibility with NASA's Langley Research Center, Hampton, Virginia. Dryden's primary role is to fly three unpiloted X-43A research vehicles to validate engine technologies and hypersonic design tools as well as the hypersonic test facility at Langley. Langley manages the program and leads the technology development effort. The Hyper-X Program seeks to significantly expand the speed boundaries of air-breathing propulsion by being the first aircraft to demonstrate an airframe-integrated, scramjet-powered free flight. Scramjets (supersonic-combustion ramjets) are ramjet engines in which the airflow through the whole engine remains supersonic. Scramjet technology is challenging because only limited testing can be performed in ground facilities. Long duration, full-scale testing requires flight research. Scramjet engines are air-breathing, capturing their oxygen from the atmosphere. Current spacecraft, such as the Space Shuttle, are rocket powered, so they must carry both fuel and oxygen for propulsion. Scramjet technology-based vehicles need to carry only fuel. By eliminating the need to carry oxygen, future hypersonic vehicles will be able to carry heavier payloads. Another unique aspect of the X-43A vehicle is the airframe integration. The body of the vehicle itself forms critical elements of the engine. The forebody acts as part of the intake for airflow and the aft section serves as the nozzle. The X-43A vehicles were manufactured by Micro Craft, Inc., Tullahoma, Tennessee. Orbital Sciences Corporation, Chandler, Arizona, built the Pegasus rocket booster used to launch the X-43 vehicles. For the Dryden research flights, the Pegasus rocket booster and attached X-43 will be air launched by Dryden's B-52 'Mothership.' After release from the B-52, the booster will accelerate the X-43A vehicle to the established test conditions (Mach 7 to 10) at an altitude of approximately 100,000 feet where the X-43 will separate from the booster and fly under its own power and preprogrammed control.

Hyper-X Vehicle Model - Front View

NASA Technical Reports Server (NTRS)

1996-01-01

A front view of an early desk-top model of NASA's X-43A 'Hyper-X,' or Hypersonic Experimental Vehicle, which has been developed to flight test a dual-mode ramjet/scramjet propulsion system at speeds from Mach 7 up to Mach 10 (7 to 10 times the speed of sound, which varies with temperature and altitude). Hyper-X, the flight vehicle for which is designated as X-43A, is an experimental flight-research program seeking to demonstrate airframe-integrated, 'air-breathing' engine technologies that promise to increase payload capacity for future vehicles, including hypersonic aircraft (faster than Mach 5) and reusable space launchers. This multiyear program is currently underway at NASA Dryden Flight Research Center, Edwards, California. The Hyper-X schedule calls for its first flight later this year (2000). Hyper-X is a joint program, with Dryden sharing responsibility with NASA's Langley Research Center, Hampton, Virginia. Dryden's primary role is to fly three unpiloted X-43A research vehicles to validate engine technologies and hypersonic design tools as well as the hypersonic test facility at Langley. Langley manages the program and leads the technology development effort. The Hyper-X Program seeks to significantly expand the speed boundaries of air-breathing propulsion by being the first aircraft to demonstrate an airframe-integrated, scramjet-powered free flight. Scramjets (supersonic-combustion ramjets) are ramjet engines in which the airflow through the whole engine remains supersonic. Scramjet technology is challenging because only limited testing can be performed in ground facilities. Long duration, full-scale testing requires flight research. Scramjet engines are air-breathing, capturing their oxygen from the atmosphere. Current spacecraft, such as the Space Shuttle, are rocket powered, so they must carry both fuel and oxygen for propulsion. Scramjet technology-based vehicles need to carry only fuel. By eliminating the need to carry oxygen, future hypersonic vehicles will be able to carry heavier payloads. Another unique aspect of the X-43A vehicle is the airframe integration. The body of the vehicle itself forms critical elements of the engine. The forebody acts as part of the intake for airflow and the aft section serves as the nozzle. The X-43A vehicles were manufactured by Micro Craft, Inc., Tullahoma, Tennessee. Orbital Sciences Corporation, Chandler, Arizona, built the Pegasus rocket booster used to launch the X-43 vehicles. For the Dryden research flights, the Pegasus rocket booster and attached X-43 will be air launched by Dryden's B-52 'Mothership.' After release from the B-52, the booster will accelerate the X-43A vehicle to the established test conditions (Mach 7 to 10) at an altitude of approximately 100,000 feet where the X-43 will separate from the booster and fly under its own power and preprogrammed control.

Artist Concept of X-43A/Hyper-X Hypersonic Experimental Research Vehicle in Flight

NASA Technical Reports Server (NTRS)

1998-01-01

An artist's conception of the X-43A Hypersonic Experimental Vehicle, or 'Hyper-X' in flight. The X-43A was developed to flight test a dual-mode ramjet/scramjet propulsion system at speeds from Mach 7 up to Mach 10 (7 to 10 times the speed of sound, which varies with temperature and altitude). Hyper-X, the flight vehicle for which is designated as X-43A, is an experimental flight-research program seeking to demonstrate airframe-integrated, 'air-breathing' engine technologies that promise to increase payload capacity for future vehicles, including hypersonic aircraft (faster than Mach 5) and reusable space launchers. This multiyear program is currently underway at NASA Dryden Flight Research Center, Edwards, California. The Hyper-X schedule calls for its first flight later this year (2000). Hyper-X is a joint program, with Dryden sharing responsibility with NASA's Langley Research Center, Hampton, Virginia. Dryden's primary role is to fly three unpiloted X-43A research vehicles to validate engine technologies and hypersonic design tools as well as the hypersonic test facility at Langley. Langley manages the program and leads the technology development effort. The Hyper-X Program seeks to significantly expand the speed boundaries of air-breathing propulsion by being the first aircraft to demonstrate an airframe-integrated, scramjet-powered free flight. Scramjets (supersonic-combustion ramjets) are ramjet engines in which the airflow through the whole engine remains supersonic. Scramjet technology is challenging because only limited testing can be performed in ground facilities. Long duration, full-scale testing requires flight research. Scramjet engines are air-breathing, capturing their oxygen from the atmosphere. Current spacecraft, such as the Space Shuttle, are rocket powered, so they must carry both fuel and oxygen for propulsion. Scramjet technology-based vehicles need to carry only fuel. By eliminating the need to carry oxygen, future hypersonic vehicles will be able to carry heavier payloads. Another unique aspect of the X-43A vehicle is the airframe integration. The body of the vehicle itself forms critical elements of the engine. The forebody acts as part of the intake for airflow and the aft section serves as the nozzle. The X-43A vehicles were manufactured by Micro Craft, Inc., Tullahoma, Tennessee. Orbital Sciences Corporation, Chandler, Arizona, built the Pegasus rocket booster used to launch the X-43 vehicles. For the Dryden research flights, the Pegasus rocket booster and attached X-43 will be air launched by Dryden's B-52 'Mothership.' After release from the B-52, the booster will accelerate the X-43A vehicle to the established test conditions (Mach 7 to 10) at an altitude of approximately 100,000 feet where the X-43 will separate from the booster and fly under its own power and preprogrammed control.

Hyper-X Vehicle Model - Side View

NASA Technical Reports Server (NTRS)

1996-01-01

Sleek lines are apparent in this side-view of an early desk-top model of NASA's X-43A 'Hyper-X,' or Hypersonic Experimental Vehicle, which has been developed to flight test a dual-mode ramjet/scramjet propulsion system at speeds from Mach 7 up to Mach 10 (7 to 10 times the speed of sound, which varies with temperature and altitude). Hyper-X, the flight vehicle for which is designated as X-43A, is an experimental flight-research program seeking to demonstrate airframe-integrated, 'air-breathing' engine technologies that promise to increase payload capacity for future vehicles, including hypersonic aircraft (faster than Mach 5) and reusable space launchers. This multiyear program is currently underway at NASA Dryden Flight Research Center, Edwards, California. The Hyper-X schedule calls for its first flight later this year (2000). Hyper-X is a joint program, with Dryden sharing responsibility with NASA's Langley Research Center, Hampton, Virginia. Dryden's primary role is to fly three unpiloted X-43A research vehicles to validate engine technologies and hypersonic design tools as well as the hypersonic test facility at Langley. Langley manages the program and leads the technology development effort. The Hyper-X Program seeks to significantly expand the speed boundaries of air-breathing propulsion by being the first aircraft to demonstrate an airframe-integrated, scramjet-powered free flight. Scramjets (supersonic-combustion ramjets) are ramjet engines in which the airflow through the whole engine remains supersonic. Scramjet technology is challenging because only limited testing can be performed in ground facilities. Long duration, full-scale testing requires flight research. Scramjet engines are air-breathing, capturing their oxygen from the atmosphere. Current spacecraft, such as the Space Shuttle, are rocket powered, so they must carry both fuel and oxygen for propulsion. Scramjet technology-based vehicles need to carry only fuel. By eliminating the need to carry oxygen, future hypersonic vehicles will be able to carry heavier payloads. Another unique aspect of the X-43A vehicle is the airframe integration. The body of the vehicle itself forms critical elements of the engine. The forebody acts as part of the intake for airflow and the aft section serves as the nozzle. The X-43A vehicles were manufactured by Micro Craft, Inc., Tullahoma, Tennessee. Orbital Sciences Corporation, Chandler, Arizona, built the Pegasus rocket booster used to launch the X-43 vehicles. For the Dryden research flights, the Pegasus rocket booster and attached X-43 will be air launched by Dryden's B-52 'Mothership.' After release from the B-52, the booster will accelerate the X-43A vehicle to the established test conditions (Mach 7 to 10) at an altitude of approximately 100,000 feet where the X-43 will separate from the booster and fly under its own power and preprogrammed control.

Hyper-X Research Vehicle - Artist Concept in Flight

NASA Technical Reports Server (NTRS)

1997-01-01

An artist's conception of the X-43A Hypersonic Experimental Vehicle, or 'Hyper-X' in flight. The X-43A was developed to flight test a dual-mode ramjet/scramjet propulsion system at speeds from Mach 7 up to Mach 10 (7 to 10 times the speed of sound, which varies with temperature and altitude). Hyper-X, the flight vehicle for which is designated as X-43A, is an experimental flight-research program seeking to demonstrate airframe-integrated, 'air-breathing' engine technologies that promise to increase payload capacity for future vehicles, including hypersonic aircraft (faster than Mach 5) and reusable space launchers. This multiyear program is currently underway at NASA Dryden Flight Research Center, Edwards, California. The Hyper-X schedule calls for its first flight later this year (2000). Hyper-X is a joint program, with Dryden sharing responsibility with NASA's Langley Research Center, Hampton, Virginia. Dryden's primary role is to fly three unpiloted X-43A research vehicles to validate engine technologies and hypersonic design tools as well as the hypersonic test facility at Langley. Langley manages the program and leads the technology development effort. The Hyper-X Program seeks to significantly expand the speed boundaries of air-breathing propulsion by being the first aircraft to demonstrate an airframe-integrated, scramjet-powered free flight. Scramjets (supersonic-combustion ramjets) are ramjet engines in which the airflow through the whole engine remains supersonic. Scramjet technology is challenging because only limited testing can be performed in ground facilities. Long duration, full-scale testing requires flight research. Scramjet engines are air-breathing, capturing their oxygen from the atmosphere. Current spacecraft, such as the Space Shuttle, are rocket powered, so they must carry both fuel and oxygen for propulsion. Scramjet technology-based vehicles need to carry only fuel. By eliminating the need to carry oxygen, future hypersonic vehicles will be able to carry heavier payloads. Another unique aspect of the X-43A vehicle is the airframe integration. The body of the vehicle itself forms critical elements of the engine. The forebody acts as part of the intake for airflow and the aft section serves as the nozzle. The X-43A vehicles were manufactured by Micro Craft, Inc., Tullahoma, Tennessee. Orbital Sciences Corporation, Chandler, Arizona, built the Pegasus rocket booster used to launch the X-43 vehicles. For the Dryden research flights, the Pegasus rocket booster and attached X-43 will be air launched by Dryden's B-52 'Mothership.' After release from the B-52, the booster will accelerate the X-43A vehicle to the established test conditions (Mach 7 to 10) at an altitude of approximately 100,000 feet where the X-43 will separate from the booster and fly under its own power and preprogrammed control.

Hyper-X Vehicle Model - Top Rear View

NASA Technical Reports Server (NTRS)

1996-01-01

This aft-quarter model view of NASA's X-43A 'Hyper-X' or Hypersonic Experimental Vehicle shows its sleek, geometric design. The X-43A was developed to flight test a dual-mode ramjet/scramjet propulsion system at speeds from Mach 7 up to Mach 10 (7 to 10 times the speed of sound, which varies with temperature and altitude). Hyper-X, the flight vehicle for which is designated as X-43A, is an experimental flight-research program seeking to demonstrate airframe-integrated, 'air-breathing' engine technologies that promise to increase payload capacity for future vehicles, including hypersonic aircraft (faster than Mach 5) and reusable space launchers. This multiyear program is currently underway at NASA Dryden Flight Research Center, Edwards, California. The Hyper-X schedule calls for its first flight later this year (2000). Hyper-X is a joint program, with Dryden sharing responsibility with NASA's Langley Research Center, Hampton, Virginia. Dryden's primary role is to fly three unpiloted X-43A research vehicles to validate engine technologies and hypersonic design tools as well as the hypersonic test facility at Langley. Langley manages the program and leads the technology development effort. The Hyper-X Program seeks to significantly expand the speed boundaries of air-breathing propulsion by being the first aircraft to demonstrate an airframe-integrated, scramjet-powered free flight. Scramjets (supersonic-combustion ramjets) are ramjet engines in which the airflow through the whole engine remains supersonic. Scramjet technology is challenging because only limited testing can be performed in ground facilities. Long duration, full-scale testing requires flight research. Scramjet engines are air-breathing, capturing their oxygen from the atmosphere. Current spacecraft, such as the Space Shuttle, are rocket powered, so they must carry both fuel and oxygen for propulsion. Scramjet technology-based vehicles need to carry only fuel. By eliminating the need to carry oxygen, future hypersonic vehicles will be able to carry heavier payloads. Another unique aspect of the X-43A vehicle is the airframe integration. The body of the vehicle itself forms critical elements of the engine. The forebody acts as part of the intake for airflow and the aft section serves as the nozzle. The X-43A vehicles were manufactured by Micro Craft, Inc., Tullahoma, Tennessee. Orbital Sciences Corporation, Chandler, Arizona, built the Pegasus rocket booster used to launch the X-43 vehicles. For the Dryden research flights, the Pegasus rocket booster and attached X-43 will be air launched by Dryden's B-52 'Mothership.' After release from the B-52, the booster will accelerate the X-43A vehicle to the established test conditions (Mach 7 to 10) at an altitude of approximately 100,000 feet where the X-43 will separate from the booster and fly under its own power and preprogrammed control.

Hyper-X Vehicle Model - Top Front View

NASA Technical Reports Server (NTRS)

1996-01-01

A top front view of an early desk-top model of NASA's X-43A 'Hyper-X,' or Hypersonic Experimental Vehicle, developed to flight test a dual-mode ramjet/scramjet propulsion system at speeds from Mach 7 up to Mach 10 (7 to 10 times the speed of sound, which varies with temperature and altitude). Hyper-X, the flight vehicle for which is designated as X-43A, is an experimental flight-research program seeking to demonstrate airframe-integrated, 'air-breathing' engine technologies that promise to increase payload capacity for future vehicles, including hypersonic aircraft (faster than Mach 5) and reusable space launchers. This multiyear program is currently underway at NASA Dryden Flight Research Center, Edwards, California. The Hyper-X schedule calls for its first flight later this year (2000). Hyper-X is a joint program, with Dryden sharing responsibility with NASA's Langley Research Center, Hampton, Virginia. Dryden's primary role is to fly three unpiloted X-43A research vehicles to validate engine technologies and hypersonic design tools as well as the hypersonic test facility at Langley. Langley manages the program and leads the technology development effort. The Hyper-X Program seeks to significantly expand the speed boundaries of air-breathing propulsion by being the first aircraft to demonstrate an airframe-integrated, scramjet-powered free flight. Scramjets (supersonic-combustion ramjets) are ramjet engines in which the airflow through the whole engine remains supersonic. Scramjet technology is challenging because only limited testing can be performed in ground facilities. Long duration, full-scale testing requires flight research. Scramjet engines are air-breathing, capturing their oxygen from the atmosphere. Current spacecraft, such as the Space Shuttle, are rocket powered, so they must carry both fuel and oxygen for propulsion. Scramjet technology-based vehicles need to carry only fuel. By eliminating the need to carry oxygen, future hypersonic vehicles will be able to carry heavier payloads. Another unique aspect of the X-43A vehicle is the airframe integration. The body of the vehicle itself forms critical elements of the engine. The forebody acts as part of the intake for airflow and the aft section serves as the nozzle. The X-43A vehicles were manufactured by Micro Craft, Inc., Tullahoma, Tennessee. Orbital Sciences Corporation, Chandler, Arizona, built the Pegasus rocket booster used to launch the X-43 vehicles. For the Dryden research flights, the Pegasus rocket booster and attached X-43 will be air launched by Dryden's B-52 'Mothership.' After release from the B-52, the booster will accelerate the X-43A vehicle to the established test conditions (Mach 7 to 10) at an altitude of approximately 100,000 feet where the X-43 will separate from the booster and fly under its own power and preprogrammed control.

DOE Office of Scientific and Technical Information (OSTI.GOV)

None

Progress is reported on fundamental research in: crystal physics, reactions at metal surfaces, spectroscopy of ionic media, structure of metals, theory of alloying, physical properties, sintering, deformation of crystalline solids, x ray diffraction, metallurgy of superconducting materials, and electron microscope studies. Long-randge applied research studies were conducted for: zirconium metallurgy, materials compatibility, solid reactions, fuel element development, mechanical properties, non-destructive testing, and high-temperature materials. Reactor development support work was carried out for: gas-cooled reactor program, molten-salt reactor, high-flux isotope reactor, space-power program, thorium-utilization program, advanced-test reactor, Army Package Power Reactor, Enrico Fermi fast-breeder reactor, and water desalination program. Other programmore » activities, for which research was conducted, included: thermonuclear project, transuraniunn program, and post-irradiation examination laboratory. Separate abstracts were prepared for 30 sections of the report. (B.O.G.)« less

The U.S. Earthquake Prediction Program

USGS Publications Warehouse

Wesson, R.L.; Filson, J.R.

1981-01-01

There are two distinct motivations for earthquake prediction. The mechanistic approach aims to understand the processes leading to a large earthquake. The empirical approach is governed by the immediate need to protect lives and property. With our current lack of knowledge about the earthquake process, future progress cannot be made without gathering a large body of measurements. These are required not only for the empirical prediction of earthquakes, but also for the testing and development of hypotheses that further our understanding of the processes at work. The earthquake prediction program is basically a program of scientific inquiry, but one which is motivated by social, political, economic, and scientific reasons. It is a pursuit that cannot rely on empirical observations alone nor can it carried out solely on a blackboard or in a laboratory. Experiments must be carried out in the real Earth. 

Marshall Space Flight Center head development program

NASA Technical Reports Server (NTRS)

Harrer, Jim

1994-01-01

This report summarizes the results of the candidate head evaluation for the new long-life magnetic head per the SOW of Contract No. NAS8-39407, MSFC Head Development Program. The original program plans were to test a candidate head, fabricate a new head, then qualify the new head. These activities were scheduled to be carried out between March 1993 and March 1994. The program was halted after the evaluation of the candidate head by NAS8-39407 Amendment No. 4. MSFC has provided and authorized the use the MARS-2000 SRB QUAL Recorder PN 10400-0677-801 - Serial Number 200004 (Datatape PN 591000 - Serial Number 1004), Reproduce Amplifier Module (RAM) Datatape PN 533040 - Serial Number 2006, associated cables, and magnetic tape on special SRB/DFI tapered reels to Datatape for this program. All the testing that has been done for the candidate head evaluation was done at Datatape's facility in Pasadena,CA. The testing was performed in a Class 100,000 particle counts clean room at ambient temperature, except for the thermal testing which was conducted in a different area at Datatape. The Performance Verification Test Procedure PVT-11004-4 (PVT) and Acceptance Test Procedure ATP-11004-09 (ATP) procedures were used when tests were conducted on the recorder.

MLP-1 on Crawler Transporter 2 (CT-2)

NASA Image and Video Library

2017-03-22

Ground support technicians walk alongside NASA's upgraded crawler-transporter 2 (CT-2), carrying mobile launcher platform 1, as it slowly travels on the crawlerway at the agency's Kennedy Space Center in Florida. The crawler's upgrades and modifications will be monitored and tested under loaded conditions during its travel to the crawlerway Pad A/B split and back to the crawler yard to confirm it is ready to support the load of the mobile launcher carrying the Space Launch System with Orion atop for the first test flight, Exploration Mission 1. The Ground Systems Development and Operations Program at Kennedy is managing upgrades to the crawler.

Results of a neonatal hearing screening program in Maceió.

PubMed

Dantas, Margareth Barbosa de Souza; Anjos, César Antônio Lira Dos; Camboim, Elizângela Dias; Pimentel, Marcella de Carvalho Ramos

2009-01-01

Since 1998, after we started the support group for neonatal hearing screening, many other hearing screening programs were held in Brazil. In Alagoas, the first program started in 2003, but none of its results were published. Hearing is paramount for human communication; therefore, childhood hearing loss can impair speech acquisition, emotional, educational and social development. to present the results achieved in a neonatal hearing screening program in Maceió. a retrospective analytical study was carried out in order to study the results from tests carried out from September 2003 to December 2006 in a private hospital of Maceió. from a total of 2002 newborns, 1,626 fitted the inclusion criteria, 835 (51.4%) males. The hearing screening was considered appropriate in 1416 cases (87.1%), and the most frequently found age was between 16 and 30 days. Finally, 163 (10.0%) children presented risk indicators for hearing loss, and hyperbilirubinemia was the most common indicator. statistical results obtained from this hearing screening program show the importance of holding such programs. This study is important because it contributes to further regional or multinational studies.

[Unipedal stance time and fall risk in the elderly].

PubMed

Domínguez-Carrillo, Luis Gerardo; Arellano-Aguilar, Gregorio; Leos-Zierold, Héctor

2007-01-01

We undertook this study to relate unipodal stance time (UST) as a falls indicator in the elderly and to corroborate with UST exercise increments. One hundred sixty eight elderly subjects (age >70 years) with two or more falls during the previous 12 months were compared with 150 similar subjects without falls. UST chronometry and quadriceps and triceps brachialis strength dynamometry were used. Equilibrium and antigravity muscle-strengthening exercise program with 20 work sessions were carried out. Results were analyzed with chi(2), Student's t-test, and Fisher tests. UST of the control group showed 28.84 +/- 4.73 sec (mean +/- SD). The UST sample showed 19.18 +/- 4.24 sec. The test was initially impossible to carry out in 42 cases (p = 0.05). The final evaluation showed 142 cases with 30 sec of UST (p = 0.00001), isometric force increased in 70% and 30%, respectively (p = 0.05). At 6-month follow-up, 53 falls were reported, 29 were in patients who could not accomplish UST measurement on initial evaluation. UST <30 sec is an indicator of falls in elderly people, and exercise programs increase UST.

Simulation of Propagation of Compartment Fire on Building Facades

NASA Astrophysics Data System (ADS)

Simion, A.; Dragne, H.; Stoica, D.; Anghel, I.

2018-06-01

The façade fire simulation of buildings is carried out with Pyrosim numerical fire modeling program, following the implementation of a fire scenario in this simulation program. The scenario that was implemented in the Pyrosim program by researchers from the INCERC Fire Safety Research and Testing Laboratory complied with the requirements of BS 8414. The results obtained following the run of the computational program led to the visual validation of effluents at different time points from the beginning of the thermal load burning, as well as the validation in terms of recorded temperatures. It is considered that the results obtained are reasonable, the test being fully validated from the point of view of the implementation of the fire scenario, of the correct development of the effluents and of the temperature values [1].

Dynamic Impact Testing and Model Development in Support of NASA's Advanced Composites Program

NASA Technical Reports Server (NTRS)

Melis, Matthew E.; Pereira, J. Michael; Goldberg, Robert; Rassaian, Mostafa

2018-01-01

The purpose of this paper is to provide an executive overview of the HEDI effort for NASA's Advanced Composites Program and establish the foundation for the remaining papers to follow in the 2018 SciTech special session NASA ACC High Energy Dynamic Impact. The paper summarizes the work done for the Advanced Composites Program to advance our understanding of the behavior of composite materials during high energy impact events and to advance the ability of analytical tools to provide predictive simulations. The experimental program carried out at GRC is summarized and a status on the current development state for MAT213 will be provided. Future work will be discussed as the HEDI effort transitions from fundamental analysis and testing to investigating sub-component structural concept response to impact events.

X-43A Vehicle During Ground Testing

NASA Technical Reports Server (NTRS)

1999-01-01

This photo shows a close-up, rear view of the X-43A Hypersonic Experimental Vehicle, or 'Hyper-X' undergoing ground testing at NASA's Dryden Flight Research Center, Edwards, California in December 1999. The X-43A was developed to research a dual-mode ramjet/scramjet propulsion system at speeds from Mach 7 up to Mach 10 (7 to 10 times the speed of sound, which varies with temperature and altitude). Hyper-X, the flight vehicle for which is designated as X-43A, is an experimental flight-research program seeking to demonstrate airframe-integrated, 'air-breathing' engine technologies that promise to increase payload capacity for future vehicles, including hypersonic aircraft (faster than Mach 5) and reusable space launchers. This multiyear program is currently underway at NASA Dryden Flight Research Center, Edwards, California. The Hyper-X schedule calls for its first flight later this year (2000). Hyper-X is a joint program, with Dryden sharing responsibility with NASA's Langley Research Center, Hampton, Virginia. Dryden's primary role is to fly three unpiloted X-43A research vehicles to validate engine technologies and hypersonic design tools as well as the hypersonic test facility at Langley. Langley manages the program and leads the technology development effort. The Hyper-X Program seeks to significantly expand the speed boundaries of air-breathing propulsion by being the first aircraft to demonstrate an airframe-integrated, scramjet-powered free flight. Scramjets (supersonic-combustion ramjets) are ramjet engines in which the airflow through the whole engine remains supersonic. Scramjet technology is challenging because only limited testing can be performed in ground facilities. Long duration, full-scale testing requires flight research. Scramjet engines are air-breathing, capturing their oxygen from the atmosphere. Current spacecraft, such as the Space Shuttle, are rocket powered, so they must carry both fuel and oxygen for propulsion. Scramjet technology-based vehicles need to carry only fuel. By eliminating the need to carry oxygen, future hypersonic vehicles will be able to carry heavier payloads. Another unique aspect of the X-43A vehicle is the airframe integration. The body of the vehicle itself forms critical elements of the engine. The forebody acts as part of the intake for airflow and the aft section serves as the nozzle. The X-43A vehicles were manufactured by Micro Craft, Inc., Tullahoma, Tennessee. Orbital Sciences Corporation, Chandler, Arizona, built the Pegasus rocket booster used to launch the X-43 vehicles. For the Dryden research flights, the Pegasus rocket booster and attached X-43 will be air launched by Dryden's B-52 'Mothership.' After release from the B-52, the booster will accelerate the X-43A vehicle to the established test conditions (Mach 7 to 10) at an altitude of approximately 100,000 feet where the X-43 will separate from the booster and fly under its own power and preprogrammed control.

X-43A Vehicle During Ground Testing

NASA Technical Reports Server (NTRS)

1999-01-01

The X-43A Hypersonic Experimental Vehicle, or 'Hyper-X' is seen here undergoing ground testing at NASA's Dryden Flight Research Center, Edwards, California in December 1999. The X-43A was developed to research a dual-mode ramjet/scramjet propulsion system at speeds from Mach 7 up to Mach 10 (7 to 10 times the speed of sound, which varies with temperature and altitude). Hyper-X, the flight vehicle for which is designated as X-43A, is an experimental flight-research program seeking to demonstrate airframe-integrated, 'air-breathing' engine technologies that promise to increase payload capacity for future vehicles, including hypersonic aircraft (faster than Mach 5) and reusable space launchers. This multiyear program is currently underway at NASA Dryden Flight Research Center, Edwards, California. The Hyper-X schedule calls for its first flight later this year (2000). Hyper-X is a joint program, with Dryden sharing responsibility with NASA's Langley Research Center, Hampton, Virginia. Dryden's primary role is to fly three unpiloted X-43A research vehicles to validate engine technologies and hypersonic design tools as well as the hypersonic test facility at Langley. Langley manages the program and leads the technology development effort. The Hyper-X Program seeks to significantly expand the speed boundaries of air-breathing propulsion by being the first aircraft to demonstrate an airframe-integrated, scramjet-powered free flight. Scramjets (supersonic-combustion ramjets) are ramjet engines in which the airflow through the whole engine remains supersonic. Scramjet technology is challenging because only limited testing can be performed in ground facilities. Long duration, full-scale testing requires flight research. Scramjet engines are air-breathing, capturing their oxygen from the atmosphere. Current spacecraft, such as the Space Shuttle, are rocket powered, so they must carry both fuel and oxygen for propulsion. Scramjet technology-based vehicles need to carry only fuel. By eliminating the need to carry oxygen, future hypersonic vehicles will be able to carry heavier payloads. Another unique aspect of the X-43A vehicle is the airframe integration. The body of the vehicle itself forms critical elements of the engine. The forebody acts as part of the intake for airflow and the aft section serves as the nozzle. The X-43A vehicles were manufactured by Micro Craft, Inc., Tullahoma, Tennessee. Orbital Sciences Corporation, Chandler, Arizona, built the Pegasus rocket booster used to launch the X-43 vehicles. For the Dryden research flights, the Pegasus rocket booster and attached X-43 will be air launched by Dryden's B-52 'Mothership.' After release from the B-52, the booster will accelerate the X-43A vehicle to the established test conditions (Mach 7 to 10) at an altitude of approximately 100,000 feet where the X-43 will separate from the booster and fly under its own power and preprogrammed control.

A Study of Facilities and Infrastructure Planning, Prioritization, and Assessment at Federal Security Laboratories (Revised)

DTIC Science & Technology

2013-02-01

or funds authorized under Section 219(a) for projects costing no more than $4M. Research , Development, Test , and Evaluation (RDT&E) Appropriations...The RDT&E appropriation consists of the mission program budgets for all research , development, test and evaluation work performed by contractors...carry out an unspecified minor military construction project costing not more than $4,000,000. 9 f. Research , Development, Test , and Evaluation

Fire Resistance of Geopolymer Concretes

DTIC Science & Technology

2010-03-21

1 Project report – Grant FA23860814096, "Fire resistance of geopolymer concretes" – J. Provis, University of Melbourne 1. Background and...experimental program This project provided funding for us to carry out fire testing of geopolymer concrete specimens and associated laboratory...testing. The focus of this report will be the outcomes of the series of pilot-scale (4’×4’×6”) tests on geopolymer concrete panels, which were conducted

BIOSPEX: Biological space experiments, a compendium of life sciences experiments carried on US spacecraft

NASA Technical Reports Server (NTRS)

Anderson, M.; Rummel, J. A. (Editor); Deutsch, S. (Editor)

1979-01-01

United States space life science experiments, encompassing 27 years of experience beginning with sounding rocket flights carrying primates (1948) to the last U.S. spaceflight, the joint US/USSR Apollo Test Project (1975), are presented. The information for each experiment includes Principal Investigators, the program and mission on which it was flown, the specimens used, the objectives, protocol, equipment, results, conclusions, and bibliographic reference citations for publications derived from each experiment.

Life science experiments during parabolic flight: The McGill experience

NASA Technical Reports Server (NTRS)

Watt, D. G. D.

1988-01-01

Over the past twelve years, members of the Aerospace Medical Research Unit of McGill University have carried out a wide variety of tests and experiments in the weightless condition created by parabolic flight. This paper discusses the pros and cons of that environment for the life scientist, and uses examples from the McGill program of the types of activities which can be carried out in a transport aircraft such as the NASA KC-135.

Pegasus Mated to B-52 Mothership - First Flight

NASA Technical Reports Server (NTRS)

1989-01-01

The Pegasus air-launched space booster is carried aloft under the right wing of NASA's B-52 carrier aircraft on its first captive flight from the Dryden Flight Research Center, Edwards, California. The first of two scheduled captive flights was completed on November 9, 1989. Pegasus is used to launch satellites into low-earth orbits cheaply. In 1997, a Pegasus rocket booster was also modified to test a hypersonic experiment (PHYSX). An experimental 'glove,' installed on a section of its wing, housed hundreds of temperature and pressure sensors that sent hypersonic flight data to ground tracking facilities during the experiment's flight. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

X-38 Mounted on Pylon of B-52 Mothership

NASA Technical Reports Server (NTRS)

1997-01-01

A close-up view of the X-38 research vehicle mounted under the wing of the B-52 mothership prior to a 1997 test flight. The X-38, which was designed to help develop technology for an emergency crew return vehicle (CRV) for the International Space Station, is one of many research vehicles the B-52 has carried aloft over the past 40 years. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

Image analysis software for following progression of peripheral neuropathy

NASA Astrophysics Data System (ADS)

Epplin-Zapf, Thomas; Miller, Clayton; Larkin, Sean; Hermesmeyer, Eduardo; Macy, Jenny; Pellegrini, Marco; Luccarelli, Saverio; Staurenghi, Giovanni; Holmes, Timothy

2009-02-01

A relationship has been reported by several research groups [1 - 4] between the density and shapes of nerve fibers in the cornea and the existence and severity of peripheral neuropathy. Peripheral neuropathy is a complication of several prevalent diseases or conditions, which include diabetes, HIV, prolonged alcohol overconsumption and aging. A common clinical technique for confirming the condition is intramuscular electromyography (EMG), which is invasive, so a noninvasive technique like the one proposed here carries important potential advantages for the physician and patient. A software program that automatically detects the nerve fibers, counts them and measures their shapes is being developed and tested. Tests were carried out with a database of subjects with levels of severity of diabetic neuropathy as determined by EMG testing. Results from this testing, that include a linear regression analysis are shown.

Cryogenic lifetime tests on a commercial epoxy resin high voltage bushing

DOE Office of Scientific and Technical Information (OSTI.GOV)

Schwenterly, S W; Pleva, Ed; Ha, Tam T

2012-06-12

High-temperature superconducting (HTS) power devices operating in liquid nitrogen frequently require high-voltage bushings to carry the current leads from the superconducting windings to the room temperature grid connections. Oak Ridge National Laboratory is collaborating with Waukesha Electric Systems, SuperPower, and Southern California Edison to develop and demonstrate an HTS utility power transformer. Previous dielectric high voltage tests in support of this program have been carried out in test cryostats with commercial epoxy resin bushings from Electro Composites Inc. (ECI). Though the bushings performed well in these short-term tests, their long-term operation at high voltage in liquid nitrogen needs to bemore » verified for use on the utility grid. Long-term tests are being carried out on a sample 28-kV-class ECI bushing. The bushing has a monolithic cast, cycloaliphatic resin body and is fire- and shatter-resistant. The test cryostat is located in an interlocked cage and is energized at 25 kVac around the clock. Liquid nitrogen (LN) is automatically refilled every 9.5 hours. Partial discharge, capacitance, and leakage resistance tests are periodically performed to check for deviations from factory values. At present, over 2400 hours have been accumulated with no changes in these parameters. The tests are scheduled to run for four to six months.« less

Cryogenic lifetime tests on a commercial epoxy resin high voltage bushing

NASA Astrophysics Data System (ADS)

Schwenterly, S. W.; Pleva, E. F.; Ha, T. T.

2012-06-01

High-temperature superconducting (HTS) power devices operating in liquid nitrogen frequently require high-voltage bushings to carry the current leads from the superconducting windings to the room temperature grid connections. Oak Ridge National Laboratory (ORNL) is collaborating with Waukesha Electric Systems (WES), SuperPower (SP), and Southern California Edison (SCE) to develop and demonstrate an HTS utility power transformer. Previous dielectric high voltage tests in support of this program have been carried out in test cryostats with commercial epoxy resin bushings from Electro Composites Inc. (ECI). Though the bushings performed well in these short-term tests, their long-term operation at high voltage in liquid nitrogen (LN) needs to be verified for use on the utility grid. Long-term tests are being carried out on a sample 28-kV-rms-class ECI bushing. The bushing has a monolithic cast, cycloaliphatic resin body and is fire- and shatter-resistant. The test cryostat is located in an interlocked cage and is continuously energized at 25 kVac rms. LN is automatically refilled every 9.5 hours. Partial discharge, capacitance, and leakage resistance tests are periodically performed to check for deviations from factory values. At present, over 2400 hours have been accumulated with no changes in these parameters. The tests are scheduled to run for four to six months.

DOE Office of Scientific and Technical Information (OSTI.GOV)

Eperin, A.P.; Zakharzhevsky, Yu.O.; Arzhaev, A.I.

A two-year Finnish-Russian cooperation program has been initiated in 1995 to demonstrate the applicability of the leak-before-break concept (LBB) to the primary circuit piping of the Leningrad NPP. The program includes J-R curve testing of authentic pipe materials at full operating temperature, screening and computational LBB analyses complying with the USNRC Standard Review Plan 3.6.3, and exchange of LBB-related information with emphasis on NDE. Domestic computer codes are mainly used, and all tests and analyses are independently carried out by each party. The results are believed to apply generally to RBMK type plants of the first generation.

Results of the 1979 NASA/JPL balloon flight solar cell calibration program

NASA Technical Reports Server (NTRS)

Seaman, C. H.; Weiss, R. S.

1980-01-01

Calibration of solar cells to be used as reference standards in simulator testing of cells and arrays was accomplished. Thirty-eight modules were carried to an altitude of about 36 kilometers during the solar cell calibration balloon flight.

Application of Terrestrial Environments in Orion Assessments

NASA Technical Reports Server (NTRS)

Barbre, Robert E.

2016-01-01

This presentation summarizes the Marshall Space Flight Center Natural Environments Terrestrial and Planetary Environments (TPE) Team support to the NASA Orion space vehicle. The TPE utilizes meteorological data to assess the sensitivities of the vehicle due to the terrestrial environment. The Orion vehicle, part of the Multi-Purpose Crew Vehicle Program, is designed to carry astronauts beyond low-earth orbit and is currently undergoing a series of tests including Exploration Test Flight (EFT) - 1. The presentation describes examples of TPE support for vehicle design and several tests, as well as support for EFT-1 and planning for upcoming Exploration Missions while emphasizing the importance of accounting for the natural environment's impact to the vehicle early in the vehicle's program.

NearFar: A computer program for nearside farside decomposition of heavy-ion elastic scattering amplitude

NASA Astrophysics Data System (ADS)

Cha, Moon Hoe

2007-02-01

The NearFar program is a package for carrying out an interactive nearside-farside decomposition of heavy-ion elastic scattering amplitude. The program is implemented in Java to perform numerical operations on the nearside and farside angular distributions. It contains a graphical display interface for the numerical results. A test run has been applied to the elastic O16+Si28 scattering at E=1503 MeV. Program summaryTitle of program: NearFar Catalogue identifier: ADYP_v1_0 Program summary URL:http://cpc.cs.qub.ac.uk/summaries/ADYP_v1_0 Program obtainable from: CPC Program Library, Queen's University of Belfast, N. Ireland Licensing provisions: none Computers: designed for any machine capable of running Java, developed on PC-Pentium-4 Operating systems under which the program has been tested: Microsoft Windows XP (Home Edition) Program language used: Java Number of bits in a word: 64 Memory required to execute with typical data: case dependent No. of lines in distributed program, including test data, etc.: 3484 Number of bytes distributed program, including test data, etc.: 142 051 Distribution format: tar.gz Other software required: A Java runtime interpreter, or the Java Development Kit, version 5.0 Nature of physical problem: Interactive nearside-farside decomposition of heavy-ion elastic scattering amplitude. Method of solution: The user must supply a external data file or PPSM parameters which calculates theoretical values of the quantities to be decomposed. Typical running time: Problem dependent. In a test run, it is about 35 s on a 2.40 GHz Intel P4-processor machine.

Pegasus Mated to B-52 Mothership - Front View

NASA Technical Reports Server (NTRS)

1991-01-01

NASA's B-52 launch aircraft takes off with the second Pegasus vehicle under its wing from the Dryden Flight Research Facility (now the Dryden Flight Research Center), Edwards, California. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

Damage Tolerance Characterisitics of Composite Sandwich Structures

DTIC Science & Technology

2000-02-01

requirements impose strict test program is devised and carried out, with hundreds of tests at constraints on the design of composite aircraft... design A particular effort was dedicated to the study of delamination methodologies, as well as static and fatigue strength and growth under...partition according to the theoretical tools, the industries are more or less forced, for the fundamental modes. design of primary composite structures

[327] Biomedical Research Deferred in the Aftermath of the Apollo Fire: Impact to Progress in Human Spaceflight

NASA Technical Reports Server (NTRS)

Charles, John B.

2017-01-01

Before Apollo fire, early Apollo missions were expected to continue pattern established in Gemini program of accommodating significant scientific and biological experimentation, including human biomedical studies, during flights. Apollo1 and Apollo2, both 2-week engineering test flights, were to carry almost as many biomedical studies as Gemini 7, a 2-week medical test mission.

Spinal cord testing: auditing for quality assurance.

PubMed

Marr, J A; Reid, B

1991-04-01

A quality assurance audit of spinal cord testing as documented by staff nurses was carried out. Twenty-five patient records were examined for accuracy of documented testing and compared to assessments performed by three investigators. A pilot study established interrater reliability of a tool that was designed especially for this study. Results indicated staff nurses failed to meet pre-established 100% standard in all categories of testing when compared with investigator's findings. Possible reasons for this disparity are discussed as well as indications for modifications in the spinal testing record, teaching program and preset standards.

X-15 Mated to B-52 Captive Flight

NASA Technical Reports Server (NTRS)

1959-01-01

One of three X-15 rocket-powered research aircraft being carried aloft under the wing of its B-52 mothership. The X-15 was air launched from the B-52 so the rocket plane would have enough fuel to reach its high speed and altitude test points. For flight in the dense air of the usable atmosphere, the X-15 used conventional aerodynamic controls. For flight in the thin air outside of the appreciable Earth's atmosphere, the X-15 used a reaction control system. Hydrogen peroxide thrust rockets located on the nose of the aircraft provided pitch and yaw control. Those on the wings provided roll control. The X-15s made a total of 199 flights over a period of nearly 10 years and set world's unofficial speed and altitude records of 4,520 miles per hour (Mach 6.7) and 354,200 feet. Information gained from the highly successful X-15 program contributed to the development of the Mercury, Gemini, and Apollo manned spaceflight programs and also the Space Shuttle program. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet.. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

Computer assisted performance tests of the Lyman Alpha Coronagraph

NASA Technical Reports Server (NTRS)

Parkinson, W. H.; Kohl, J. L.

1979-01-01

Preflight calibration and performance tests of the Lyman Alpha Coronagraph rocket instrument in the laboratory, with the experiment in its flight configuration and illumination levels near those expected during flight were successfully carried out using a pulse code modulation telemetry system simulator interfaced in real time to a PDP 11/10 computer system. Post acquisition data reduction programs developed and implemented on the same computer system aided in the interpretation of test and calibration data.

30 CFR 582.23 - Testing Plan.

Code of Federal Regulations, 2013 CFR

2013-07-01

... Resources BUREAU OF OCEAN ENERGY MANAGEMENT, DEPARTMENT OF THE INTERIOR OFFSHORE OPERATIONS IN THE OUTER... detailed Mining Plan than is obtainable under an approved Delineation Plan, to prepare feasibility studies, to carry out a pilot program to evaluate processing techniques or technology or mining equipment, or...

30 CFR 582.23 - Testing Plan.

Code of Federal Regulations, 2014 CFR

2014-07-01

... Resources BUREAU OF OCEAN ENERGY MANAGEMENT, DEPARTMENT OF THE INTERIOR OFFSHORE OPERATIONS IN THE OUTER... detailed Mining Plan than is obtainable under an approved Delineation Plan, to prepare feasibility studies, to carry out a pilot program to evaluate processing techniques or technology or mining equipment, or...

30 CFR 582.23 - Testing Plan.

Code of Federal Regulations, 2012 CFR

2012-07-01

... Resources BUREAU OF OCEAN ENERGY MANAGEMENT, DEPARTMENT OF THE INTERIOR OFFSHORE OPERATIONS IN THE OUTER... detailed Mining Plan than is obtainable under an approved Delineation Plan, to prepare feasibility studies, to carry out a pilot program to evaluate processing techniques or technology or mining equipment, or...

Development of composite carrythrough bulkhead

NASA Technical Reports Server (NTRS)

Ehlen, R. J.; Libeskind, M.

1992-01-01

A structural development program was recently completed in which the weight and fatigue advantages of an all composite major load carrying bulkhead was successfully demonstrated. Fabrication of a full scale article, including static and fatigue testing of the carry-through beam portion verified the producibility, strength and durability of this design, thereby presenting the opportunity for use on aircraft upgrades and new aircraft. A 15% weight saving is achievable and, more importantly, the fatigue problems that normally plague metal bulkheads are virtually eliminated.

Effectiveness of Intelligent Tutoring Systems: A Meta Analytic Review

DTIC Science & Technology

2017-02-01

studies of peer tutoring in elementary and secondary school mathematics, reported that tutoring programs raised math test scores by an average of 0.60...programs in elementary and secondary schools. Mathes and Fuchs (1994) found an improvement of 0.36 stan- dard deviations in 11 studies of peer...per- centile. Slavin et al. analyzed evaluations carried out in math courses in both middle and high schools. They located 13 evaluations, but only

Results of the 1983 NASA/JPL balloon flight solar cell calibration program

NASA Technical Reports Server (NTRS)

Downing, R. G.; Weiss, R. S.

1984-01-01

The 1983 solar cell calibration balloon flight was successfully completed and met all objectives of the program. Thirty-four modules were carried to an altitude of 36.0 kilometers. The calibrated cells can now be used as reference standards in simulator testing of cells and arrays. Cell calibration data are tabulated as well as the repeatability of standard solar cell BFS-17A (35 flights over a 21-year period).

Prediction of thermal cycling induced cracking in polmer matrix composites

NASA Technical Reports Server (NTRS)

Mcmanus, Hugh L.

1994-01-01

The work done in the period August 1993 through February 1994 on the 'Prediction of Thermal Cycling Induced Cracking In Polymer Matrix Composites' program is summarized. Most of the work performed in this period, as well as the previous one, is described in detail in the attached Master's thesis, 'Analysis of Thermally Induced Damage in Composite Space Structures,' by Cecelia Hyun Seon Park. Work on a small thermal cycling and aging chamber was concluded in this period. The chamber was extensively tested and calibrated. Temperatures can be controlled very precisely, and are very uniform in the test chamber. Based on results obtained in the previous period of this program, further experimental progressive cracking studies were carried out. The laminates tested were selected to clarify the differences between the behaviors of thick and thin ply layers, and to explore other variables such as stacking sequence and scaling effects. Most specimens tested were made available from existing stock at Langley Research Center. One laminate type had to be constructed from available prepreg material at Langley Research Center. Specimens from this laminate were cut and prepared at MIT. Thermal conditioning was carried out at Langley Research Center, and at the newly constructed MIT facility. Specimens were examined by edge inspection and by crack configuration studies, in which specimens were sanded down in order to examine the distribution of cracks within the specimens. A method for predicting matrix cracking due to decreasing temperatures and/or thermal cycling in all plies of an arbitrary laminate was implemented as a computer code. The code also predicts changes in properties due to the cracking. Extensive correlations between test results and code predictions were carried out. The computer code was documented and is ready for distribution.

Mission definition study for Stanford relativity satellite. Volume 2: Engineering flight test program

NASA Technical Reports Server (NTRS)

1971-01-01

The need is examined for orbital flight tests of gyroscope, dewar, and other components, in order to reduce the technical and financial risk in performing the relativity experiment. A program is described that would generate engineering data to permit prediction of final performance. Two flight tests are recommended. The first flight would test a dewar smaller than that required for the final flight, but of size and form sufficient to allow extrapolation to the final design. The second flight would use the same dewar design to carry a set of three gyroscopes, which would be evaluated for spinup and drift characteristics for a period of a month or more. A proportional gas control system using boiloff helium gas from the dewar, and having the ability to prevent sloshing of liquid helium, would also be tested.

A comparison of fitness-case sampling methods for genetic programming

NASA Astrophysics Data System (ADS)

Martínez, Yuliana; Naredo, Enrique; Trujillo, Leonardo; Legrand, Pierrick; López, Uriel

2017-11-01

Genetic programming (GP) is an evolutionary computation paradigm for automatic program induction. GP has produced impressive results but it still needs to overcome some practical limitations, particularly its high computational cost, overfitting and excessive code growth. Recently, many researchers have proposed fitness-case sampling methods to overcome some of these problems, with mixed results in several limited tests. This paper presents an extensive comparative study of four fitness-case sampling methods, namely: Interleaved Sampling, Random Interleaved Sampling, Lexicase Selection and Keep-Worst Interleaved Sampling. The algorithms are compared on 11 symbolic regression problems and 11 supervised classification problems, using 10 synthetic benchmarks and 12 real-world data-sets. They are evaluated based on test performance, overfitting and average program size, comparing them with a standard GP search. Comparisons are carried out using non-parametric multigroup tests and post hoc pairwise statistical tests. The experimental results suggest that fitness-case sampling methods are particularly useful for difficult real-world symbolic regression problems, improving performance, reducing overfitting and limiting code growth. On the other hand, it seems that fitness-case sampling cannot improve upon GP performance when considering supervised binary classification.

Hyper-X and Pegasus Launch Vehicle: A Three-Foot Model of the Hypersonic Experimental Research Vehic

NASA Technical Reports Server (NTRS)

1997-01-01

A close-up view of the X-43A Hypersonic Experimental Research Vehicle, or Hyper-X, portion of a three-foot-long model of the vehicle/booster combination at NASA's Dryden Flight Research Center, Edwards, California. Hyper-X, the flight vehicle for which is designated as X-43A, is an experimental flight-research program seeking to demonstrate airframe-integrated, 'air-breathing' engine technologies that promise to increase payload capacity for future vehicles, including hypersonic aircraft (faster than Mach 5) and reusable space launchers. This multiyear program is currently underway at NASA Dryden Flight Research Center, Edwards, California. The Hyper-X schedule calls for its first flight later this year (2000). Hyper-X is a joint program, with Dryden sharing responsibility with NASA's Langley Research Center, Hampton, Virginia. Dryden's primary role is to fly three unpiloted X-43A research vehicles to validate engine technologies and hypersonic design tools as well as the hypersonic test facility at Langley. Langley manages the program and leads the technology development effort. The Hyper-X Program seeks to significantly expand the speed boundaries of air-breathing propulsion by being the first aircraft to demonstrate an airframe-integrated, scramjet-powered free flight. Scramjets (supersonic-combustion ramjets) are ramjet engines in which the airflow through the whole engine remains supersonic. Scramjet technology is challenging because only limited testing can be performed in ground facilities. Long duration, full-scale testing requires flight research. Scramjet engines are air-breathing, capturing their oxygen from the atmosphere. Current spacecraft, such as the Space Shuttle, are rocket powered, so they must carry both fuel and oxygen for propulsion. Scramjet technology-based vehicles need to carry only fuel. By eliminating the need to carry oxygen, future hypersonic vehicles will be able to carry heavier payloads. Another unique aspect of the X-43A vehicle is the airframe integration. The body of the vehicle itself forms critical elements of the engine. The forebody acts as part of the intake for airflow and the aft section serves as the nozzle. The X-43A vehicles were manufactured by Micro Craft, Inc., Tullahoma, Tennessee. Orbital Sciences Corporation, Chandler, Arizona, built the Pegasus rocket booster used to launch the X-43 vehicles. For the Dryden research flights, the Pegasus rocket booster and attached X-43 will be air launched by Dryden's B-52 'Mothership.' After release from the B-52, the booster will accelerate the X-43A vehicle to the established test conditions (Mach 7 to 10) at an altitude of approximately 100,000 feet where the X-43 will separate from the booster and fly under its own power and preprogrammed control.

Hyper-X and Pegasus Launch Vehicle: A Three-Foot Model of the Hypersonic Experimental Research Vehic

NASA Technical Reports Server (NTRS)

1997-01-01

The configuration of the X-43A Hypersonic Experimental Research Vehicle, or Hyper-X, attached to a Pegasus launch vehicle is displayed in this three-foot-long model at NASA's Dryden Flight Research Center, Edwards, California. Hyper-X, the flight vehicle for which is designated as X-43A, is an experimental flight-research program seeking to demonstrate airframe-integrated, 'air-breathing' engine technologies that promise to increase payload capacity for future vehicles, including hypersonic aircraft (faster than Mach 5) and reusable space launchers. This multiyear program is currently underway at NASA Dryden Flight Research Center, Edwards, California. The Hyper-X schedule calls for its first flight later this year (2000). Hyper-X is a joint program, with Dryden sharing responsibility with NASA's Langley Research Center, Hampton, Virginia. Dryden's primary role is to fly three unpiloted X-43A research vehicles to validate engine technologies and hypersonic design tools as well as the hypersonic test facility at Langley. Langley manages the program and leads the technology development effort. The Hyper-X Program seeks to significantly expand the speed boundaries of air-breathing propulsion by being the first aircraft to demonstrate an airframe-integrated, scramjet-powered free flight. Scramjets (supersonic-combustion ramjets) are ramjet engines in which the airflow through the whole engine remains supersonic. Scramjet technology is challenging because only limited testing can be performed in ground facilities. Long duration, full-scale testing requires flight research. Scramjet engines are air-breathing, capturing their oxygen from the atmosphere. Current spacecraft, such as the Space Shuttle, are rocket powered, so they must carry both fuel and oxygen for propulsion. Scramjet technology-based vehicles need to carry only fuel. By eliminating the need to carry oxygen, future hypersonic vehicles will be able to carry heavier payloads. Another unique aspect of the X-43A vehicle is the airframe integration. The body of the vehicle itself forms critical elements of the engine. The forebody acts as part of the intake for airflow and the aft section serves as the nozzle. The X-43A vehicles were manufactured by Micro Craft, Inc., Tullahoma, Tennessee. Orbital Sciences Corporation, Chandler, Arizona, built the Pegasus rocket booster used to launch the X-43 vehicles. For the Dryden research flights, the Pegasus rocket booster and attached X-43 will be air launched by Dryden's B-52 'Mothership.' After release from the B-52, the booster will accelerate the X-43A vehicle to the established test conditions (Mach 7 to 10) at an altitude of approximately 100,000 feet where the X-43 will separate from the booster and fly under its own power and preprogrammed control.

Hyper-X and Pegasus Launch Vehicle: A Three-Foot Model of the Hypersonic Experimental Research Vehic

NASA Technical Reports Server (NTRS)

1997-01-01

The configuration of the X-43A Hypersonic Experimental Research Vehicle, or Hyper-X, attached to a Pegasus launch vehicle is displayed in this side view of a three-foot-long model of the vehicle/booster combination at NASA's Dryden Flight Research Center, Edwards, California. Hyper-X, the flight vehicle for which is designated as X-43A, is an experimental flight-research program seeking to demonstrate airframe-integrated, 'air-breathing' engine technologies that promise to increase payload capacity for future vehicles, including hypersonic aircraft (faster than Mach 5) and reusable space launchers. This multiyear program is currently underway at NASA Dryden Flight Research Center, Edwards, California. The Hyper-X schedule calls for its first flight later this year (2000). Hyper-X is a joint program, with Dryden sharing responsibility with NASA's Langley Research Center, Hampton, Virginia. Dryden's primary role is to fly three unpiloted X-43A research vehicles to validate engine technologies and hypersonic design tools as well as the hypersonic test facility at Langley. Langley manages the program and leads the technology development effort. The Hyper-X Program seeks to significantly expand the speed boundaries of air-breathing propulsion by being the first aircraft to demonstrate an airframe-integrated, scramjet-powered free flight. Scramjets (supersonic-combustion ramjets) are ramjet engines in which the airflow through the whole engine remains supersonic. Scramjet technology is challenging because only limited testing can be performed in ground facilities. Long duration, full-scale testing requires flight research. Scramjet engines are air-breathing, capturing their oxygen from the atmosphere. Current spacecraft, such as the Space Shuttle, are rocket powered, so they must carry both fuel and oxygen for propulsion. Scramjet technology-based vehicles need to carry only fuel. By eliminating the need to carry oxygen, future hypersonic vehicles will be able to carry heavier payloads. Another unique aspect of the X-43A vehicle is the airframe integration. The body of the vehicle itself forms critical elements of the engine. The forebody acts as part of the intake for airflow and the aft section serves as the nozzle. The X-43A vehicles were manufactured by Micro Craft, Inc., Tullahoma, Tennessee. Orbital Sciences Corporation, Chandler, Arizona, built the Pegasus rocket booster used to launch the X-43 vehicles. For the Dryden research flights, the Pegasus rocket booster and attached X-43 will be air launched by Dryden's B-52 'Mothership.' After release from the B-52, the booster will accelerate the X-43A vehicle to the established test conditions (Mach 7 to 10) at an altitude of approximately 100,000 feet where the X-43 will separate from the booster and fly under its own power and preprogrammed control.

X-38 - First Flight

NASA Technical Reports Server (NTRS)

1997-01-01

Reminiscent of the lifting body research flights conducted more than 30 years earlier, NASA's B-52 mothership lifts off carrying a new generation of lifting body research vehicle--the X-38. The X-38 was designed to help develop an emergency crew return vehicle for the International Space Station. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

X-38 Ship #2 Mated to B-52 Mothership in Flight

NASA Technical Reports Server (NTRS)

1999-01-01

This photo shows one of the X-38 lifting-body research vehicles mated to NASA's B-52 mothership in flight prior to launch. The B-52 has been a workhorse for the Dryden Flight Research Center for more than 40 years, carrying numerous research vehicles aloft and conducting a variety of other research flight experiments. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

X-38 - First Flight

NASA Technical Reports Server (NTRS)

1997-01-01

In a scene reminiscent of the lifting body research flights conducted more than 30 years earlier, this photo shows a close-up view of NASA's B-52 mothership as it lifts off carrying a new generation of lifting body research vehicle--the X-38. The X-38 was designed to help develop an emergency crew return vehicle for the International Space Station. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

Close-up of Wing Fit Check of Pylon to Carry the X-38 on B-52 Launch Aircraft

NASA Technical Reports Server (NTRS)

1997-01-01

Tom McMullen, Chief of Dryden's Experimental Fabrication Shop, makes adjustments to the new pylon for NASA's X-38 during a fit-check on NASA's B-52 at the Dryden Flight Research Center, Edwards, California, in 1997. The fit-check was the first time the 1,200-pound steel pylon was mated to the B-52 following fabrication at Dryden by the Center's Experimental Fabrication Shop. The pylon was built as an 'adapter' to allow the X-38 to be attached to and launched from the B-52's wing. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

Spin Research Vehicle (SRV) in B-52 Captive Flight

NASA Technical Reports Server (NTRS)

1981-01-01

This in-flight photo of NASA's B-52 mothership shows the bomber carrying a subscale model of an Air Force F-15, a remotely piloted vehicle that was used to conduct spin research. The F-15 Remotely Piloted Research Vehicles (RPRV) was air launched from the B-52 at approximately 45,000 feet and was controlled by a pilot in a ground cockpit complete with flight controls and a television screen. The F-15 model in this particular configuration was known as the Spin Research Vehicle (SRV). NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

Hyper-X Research Vehicle - Artist Concept in Flight with Scramjet Engine Firing

NASA Technical Reports Server (NTRS)

1997-01-01

This is an artist's depiction of a Hyper-X research vehicle under scramjet power in free-flight following separation from its booster rocket. The X-43A was developed to flight test a dual-mode ramjet/scramjet propulsion system at speeds from Mach 7 up to Mach 10 (7 to 10 times the speed of sound, which varies with temperature and altitude). Hyper-X, the flight vehicle for which is designated as X-43A, is an experimental flight-research program seeking to demonstrate airframe-integrated, 'air-breathing' engine technologies that promise to increase payload capacity for future vehicles, including hypersonic aircraft (faster than Mach 5) and reusable space launchers. This multiyear program is currently underway at NASA Dryden Flight Research Center, Edwards, California. The Hyper-X schedule calls for its first flight later this year (2000). Hyper-X is a joint program, with Dryden sharing responsibility with NASA's Langley Research Center, Hampton, Virginia. Dryden's primary role is to fly three unpiloted X-43A research vehicles to validate engine technologies and hypersonic design tools as well as the hypersonic test facility at Langley. Langley manages the program and leads the technology development effort. The Hyper-X Program seeks to significantly expand the speed boundaries of air-breathing propulsion by being the first aircraft to demonstrate an airframe-integrated, scramjet-powered free flight. Scramjets (supersonic-combustion ramjets) are ramjet engines in which the airflow through the whole engine remains supersonic. Scramjet technology is challenging because only limited testing can be performed in ground facilities. Long duration, full-scale testing requires flight research. Scramjet engines are air-breathing, capturing their oxygen from the atmosphere. Current spacecraft, such as the Space Shuttle, are rocket powered, so they must carry both fuel and oxygen for propulsion. Scramjet technology-based vehicles need to carry only fuel. By eliminating the need to carry oxygen, future hypersonic vehicles will be able to carry heavier payloads. Another unique aspect of the X-43A vehicle is the airframe integration. The body of the vehicle itself forms critical elements of the engine. The forebody acts as part of the intake for airflow and the aft section serves as the nozzle. The X-43A vehicles were manufactured by Micro Craft, Inc., Tullahoma, Tennessee. Orbital Sciences Corporation, Chandler, Arizona, built the Pegasus rocket booster used to launch the X-43 vehicles. For the Dryden research flights, the Pegasus rocket booster and attached X-43 will be air launched by Dryden's B-52 'Mothership.' After release from the B-52, the booster will accelerate the X-43A vehicle to the established test conditions (Mach 7 to 10) at an altitude of approximately 100,000 feet where the X-43 will separate from the booster and fly under its own power and preprogrammed control.

Hyper-X Research Vehicle - Artist Concept Mounted on Pegasus Rocket Attached to B-52 Launch Aircraft

NASA Technical Reports Server (NTRS)

1997-01-01

This artist's concept depicts the Hyper-X research vehicle riding on a booster rocket prior to being launched by the Dryden Flight Research Center's B-52 at about 40,000 feet. The X-43A was developed to flight test a dual-mode ramjet/scramjet propulsion system at speeds from Mach 7 up to Mach 10 (7 to 10 times the speed of sound, which varies with temperature and altitude). Hyper-X, the flight vehicle for which is designated as X-43A, is an experimental flight-research program seeking to demonstrate airframe-integrated, 'air-breathing' engine technologies that promise to increase payload capacity for future vehicles, including hypersonic aircraft (faster than Mach 5) and reusable space launchers. This multiyear program is currently underway at NASA Dryden Flight Research Center, Edwards, California. The Hyper-X schedule calls for its first flight later this year (2000). Hyper-X is a joint program, with Dryden sharing responsibility with NASA's Langley Research Center, Hampton, Virginia. Dryden's primary role is to fly three unpiloted X-43A research vehicles to validate engine technologies and hypersonic design tools as well as the hypersonic test facility at Langley. Langley manages the program and leads the technology development effort. The Hyper-X Program seeks to significantly expand the speed boundaries of air-breathing propulsion by being the first aircraft to demonstrate an airframe-integrated, scramjet-powered free flight. Scramjets (supersonic-combustion ramjets) are ramjet engines in which the airflow through the whole engine remains supersonic. Scramjet technology is challenging because only limited testing can be performed in ground facilities. Long duration, full-scale testing requires flight research. Scramjet engines are air-breathing, capturing their oxygen from the atmosphere. Current spacecraft, such as the Space Shuttle, are rocket powered, so they must carry both fuel and oxygen for propulsion. Scramjet technology-based vehicles need to carry only fuel. By eliminating the need to carry oxygen, future hypersonic vehicles will be able to carry heavier payloads. Another unique aspect of the X-43A vehicle is the airframe integration. The body of the vehicle itself forms critical elements of the engine. The forebody acts as part of the intake for airflow and the aft section serves as the nozzle. The X-43A vehicles were manufactured by Micro Craft, Inc., Tullahoma, Tennessee. Orbital Sciences Corporation, Chandler, Arizona, built the Pegasus rocket booster used to launch the X-43 vehicles. For the Dryden research flights, the Pegasus rocket booster and attached X-43 will be air launched by Dryden's B-52 'Mothership.' After release from the B-52, the booster will accelerate the X-43A vehicle to the established test conditions (Mach 7 to 10) at an altitude of approximately 100,000 feet where the X-43 will separate from the booster and fly under its own power and preprogrammed control.

Analysis of the national school feeding program in the municipality of Viçosa, state of Minas Gerais

PubMed Central

Rocha, Naruna Pereira; Filgueiras, Mariana De Santis; de Albuquerque, Fernanda Martins; Milagres, Luana Cupertino; Castro, Ana Paula Pereira; Silva, Mariane Alves; da Costa, Glauce Dias; Priore, Silvia Eloiza; de Novaes, Juliana Farias

2018-01-01

ABSTRACT OBJECTIVE To analyze the implementation of the Brazilian National School Feeding Program as a food and nutritional security policy in public schools. METHODS This a cross-sectional study, with a quantitative and qualitative approach, carried out with 268 schoolchildren aged eight to nine years from the public school system of Viçosa, state of Minas Gerais, Brazil, in 2015. Interviews were carried out using semi-structured questionnaires with the children, parents, cooks, nutritionists, trainer of the Technical Assistance and Rural Extension Company, and president of the School Feeding Council. In order to analyze the implementation of the National School Feeding Program in Viçosa, we evaluated the direct weighing of the food served in the schools using mechanical balances with a capacity of up to 10 kg and the perception of the social players involved in the implementation of the National School Feeding Program. The children were questioned about the acceptance of and adherence to the food offered, in addition to the habit of bringing food from home. Parents reported knowledge about the School Feeding Program and Council. The qualitative analysis consisted of content analysis and quantitative analysis using the chi-square test, Fisher’s exact test, and Mann-Whitney test. We adopted the statistical significance of 5% for quantitative analysis. RESULTS Children reported low adherence to the school feeding program and most of them used to bring food from home. Irregularities were identified in the implementation of the National School Feeding Program, such as: inadequate number of nutritionists, suspension of Council meetings, inadequate infrastructure in the areas of preparation and distribution of meals, lack of training of cooks, lack of nutritional adequacy of the food offered, and lack of actions on food and nutritional education. The Program complied with the recommendations for purchasing food from family farms. CONCLUSIONS The National School Feeding Program presented many irregularities in Viçosa. It is important to monitor the problems identified for better reformulation and planning of the Program, in order to guarantee the food and nutritional security of the children served. PMID:29489989

Analysis of the national school feeding program in the municipality of Viçosa, state of Minas Gerais.

PubMed

Rocha, Naruna Pereira; Filgueiras, Mariana De Santis; Albuquerque, Fernanda Martins de; Milagres, Luana Cupertino; Castro, Ana Paula Pereira; Silva, Mariane Alves; Costa, Glauce Dias da; Priore, Silvia Eloiza; Novaes, Juliana Farias de

2018-01-01

OBJECTIVE To analyze the implementation of the Brazilian National School Feeding Program as a food and nutritional security policy in public schools. METHODS This a cross-sectional study, with a quantitative and qualitative approach, carried out with 268 schoolchildren aged eight to nine years from the public school system of Viçosa, state of Minas Gerais, Brazil, in 2015. Interviews were carried out using semi-structured questionnaires with the children, parents, cooks, nutritionists, trainer of the Technical Assistance and Rural Extension Company, and president of the School Feeding Council. In order to analyze the implementation of the National School Feeding Program in Viçosa, we evaluated the direct weighing of the food served in the schools using mechanical balances with a capacity of up to 10 kg and the perception of the social players involved in the implementation of the National School Feeding Program. The children were questioned about the acceptance of and adherence to the food offered, in addition to the habit of bringing food from home. Parents reported knowledge about the School Feeding Program and Council. The qualitative analysis consisted of content analysis and quantitative analysis using the chi-square test, Fisher's exact test, and Mann-Whitney test. We adopted the statistical significance of 5% for quantitative analysis. RESULTS Children reported low adherence to the school feeding program and most of them used to bring food from home. Irregularities were identified in the implementation of the National School Feeding Program, such as: inadequate number of nutritionists, suspension of Council meetings, inadequate infrastructure in the areas of preparation and distribution of meals, lack of training of cooks, lack of nutritional adequacy of the food offered, and lack of actions on food and nutritional education. The Program complied with the recommendations for purchasing food from family farms. CONCLUSIONS The National School Feeding Program presented many irregularities in Viçosa. It is important to monitor the problems identified for better reformulation and planning of the Program, in order to guarantee the food and nutritional security of the children served.

'Secret' Shuttle payloads revealed

NASA Astrophysics Data System (ADS)

Powell, Joel W.

1993-05-01

A secret military payload carried by the orbiter Discovery launched on January 24 1985 is discussed. Secondary payloads on the military Shuttle flights are briefly reviewed. Most of the military middeck experiments were sponsored by the Space Test Program established at the Pentagon to oversee all Defense Department space research projects.

B-52 Testing Developmental Space Shuttle Drag Chute

NASA Technical Reports Server (NTRS)

1990-01-01

A close-up of an experimental drag chute deploying in a cloud of dust behind NASA's B-52 research aircraft just after landing on Rogers Dry Lake, adjacent to the Dryden Flight Research Center, Edwards, California, on a 1990 research flight. The B-52's tests led to the development of a drag chute to help the Space Shuttle land more safely and easily. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

B-52 Testing F-111 Parachute

NASA Technical Reports Server (NTRS)

1988-01-01

A mock-up of an F-111 cockpit section drops out of the bomb bay of NASA's B-52 mothership on a test flight of a new parachute system for the F-111 'Aardvark' bomber. The F-111's ejection system separated the entire cockpit from the rest of the aircraft, and a large parachute was then deployed to lower the cockpit section to the ground. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

B-52 Testing Developmental Space Shuttle Drag Chute

NASA Technical Reports Server (NTRS)

1990-01-01

An aerial view of NASA's B-52 research aircraft deploying an experimental drag chute just after landing on Rogers Dry Lake, adjacent to the Dryden Flight Research Center, Edwards, California, on a 1990 research flight. The B-52's tests led to the development of a drag chute to help the Space Shuttle land more safely and easily. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

HiMAT Subscale Research Vehicle Mated to B-52 Mothership in Flight, Close-up View

NASA Technical Reports Server (NTRS)

1980-01-01

A close-up view of the Highly Maneuverable Aircraft Technology (HiMAT) research vehicle attached to a wing pylon on NASA's B-52 mothership during a 1980 test flight. The HiMAT used sharply swept-back wings and a canard configuration to test possible technology for advanced fighters. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

B-52 Testing Developmental Space Shuttle Drag Chute

NASA Technical Reports Server (NTRS)

1990-01-01

NASA's B-52 research aircraft deploys an experimental drag chute just after landing the runway at the Dryden Flight Research Center, Edwards, California, on a 1990 research flight. The B-52's tests led to the development of a drag chute to help the Space Shuttle land more safely and easily. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

B-52 Testing Developmental Space Shuttle Drag Chute

NASA Technical Reports Server (NTRS)

1990-01-01

An experimental drag chute deploys amidst a cloud of dust behind NASA's B-52 research aircraft just after landing on Rogers Dry Lake, adjacent to the Dryden Flight Research Center, Edwards, California, on a 1990 research flight. The B-52's tests led to the development of a drag chute to help the Space Shuttle land more safely and easily. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

B-52 Testing Developmental Space Shuttle Drag Chute

NASA Technical Reports Server (NTRS)

1990-01-01

A rear view of NASA's B-52 research aircraft deploying an experimental drag chute just after landing on Rogers Dry Lake, adjacent to the Dryden Flight Research Center, Edwards, California, on a 1990 research flight. The B-52's tests led to the development of a drag chute to help the Space Shuttle land more safely and easily. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

B-52 Testing F-111 Parachute

NASA Technical Reports Server (NTRS)

1988-01-01

The main parachute begins to deploy on the mock-up of an F-111 'Aardvark' bomber cockpit section after being dropped from NASA's B-52 mothership during 1988 flight tests on improved parachute systems for the Air Force bomber. The F-111's ejection system separated the entire cockpit from the rest of the aircraft, and a large parachute was then deployed to lower the cockpit section to the ground. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

X-38 Ship #2 in Free Flight after Release from B-52 Mothership

NASA Technical Reports Server (NTRS)

1999-01-01

The X-38 research vehicle drops away from NASA's B-52 mothership immediately after being released from the B-52's wing pylon. More than 30 years earlier, this same B-52 launched the original lifting-body vehicles flight tested by NASA and the Air Force at what is now called the Dryden Flight Research Center and the Air Force Flight Test Center. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

Effectiveness of cognitive behavioral therapy based on the pain sustainment/exacerbation model in patients with tension-type headache: a pilot study.

PubMed

Motoya, Ryo; Oda, Keiko; Ito, Eiji; Ichikawa, Masahiro; Sato, Taku; Watanabe, Tadashi; Sakuma, Jun; Saito, Kiyoshi; Niwa, Shin-Ichi; Yabe, Hirooki

2014-01-01

The purpose of this study was to carry out a program of Cognitive Behavioral Therapy (CBT) based on the pain sustainment/exacerbation model for tension-type headache (TTH) patients and to examine the effectiveness as a pilot study. The participants were 4 TTH patients who consulted the outpatient clinic of a university hospital. It consisted of 4 individualized sessions as CBT program (including psychological education, self-monitoring, relaxation technique, cognitive restricting and exposure), and a follow-up examination was carried out 1 month after its completion. The sessions, each of which was 60 minutes long, were executed at weekly intervals. As a result, the score of the Pain Catastrophizing Scale (PCS) decreased after program compared with before program in all patients. The score of escape/avoidance was also reduced at the post-program and follow-up (1 month later) compared with the score of pre-program in patients except Case 2, in whom the score was 0 throughout the study. The degree of the Headache Impact Test (HIT-6) improved by program and changed to "mild" or "none" in all participants. These findings show that in patients with TTH this short CBT program has effect on pain catastrophizing, escape/avoidance and daily disability.

KSC-2009-2504

NASA Image and Video Library

2009-04-02

CAPE CANAVERAL, Fla. – On display at the Kennedy Space Center Visitor Complex in Florida is the Orion crew exploration vehicle mockup (left) and an exhibit about the Constellation Program. The Orion mockup is on display before heading offshore to be tested in open water. The spacecraft mock-up traveled from the Naval Surface Warfare Center's Carderock Division in Bethesda, Md. The goal of the open water testing, dubbed the Post-landing Orion Recovery Test, or PORT, is to determine what kind of motion astronauts can expect after landing, as well as outside conditions for recovery teams. Part of the Constellation Program, Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. Photo credit: NASA/Jack Pfaller

KSC-2009-2507

NASA Image and Video Library

2009-04-02

CAPE CANAVERAL, Fla. – On display at the Kennedy Space Center Visitor Complex in Florida is the Orion crew exploration vehicle mockup (right) and an exhibit about the Constellation Program. The Orion mockup is on display before heading offshore to be tested in open water. The spacecraft mock-up traveled from the Naval Surface Warfare Center's Carderock Division in Bethesda, Md. The goal of the open water testing, dubbed the Post-landing Orion Recovery Test, or PORT, is to determine what kind of motion astronauts can expect after landing, as well as outside conditions for recovery teams. Part of the Constellation Program, Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. Photo credit: NASA/Jack Pfaller

KSC-2009-2505

NASA Image and Video Library

2009-04-02

CAPE CANAVERAL, Fla. – A NASA official talks to visitors at the Kennedy Space Center Visitor Complex in Florida about the Orion crew exploration vehicle mockup and the Constellation Program. The Orion mockup is on display before heading offshore to be tested in open water. The spacecraft mock-up traveled from the Naval Surface Warfare Center's Carderock Division in Bethesda, Md. The goal of the open water testing, dubbed the Post-landing Orion Recovery Test, or PORT, is to determine what kind of motion astronauts can expect after landing, as well as outside conditions for recovery teams. Part of the Constellation Program, Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. Photo credit: NASA/Jack Pfaller

KSC-2013-3391

NASA Image and Video Library

2013-08-22

EDWARDS AFB, Calif. - ED13-0300-002 – An Erickson Air-Crane helicopter lifts Sierra Nevada Corporation's Dream Chaser flight vehicle during a captive-carry flight test. The test was a rehearsal for free flights at Edwards later this year. The spacecraft is under development in partnership with NASA's Commercial Crew Program. Although the spacecraft is designed for crew members, the vehicle will not have anyone onboard during the free flights. Photo credit: NASA/Carla Thomas

KSC-2013-3390

NASA Image and Video Library

2013-08-22

EDWARDS AFB, Calif. - ED13-0300-001 – An Erickson Air-Crane helicopter lifts Sierra Nevada Corporation's Dream Chaser flight vehicle during a captive-carry flight test. The test was a rehearsal for free flights at Edwards later this year. The spacecraft is under development in partnership with NASA's Commercial Crew Program. Although the spacecraft is designed for crew members, the vehicle will not have anyone onboard during the free flights. Photo credit: NASA/Carla Thomas

KSC-2013-3392

NASA Image and Video Library

2013-08-22

EDWARDS AFB, Calif. - ED13-0300-003 – An Erickson Air-Crane helicopter lifts Sierra Nevada Corporation's Dream Chaser flight vehicle during a captive-carry flight test. The test was a rehearsal for free flights at Edwards later this year. The spacecraft is under development in partnership with NASA's Commercial Crew Program. Although the spacecraft is designed for crew members, the vehicle will not have anyone onboard during the free flights. Photo credit: NASA/Carla Thomas

Development and Testing of Physically-Based Methods for Filling Gaps in Remotely Sensed River Data

DTIC Science & Technology

2011-09-30

Filling Gaps in Remotely Sensed River Data Jonathan M. Nelson US Geological Survey National Research Program Geomorphology and Sediment Transport...the research work carried out under this grant are to develop and test two methods for filling in gaps in remotely sensed river data. The first...information, including suggestions for reducing this burden, to Washington Headquarters Services, Directorate for Information Operations and Reports, 1215

Integrated Vehicle Ground Vibration Testing of Manned Spacecraft: Historical Precedent

NASA Technical Reports Server (NTRS)

Lemke, Paul R.; Tuma, Margaret L.; Askins, Bruce R.

2008-01-01

For the first time in nearly 30 years, NASA is developing a new manned space flight launch system. The Ares I will carry crew and cargo to not only the International Space Station, but onward for the future exploration of the Moon and Mars. The Ares I control system and structural designs use complex computer models for their development. An Integrated Vehicle Ground Vibration Test (IVGVT) will validate the efficacy of these computer models. The IVGVT will reduce the technical risk of unexpected conditions that could place the vehicle or crew in jeopardy. The Ares Project Office's Flight and Integrated Test Office commissioned a study to determine how historical programs, such as Saturn and Space Shuttle, validated the structural dynamics of an integrated flight vehicle. The study methodology was to examine the historical record and seek out members of the engineering community who recall the development of historic manned launch vehicles. These records and interviews provided insight into the best practices and lessons learned from these historic development programs. The information that was gathered allowed the creation of timelines of the historic development programs. The timelines trace the programs from the development of test articles through test preparation, test operations, and test data reduction efforts. These timelines also demonstrate how the historical tests fit within their overall vehicle development programs. Finally, the study was able to quantify approximate staffing levels during historic development programs. Using this study, the Flight and Integrated Test Office was able to evaluate the Ares I Integrated Vehicle Ground Vibration Test schedule and workforce budgets in light of the historical precedents to determine if the test had schedule or cost risks associated with it.

Shuttle OFT medical report: Summary of medical results from STS-1, STS-2, STS-3, and STS-4

NASA Technical Reports Server (NTRS)

Pool, S. L. (Editor); Johnson, P. C., Jr. (Editor); Mason, J. A. (Editor)

1983-01-01

The medical operations for the orbital test flights which includes a review of the health of the crews before, during, and immediately after the four shuttle orbital flights are reported. Health evaluation, health stabilization program, medical training, medical "kit" carried in flight, tests and countermeasures for space motion sickness, cardiovascular, biochemistry and endocrinology results, hematology and immunology analyses, medical microbiology, food and nutrition, potable water, Shuttle toxicology, radiological health, and cabin acoustical noise are reviewed. Information on environmental effects of Shuttle launch and landing, medical information management, and management, planning, and implementation of the medical program are included.

The NASA-Lewis/ERDA solar heating and cooling technology program. [project planning/energy policy

NASA Technical Reports Server (NTRS)

Couch, J. P.; Bloomfield, H. S.

1975-01-01

Plans by NASA to carry out a major role in a solar heating and cooling program are presented. This role would be to create and test the enabling technology for future solar heating, cooling, and combined heating/cooling systems. The major objectives of the project are to achieve reduction in solar energy system costs, while maintaining adequate performance, reliability, life, and maintenance characteristics. The project approach is discussed, and will be accomplished principally by contract with industry to develop advanced components and subsystems. Advanced hardware will be tested to establish 'technology readiness' both under controlled laboratory conditions and under real sun conditions.

Human-rated Safety Certification of a High Voltage Robonaut Lithium-ion Battery

NASA Technical Reports Server (NTRS)

Jeevarajan, Judith; Yayathi, S.; Johnson, M.; Waligora, T.; Verdeyen, W.

2013-01-01

NASA's rigorous certification process is being followed for the R2 high voltage battery program for use of R2 on International Space Station (ISS). Rigorous development testing at appropriate levels to credible off-nominal conditions and review of test data led to design improvements for safety at the virtual cell, cartridge and battery levels. Tests were carried out at all levels to confirm that both hardware and software controls work. Stringent flight acceptance testing of the flight battery will be completed before launch for mission use on ISS.

Status of high temperature superconductor cable and fault current limiter projects at American Superconductor

NASA Astrophysics Data System (ADS)

Maguire, J. F.; Yuan, J.

2009-10-01

This paper will describe the status of three key programs currently underway at American Superconductor Corp. The first program is the LIPA project which is a transmission voltage high temperature superconducting cable program, with funding support from the US Department of Energy. The 600 m cable, capable of carrying 574 MVA, was successfully installed and commissioned in LIPA grid on April 22, 2008. An overview of the project, system level design details and operational data will be provided. In addition, the status of the newly awarded LIPA II project will be described. The second program is Project Hydra, with funding support from the US Department of Homeland Security, to design, develop and demonstrate an HTS cable with fault current limiting functionality. The cable is 300 m long and is being designed to carry 96 MVA at a distribution level voltage of 13.8 kV. The cable will be permanently installed and energized in Manhattan, New York in 2010. The initial status of Project Hydra will be presented. The final program to be discussed is a transmission voltage, high temperature superconducting fault current limiter funded by the US DOE. The project encompasses the design, construction and test of a 115 kV FCL for power transmission within a time frame of 4-5 years. Installation and testing are planned for a Southern California Edison substation. A project overview and progress under the first phase will be reported.

Results of the 1994 NASA/JPL balloon flight solar cell calibration program

NASA Technical Reports Server (NTRS)

Anspaugh, B. E.; Weiss, R. S.

1994-01-01

The 1994 solar cell calibration balloon flight was completed on August 6, 1994. All objectives of the flight program were met. Thirty-seven modules were carried to an altitude of 119,000 ft (36.6 km). Data telemetered from the modules was corrected to 28 C and to 1 AU. The calibrated cells have been returned to the 6 participants and can now be used as reference standards in simulator testing of cells and arrays.

Results of the 1991 NASA/JPL balloon flight solar cell calibration program

NASA Technical Reports Server (NTRS)

Anspaugh, B. E.; Weiss, R. S.

1991-01-01

The 1991 solar cell calibration balloon flight was completed on August 1, 1991. All objectives of the flight program were met. Thirty-nine modules were carried to an altitude of 119,000 ft. (36.3 km). Data telemetered from the modules were corrected to 28 C and to 1 AU. The calibrated cells have been returned to the participants and can now be used as reference standards in simulator testing of cells and arrays.

Results of the 1992 NASA/JPL Balloon Flight Solar Cell Calibration Program

NASA Technical Reports Server (NTRS)

Anspaugh, B. E.; Weiss, R. S.

1992-01-01

The 1992 solar cell calibration balloon flight was completed on August 1, 1992. All objectives of the flight program were met. Forty-one modules were carried to an altitude of 119,000 ft (36.3 km). Data telemetered from the modules was corrected to 28 C and 1 AU. The calibrated cells have been returned to 39 participants and can now be used as reference standards in simulator testing of cells and arrays.

Results of the 1993 NASA/JPL balloon flight solar cell calibration program

NASA Technical Reports Server (NTRS)

Anspaugh, B. E.; Weiss, R. S.

1993-01-01

The 1993 solar cell calibration balloon flight was completed on July 29, 1993. All objectives of the flight program were met. Forty modules were carried to an altitude of 120,000 ft (36.6 km). Data telemetered from the modules was corrected to 28 C and to 1 AU. The calibrated cells have been returned to 8 participants and can now be used as reference standards in simulator testing of cells and arrays.

ECN-5033

NASA Image and Video Library

1976-01-29

The General Dynamics TACT/F-111A (Serial #63-9778) banks over the Mojave Desert. Note the fully loaded racks of inert pratice bombs which were carried for weapon loads evaluations on the supercritical wing (SCW) that was the main feature of the Transonic Aircraft Technology F-111 research program. Intense interest in the results of the earlier F-8 SCW program spurred NASA and the U.S. Air Force to modify the number 13 F-111A for the TACT program. This aircraft participated in a major research and flight testing program that spanned nearly 20 years, beginning in 1971 at the NASA Flight Research Center at Edwards AFB, California.

Qualification of Electrical Ground Support Equipment for New Space Programs

NASA Technical Reports Server (NTRS)

SotoToro, Felix A.; Vu, Bruce T.; Hamilton, Mark S.

2011-01-01

With the Space Shuttle program coming to an end, the National Aeronautics and Space Administration (NASA) is moving to a new space flight program that will allow expeditions beyond low earth orbit. The space vehicles required to comply with these missions will be carrying heavy payloads. This implies that the Earth departure stage capabilities must be of higher magnitudes, given the current propulsion technology. The engineering design of the new flight hardware comes with some structural, thermal, propulsion and other subsystems' challenges. Meanwhile, the necessary ground support equipment (GSE) used to test, validate, verify and process the flight hardware must withstand the new program specifications. This paper intends to provide the qualification considerations during implementation of new electrical GSE for space programs. A team of engineers was formed to embark on this task, and facilitate the logistics process and ensure that the electrical, mechanical and fluids subsystems conduct the proper level of testing. Ultimately, each subsystem must certify that each piece of ground support equipment used in the field is capable of withstanding the strenuous vibration, acoustics, environmental, thermal and Electromagnetic Interference (EMf) levels experienced during pre-launch, launch and post-launch activities. The benefits of capturing and sharing these findings will provide technical, cost savings and schedule impacts infon11ation to both the technical and management community. Keywords: Qualification; Testing; Ground Support Equipment; Electromagnetic Interference Testing; Vibration Testing; Acoustic Testing; Power Spectral Density.

[Support for Adult ASD in Medical Rework Program: Mutual Communication Program and Psychodrama].

PubMed

Yokoyama, Motonori

2015-01-01

While carrying out the Medical Rework Program, we realized the necessity for a supplementary medical treatment program aimed at adult ASD. Consequently, we started the Mutual Communication Program, which consists of standard SST and the new element of psychodrama. As a result, 32 participants have returned to their workplace in the three-year period, and the rate of successfully continuing to work was 93.8% at the time of the investigation. Various psychological tests also indicated significant improvement. In this article, we present a case study, explain psychodrama techniques employed in the program, and discuss their usefulness. The results suggest that psychodrama is a very effective assistive technique when the characteristics of ASD are taken into consideration.

Remote sensing in operational range management programs in Western Canada

NASA Technical Reports Server (NTRS)

Thompson, M. D.

1977-01-01

A pilot program carried out in Western Canada to test remote sensing under semi-operational conditions and display its applicability to operational range management programs was described. Four agencies were involved in the program, two in Alberta and two in Manitoba. Each had different objectives and needs for remote sensing within its range management programs, and each was generally unfamiliar with remote sensing techniques and their applications. Personnel with experience and expertise in the remote sensing and range management fields worked with the agency personnel through every phase of the pilot program. Results indicate that these agencies have found remote sensing to be a cost effective tool and will begin to utilize remote sensing in their operational work during ensuing seasons.

Ground crewmen help guide the alignment of the X-40A as the experimental craft is gently lowered to the ground by a U.S. Army CH-47 Chinook helicopter following a captive-carry test flight

NASA Image and Video Library

2000-12-08

Ground crewmen help guide the alignment of the X-40 technology demonstrator as the experimental craft is gently lowered to the ground by a U.S. Army CH-47 Chinook cargo helicopter following a captive-carry test flight at NASA's Dryden Flight Research Center, Edwards, California. The X-40 is an unpowered 82 percent scale version of the X-37, a Boeing-developed spaceplane designed to demonstrate various advanced technologies for development of future lower-cost access to space vehicles. The X-37 will be carried into space aboard a space shuttle and then released to perform various maneuvers and a controlled re-entry through the Earth's atmosphere to an airplane-style landing on a runway, controlled entirely by pre-programmed computer software. Following a series of captive-carry flights, the X-40 made several free flights from a launch altitude of about 15,000 feet above ground, gliding to a fully autonomous landing. The captive carry flights helped verify the X-40's navigation and control systems, rigging angles for its sling, and stability and control of the helicopter while carrying the X-40 on a tether.

Investigation of a low NOx full-scale annular combustor

NASA Technical Reports Server (NTRS)

1982-01-01

An atmospheric test program was conducted to evaluate a low NOx annular combustor concept suitable for a supersonic, high-altitude aircraft application. The lean premixed combustor, known as the vortex air blast (VAB) concept, was tested as a 22.0-cm diameter model in the early development phases to arrive at basic design and performance criteria. Final demonstration testing was carried out on a full scale combustor of 0.66-m diameter. Variable geometry dilution ports were incorporated to allow operation of the combustor across the range of conditions between idle (T(in) = 422 K, T(out) = 917 K) and cruise (T(in) = 833 K, T(out) - 1778 K). Test results show that the design could meet the program NOx goal of 1.0 g NO2/kg fuel at a one-atmospheric simulated cruise condition.

Airborne polar experiment (APE): tests and qualification of the scientific instrumentation installed on the stratospheric platform M-55 aircraft

NASA Astrophysics Data System (ADS)

de Rossi, Giuseppe; Puccini, Massimo; Puccetti, Giuseppe

1995-12-01

The paper describes the environmental tests to be carried out on the scientific instrumentation to be flown on the M-55 Geophysika in the frame of the APE Program. The instruments, developed by different European research institutes, are for remote sensing and in situ measurements of the major components of the Earth's stratosphere. The paper presents the technological activities that ENEA (Ente Nazionale per le Nuove Tecnologie l'Energia e l'Ambiente) is carrying out in its laboratories to verify the correspondence of the various instruments to meet the requirements for airborne application. The reference documents used have been the RTCA/DO-160C and the MDB (Myasishchev Design Bureau) specifications.

Tipjet 80-inch Model Rotor Hover Test: Test No. 1198

DTIC Science & Technology

1993-09-01

primarily working papers Intended for internal use. They I carry an Identifying number which indicates their type and the numerical code of the oriwginatn...rotor lifting system, while exhbitin the highes aumntbnratio eve recorded for a CC rotor, sufer an induced power penalty due to the norilifting regon...INFORMATION This work was conducted by the Ship Systems and Programs DirectorateI (Code 22) of the Carderock Division, Naval Surface Warfare Center

Dryden B-52 Launch Aircraft on Edwards AFB Runway

NASA Technical Reports Server (NTRS)

1996-01-01

NASA's venerable workhorse, the B-52 mothership, rolls out on the Edwards AFB runway after a test flight in 1996. Over the course of more than 40 years, the B-52 launched numerous experimental aircraft, ranging from the X-15 to the X-38, and was also used as a flying testbed for a variety of other research projects. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

M2-F2 Mated to B-52 Mothership on Ramp

NASA Technical Reports Server (NTRS)

1965-01-01

A head-on view of the M2-F2 lifting body mounted on the wing pylon of its B-52 mothership in 1965. This was for a captive flight made the following month. The M2-F2 remained attached to the B-52 throughout the flight to test its on-board systems. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet.. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

HiMAT Subscale Research Vehicle Mated to B-52 Mothership in Flight

NASA Technical Reports Server (NTRS)

1980-01-01

The Highly Maneuverable Aircraft Technology (HiMAT) research vehicle is shown here mated to a wing pylon on NASA's B-52 mothership aircraft. The HiMAT was a technology demonstrator to test structures and configurations for advanced fighter concepts. Over the course of more than 40 years, the B-52 proved a valuable workhorse for NASA's Dryden Flight Research Center (under various names), launching a wide variety of vehicles and conducting numerous other research flights. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

Support services for the automative gas turbine project

NASA Technical Reports Server (NTRS)

Golec, T. (Editor)

1981-01-01

Support was provided to DOE and NASA in their efforts to inform industry, the public, and Government on the benefits and purpose of the gas turbine programs through demonstrations and exhibits. Tasks were carried out for maintenance, repair, and retrofit of the experimental gas turbine engines being used by NASA in their gas turbine technology programs and in program demonstrations. Limited support testing was conducted at Chrysler in which data were generated on air bearing rotor shaft dynamics, heavy duty variable sheave rubber belts, high temperature elastomer regenerator drive mounting and graphite regenerator seal friction characteristics.

Pressurized fluidized-bed component test program shows good promise

DOE Office of Scientific and Technical Information (OSTI.GOV)

Not Available

1985-04-01

The test program described has involved extensive theoretical and laboratory work since 1976, which culminated in a series of PFBC rig tests at the Coal Utilization Research Laboratories (CURL) in Leatherhead, England, and eventually in the design and construction of a component test facility (CTF) at the Oresund Power Station of Sydkraft in Malmo, Sweden. The rig tests are listed. Those preceding the 1000-hr test in 1979 were carried out with and without cooling tubes in the bed, and with different bed characteristics; the main emphasis was on gas clean-up, combustion efficiency, and emission of sulfur and nitrogen oxides. Inmore » these tests, the exhaust gases from the PFBC were passed through a cyclone train containing two cyclones to remove particulate matter, and then through a static cascade that contained parts of turbine blades from an ASEA STAL GT-120 machine. Good performance data, for the most part, are reported. 4 references, 3 figures.« less

Full-Scale Turbofan-Engine Turbine-Transfer Function Determination Using Three Internal Sensors

NASA Technical Reports Server (NTRS)

Hultgren, Lennart S.

2012-01-01

Noise-source separation techniques, using three engine-internal sensors, are applied to existing static-engine test data to determine the turbine transfer function for the currently subdominant combustion noise. The results are used to assess the combustion-noise prediction capability of the Aircraft Noise Prediction Program (ANOPP) and an improvement to the combustion-noise module GECOR is suggested. The work was carried out in response to the NASA Fundamental Aeronautics Subsonic Fixed Wing Program s Reduced-Perceived-Noise Technical Challenge.

The reduction, verification and interpretation of MAGSAT magnetic data over Canada

NASA Technical Reports Server (NTRS)

Coles, R. L. (Principal Investigator); Haines, G. V.; Vanbeek, G. J.; Walker, J. K.; Newitt, L. R.

1982-01-01

Consideration is being given to representing the magnetic field in the area 40 deg N to 83 deg N by means of functions in spherical coordinates. A solution to Laplace's equation for the magnetic potential over a restricted area was found, and programming and testing are currently being carried out. Magnetic anomaly modelling is proceeding. The program SPHERE, which was adapted to function correctly on the Cyber computer, is now operational, for deriving gravity and magnetic models in a spherical coordinate system.

Saturn S-2 quality assurance techniques, critical process control. Volume 7: Metallic materials

NASA Technical Reports Server (NTRS)

Ross, W. D., Jr.

1970-01-01

The special skills developed during the Saturn S-2 Program are documented to enable qualified personnel to carry out efficient operations in future S-2 production. Skills covered include: acceptance testing of fusion-welding equipment, weld operators and inspector certification, machine certification, preweld operations, and repair weld certification.

48 CFR 19.707 - The Small Business Administration's role in carrying out the program.

Code of Federal Regulations, 2011 CFR

2011-10-01

... Subcontracting Program 19.707 The Small Business Administration's role in carrying out the program. (a) Under the... 48 Federal Acquisition Regulations System 1 2011-10-01 2011-10-01 false The Small Business Administration's role in carrying out the program. 19.707 Section 19.707 Federal Acquisition Regulations System...

48 CFR 19.707 - The Small Business Administration's role in carrying out the program.

Code of Federal Regulations, 2010 CFR

2010-10-01

... Administration's role in carrying out the program. 19.707 Section 19.707 Federal Acquisition Regulations System... Subcontracting Program 19.707 The Small Business Administration's role in carrying out the program. (a) Under the... nature; and (4) Evaluate compliance with subcontracting plans, either on a contract-by-contract basis, or...

Research Pilot Milt Thompson in M2-F2 Aircraft Attached to B-52 Mothership

NASA Technical Reports Server (NTRS)

1966-01-01

NASA research pilot Milt Thompson sits in the M2-F2 'heavyweight' lifting body research vehicle before a 1966 test flight. The M2-F2 and the other lifting-body designs were all attached to a wing pylon on NASA's B-52 mothership and carried aloft. The vehicles were then drop-launched and, at the end of their flights, glided back to wheeled landings on the dry lake or runway at Edwards AFB. The lifting body designs influenced the design of the Space Shuttle and were also reincarnated in the design of the X-38 in the 1990s. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

DOE Office of Scientific and Technical Information (OSTI.GOV)

Hansen, E.A.; Smed, P.F.; Bryndum, M.B.

The paper describes the numerical program, PIPESIN, that simulates the behavior of a pipeline placed on an erodible seabed. PIPEline Seabed INteraction from installation until a stable pipeline seabed configuration has occurred is simulated in the time domain including all important physical processes. The program is the result of the joint research project, ``Free Span Development and Self-lowering of Offshore Pipelines`` sponsored by EU and a group of companies and carried out by the Danish Hydraulic Institute and Delft Hydraulics. The basic modules of PIPESIN are described. The description of the scouring processes has been based on and verified throughmore » physical model tests carried out as part of the research project. The program simulates a section of the pipeline (typically 500 m) in the time domain, the main input being time series of the waves and current. The main results include predictions of the onset of free spans, their length distribution, their variation in time, and the lowering of the pipeline as function of time.« less

Laser metrology and optic active control system for GAIA

NASA Astrophysics Data System (ADS)

D'Angelo, F.; Bonino, L.; Cesare, S.; Castorina, G.; Mottini, S.; Bertinetto, F.; Bisi, M.; Canuto, E.; Musso, F.

2017-11-01

The Laser Metrology and Optic Active Control (LM&OAC) program has been carried out under ESA contract with the purpose to design and validate a laser metrology system and an actuation mechanism to monitor and control at microarcsec level the stability of the Basic Angle (angle between the lines of sight of the two telescopes) of GAIA satellite. As part of the program, a breadboard (including some EQM elements) of the laser metrology and control system has been built and submitted to functional, performance and environmental tests. In the followings we describe the mission requirements, the system architecture, the breadboard design, and finally the performed validation tests. Conclusion and appraisals from this experience are also reported.

Constant-parameter capture-recapture models

USGS Publications Warehouse

Brownie, C.; Hines, J.E.; Nichols, J.D.

1986-01-01

Jolly (1982, Biometrics 38, 301-321) presented modifications of the Jolly-Seber model for capture-recapture data, which assume constant survival and/or capture rates. Where appropriate, because of the reduced number of parameters, these models lead to more efficient estimators than the Jolly-Seber model. The tests to compare models given by Jolly do not make complete use of the data, and we present here the appropriate modifications, and also indicate how to carry out goodness-of-fit tests which utilize individual capture history information. We also describe analogous models for the case where young and adult animals are tagged. The availability of computer programs to perform the analysis is noted, and examples are given using output from these programs.

Computational Fluid Dynamics (CFD) Image of Hyper-X Research Vehicle at Mach 7 with Engine Operating

NASA Technical Reports Server (NTRS)

1997-01-01

This computational fluid dynamics (CFD) image shows the Hyper-X vehicle at a Mach 7 test condition with the engine operating. The solution includes both internal (scramjet engine) and external flow fields, including the interaction between the engine exhaust and vehicle aerodynamics. The image illustrates surface heat transfer on the vehicle surface (red is highest heating) and flowfield contours at local Mach number. The last contour illustrates the engine exhaust plume shape. This solution approach is one method of predicting the vehicle performance, and the best method for determination of vehicle structural, pressure and thermal design loads. The Hyper-X program is an ambitious series of experimental flights to expand the boundaries of high-speed aeronautics and develop new technologies for space access. When the first of three aircraft flies, it will be the first time a non-rocket engine has powered a vehicle in flight at hypersonic speeds--speeds above Mach 5, equivalent to about one mile per second or approximately 3,600 miles per hour at sea level. Hyper-X, the flight vehicle for which is designated as X-43A, is an experimental flight-research program seeking to demonstrate airframe-integrated, 'air-breathing' engine technologies that promise to increase payload capacity for future vehicles, including hypersonic aircraft (faster than Mach 5) and reusable space launchers. This multiyear program is currently underway at NASA Dryden Flight Research Center, Edwards, California. The Hyper-X schedule calls for its first flight later this year (2000). Hyper-X is a joint program, with Dryden sharing responsibility with NASA's Langley Research Center, Hampton, Virginia. Dryden's primary role is to fly three unpiloted X-43A research vehicles to validate engine technologies and hypersonic design tools as well as the hypersonic test facility at Langley. Langley manages the program and leads the technology development effort. The Hyper-X Program seeks to significantly expand the speed boundaries of air-breathing propulsion by being the first aircraft to demonstrate an airframe-integrated, scramjet-powered free flight. Scramjets (supersonic-combustion ramjets) are ramjet engines in which the airflow through the whole engine remains supersonic. Scramjet technology is challenging because only limited testing can be performed in ground facilities. Long duration, full-scale testing requires flight research. Scramjet engines are air-breathing, capturing their oxygen from the atmosphere. Current spacecraft, such as the Space Shuttle, are rocket powered, so they must carry both fuel and oxygen for propulsion. Scramjet technology-based vehicles need to carry only fuel. By eliminating the need to carry oxygen, future hypersonic vehicles will be able to carry heavier payloads. Another unique aspect of the X-43A vehicle is the airframe integration. The body of the vehicle itself forms critical elements of the engine. The forebody acts as part of the intake for airflow and the aft section serves as the nozzle. The X-43A vehicles were manufactured by Micro Craft, Inc., Tullahoma, Tennessee. Orbital Sciences Corporation, Chandler, Arizona, built the Pegasus rocket booster used to launch the X-43 vehicles. For the Dryden research flights, the Pegasus rocket booster and attached X-43 will be air launched by Dryden's B-52 'Mothership.' After release from the B-52, the booster will accelerate the X-43A vehicle to the established test conditions (Mach 7 to 10) at an altitude of approximately 100,000 feet where the X-43 will separate from the booster and fly under its own power and preprogrammed control.

Shear Tests and Calculation of Shear Resistance with the PC Program RFEM from Thin Partition Walls of Brick in Old Buildings

NASA Astrophysics Data System (ADS)

Korjenic, Sinan; Nowak, Bernhard; Löffler, Philipp; Vašková, Anna

2015-11-01

This paper is about the shear capacity of partition walls in old buildings based on shear tests which were carried out under real conditions in an existing building. There were experiments conducted on different floors and in each case, the maximum recordable horizontal force and the horizontal displacement of the respective mortar were measured. At the same time material studies and material investigations were carried out in the laboratory. The material parameters were used for the calculation of the precise shear capacity of each joint. In the shear tests, the maximum displacement of a mortar joint was determined at a maximum of two to four millimetres. Furthermore, no direct linear relationship between the theoretical load (wall above it) and the shear stress occurred could be detected in the analysis of the experiment, as it was previously assumed.

Flight testing of airbreathing hypersonic vehicles

NASA Technical Reports Server (NTRS)

Hicks, John W.

1993-01-01

Using the scramjet engine as the prime example of a hypersonic airbreathing concept, this paper reviews the history of and addresses the need for hypersonic flight tests. It also describes how such tests can contribute to the development of airbreathing technology. Aspects of captive-carry and free-flight concepts are compared. An incremental flight envelope expansion technique for manned flight vehicles is also described. Such critical issues as required instrumentation technology and proper scaling of experimental devices are addressed. Lastly, examples of international flight test approaches, existing programs, or concepts currently under study, development, or both, are given.

X-43A/Hyper-X Vehicle Arrives at NASA Dryden

NASA Technical Reports Server (NTRS)

1999-01-01

A close-up of the X-43A Hypersonic Experimental Vehicle, or 'Hyper-X,' in its protective shipping framework as it arrives at the Dryden Flight Research Center in October 1999. The X-43A was developed to research a dual-mode ramjet/scramjet propulsion system at speeds from Mach 7 up to Mach 10 (7 to 10 times the speed of sound, which varies with temperature and altitude). Hyper-X, the flight vehicle for which is designated as X-43A, is an experimental flight-research program seeking to demonstrate airframe-integrated, 'air-breathing' engine technologies that promise to increase payload capacity for future vehicles, including hypersonic aircraft (faster than Mach 5) and reusable space launchers. This multiyear program is currently underway at NASA Dryden Flight Research Center, Edwards, California. The Hyper-X schedule calls for its first flight later this year (2000). Hyper-X is a joint program, with Dryden sharing responsibility with NASA's Langley Research Center, Hampton, Virginia. Dryden's primary role is to fly three unpiloted X-43A research vehicles to validate engine technologies and hypersonic design tools as well as the hypersonic test facility at Langley. Langley manages the program and leads the technology development effort. The Hyper-X Program seeks to significantly expand the speed boundaries of air-breathing propulsion by being the first aircraft to demonstrate an airframe-integrated, scramjet-powered free flight. Scramjets (supersonic-combustion ramjets) are ramjet engines in which the airflow through the whole engine remains supersonic. Scramjet technology is challenging because only limited testing can be performed in ground facilities. Long duration, full-scale testing requires flight research. Scramjet engines are air-breathing, capturing their oxygen from the atmosphere. Current spacecraft, such as the Space Shuttle, are rocket powered, so they must carry both fuel and oxygen for propulsion. Scramjet technology-based vehicles need to carry only fuel. By eliminating the need to carry oxygen, future hypersonic vehicles will be able to carry heavier payloads. Another unique aspect of the X-43A vehicle is the airframe integration. The body of the vehicle itself forms critical elements of the engine. The forebody acts as part of the intake for airflow and the aft section serves as the nozzle. The X-43A vehicles were manufactured by Micro Craft, Inc., Tullahoma, Tennessee. Orbital Sciences Corporation, Chandler, Arizona, built the Pegasus rocket booster used to launch the X-43 vehicles. For the Dryden research flights, the Pegasus rocket booster and attached X-43 will be air launched by Dryden's B-52 'Mothership.' After release from the B-52, the booster will accelerate the X-43A vehicle to the established test conditions (Mach 7 to 10) at an altitude of approximately 100,000 feet where the X-43 will separate from the booster and fly under its own power and preprogrammed control.

X-43A/Hyper-X Vehicle Arrives at NASA Dryden

NASA Technical Reports Server (NTRS)

1999-01-01

The X-43A Hypersonic Experimental Vehicle, or 'Hyper-X,' carefully packed in a protective shipping framework, is unloaded from a container after its arrival at NASA's Dryden Flight Research Center in October 1999. The X-43A was developed to research a dual-mode ramjet/scramjet propulsion system at speeds from Mach 7 up to Mach 10 (7 to 10 times the speed of sound, which varies with temperature and altitude). Hyper-X, the flight vehicle for which is designated as X-43A, is an experimental flight-research program seeking to demonstrate airframe-integrated, 'air-breathing' engine technologies that promise to increase payload capacity for future vehicles, including hypersonic aircraft (faster than Mach 5) and reusable space launchers. This multiyear program is currently underway at NASA Dryden Flight Research Center, Edwards, California. The Hyper-X schedule calls for its first flight later this year (2000). Hyper-X is a joint program, with Dryden sharing responsibility with NASA's Langley Research Center, Hampton, Virginia. Dryden's primary role is to fly three unpiloted X-43A research vehicles to validate engine technologies and hypersonic design tools as well as the hypersonic test facility at Langley. Langley manages the program and leads the technology development effort. The Hyper-X Program seeks to significantly expand the speed boundaries of air-breathing propulsion by being the first aircraft to demonstrate an airframe-integrated, scramjet-powered free flight. Scramjets (supersonic-combustion ramjets) are ramjet engines in which the airflow through the whole engine remains supersonic. Scramjet technology is challenging because only limited testing can be performed in ground facilities. Long duration, full-scale testing requires flight research. Scramjet engines are air-breathing, capturing their oxygen from the atmosphere. Current spacecraft, such as the Space Shuttle, are rocket powered, so they must carry both fuel and oxygen for propulsion. Scramjet technology-based vehicles need to carry only fuel. By eliminating the need to carry oxygen, future hypersonic vehicles will be able to carry heavier payloads. Another unique aspect of the X-43A vehicle is the airframe integration. The body of the vehicle itself forms critical elements of the engine. The forebody acts as part of the intake for airflow and the aft section serves as the nozzle. The X-43A vehicles were manufactured by Micro Craft, Inc., Tullahoma, Tennessee. Orbital Sciences Corporation, Chandler, Arizona, built the Pegasus rocket booster used to launch the X-43 vehicles. For the Dryden research flights, the Pegasus rocket booster and attached X-43 will be air launched by Dryden's B-52 'Mothership.' After release from the B-52, the booster will accelerate the X-43A vehicle to the established test conditions (Mach 7 to 10) at an altitude of approximately 100,000 feet where the X-43 will separate from the booster and fly under its own power and preprogrammed control.

X-43A/Hyper-X Vehicle Arrives at NASA Dryden

NASA Technical Reports Server (NTRS)

1999-01-01

A head-on view of the X-43A Hypersonic Experimental Vehicle, or 'Hyper-X,' in its protective shipping framework as it arrives at the Dryden Flight Research Center in October 1999. The X-43A was developed to research a dual-mode ramjet/scramjet propulsion system at speeds from Mach 7 up to Mach 10 (7 to 10 times the speed of sound, which varies with temperature and altitude). Hyper-X, the flight vehicle for which is designated as X-43A, is an experimental flight-research program seeking to demonstrate airframe-integrated, 'air-breathing' engine technologies that promise to increase payload capacity for future vehicles, including hypersonic aircraft (faster than Mach 5) and reusable space launchers. This multiyear program is currently underway at NASA Dryden Flight Research Center, Edwards, California. The Hyper-X schedule calls for its first flight later this year (2000). Hyper-X is a joint program, with Dryden sharing responsibility with NASA's Langley Research Center, Hampton, Virginia. Dryden's primary role is to fly three unpiloted X-43A research vehicles to validate engine technologies and hypersonic design tools as well as the hypersonic test facility at Langley. Langley manages the program and leads the technology development effort. The Hyper-X Program seeks to significantly expand the speed boundaries of air-breathing propulsion by being the first aircraft to demonstrate an airframe-integrated, scramjet-powered free flight. Scramjets (supersonic-combustion ramjets) are ramjet engines in which the airflow through the whole engine remains supersonic. Scramjet technology is challenging because only limited testing can be performed in ground facilities. Long duration, full-scale testing requires flight research. Scramjet engines are air-breathing, capturing their oxygen from the atmosphere. Current spacecraft, such as the Space Shuttle, are rocket powered, so they must carry both fuel and oxygen for propulsion. Scramjet technology-based vehicles need to carry only fuel. By eliminating the need to carry oxygen, future hypersonic vehicles will be able to carry heavier payloads. Another unique aspect of the X-43A vehicle is the airframe integration. The body of the vehicle itself forms critical elements of the engine. The forebody acts as part of the intake for airflow and the aft section serves as the nozzle. The X-43A vehicles were manufactured by Micro Craft, Inc., Tullahoma, Tennessee. Orbital Sciences Corporation, Chandler, Arizona, built the Pegasus rocket booster used to launch the X-43 vehicles. For the Dryden research flights, the Pegasus rocket booster and attached X-43 will be air launched by Dryden's B-52 'Mothership.' After release from the B-52, the booster will accelerate the X-43A vehicle to the established test conditions (Mach 7 to 10) at an altitude of approximately 100,000 feet where the X-43 will separate from the booster and fly under its own power and preprogrammed control.

Thinking, Fast and Slow? Some Field Experiments to Reduce Crime and Dropout in Chicago.

PubMed

Heller, Sara B; Shah, Anuj K; Guryan, Jonathan; Ludwig, Jens; Mullainathan, Sendhil; Pollack, Harold A

2017-02-01

We present the results of three large-scale randomized controlled trials (RCTs) carried out in Chicago, testing interventions to reduce crime and dropout by changing the decision making of economically disadvantaged youth. We study a program called Becoming a Man (BAM), developed by the nonprofit Youth Guidance, in two RCTs implemented in 2009-2010 and 2013-2015. In the two studies participation in the program reduced total arrests during the intervention period by 28-35%, reduced violent-crime arrests by 45-50%, improved school engagement, and in the first study where we have follow-up data, increased graduation rates by 12-19%. The third RCT tested a program with partially overlapping components carried out in the Cook County Juvenile Temporary Detention Center (JTDC), which reduced readmission rates to the facility by 21%. These large behavioral responses combined with modest program costs imply benefit-cost ratios for these interventions from 5-to-1 up to 30-to-1 or more. Our data on mechanisms are not ideal, but we find no positive evidence that these effects are due to changes in emotional intelligence or social skills, self-control or "grit," or a generic mentoring effect. We find suggestive support for the hypothesis that the programs work by helping youth slow down and reflect on whether their automatic thoughts and behaviors are well suited to the situation they are in, or whether the situation could be construed differently. JEL Codes: C91, C93, D03, D1, I24, I3, I32, K42.

Thinking, Fast and Slow? Some Field Experiments to Reduce Crime and Dropout in Chicago*

PubMed Central

Heller, Sara B.; Shah, Anuj K.; Guryan, Jonathan; Ludwig, Jens; Pollack, Harold A.

2017-01-01

Abstract We present the results of three large-scale randomized controlled trials (RCTs) carried out in Chicago, testing interventions to reduce crime and dropout by changing the decision making of economically disadvantaged youth. We study a program called Becoming a Man (BAM), developed by the nonprofit Youth Guidance, in two RCTs implemented in 2009–2010 and 2013–2015. In the two studies participation in the program reduced total arrests during the intervention period by 28–35%, reduced violent-crime arrests by 45–50%, improved school engagement, and in the first study where we have follow-up data, increased graduation rates by 12–19%. The third RCT tested a program with partially overlapping components carried out in the Cook County Juvenile Temporary Detention Center (JTDC), which reduced readmission rates to the facility by 21%. These large behavioral responses combined with modest program costs imply benefit-cost ratios for these interventions from 5-to-1 up to 30-to-1 or more. Our data on mechanisms are not ideal, but we find no positive evidence that these effects are due to changes in emotional intelligence or social skills, self-control or “grit,” or a generic mentoring effect. We find suggestive support for the hypothesis that the programs work by helping youth slow down and reflect on whether their automatic thoughts and behaviors are well suited to the situation they are in, or whether the situation could be construed differently. JEL Codes: C91, C93, D03, D1, I24, I3, I32, K42. PMID:29456270

The program complex for vocal recognition

NASA Astrophysics Data System (ADS)

Konev, Anton; Kostyuchenko, Evgeny; Yakimuk, Alexey

2017-01-01

This article discusses the possibility of applying the algorithm of determining the pitch frequency for the note recognition problems. Preliminary study of programs-analogues were carried out for programs with function “recognition of the music”. The software package based on the algorithm for pitch frequency calculation was implemented and tested. It was shown that the algorithm allows recognizing the notes in the vocal performance of the user. A single musical instrument, a set of musical instruments, and a human voice humming a tune can be the sound source. The input file is initially presented in the .wav format or is recorded in this format from a microphone. Processing is performed by sequentially determining the pitch frequency and conversion of its values to the note. According to test results, modification of algorithms used in the complex was planned.

[Effects of a group counseling integration program on self-determination and Internet addiction in high school students with tendency to Internet addiction].

PubMed

Park, Gyeong Ran; Kim, Hee Sook

2011-10-01

In this study the effects of a Group Counseling Integration Program for students with a tendency to Internet addiction were examined. Thirty-seven students who were in a vocational high school in G city participated in a survey, which was carried out from October 12 to November 12, 2009. To test the effects of the Group Counseling Integration Program, the participants were divided into two groups, an experimental group (18) and a control group (19). The research design used in this study was a nonequivalent control group non-synchronized pre-posttest quasi-experimental research design. The research tools included a self-determination scale and an internet addiction scale. Data were analyzed using Chi-square test, t-test, and ANCOVA with the SPSS/WIN 14.0 program. Significant differences were found in self-determination scores and internet addiction scores between the experimental group and the control group (F=5.99, p=.020) (t=-2.53, p=.016). The results indicate that Group Counseling Integration Programs are an effective nursing intervention for improving self-determination and decreasing Internet addiction in students with a tendency to Internet addiction.

Development of a full-scale transmission testing procedure to evaluate advanced lubricants

NASA Technical Reports Server (NTRS)

Lewicki, David G.; Decker, Harry J.; Shimski, John T.

1992-01-01

Experimental tests were performed on the OH-58A helicopter main rotor transmission in the NASA Lewis 500-hp Helicopter Transmission Test Stand. The testing was part of a joint Navy/NASA/Army lubrication program. The objective of the program was to develop a separate lubricant for gearboxes and demonstrate an improved performance in life and load-carrying capacity. The goal of the experiments was to develop a testing procedure to fail certain transmission components using a MIL-L-23699 base reference oil, then run identical tests with improved lubricants and demonstrate performance. The tests were directed at failing components that the Navy has had problems with due to marginal lubrication. These failures included mast shaft bearing micropitting, sun gear and planet bearing fatigue, and spiral bevel gear scoring. A variety of tests were performed and over 900 hours of total run time accumulated for these tests. Some success was achieved in developing a testing procedure to produce sun gear and planet bearing fatigue failures. Only marginal success was achieved in producing mast shaft bearing micropitting and spiral bevel gear scoring.

Variability of Uncrossmatched Blood Use by Helicopter EMS Programs in the United States.

PubMed

Karl, Alyssa; Pham, Tiffany; Yanosky, Jeff D; Lubin, Jeffrey

2016-01-01

Some helicopter emergency medical services (HEMS) maintain an independent supply of blood for use during transport, although practice is variable and not well described. We aimed to characterize the blood-carrying practices by HEMS programs across the United States. Online surveys were sent to the leadership of the 261 HEMS programs nationwide listed in the 2011 Atlas and Database of Air Medical Services (ADAMS) database. We examined blood-carrying practices in aggregate, including typical transport time, proportion of scene transports, and local population density. A GIS (Geographic Information System) and multivariable logistic regression models were used to estimate the impact of characteristics of local practice on each program's decision to carry blood. A total of 235 (91%) programs responded to the survey, representing 857 of the 929 (92.2%) HEMS rotor wing aircraft nationwide. Fifty-nine (25.3%) programs independently carried blood. A higher proportion of interfacility transports (OR 1.023; 95% CI 1.010-1.036) and decreased local population density (OR 1.006; 95% CI 1.001-1.011) were associated with increased odds of carrying blood. Transport time (OR 1.006; 95% CI 0.991-1.020) and number of transports (OR 1.000; CI 1.000-1.000) were not associated with a program's blood carrying practices. There was no effect of local practices on a program's decision to carry blood (OR 1.002; 95% CI 0.980-1.026). There is great variability in the utilization of blood by HEMS programs in the United States. Programs that serve more rural areas and programs with a larger percentage of interfacility transports are more likely to independently carry blood.

KSC-2009-5249

NASA Image and Video Library

2009-09-25

CAPE CANAVERAL, Fla. – The Ares I-X rocket stands tall inside NASA Kennedy Space Center's Vehicle Assembly Building Bay 3. Part of the Constellation Program, the Ares I-X is the test vehicle for the Ares I, which is the essential core of a space transportation system that eventually will carry crewed missions back to the moon, on to Mars and out into the solar system . The Ares I-X flight test is targeted for Oct. 27. Photo credit: NASA/Kim Shiflett

Program and Abstracts of the International Symposium on Detection of Subsurface Flow Phenomena by Self-Potential/Geoelectrical and Thermical Methods Held in Karlsruhe, Federal Republic of Germany on March 14-18, 1988

DTIC Science & Technology

1988-03-18

The tests were carried out at Le Mayet-de-Montagne (Allier). This test site is used by I.N.A.G. (Institut National d’Astronomie et de Geophysique ...study. Dep. Geophysique , Bureau de Recherches Geologiques et Minieres, B.P. 6009, 45060 Orleans Cedex 2, France 41 - THE USE OF INFRARED THERMOGRAPHY

Study of the damping characteristics of general aviation aircraft panels and development of computer programs to calculate the effectiveness of interior noise control treatment, part 1

NASA Technical Reports Server (NTRS)

Navaneethan, R.; Hunt, J.; Quayle, B.

1982-01-01

Tests were carried out on 20 inch x 20 inch panels at different test conditions using free-free panels, clamped panels, and panels as installed in the KU-FRL acoustic test facility. Tests with free-free panels verified the basic equipment set-up and test procedure. They also provided a basis for comparison. The results indicate that the effect of installed panels is to increase the damping ratio at the same frequency. However, a direct comparison is not possible, as the fundamental frequency of a free-free panel differs from the resonance frequency of the panel when installed. The damping values of panels installed in the test facility are closer to the damping values obtained with fixed-fixed panels. Effects of damping tape, stiffeners, and bonded and riveted edged conditions were also investigated. Progress in the development of a simple interior noise level control program is reported.

YF-12 Lockalloy ventral fin program, volume 1. [design analysis, fabrication, and manufacturing of aircraft structures using aluminum and beryllium alloys for the lockheed YF-12 aircraft

NASA Technical Reports Server (NTRS)

Duba, R. J.; Haramis, A. C.; Marks, R. F.; Payne, L.; Sessing, R. C.

1976-01-01

Results are presented of the YF-12 Lockalloy Ventral Fin Program which was carried out by Lockheed Aircraft Corporation - Advanced Development Projects for the joint NASA/USAF YF-12 Project. The primary purpose of the program was to redesign and fabricate the ventral fin of the YF-12 research airplane (to reduce flutter) using Lockalloy, and alloy of beryllium and aluminum, as a major structural material. A secondary purpose, was to make a material characterization study (thermodynamic properties, corrosion; fatigue tests, mechanical properties) of Lockalloy to validate the design of the ventral fin and expand the existing data base on this material. All significant information pertinent to the design and fabrication of the ventral fin is covered. Emphasis throughout is given to Lockalloy fabrication and machining techniques and attendant personnel safety precautions. Costs are also examined. Photographs of tested alloy specimens are shown along with the test equipment used.

NSTAR Ion Thruster and Breadboard Power Processor Functional Integration Test Results

NASA Technical Reports Server (NTRS)

Hamley, John A.; Pinero, Luis R.; Rawlin, Vincent K.; Miller, John R.; Myers, Roger M.; Bowers, Glen E.

1996-01-01

A 2.3 kW Breadboard Power Processing Unit (BBPPU) was developed as part of the NASA Solar Electric Propulsion Technology Application Readiness (NSTAR) Program. The NSTAR program will deliver an electric propulsion system based on a 30 cm xenon ion thruster to the New Millennium (NM) program for use as the primary propulsion system for the initial NM flight. The final development test for the BBPPU, the Functional Integration Test, was carried out to demonstrate all aspects of BBPPU operation with an Engineering Model Thruster. Test objectives included: (1) demonstration and validation of automated thruster start procedures, (2) demonstration of stable closed loop control of the thruster beam current, (3) successful response and recovery to thruster faults, and (4) successful safing of the system during simulated spacecraft faults. These objectives were met over the specified 80-120 VDC input voltage range and 0.5-2.3 output power capability of the BBPPU. Two minor anomalies were noted in discharge and neutralizer keeper current. These anomalies did not affect the stability of the system and were successfully corrected.

Dryden B-52 Launch Aircraft on Dryden Ramp

NASA Technical Reports Server (NTRS)

1996-01-01

NASA's venerable B-52 mothership sits on the ramp in front of the Dryden Flight Research Center, Edwards, California. Over the course of more than 40 years, the B-52 launched numerous experimental aircraft, ranging from the X-15 to the X-38, and was also used as a flying testbed for a variety of other research projects. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

Dryden B-52 Launch Aircraft in Flight over Dryden

NASA Technical Reports Server (NTRS)

1996-01-01

NASA's venerable B-52 mothership flies over the main building at the Dryden Flight Research Center, Edwards, California. The B-52, used for launching experimental aircraft and for other flight research projects, has been a familiar sight in the skies over Edwards for more than 40 years and has also been both the oldest B-52 still flying and the aircraft with the lowest flight time of any B-52. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

B-52 Flight Mission Symbology on Side of Craft

NASA Technical Reports Server (NTRS)

1993-01-01

A view of some of the mission markings, painted on the side of NASA's B-52 mothership, that tell the story of its colorful history. Just as combat aircraft would paint a bomb on the side of an aircraft for each bombing mission completed, NASA crew members painted a silhouette on the side of the B-52's fuselage to commemorate each drop of an X-15, lifting body, remotely piloted research vehicle, X-38 crew return vehicle, or other experimental vehicle or parachute system. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

B-52 Flight Mission Symbology - Close up

NASA Technical Reports Server (NTRS)

1993-01-01

A close-up view of some of the mission markings that tell the story of the NASA B-52 mothership's colorful history. These particular markings denote some of the experiments the bomber conducted to develop parachute recovery systems for the solid rocket boosters used by the Space Shuttle. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet.. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

X-38 on B-52 Wing Pylon - View from Observation Window

NASA Technical Reports Server (NTRS)

1997-01-01

A unique, close-up view of the X-38 under the wing of NASA's B-52 mothership prior to launch of the lifting-body research vehicle. The photo was taken from the observation window of the B-52 bomber as it banked in flight. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

B-52B Cockpit Instrument Panel

NASA Technical Reports Server (NTRS)

1996-01-01

This photo shows a close-up view of the instrument panel in the cockpit of NASA's B-52 research aircraft. Over the course of more than 40 years, the B-52 launched numerous experimental aircraft, ranging from the X-15 to the HiMAT, and was also used as a flying testbed for a variety of other research projects. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

Jay L. King, Joseph D. Huxman, and Orion D. Billeter Assist Pilot Milt Thompson into the M2-F2 Attac

NASA Technical Reports Server (NTRS)

1966-01-01

NASA research pilot Milt Thompson is helped into the cockpit of the M2-F2 lifting body research aircraft at NASA's Flight Research Center (now the Dryden Flight Research Center). The M2-F2 is attached to a wing pylon under the wing of NASA's B-52 mothership. The flight was a captive flight with the pilot on-board. Milt Thompson flew in the lifting body throughout the flight, but it was never dropped from the mothership. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet.. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

KSC-2013-4208

NASA Image and Video Library

2013-12-03

CAPE CANAVERAL, Fla. -- A truck sprays water along the crawlerway to reduce dust ahead of crawler-transporter 1 as it continues its trek to Launch Pad 39A at NASA’s Kennedy Space Center in Florida. New jacking, equalizing and leveling, or JEL, hydraulic cylinders were installed on CT-1 and will be tested for increased load carrying capacity and reliability. The Ground Systems Development and Operations Program at Kennedy continues to upgrade the crawler-transporter as part of its general maintenance. CT-1 could be available to carry a variety of launch vehicles to the launch pad. Two crawler-transporters were used to carry the mobile launcher platform and space shuttle to Launch Complex 39 for space shuttle launches for 30 years. Photo credit: NASA/Jim Grossmann

KSC-2013-4202

NASA Image and Video Library

2013-12-02

CAPE CANAVERAL, Fla. -- A truck sprays water along the crawlerway to reduce dust ahead of crawler-transporter 1 as it begins its trek to Launch Pad 39A at NASA’s Kennedy Space Center in Florida. New jacking, equalizing and leveling, or JEL, hydraulic cylinders were installed on CT-1 and are being tested for increased load carrying capacity and reliability. The Ground Systems Development and Operations Program at Kennedy continues to upgrade the crawler-transporter as part of its general maintenance. CT-1 could be available to carry a variety of launch vehicles to the launch pad. Two crawler-transporters were used to carry the mobile launcher platform and space shuttle to Launch Complex 39 for space shuttle launches for 30 years. Photo credit: NASA/Daniel Casper

34 CFR 406.31 - How does a State carry out the State-Administered Tech-Prep Education Program?

Code of Federal Regulations, 2011 CFR

2011-07-01

... 34 Education 3 2011-07-01 2011-07-01 false How does a State carry out the State-Administered Tech... TECH-PREP EDUCATION PROGRAM What Conditions Must Be Met After a State Receives an Award? § 406.31 How does a State carry out the State-Administered Tech-Prep Education Program? (a) A State board carries...

Advanced Turbine Technology Applications Project (ATTAP)

NASA Technical Reports Server (NTRS)

1993-01-01

This report is the fifth in a series of Annual Technical Summary Reports for the Advanced Turbine Technology Applications Project (ATTAP), sponsored by the U.S. Department of Energy (DOE). The report was prepared by Garrett Auxiliary Power Division (GAPD), a unit of Allied-Signal Aerospace Company, a unit of Allied Signal, Inc. The report includes information provided by Garrett Ceramic Components, and the Norton Advanced Ceramics Company, (formerly Norton/TRW Ceramics), subcontractors to GAPD on the ATTAP. This report covers plans and progress on ceramics development for commercial automotive applications over the period 1 Jan. through 31 Dec. 1992. Project effort conducted under this contract is part of the DOE Gas Turbine Highway Vehicle System program. This program is directed to provide the U.S. automotive industry the high-risk, long-range technology necessary to produce gas turbine engines for automobiles with reduced fuel consumption, reduced environmental impact, and a decreased reliance on scarce materials and resources. The program is oriented toward developing the high-risk technology of ceramic structural component design and fabrication, such that industry can carry this technology forward to production in the 1990's. The ATTAP test bed engine, carried over from the previous AGT101 project, is being used for verification testing of the durability of next generation ceramic components, and their suitability for service at Reference Powertrain Design conditions. This document reports the technical effort conducted by GAPD and the ATTAP subcontractors during the fifth year of the project. Topics covered include ceramic processing definition and refinement, design improvements to the ATTAP test bed engine and test rigs, and the methodology development of ceramic impact and fracture mechanisms. Appendices include reports by ATTAP subcontractors in the development of silicon nitride materials and processes.

Evaluation of a women group led health communication program in Haryana, India.

PubMed

Kaur, Manmeet; Jaswal, Nidhi; Saddi, Anil Kumar

2017-12-01

Sakshar Mahila Smooh (SMS) program was launched in rural areas of Haryana in India during 2008. A total of 6788 SMSs, each having 5-10 literate women, were equipped to enhance health communication. We carried out process evaluation of this program as an external agency. After a review of program documents, a random sample survey of Auxiliary Nurse Midwives (ANMs), SMS members, and village women was conducted. Out of four divisions of the state, one was randomly chosen, which had five districts. From 330 randomly chosen villages, 283 ANMs, 1164 SMS members, and 1123 village women were interviewed using a semi- structured interview schedule. Program inputs, processes, and outputs were compared in the five districts. Chi square was used for significance test. In the sampled division, out of 2009 villages, 1732 (86%) had functional SMS. In three years, SMS conducted 15036 group meetings, 2795 rallies, 2048 wall writings, and 803 competitions, and 44.5% of allocated budget was utilized. Most ANMs opined that SMSs are better health communicators. SMS members were aware about their roles and responsibilities. Majority of village women reported that SMS carry out useful health education activities. The characteristics of SMS members were similar but program performance was better in districts where health managers were proactive in program planning and monitoring. SMS Program has communicated health messages to majority of rural population, however, better planning & monitoring can improve program performance. Copyright © 2017 Elsevier Ltd. All rights reserved.

HALOE test and evaluation software

NASA Technical Reports Server (NTRS)

Edmonds, W.; Natarajan, S.

1987-01-01

Computer programming, system development and analysis efforts during this contract were carried out in support of the Halogen Occultation Experiment (HALOE) at NASA/Langley. Support in the major areas of data acquisition and monitoring, data reduction and system development are described along with a brief explanation of the HALOE project. Documented listings of major software are located in the appendix.

Core Principles and Test Item Development for Advanced High School and Introductory University Level Food Science

ERIC Educational Resources Information Center

Laing-Kean, Claudine A. M.

2010-01-01

Programs supported by the Carl D. Perkins Act of 2006 are required to operate under the state or national content standards, and are expected to carry out evaluation procedures that address accountability. The Indiana high school course, "Advanced Life Science: Foods" ("ALS: Foods") operates under the auspices of the Perkins…

Phase 1 Space Fission Propulsion System Testing and Development Progress

NASA Technical Reports Server (NTRS)

VanDyke, Melissa; Houts, Mike; Godfroy, Tom; Dickens, Ricky; Poston, David; Kapernick, Rick; Reid, Bob; Salvail, Pat; Ring, Peter; Schafer, Charles (Technical Monitor)

2001-01-01

Successful development of space fission systems requires an extensive program of affordable and realistic testing. In addition to tests related to design/development of the fission system, realistic testing of the actual flight unit must also be performed. If the system is designed to operate within established radiation damage and fuel burn up limits while simultaneously being designed to allow close simulation of heat from fission using resistance heaters, high confidence in fission system performance and lifetime can be attained through a series of non-nuclear tests. The Safe Affordable Fission Engine (SAFE) test series, whose ultimate goal is the demonstration of a 300 kW flight configuration system, has demonstrated that realistic testing can be performed using non-nuclear methods. This test series, carried out in collaboration with other NASA centers, other government agencies, industry, and universities, successfully completed a testing program with a 30 kWt core, Stirling engine, and ion engine configuration. Additionally, a 100 kWt core is in fabrication and appropriate test facilities are being reconfigured. This paper describes the current SAFE non-nuclear tests, which includes test article descriptions, test results and conclusions, and future test plans.

Advanced very high resolution radiometer

NASA Technical Reports Server (NTRS)

1978-01-01

The program covered the design, construction, and test of a Breadboard Model, Engineering Model, Protoflight Model, Mechanical/Structural Model, and a Life Test Model. Special bench test and calibration equipment was also developed for use on the program. Initially, the instrument was to operate from a 906 n.mi. orbit and be thermally isolated from the spacecraft. The Breadboard Model and the Mechanical/Structural Model were designed and built to these requirements. The spacecraft altitude was changed to 450 n.mi., IFOVs and spectral characteristics were modified, and spacecraft interfaces were changed. The final spacecraft design provided a temperature-controlled Instrument Mounting Platform (IMP) to carry the AVHRR and other instruments. The design of the AVHRR was modified to these new requirements and the modifications were incorporated in the Engineering Model. The Protoflight Model and the Flight Models conform to this design.

Autonomous landing guidance program

NASA Astrophysics Data System (ADS)

Brown, John A.

1996-05-01

The Autonomous Landing Guidance program is partly funded by the US Government under the Technology Reinvestment Project. The program consortium consists of avionics and other equipment vendors, airlines and the USAF. A Sextant Avionique HUD is used to present flight symbology in cursive form as well as millimeter wave radar imagery from Lear Astronics equipment and FLIR Systems dual-channel, forward-looking, infrared imagery. All sensor imagery is presented in raster form. A future aim is to fuse all imagery data into a single presentation. Sensor testing has been accomplished in a Cessna 402 operated by the Maryland Advanced Development Laboratory. Development testing is under way in a Northwest Airlines simulator equipped with HUD and image simulation. Testing is also being carried out using United Airlines Boeing 727 and USAF C-135C (Boeing 707) test aircraft. The paper addresses the technology utilized in sensory and display systems as well as modifications made to accommodate the elements in the aircraft. Additions to the system test aircraft include global positioning systems, inertial navigation systems and extensive data collection equipment. Operational philosophy and benefits for both civil and military users are apparent. Approach procedures have been developed allowing use of Category 1 ground installations in Category 3 conditions.

The Hyper-X Flight Systems Validation Program

NASA Technical Reports Server (NTRS)

Redifer, Matthew; Lin, Yohan; Bessent, Courtney Amos; Barklow, Carole

2007-01-01

For the Hyper-X/X-43A program, the development of a comprehensive validation test plan played an integral part in the success of the mission. The goal was to demonstrate hypersonic propulsion technologies by flight testing an airframe-integrated scramjet engine. Preparation for flight involved both verification and validation testing. By definition, verification is the process of assuring that the product meets design requirements; whereas validation is the process of assuring that the design meets mission requirements for the intended environment. This report presents an overview of the program with emphasis on the validation efforts. It includes topics such as hardware-in-the-loop, failure modes and effects, aircraft-in-the-loop, plugs-out, power characterization, antenna pattern, integration, combined systems, captive carry, and flight testing. Where applicable, test results are also discussed. The report provides a brief description of the flight systems onboard the X-43A research vehicle and an introduction to the ground support equipment required to execute the validation plan. The intent is to provide validation concepts that are applicable to current, follow-on, and next generation vehicles that share the hybrid spacecraft and aircraft characteristics of the Hyper-X vehicle.

KSC-2009-5081

NASA Image and Video Library

2009-09-11

CAPE CANAVERAL, Fla. – In NASA Kennedy Space Center's Vehicle Assembly Building High Bay 3, NASA's Ares I-X rocket is ready to undergo its first power-up. Part of the Constellation Program, the Ares I-X is the test vehicle for the Ares I, which is the essential core of a space transportation system that eventually will carry crewed missions back to the moon, on to Mars and out into the solar system. The Ares I-X flight test is targeted for Oct. 31. Photo credit: NASA/Cory Huston

KSC-2009-5085

NASA Image and Video Library

2009-09-11

CAPE CANAVERAL, Fla. – In NASA Kennedy Space Center's Vehicle Assembly Building High Bay 3, NASA's Ares I-X rocket undergoes its first power-up. Part of the Constellation Program, the Ares I-X is the test vehicle for the Ares I, which is the essential core of a space transportation system that eventually will carry crewed missions back to the moon, on to Mars and out into the solar system. The Ares I-X flight test is targeted for Oct. 31. Photo credit: NASA/Cory Huston

Close-up of Wing Fit Check of Pylon to Carry the X-38 on B-52 Launch Aircraft

NASA Technical Reports Server (NTRS)

1997-01-01

Andy Blua and Jeff Doughty of Dryden's Experimental Fabrication Shop, along with B-52 Crew Chief Dan Bains and assistant Mark Thompson, all eye the new X-38 pylon during a fit-check on NASA's B-52 at the Dryden Flight Research Center, Edwards, California. The fit-check was the first time the 1,200-pound steel pylon, which was fabricated at Dryden, was mated to the B-52. The pylon served as an 'adapter' that allowed the X-38 to be attached to the B-52's wing. Earlier flight research vehicles had used the X-15 pylon for attachment to and launch from the B-52. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

The Effectiveness of Assertiveness Training on the Levels of Stress, Anxiety, and Depression of High School Students.

PubMed

Eslami, Ahmad Ali; Rabiei, Leili; Afzali, Seyed Mohammad; Hamidizadeh, Saeed; Masoudi, Reza

2016-01-01

Adolescence is a transition period from childhood to early adulthood. Because of the immense pressure imposed on adolescents due to the complications and ambiguities of this transition, their level of excitement increases and sometimes it appears in the form of sensitivity and intense excitement. This study aimed at determining the effectiveness of assertiveness training on the levels of stress, anxiety, and depression of high school students. This quasi-experimental study was conducted on high school students of Isfahan in academic year 2012 - 13. A total of 126 second grade high school students were collected according to simple random sampling method and divided into two groups: experimental with 63 participants and control with the same number. Data gathering instruments included a demographic questionnaire, Gambill-Richey assertiveness scale, and depression anxiety stress scales (DASS-21). Assertiveness training was carried out on the experimental group in 8 sessions; after 8 weeks, posttest was carried out on both groups. Statistical tests such as independent t test, repeated measures ANOVA, Chi-square test, and the Mann-Whitney test were used to interpret and analyze the data. The Chi-square and Mann-Whitney tests did not show significant statistical differences between the two groups in terms of demographic variables (P ≥ 0.05). Repeated measures ANOVA showed no significant difference between the mean scores for assertiveness before (100.23 ± 7.37), immediately after (101.57 ± 16.06), and 2 months after (100.77 ± 12.50) the intervention in the control group. However, the same test found a significant difference between the mean score for assertiveness in the experimental group before (101.6 ± 9.1), immediately after (96.47 ± 10.84), and 2 months after (95.41 ± 8.37) implementing the training program (P = 0.002). The independent t test showed no significant difference in the mean score for anxiety and stress between two groups before the assertiveness training program; however, 2 months after the intervention, the mean score for anxiety in the experimental group was found significantly lower than the control group. As for the mean score for depression, the independent t test showed no significant difference between two groups before training; however, despite the decrease in the mean scores for depression in the experimental group following the intervention, the difference was not significant (P = 0.09). The results of the current study show that conducting assertive training in high school students decreases their anxiety, stress, and depression. Given that high school years are among the most sensitive stages of one's life plus the fact that conducting such training programs besides their safe and low cost nature are effective and practical, it is highly recommended that such programs be carried out among high school adolescents.

The Effectiveness of Assertiveness Training on the Levels of Stress, Anxiety, and Depression of High School Students

PubMed Central

Eslami, Ahmad Ali; Rabiei, Leili; Afzali, Seyed Mohammad; Hamidizadeh, Saeed; Masoudi, Reza

2016-01-01

Background: Adolescence is a transition period from childhood to early adulthood. Because of the immense pressure imposed on adolescents due to the complications and ambiguities of this transition, their level of excitement increases and sometimes it appears in the form of sensitivity and intense excitement. Objectives: This study aimed at determining the effectiveness of assertiveness training on the levels of stress, anxiety, and depression of high school students. Materials and Methods: This quasi-experimental study was conducted on high school students of Isfahan in academic year 2012 - 13. A total of 126 second grade high school students were collected according to simple random sampling method and divided into two groups: experimental with 63 participants and control with the same number. Data gathering instruments included a demographic questionnaire, Gambill-Richey assertiveness scale, and depression anxiety stress scales (DASS-21). Assertiveness training was carried out on the experimental group in 8 sessions; after 8 weeks, posttest was carried out on both groups. Statistical tests such as independent t test, repeated measures ANOVA, Chi-square test, and the Mann-Whitney test were used to interpret and analyze the data. Results: The Chi-square and Mann-Whitney tests did not show significant statistical differences between the two groups in terms of demographic variables (P ≥ 0.05). Repeated measures ANOVA showed no significant difference between the mean scores for assertiveness before (100.23 ± 7.37), immediately after (101.57 ± 16.06), and 2 months after (100.77 ± 12.50) the intervention in the control group. However, the same test found a significant difference between the mean score for assertiveness in the experimental group before (101.6 ± 9.1), immediately after (96.47 ± 10.84), and 2 months after (95.41 ± 8.37) implementing the training program (P = 0.002). The independent t test showed no significant difference in the mean score for anxiety and stress between two groups before the assertiveness training program; however, 2 months after the intervention, the mean score for anxiety in the experimental group was found significantly lower than the control group. As for the mean score for depression, the independent t test showed no significant difference between two groups before training; however, despite the decrease in the mean scores for depression in the experimental group following the intervention, the difference was not significant (P = 0.09). Conclusions: The results of the current study show that conducting assertive training in high school students decreases their anxiety, stress, and depression. Given that high school years are among the most sensitive stages of one’s life plus the fact that conducting such training programs besides their safe and low cost nature are effective and practical, it is highly recommended that such programs be carried out among high school adolescents. PMID:26889390

Design for improved maintenance of the fiber-optic cable system (As carried out in a concurrent engineering environment)

NASA Astrophysics Data System (ADS)

Tremoulet, P. C.

The author describes a number of maintenance improvements in the Fiber Optic Cable System (FOCS). They were achieved during a production phase pilot concurrent engineering program. Listed in order of importance (saved maintenance time and material) by maintenance level, they are: (1) organizational level: improved fiber optic converter (FOC) BITE; (2) Intermediate level: reduced FOC adjustments from 20 to 2; partitioned FOC into electrical and optical parts; developed cost-effective fault isolation test points and test using standard test equipment; improved FOC chassis to have lower mean time to repair; and (3) depot level: revised test requirements documents (TRDs) for common automatic test equipment and incorporated ATE testability into circuit and assemblies and application-specific integrated circuits. These improvements met this contract's tailored logistics MIL-STD 1388-1A requirements of monitoring the design for supportability and determining the most effective support equipment. Important logistics lessons learned while accomplishing these maintainability and supportability improvements on the pilot concurrent engineering program are also discussed.

Testing of Environmental Satellite Bus-Instrument Interfaces Using Engineering Models

NASA Technical Reports Server (NTRS)

Gagnier, Don; Hayner, Rick; Roza, Michael; Nosek, Thomas; Razzaghi, Andrea

2004-01-01

This paper discusses the formulation and execution of a laboratory test of the electrical interfaces between multiple atmospheric science instruments and the spacecraft bus that carries them. The testing, performed in 2002, used engineering models of the instruments that will be flown on the Aura s p a c m and of the Aura spacecraft bus electronics. Aura is one of NASA's Earth Observing System @OS) Program missions managed by the Goddard Space Flight Center. The test was designed to evaluate the complex interfaces in the spacecraft and instrument command and data handling (C&DH) subsystems prior to integration of the complete flight instruments on the spacecraft. A problem discovered during (and not before) the flight hardware integration phase can cause significant cost and schedule impacts. The testing successfully surfaced problems and led to their resolution before the full-up integration phase, saving significant cost and schedule time. This approach could be used on future environmental satellite programs involving multiple, complex scientific instruments being integrated onto a bus.

STS-1 medical report

NASA Technical Reports Server (NTRS)

Pool, S. L. (Editor); Johnson, P. C., Jr. (Editor); Mason, J. A. (Editor)

1981-01-01

The report includes a review of the health of the crew before, during and immediately after the first Shuttle orbital flight (April 12-14, 1981). Areas reviewed include: health evaluation, medical debriefing of crewmembers, health stabilization program, medical training, medical kit carried inflight; tests and countermeasures for space motion sickness, cardiovascular profile, biochemistry and endocrinology results; hematology and immunology analyses; medical microbiology; food and nutrition; potable water; shuttle toxicology; radiological health; cabin acoustical noise. Also included is information on: environmental effects of Shuttle launch and landing, medical information management; and management, planning and implementation of the medical program.

75 FR 26121 - Regulation of Fuels and Fuel Additives: Alternative Affirmative Defense Requirements for Ultra...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-05-11

...EPA is issuing a direct final rule to amend the diesel sulfur regulations to allow refiners, importers, distributors, and retailers of highway diesel fuel the option to use an alternative affirmative defense if the Agency finds highway diesel fuel samples above the specified sulfur standard at retail facilities. This alternative defense consists of a comprehensive program of quality assurance sampling and testing that would cover all participating companies that produce and/or distribute highway diesel fuel if certain other conditions are met. The sampling and testing program would be carried out by an independent surveyor. The program would be conducted pursuant to a survey plan approved by EPA that is designed to achieve the same objectives as the current regulatory quality assurance requirement. This rule also amends the gasoline benzene regulations to allow disqualified small refiners the same opportunity to generate gasoline benzene credits as that afforded to non-small refiners.

The NASA-Lewis/ERDA Solar Heating and Cooling Technology Program

NASA Technical Reports Server (NTRS)

Couch, J. P.; Bloomfield, H. S.

1975-01-01

The NASA Lewis Research Center plans to carry out a major role in the ERDA Solar Heating and Cooling Program. This role would be to create and test the enabling technology for future solar heating, cooling, and combined heating/cooling systems. The major objectives of the project are to achieve reduction in solar energy system costs, while maintaining adequate performance, reliability, life, and maintenance characteristics. The project approach is to move progressively through component, subsystem, and then system technology advancement phases in parallel with continuing manufacturing cost assessment studies. This approach will be accomplished principally by contract with industry to develop advanced components and subsystems. This advanced hardware will be tested to establish 'technology readiness' both under controlled laboratory conditions and under real sun conditions.

Optical/thermal analysis methodology for a space-qualifiable RTP furnace

NASA Technical Reports Server (NTRS)

Bugby, D.; Dardarian, S.; Cole, E.

1993-01-01

A methodology to predict the coupled optical/thermal performance of a reflective cavity heating system was developed and a laboratory test to verify the method was carried out. The procedure was utilized to design a rapid thermal processing (RTP) furnace for the Robot-Operated Material Processing in Space (ROMPS) Program which is a planned STS HH-G canister experiment involving robotics and material processing in microgravity. The laboratory test employed a tungsten-halogen reflector/lamp to heat thin, p-type silicon wafers. Measurements instrumentation consisted of 5-mil Pt/Pt-Rh thermocouples and an optical pyrometer. The predicted results, utilizing an optical ray-tracing program and a lumped-capacitance thermal analyzer, showed good agreement with the measured data for temperatures exceeding 1300 C.

Main propulsion system test requirements for the two-engine Shuttle-C

NASA Technical Reports Server (NTRS)

Lynn, E. E.; Platt, G. K.

1989-01-01

The Shuttle-C is an unmanned cargo carrying derivative of the space shuttle with optional two or three space shuttle main engines (SSME's), whereas the shuttle has three SSME's. Design and operational differences between the Shuttle-C and shuttle were assessed to determine requirements for additional main propulsion system (MPS) verification testing. Also, reviews were made of the shuttle main propulsion test program objectives and test results and shuttle flight experience. It was concluded that, if significant MPS modifications are not made beyond those currently planned, then main propulsion system verification can be concluded with an on-pad flight readiness firing.

Cryo-Vacuum Testing of the Integrated Science Instrument Module for the James Webb Space Telescope

NASA Technical Reports Server (NTRS)

Kimble, Randy A.; Davila, P. S.; Drury, M. P.; Glazer, S. D.; Krom, J. R.; Lundquist, R. A.; Mann, S. D.; McGuffey, D. B.; Perry, R. L.; Ramey, D. D.

2011-01-01

With delivery of the science instruments for the James Webb Space Telescope (JWST) to Goddard Space Flight Center (GSFC) expected in 2012, current plans call for the first cryo-vacuum test of the Integrated Science Instrument Module (ISIM) to be carried out at GSFC in early 2013. Plans are well underway for conducting this ambitious test, which will perform critical verifications of a number of optical, thermal, and operational requirements of the IS 1M hardware, at its deep cryogenic operating temperature. We describe here the facilities, goals, methods, and timeline for this important Integration & Test milestone in the JWST program.

Space Plasma Testing of High-Voltage Thin-Film Solar Arrays with Protective Coatings

NASA Technical Reports Server (NTRS)

Tlomak, Pawel; Hausgen, Paul E.; Merrill, John; Senft, Donna; Piszczor, Michael F., Jr.

2007-01-01

This paper gives an overview of the space plasma test program for thin-film photovoltaics (TFPV) technologies developed at the Air Force Research Laboratory (AFRL). The main objective of this program is to simulate the effects of space plasma characteristic of LEO and MEO environments on TFPV. Two types of TFPV, amorphous silicon (a-Si) and copper-indium-gallium-diselenide (CIGS), coated with two types of thin-film, multifunctional coatings were used for these studies. This paper reports the results of the first phase of this program, namely the results of preliminary electrostatic charging, arcing, dielectric breakdown, and collection current measurements carried out with a series of TFPV exposed to simulated space plasma at the NASA Glenn Plasma Interaction Facility. The experimental data demonstrate that multifunctional coatings developed for this program provide effective protection against the plasma environment while minimizing impact on power generation performance. This effort is part of an ongoing program led by the Space Vehicles Directorate at the AFRL devoted to the development and space qualification of TFPV and their protective coatings.

Carryover effect of hip and knee exercises program on functional performance in individuals with patellofemoral pain syndrome

PubMed Central

Ahmed Hamada, Hamada; Hussein Draz, Amira; Koura, Ghada Mohamed; Saab, Ibtissam M.

2017-01-01

[Purpose] This study was carried out to investigate the carryover effect of hip and knee exercises program on functional performance (single legged hop test as functional performance test and Kujala score for functional activities). [Subjects and Methods] Thirty patients with patellofemoral pain syndrome were randomly assigned into two equal groups. Group (A) consisted of 15 patients undergoing hip strengthening exercises for four weeks then measuring all variables followed by additional four weeks of knee exercises program then measuring all variables again. Group (B): consisted of 15 patients undergoing knee exercises program for four weeks then measuring all variables followed by additional four weeks of hip strengthening exercises then measuring all variables. Functional abilities and knee muscles performance were assessed using Kujala questionnaire and single legged hop test respectively pre and after the completion of the first 4 weeks then after 8 weeks for both groups. [Results] Significantly increase in Kujala questionnaire in group A compared with group B was observed. While, there were significant increase in single legged hop performance test in group B compared with group A. [Conclusion] Starting with hip exercises improve the performance of subjects more than functional activities while starting with knee exercises improve the functional activities of subjects more than performance. PMID:28878459

Carryover effect of hip and knee exercises program on functional performance in individuals with patellofemoral pain syndrome.

PubMed

Ahmed Hamada, Hamada; Hussein Draz, Amira; Koura, Ghada Mohamed; Saab, Ibtissam M

2017-08-01

[Purpose] This study was carried out to investigate the carryover effect of hip and knee exercises program on functional performance (single legged hop test as functional performance test and Kujala score for functional activities). [Subjects and Methods] Thirty patients with patellofemoral pain syndrome were randomly assigned into two equal groups. Group (A) consisted of 15 patients undergoing hip strengthening exercises for four weeks then measuring all variables followed by additional four weeks of knee exercises program then measuring all variables again. Group (B): consisted of 15 patients undergoing knee exercises program for four weeks then measuring all variables followed by additional four weeks of hip strengthening exercises then measuring all variables. Functional abilities and knee muscles performance were assessed using Kujala questionnaire and single legged hop test respectively pre and after the completion of the first 4 weeks then after 8 weeks for both groups. [Results] Significantly increase in Kujala questionnaire in group A compared with group B was observed. While, there were significant increase in single legged hop performance test in group B compared with group A. [Conclusion] Starting with hip exercises improve the performance of subjects more than functional activities while starting with knee exercises improve the functional activities of subjects more than performance.

50th anniversary logo

NASA Image and Video Library

2011-03-02

John C. Stennis Space Center is celebrating its 50th anniversary in 2011. NASA announced plans to build a rocket engine test facility in Hancock County, Miss., on Oct. 25, 1961. A new anniversary logo highlights the theme of the anniversary year - celebrating Stennis as a unique federal city and its five decades of powering America's space dreams. Stennis is home to more than 30 federal, state, academic and private organizations and several technology-based companies. In addition to testing Apollo Program rocket stages that carried humans to the moon, Stennis tested every main engine used in more than 130 space shuttle flights.

Orion Flight Test Preview Briefing

NASA Image and Video Library

2014-11-06

In the Kennedy Space Center’s Press Site auditorium, members of the news media are briefed on the upcoming Orion flight test by Mark Geyer, NASA Orion Program manager. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch Dec. 4, 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket.

SLS Test Stand Site Selection

NASA Technical Reports Server (NTRS)

Crowe, Kathryn; Williams, Michael

2015-01-01

Test site selection is a critical element of the design, development and production of a new system. With the advent of the new Space Launch System (SLS), the National Aeronautics and Space Administration (NASA) had a number of test site selection decisions that needed to be made early enough in the Program to support the planned Launch Readiness Date (LRD). This case study focuses on decisions that needed to be made in 2011 and 2012 in preparation for the April 2013 DPMC decision about where to execute the Main Propulsion Test that is commonly referred to as "Green Run." Those decisions relied upon cooperative analysis between the Program, the Test Lab and Center Operations. The SLS is a human spaceflight vehicle designed to carry a crew farther into space than humans have previously flown. The vehicle consists of four parts: the crew capsule, the upper stage, the core stage, and the first stage solid rocket boosters. The crew capsule carries the astronauts, while the upper stage, the core stage, and solid rocket boosters provide thrust for the vehicle. In other words, the stages provide the "lift" part of the lift vehicle. In conjunction with the solid rocket boosters, the core stage provides the initial "get-off-the-ground" thrust to the vehicle. The ignition of the four core stage engines and two solid rocket boosters is the first step in the launch portion of the mission. The solid rocket boosters burn out after about 2 minutes of flight, and are then jettisoned. The core stage provides thrust until the vehicle reaches a specific altitude and speed, at which point the core stage is shut off and jettisoned, and the upper stage provides vehicle thrust for subsequent mission trajectories. The integrated core stage primarily consists of a liquid oxygen tank, a liquid hydrogen tank, and the four core stage engines. For the SLS program, four RS-25 engines were selected as the four core stage engines. The RS-25 engine is the same engine that was used for Space Shuttle. The test plan for the integrated core stage was broken down into several segments: Component testing, system level testing, and element level testing. In this context, components are items such as valves, controllers, sensors, etc. Systems are items such as an entire engine, a tank, or the outer stage body. The core stage itself is considered to be an element. The rocket engines are also considered an element. At the program level, it was decided to perform a single green run test on the integrated core stage prior to shipment of it to Kennedy Space Center (KSC) for use in the EM-1 test flight of the SLS vehicle. A green run test is the first live fire of the new integrated core stage and engine elements - without boosters of course. The SLS Program had to decide where to perform SLS green run testing.

Testing the Gossamer Albatross II

NASA Technical Reports Server (NTRS)

1980-01-01

The Gossamer Albatross II is seen here during a test flight at NASA's Dryden Flight Research Center, Edwards, California. The original Gossamer Albatross is best known for completing the first completely human powered flight across the English Channel on June 12, 1979. The Albatross II was the backup craft for the Channel flight. It was fitted with a small battery-powered electric motor and flight instruments for the NASA research program in low-speed flight. NASA completed its flight testing of the Gossamer Albatross II and began analysis of the results in April, 1980. During the six week program, 17 actual data gathering flights and 10 other flights were flown here as part of the joint NASA Langley/Dryden flight research program. The lightweight craft, carrying a miniaturized instrumentation system, was flown in three configurations; using human power, with a small electric motor, and towed with the propeller removed. Results from the program contributed to data on the unusual aerodynamic, performance, stability, and control characteristics of large, lightweight aircraft that fly at slow speeds for application to future high altitude aircraft. The Albatross' design and research data contributed to numerous later high altitude projects, including the Pathfinder.

The US Army Foreign Comparative Test fuel cell program

NASA Astrophysics Data System (ADS)

Bostic, Elizabeth; Sifer, Nicholas; Bolton, Christopher; Ritter, Uli; Dubois, Terry

The US Army RDECOM initiated a Foreign Comparative Test (FCT) Program to acquire lightweight, high-energy dense fuel cell systems from across the globe for evaluation as portable power sources in military applications. Five foreign companies, including NovArs, Smart Fuel Cell, Intelligent Energy, Ballard Power Systems, and Hydrogenics, Inc., were awarded competitive contracts under the RDECOM effort. This paper will report on the status of the program as well as the experimental results obtained from one of the units. The US Army has interests in evaluating and deploying a variety of fuel cell systems, where these systems show added value when compared to current power sources in use. For low-power applications, fuel cells utilizing high-energy dense fuels offer significant weight savings over current battery technologies. This helps reduce the load a solider must carry for longer missions. For high-power applications, the low operating signatures (acoustic and thermal) of fuel cell systems make them ideal power generators in stealth operations. Recent testing has been completed on the Smart Fuel Cell A25 system that was procured through the FCT program. The "A-25" is a direct methanol fuel cell hybrid and was evaluated as a potential candidate for soldier and sensor power applications.

Efficacy of a Brief Intervention to Improve Emergency Physicians' Smoking Cessation Counseling Skills, Knowledge, and Attitudes

ERIC Educational Resources Information Center

Bernstein, Steven L.; Boudreaux, Edwin D.; Cabral, Lisa; Cydulka, Rita K.; Schwegman, David; Larkin, Gregory L.; Adams, Annette L.; McCullough, Lynne B.; Rhodes, Karin V.

2009-01-01

The objective of this study was to test whether a brief educational/administrative intervention could increase tobacco counseling by emergency physicians (EPs). Pre-/post-study at eight emergency departments (EDs) with residency programs were carried out. EPs received a 1-hour lecture on the health effects of smoking and strategies to counsel…

KENNEDY SPACE CENTER, FLA. - Arturo Ramierez, Charles Curley and Duke Follistein, KSC and Costa Rican researchers, carry the hazardous gas detection system AVEMS to the central of the Turrialba volcano. The Aircraft-based Volcanic Emission Mass Spectrometer determines the presence and concentration of various chemicals. It is being tested in flights over the Turrialba volcano and in the crater, sampling and analyzing fresh volcanic gases in their natural chemical state. The AVEMS system has been developed for use in the Space Shuttle program, to detect toxic gas leaks and emissions in the Shuttle’s aft compartment and the crew compartment.

NASA Image and Video Library

2003-03-31

KENNEDY SPACE CENTER, FLA. - Arturo Ramierez, Charles Curley and Duke Follistein, KSC and Costa Rican researchers, carry the hazardous gas detection system AVEMS to the central of the Turrialba volcano. The Aircraft-based Volcanic Emission Mass Spectrometer determines the presence and concentration of various chemicals. It is being tested in flights over the Turrialba volcano and in the crater, sampling and analyzing fresh volcanic gases in their natural chemical state. The AVEMS system has been developed for use in the Space Shuttle program, to detect toxic gas leaks and emissions in the Shuttle’s aft compartment and the crew compartment.

Human-in-the-Loop Integrated Life Support Systems Ground Testing

NASA Technical Reports Server (NTRS)

Henninger, Donald L.; Marmolejo, Jose A.; Westheimer, David T.

2011-01-01

Human exploration missions beyond low earth orbit will be long duration with abort scenarios of days to months. This necessitates provisioning the crew with all the things they will need to sustain themselves while carrying out mission objectives. Systems engineering and integration is critical to the point where extensive integrated testing of life support systems on the ground is required to identify and mitigate risks. Ground test facilities (human-rated altitude chamber) at the Johnson Space Center are being readied to integrate all the systems for a mission along with a human test crew. The relevant environment will include deep space habitat human accommodations, sealed atmosphere of 8 psi total pressure and 32% oxygen concentration, life support systems (food, air, water), communications, crew accommodations, medical, EVA, tools, etc. Testing periods will approximate those of the expected missions (such as a near Earth asteroid, Earth-Moon L2 or L1, the moon). This type of integrated testing is needed for research and technology development as well as later during the mission design, development, test, and evaluation (DDT&E) phases of an approved program. Testing will evolve to be carried out at the mission level fly the mission on the ground . Mission testing will also serve to inform the public and provide the opportunity for active participation by international partners.

Biogas biodesulfurization in an anoxic biotrickling filter packed with open-pore polyurethane foam.

PubMed

Fernández, Maikel; Ramírez, Martín; Gómez, José Manuel; Cantero, Domingo

2014-01-15

Biogas biodesulfurization by an anoxic biotrickling filter packed with open pore polyurethane foam at the laboratory scale (packed volume 2.4L) has been studied. The biotrickling system was operated for 620 days with biogas supplied continuously and two nitrate feeding regimes were tested (manual and programmed). Biomass immobilization was carried out under the manual nitrate feeding regime and a study was then carried out on the effects on removal efficiency of the following parameters: nitrate source, H2S inlet load, nitrate concentration, sulfate accumulation, temperature, pH and trickling liquid velocity. The effect of increased H2S inlet load was studied under the programmed nitrate feeding regime. The results show that a removal efficiency of 99% can be obtained when working under the following conditions: inlet loads below 130gSm(-3)h(-1), a programmed nitrate feeding system, temperature of 30°C, sulfate concentration below 33gL(-1), a pH between 7.3 and 7.5, and a trickling liquid velocity higher than 4.6mh(-1). Copyright © 2013 Elsevier B.V. All rights reserved.

Process evaluation of the Living Green, Healthy and Thrifty (LiGHT) web-based child obesity management program: combining health promotion with ecology and economy.

PubMed

Jogova, Maria; Song, Joshua Eun-Soo; Campbell, Audrey Clare; Warbuton, Darren; Warshawski, Tom; Chanoine, Jean-Pierre

2013-04-01

To conduct a process evaluation of the Living Green, Healthy and Thrifty (LiGHT) program, a novel virtual child obesity management program that combines health promotion with ecology and economy (Phase 1). We carried out a mixed methods process evaluation involving qualitative and quantitative data collection in 3 phases: among 3 child-parent units, (group 1) that informed program development; 9 child-parent units (group 2) that tested the draft program and further aided program refinement; and 17 child-parent units (group 3) for a 4-week pilot of the program. In the program pilot, we assessed participants' knowledge and readiness to change pre- and postintervention and explored perceptions of the program. Participants generally felt that the online format for program delivery was convenient and accessible, the content was practical, and the integration of health-environment-economy was well received. Many parents also appreciated the involvement of the family. However, the lack of visual appeal and overabundance of text was identified as a challenge, and children/youth in particular requested assurance that their personal information (e.g. weight) was not seen by their parents. The online method of program delivery holds the unique challenge of requiring special efforts to create a sense of personal connection and community. The presence of a "Way-finder" to assist participants and discussion boards/forums are potential solutions. The LiGHT online weight management program offers an accessible, convenient weight management resource that children and families appreciate for its availability, broader educational scope, and practicality. Outcome evaluation of LiGHT will be carried out in Phase 2 of the project. Copyright © 2013 Canadian Diabetes Association. Published by Elsevier Inc. All rights reserved.

Ares I-X: First Flight of a New Era

NASA Technical Reports Server (NTRS)

Davis, Stephen R.; Askins, Bruce R.

2010-01-01

Since 2005, NASA s Constellation Program has been designing, building, and testing the next generation of launch and space vehicles to carry humans beyond low-Earth orbit (LEO). The Ares Projects at Marshall Space Flight Center (MSFC) are developing the Ares I crew launch vehicle and Ares V cargo launch vehicle. On October 28, 2009, the first development flight test of the Ares I crew launch vehicle, Ares I-X, lifted off from a launch pad at Kennedy Space Center (KSC) on successful suborbital flight. Basing exploration launch vehicle designs on Ares I-X information puts NASA one step closer to full-up "test as you fly," a best practice in vehicle design. Although the final Constellation Program architecture is under review, the Ares I-X data and experience in vehicle design and operations can be applied to any launch vehicle. This paper presents the mission background as well as results and lessons learned from the flight.

Five-week sensory motor training program improves functional performance and postural control in young male soccer players - A blind randomized clinical trial.

PubMed

Heleno, Lucas Rafael; da Silva, Rubens A; Shigaki, Leonardo; Araújo, Cynthia Gobbi Alves; Coelho Candido, Cristiane Regina; Okazaki, Victor Hugo Alves; Frisseli, Ariobaldo; Macedo, Christiane de S Guerino

2016-11-01

Sensory motor training programs are used in the rehabilitation and prevention of injuries among soccer players. Inconsistencies are found in the literature regarding the duration of the protocols and the exercises and equipment used. To evaluate the benefits of a five-week sensory motor training program on the functional performance and postural control of young soccer players. The study sample comprised 22 young male soccer players who were evaluated using: the Figure-of-Eight Test (F8), Side Hop Test (SHT), Star Excursion Balance Test (SEBT), and a force platform. The players were randomly divided into a control group (N = 10), who continued their soccer practice sessions and an intervention group (N = 12), who continued their soccer practice sessions and were also enrolled in a supervised five-week sensory motor training program. After the five-week training program, the intervention group obtained significant results in the F8, SHT and SEBT, as well as in the following parameters: area of pressure of sway center (COP), mean velocity and mean frequency of COP. The five-week sensory motor training program, carried out with easily available and low cost equipment, was effective at improving functional performance and postural control in young soccer players. Copyright © 2016 Elsevier Ltd. All rights reserved.

Initialization Method for Grammar-Guided Genetic Programming

NASA Astrophysics Data System (ADS)

García-Arnau, M.; Manrique, D.; Ríos, J.; Rodríguez-Patón, A.

This paper proposes a new tree-generation algorithm for grammarguided genetic programming that includes a parameter to control the maximum size of the trees to be generated. An important feature of this algorithm is that the initial populations generated are adequately distributed in terms of tree size and distribution within the search space. Consequently, genetic programming systems starting from the initial populations generated by the proposed method have a higher convergence speed. Two different problems have been chosen to carry out the experiments: a laboratory test involving searching for arithmetical equalities and the real-world task of breast cancer prognosis. In both problems, comparisons have been made to another five important initialization methods.

Leisure education reduces stress among older adults.

PubMed

Chang, Liang-Chih

2014-01-01

The objectives of this study were to examine whether a leisure education program could facilitate leisure competence among older adults and whether it could also reduce their stress. A pre-test-post-test randomized experimental design was conducted. Subjects were randomly assigned to either an experimental group (n = 30) or a control group (n = 30). A leisure education program was used to serve as the intervention. A day before this experiment was carried out, pre-test data were collected using leisure competence and stress scales. Thirty minutes after this experiment ended, post-test data were collected using the same scales. These data were analyzed using an analysis of covariance. The results indicated that the average post-test scores of leisure competence in the experimental group were significantly higher than those in the control group and that the average post-test scores of stress in the experimental group were significantly lower than those in the control group. Healthcare practitioners should adopt the provision of leisure education as a priority to facilitate leisure competence and reduce stress among older adults.

Feasibility of adapting a classroom balance training program to a video game platform for people with Parkinson's disease.

PubMed

Dowling, Glenna A; Hone, Robert; Brown, Charles; Mastick, Judy; Melnick, Marsha

2013-04-01

Decreased postural stability in people with Parkinson's disease (PD) is a major component of disability. Rehabilitation interventions are therefore targeted to improve balance, mobility, and strength. Virtual environment and gaming platforms can encourage therapeutic activity in the home and be challenging and fun. The aims of the project were to demonstrate the technical feasibility of adapting a classroom-based gait-and-balance training program to a video game platform. Ease of use, appeal, and safety of the proposed games were tested for both clinic and in-home use. This cross-sectional observational study was carried out in three phases. Modifications in the game platform were made in an iterative fashion based on feedback from subjects and the observations of clinical and design team members. The first two phases of testing were performed in a laboratory setting, and the final phase was carried out in subjects' homes. Subjects (n=20) scored the primary "Rail Runner" game 3.6 for ease of use (1=hard, 5=easy) and 3.9 for appeal (1=did not like at all, 5=liked very much). There were no safety issues encountered, and the games performed without technical flaws in the final phase of testing. A computer-based video game that incorporates therapeutic movements to improve gait and balance for people with PD was appealing to subjects and feasible for home use.

Contraceptive social marketing and community-based distribution systems in Colombia.

PubMed

Vernon, R; Ojeda, G; Townsend, M C

1988-01-01

Three operations research experiments were carried out in three provinces of Colombia to improve the cost-effectiveness of Profamilia's nonclinic-based programs. The experiments tested: (a) whether a contraceptive social marketing (CSM) strategy can replace a community-based distribution (CBD) program in a high contraceptive use area; (b) if wage incentives for salaried CBD instructors will increase contraceptive sales; and (c) whether a specially equipped information, education, and communication (IEC) team can replace a cadre of rural promoters to expand family planning coverage. All three strategies proved to be effective, but only the CSM system yielded a profit. Despite this, Profamilia discontinued its CSM program soon after the experiment was completed. Unexpected government controls regulating the price and sale of contraceptives in Colombia made the program unprofitable. As a result, family planning agencies are cautioned against replacing CBD programs with CSM. Instead, CBD programs might adopt a more commercial approach to become more efficient.

Fall 2012 Graduate Engineering Internship Summary

NASA Technical Reports Server (NTRS)

Ehrlich, Joshua

2013-01-01

In the fall of 2012, I participated in the National Aeronautics and Space Administration (NASA) Pathways Intern Employment Program at the Kennedy Space Center (KSC) in Florida. This was my second internship opportunity with NASA, a consecutive extension from a summer 2012 internship. During my four-month tenure, I gained valuable knowledge and extensive hands-on experience with payload design and testing as well as composite fabrication for repair design on future space vehicle structures. As a systems engineer, I supported the systems engineering and integration team with the testing of scientific payloads such as the Vegetable Production System (Veggie). Verification and validation (V&V) of the Veggie was carried out prior to qualification testing of the payload, which incorporated a lengthy process of confirming design requirements that were integrated through one or more validatjon methods: inspection, analysis, demonstration, and testing. Additionally, I provided assistance in verifying design requirements outlined in the V&V plan with the requirements outlined by the scientists in the Science Requirements Envelope Document (SRED). The purpose of the SRED was to define experiment requirements intended for the payload to meet and carry out.

KSC-2012-1308

NASA Image and Video Library

2011-12-21

LOUISVILLE, Colo. – During NASA's Commercial Crew Development Round 2 CCDev2) activities for the Commercial Crew Program CCP, Sierra Nevada Corp. SNC delivered the primary structure of its Dream Chaser flight test vehicle to the company’s office in Louisville, Colo. SNC engineers currently are assembling the full-scale prototype, which includes the integration of secondary structures and subsystems. This all-composite structure of the company's planned winged spacecraft, the Dream Chaser, will be used to carry out several remaining CCDev2 milestones including a captive carry flight and the first approach and landing test of the spacecraft. During the captive carry flight, a carrier aircraft will the Dream Chaser vehicle over NASA's Dryden Flight Research Center in Edwards, Calif. Sierra Nevada is one of seven companies NASA entered into Space Act Agreements SAAs with during CCDev2 to aid in the innovation and development of American-led commercial capabilities for crew transportation and rescue services to and from the International Space Station and other low Earth orbit destinations. For information about CCP, visit www.nasa.gov/commercialcrew. Photo credit: Sierra Nevada Corp.

Numerical modeling of exciton-polariton Bose-Einstein condensate in a microcavity

NASA Astrophysics Data System (ADS)

Voronych, Oksana; Buraczewski, Adam; Matuszewski, Michał; Stobińska, Magdalena

2017-06-01

A novel, optimized numerical method of modeling of an exciton-polariton superfluid in a semiconductor microcavity was proposed. Exciton-polaritons are spin-carrying quasiparticles formed from photons strongly coupled to excitons. They possess unique properties, interesting from the point of view of fundamental research as well as numerous potential applications. However, their numerical modeling is challenging due to the structure of nonlinear differential equations describing their evolution. In this paper, we propose to solve the equations with a modified Runge-Kutta method of 4th order, further optimized for efficient computations. The algorithms were implemented in form of C++ programs fitted for parallel environments and utilizing vector instructions. The programs form the EPCGP suite which has been used for theoretical investigation of exciton-polaritons. Catalogue identifier: AFBQ_v1_0 Program summary URL:http://cpc.cs.qub.ac.uk/summaries/AFBQ_v1_0.html Program obtainable from: CPC Program Library, Queen's University, Belfast, N. Ireland Licensing provisions: BSD-3 No. of lines in distributed program, including test data, etc.: 2157 No. of bytes in distributed program, including test data, etc.: 498994 Distribution format: tar.gz Programming language: C++ with OpenMP extensions (main numerical program), Python (helper scripts). Computer: Modern PC (tested on AMD and Intel processors), HP BL2x220. Operating system: Unix/Linux and Windows. Has the code been vectorized or parallelized?: Yes (OpenMP) RAM: 200 MB for single run Classification: 7, 7.7. Nature of problem: An exciton-polariton superfluid is a novel, interesting physical system allowing investigation of high temperature Bose-Einstein condensation of exciton-polaritons-quasiparticles carrying spin. They have brought a lot of attention due to their unique properties and potential applications in polariton-based optoelectronic integrated circuits. This is an out-of-equilibrium quantum system confined within a semiconductor microcavity. It is described by a set of nonlinear differential equations similar in spirit to the Gross-Pitaevskii (GP) equation, but their unique properties do not allow standard GP solving frameworks to be utilized. Finding an accurate and efficient numerical algorithm as well as development of optimized numerical software is necessary for effective theoretical investigation of exciton-polaritons. Solution method: A Runge-Kutta method of 4th order was employed to solve the set of differential equations describing exciton-polariton superfluids. The method was fitted for the exciton-polariton equations and further optimized. The C++ programs utilize OpenMP extensions and vector operations in order to fully utilize the computer hardware. Running time: 6h for 100 ps evolution, depending on the values of parameters

KSC-2009-1997

NASA Image and Video Library

2009-03-09

CAPE CANAVERAL, Fla. – Near Launch Pad 39B at NASA's Kennedy Space Center in Florida, Jose Perez-Morales explains use of the launch pad for the Ares rockets in the Constellation Program. Perez-Morales is Constellation senior pad project manager. Pad 39B will be used for the Ares I-X flight test, targeted for July 2009. The I-X flight will provide NASA an early opportunity to test and prove hardware, facilities and ground operations associated with Ares I, part of the Constellation Program to return men to the moon and beyond. Ares I is the essential core of a safe, reliable, cost-effective space transportation system that eventually will carry crewed missions back to the moon, on to Mars and out into the solar system. Photo credit: NASA/Jack Pfaller

Department of Physics' Involvement of the Impact Testing Project of the High Speed Civil Transport Program (HSCT)

NASA Technical Reports Server (NTRS)

VonMeerwall, Ernst D.

1994-01-01

The project involved the impact testing of a kevlar-like woven polymer material, PBO. The purpose was to determine whether this material showed any promise as a lightweight replacement material for jet engine fan containment. The currently used metal fan containment designs carry a high drag penalty due to their weight. Projectiles were fired at samples of PBO by means of a 0.5 inch diameter Helium powered gun. The Initial plan was to encase the samples inside a purpose-built steel "hot box" for heating and ricochet containment. The research associate's responsibility was to develop the data acquisition programs and techniques necessary to determine accurately the impacting projectile's velocity. Beyond this, the Research Associate's duties include any physical computations, experimental design, and data analysis necessary.

Can space station software be specified through Ada?

NASA Technical Reports Server (NTRS)

Knoebel, Arthur

1987-01-01

Programming of the space station is to be done in the Ada programming language. A breadboard of selected parts of the work package for Marshall Space Flight Center is to be built, and programming this small part will be a good testing ground for Ada. One coding of the upper levels of the design brings out several problems with top-down design when it is to be carried out strictly within the language. Ada is evaluated on the basis of this experience, and the points raised are compared with other experience as related in the literature. Rapid prototyping is another approach to the initial programming; several different types of prototypes are discussed, and compared with the art of specification. Some solutions are proposed and a number of recommendations presented.

KSC-2009-4134

NASA Image and Video Library

2009-07-15

CAPE CANAVERAL, Fla. – A crane is attached to the Ares I-X forward center assembly in NASA Kennedy Space Center's Vehicle Assembly Building. It will be mated with the aft center assembly. Part of the Constellation Program, the Ares I-X is the test vehicle for the Ares I, which is the essential core of a space transportation system that eventually will carry crewed missions back to the moon, on to Mars and out into the solar system . The Ares I-X flight test is targeted for no earlier than Aug. 30. Photo credit: NASA/Troy Cryder

Radon detection system, design, test and performance

NASA Astrophysics Data System (ADS)

Balcázar, M.; Chávez, A.; Piña-Villalpando, G.; Navarrete, M.

1999-02-01

A portable radon detection system (α-Inin) has been designed and constructed for using it in adverse environmental conditions where humidity, temperature and chemical vaporous are present. The minimum integration time is in periods of 15 min during 41 days. A 12 V battery and a photovoltaic module allow the α-Inin autonomy in field measurements. Data is collected by means of a laptop computer where data processing and α-Inin programming are carried out. α-Inin performance was simultaneously tested in a controlled radon chamber, together with a commercial α-Meter.

View of equipment used for Heat Flow and Convection Experiment

NASA Image and Video Library

1972-12-17

AS17-162-24063 (7-19 Dec. 1972) --- A close-up view of the equipment used for the Heat Flow and Convection Experiment, an engineering and operational test and demonstration carried out aboard the Apollo 17 command module during the final lunar landing mission in NASA's Apollo program. Three test cells were used in the demonstration for measuring and observing fluid flow behavior in the absence of gravity in space flight. Data obtained from such demonstrations will be valuable in the design of future science experiments and for manufacturing processes in space.

Carbon-carbon primary structure for SSTO vehicles

NASA Astrophysics Data System (ADS)

Croop, Harold C.; Lowndes, Holland B.

1997-01-01

A hot structures development program is nearing completion to validate use of carbon-carbon composite structure for primary load carrying members in a single-stage-to-orbit, or SSTO, vehicle. A four phase program was pursued which involved design development and fabrication of a full-scale wing torque box demonstration component. The design development included vehicle and component selection, design criteria and approach, design data development, demonstration component design and analysis, test fixture design and analysis, demonstration component test planning, and high temperature test instrumentation development. The fabrication effort encompassed fabrication of structural elements for mechanical property verification as well as fabrication of the demonstration component itself and associated test fixturing. The demonstration component features 3D woven graphite preforms, integral spars, oxidation inhibited matrix, chemical vapor deposited (CVD) SiC oxidation protection coating, and ceramic matrix composite fasteners. The demonstration component has been delivered to the United States Air Force (USAF) for testing in the Wright Laboratory Structural Test Facility, WPAFB, OH. Multiple thermal-mechanical load cycles will be applied simulating two atmospheric cruise missions and one orbital mission. This paper discusses the overall approach to validation testing of the wing box component and presents some preliminary analytical test predictions.

Design of the central region in the Gustaf Werner cyclotron at the Uppsala university

NASA Astrophysics Data System (ADS)

Toprek, Dragan; Reistad, Dag; Lundstrom, Bengt; Wessman, Dan

2002-07-01

This paper describes the design of the central region in the Gustaf Werner cyclotron for h=1, 2 and 3 modes of acceleration. The electric field distribution in the inflector and in the four acceleration gaps has been numerically calculated from an electric potential map produced by the program RELAX3D. The geometry of the central region has been tested with the computations of orbits carried out by means of the computer code CYCLONE. The optical properties of the spiral inflector and the central region were studied by using the programs CASINO and CYCLONE, respectively.

A numerical code for the simulation of non-equilibrium chemically reacting flows on hybrid CPU-GPU clusters

NASA Astrophysics Data System (ADS)

Kudryavtsev, Alexey N.; Kashkovsky, Alexander V.; Borisov, Semyon P.; Shershnev, Anton A.

2017-10-01

In the present work a computer code RCFS for numerical simulation of chemically reacting compressible flows on hybrid CPU/GPU supercomputers is developed. It solves 3D unsteady Euler equations for multispecies chemically reacting flows in general curvilinear coordinates using shock-capturing TVD schemes. Time advancement is carried out using the explicit Runge-Kutta TVD schemes. Program implementation uses CUDA application programming interface to perform GPU computations. Data between GPUs is distributed via domain decomposition technique. The developed code is verified on the number of test cases including supersonic flow over a cylinder.

STS-3 medical report

NASA Technical Reports Server (NTRS)

Pool, S. L. (Editor); Johnson, P. C., Jr. (Editor); Mason, J. A. (Editor)

1982-01-01

The medical operations report for STS-3, which includes a review of the health of the crew before, during, and immediately after the third Shuttle orbital flight is presented. Areas reviewed include: health evaluation, medical debriefing of crewmembers, health stabilization program, medical training, medical 'kit' carried in flight, tests and countermeasures for space motion sickness, cardiovascular profile, biochemistry and endocrinology results, hematology and immunology analyses, medical microbiology, food and nutrition, potable water, shuttle toxicology, radiological health, and cabin acoustic noise. Environmental effects of shuttle launch and landing medical information management, and management, planning, and implementation of the medical program are also dicussed.

An Evaluation of Grazing-Incidence Optics for Neutron Imaging

NASA Technical Reports Server (NTRS)

Gubarev, M. V.

2007-01-01

The refractive index for most materials is slightly less than unity, which opens an opportunity to develop the grazing incidence neutron imaging optics. The ideal material for the optics would be natural nickel and its isotopes. Marshall Space Flight Center (MSFC) has active development program on the nickel replicated optics for use in x-ray astronomy. Brief status report on the program is presented. The results of the neutron focusing optic test carried by the MSFC team at National Institute of Standards and Technology (NIST) are also presented. Possible applications of the optics are briefly discussed.

Experimental and numerical investigations of higher mode effects on seismic inelastic response of reinforced concrete shear walls

NASA Astrophysics Data System (ADS)

Ghorbanirenani, Iman

This thesis presents two experimental programs together with companion numerical studies that were carried out on reinforced concrete shear walls: static tests and dynamic (shake table) tests. The first series of experiments were monotonic and cyclic quasi-static testing on ductile reinforced concrete shear wall specimens designed and detailed according to the seismic provisions of NBCC 2005 and CSA-A23.3-04 standard. The tests were carried out on full-scale and 1:2.37 reduced scale wall specimens to evaluate the seismic design provisions and similitude law and determine the appropriate scaling factor that could be applied for further studies such as dynamic tests. The second series of experiments were shake table tests conducted on two identical 1:2.33 scaled, 8-storey moderately ductile reinforced concrete shear wall specimens to investigate the effects of higher modes on the inelastic response of slender walls under high frequency ground motions expected in Eastern North America. The walls were designed and detailed according to the seismic provisions of NBCC 2005 and CSA-A23.3-04 standard. The objectives were to validate and understand the inelastic response and interaction of shear, flexure and axial loads in plastic hinge zones of the walls considering the higher mode effects and to investigate the formation of second hinge in upper part of the wall due to higher mode responses. Second mode response significantly affected the response of the walls. This caused inelastic flexural response to develop at the 6th level with approximately the same rotation ductility compared to that observed at the base. Dynamic amplification of the base shear forces was also observed in both walls. Numerical modeling of these two shake table tests was performed to evaluate the test results and validate current modeling approaches. Nonlinear time history analyses were carried out by the reinforced concrete fibre element (OpenSees program) and finite element (VecTor2 program) methods using the shake table feedback signals as input. Good agreement was generally obtained between numerical and experimental results. Both computer programs were able to predict the natural frequency of the walls in the undamaged and damaged conditions. Both modeling techniques could predict that the maximum bending moment at the base of the walls reached the actual wall moment capacity. The inelastic response and the dual plastic hinge behaviour of the walls could be adequately reproduced using the fibre element and finite element analysis programs. The fibre element method is a good alternative in terms of computing time. It produces reasonable results in comparison with the finite element method, although particular attention needs to be given to the selection of the damping ratios. The different parametric analyses performed in this thesis showed that, for both models, adding a small amount of global viscous damping in combination with a refined reinforced concrete hysteretic model could predict better the seismic behaviour of the tested structures. For the VecTor2 program, a viscous damping of 1% led to reasonable results for the studied RC walls. For the OpenSees program, 2% damping resulted in a good match between test and predictions for the 100% EQ test on the initially undamaged wall. When increasing the earthquake intensities, the damping had to be reduced between 1.5% and 1% to achieve good results for a damaged wall with elongated vibration periods. According to the experimental results and numerical analyses on reinforced concrete shear walls subjected to ground motions from Eastern North America earthquakes, there is a high possibility of having a second plastic hinge forming in the upper part of walls in addition to the one assumed in design at the base. This second hinge could dissipate the earthquake energy more effectively and decrease the force demand on the wall. A dual plastic hinge design approach in which the structures become plastic in the upper wall segment as well as the base could be therefore more appropriate. Preliminary design recommendations considering higher mode effects on dual hinge response and base shear forces for ductile slender shear walls are given in this thesis. (Abstract shortened by UMI.)

Impact of Chemistry Experiments Outreach Program on Learning and Attitudes for Students in Their Penultimate Year of Schooling

ERIC Educational Resources Information Center

Windsor, Sarah; Bailey, Jack

2016-01-01

Year 11 chemistry students from three schools in the Sunshine Coast Region of Education Queensland carried out a choice of five experiments aligned with their school curriculum on campus at the University of the Sunshine Coast and in their own school classrooms. Significant improvements in science learning were observed in student post-test quiz…

EML Chester - 1982. Annual report of the Regional Baseline Station at Chester, New Jersey

DOE Office of Scientific and Technical Information (OSTI.GOV)

Volchok, H.L.

1982-11-01

The Environmental Measurements Laboratory (EML) has maintained a regional baseline station at Chester, New Jersey since 1976. The site provides EML with a remote, rural facility for carrying out regional baseline research and for testing field equipment. This report updates the various programs underway at the Chester site. Separate abstracts have been prepared for the included papers. (ACR)

Thinking, Fast and Slow? Some Field Experiments to Reduce Crime and Dropout in Chicago. NBER Working Paper 21178

ERIC Educational Resources Information Center

Heller, Sara B.; Shah, Anuj K.; Guryan, Jonathan; Ludwig, Jens; Mullainathan, Sendhil; Pollack, Harold A.

2015-01-01

We present the results of three large-scale randomized controlled trials (RCTs) carried out in Chicago, testing interventions to reduce crime and dropout by changing the decision-making of economically disadvantaged youth. We study a program called Becoming a Man (BAM), developed by the non-profit Youth Guidance, in two RCTs implemented in 2009-10…

Effects of a postural education program on school backpack habits related to low back pain in children.

PubMed

Vidal, Josep; Borràs, Pere A; Ponseti, Francisco J; Cantallops, Jaume; Ortega, Francisco B; Palou, Pere

2013-04-01

Population based studies have demonstrated that children and adolescents often complain of low back pain. A group-randomized controlled trial was carried out to investigate the effects of a postural education program on school backpack habits related to low back pain in children aged 10-12 year. The study sample included 137 children aged 10.7 years (SD = 0.672). Six classes from two primary schools were randomly allocated into experimental group (EG) (N = 63) or control group (CG) (N = 74). The EG received a postural education program over 6 weeks consisting of six sessions, while the CG followed the usual school curriculum. A questionnaire was fulfilled by the participants at pre-test, post-test, and 3 months after the intervention finished. The outcomes collected were: (1) try to load the minimum weight possible, (2) carry school backpack on two shoulders, (3) belief that school backpack weight does not affect to the back, and (4) the use of locker or something similar at school. A sum score was computed from the four items. Single healthy items mostly improved after the intervention and remained improved after 3-month follow-up in EG, while no substantial changes were observed in the CG. Healthy backpack use habits score was significantly increased at post-test compared to baseline in the EG (P < 0.000), and remained significantly increased after 3-month, compared to baseline (P = 0.001). No significant changes were observed in the CG (P > 0.2). The present study findings confirm that children are able to learn healthy backpack habits which might prevent future low back pain.

[Educational effectiveness of a group health education program in the workplace and an examination of educational methods to promote behavior modification].

PubMed

Kageyama, Makoto; Odagiri, Keiichi; Suzuki, Naoko; Honda, Kumiko; Onoue, Kazue; Yamamoto, Makoto; Mizuta, Isagi; Uehara, Akihiko

2014-01-01

It is well-known that health education programs carried out in the work place are useful for employees' health promotion. However, the effectiveness of group health education programs for workers as a population approach is unclear. The purpose of this study was to examine the effectiveness of a group health education program in the workplace, and to investigate educational methods which support workers modifying their health behaviors. A total of 289 workers who received a group health education program in the manufacturing industry (mean age, 42.1 ± 11.3 years old; 175 males and 114 females) were enrolled in this study. The group health education program was carried out to educate the subjects about periodontitis, oral health actions and lifestyle behaviors to prevent oral diseases. Participants were required to fill out a self-administered questionnaire which included information about oral health knowledge, oral health actions, lifestyle behaviors and symptoms of periodontitis before, immediately after and one month after the education. We used McNemar's test for the paired comparison of questionnaire responses. The relation between acquiring knowledge about periodontitis and subjects' modification of oral health action, behavior modification and symptoms of periodontitis were examined using the chi-squared test. The relationships of knowledge retention about periodontitis, the modification of the oral health actions and lifestyle behaviors (i.e., cigarette smoking, alcohol drinking and eating between meals), were examined with participants' characteristics (i.e., age, gender and occupational category) using Fisher's exact test. Knowledge about periodontitis significantly improved immediately after receiving the health education, and this effect of education was evident one month later. However, not all of the knowledge was sufficiently retained one month after the education session. The proportion of participants undertaking desirable oral health actions significantly increased one month after the education, whereas lifestyle behaviors did not alter. The modification of oral health actions improved periodontitis-related symptoms, however, no relationship was found between knowledge acquisition and behavior modification. The characteristics of the participants did not influence knowledge retention about periodontitis or modification of oral health actions. Our group health education program was appropriate and effective at providing knowledge about periodontitis and at modifying oral health actions. We should identify factors that obstruct workers behavior modification, and eliminate them to improve health behaviors.

KSC-2012-2904

NASA Image and Video Library

2012-05-22

CAPE CANAVERAL, Fla. – Powered by nine Merlin engines, the SpaceX Falcon 9 rocket lifts off Space Launch Complex-40 on Cape Canaveral Air Force Station in Florida at 3:44 a.m. EDT, carrying the Dragon capsule to orbit. The launch is the company's second demonstration test flight for NASA's Commercial Orbital Transportation Services, or COTS, Program. During the flight, the Dragon will conduct a series of check-out procedures to test and prove its systems, including rendezvous and berthing with the International Space Station. If the capsule performs as planned, the cargo and experiments it is carrying will be transferred to the station. The cargo includes food, water and provisions for the station’s Expedition crews, such as clothing, batteries and computer equipment. Under COTS, NASA has partnered with two aerospace companies to deliver cargo to the station. For more information, visit http://www.nasa.gov/spacex. Photo credit: NASA/Jim Grossmann

ksc-2012-2897

NASA Image and Video Library

2012-05-22

CAPE CANAVERAL, Fla. – The SpaceX Falcon 9 rocket soars into space from Space Launch Complex-40 on Cape Canaveral Air Force Station in Florida at 3:44 a.m. EDT, carrying the Dragon capsule to orbit. The launch is the company's second demonstration test flight for NASA's Commercial Orbital Transportation Services, or COTS, Program. During the flight, the Dragon will conduct a series of check-out procedures to test and prove its systems, including rendezvous and berthing with the International Space Station. If the capsule performs as planned, the cargo and experiments it is carrying will be transferred to the station. The cargo includes food, water and provisions for the station’s Expedition crews, such as clothing, batteries and computer equipment. Under COTS, NASA has partnered with two aerospace companies to deliver cargo to the station. For more information, visit http://www.nasa.gov/spacex. Photo credit: NASA/Alan Ault

KSC-2012-2897

NASA Image and Video Library

2012-05-22

CAPE CANAVERAL, Fla. – The SpaceX Falcon 9 rocket soars into space from Space Launch Complex-40 on Cape Canaveral Air Force Station in Florida at 3:44 a.m. EDT, carrying the Dragon capsule to orbit. The launch is the company's second demonstration test flight for NASA's Commercial Orbital Transportation Services, or COTS, Program. During the flight, the Dragon will conduct a series of check-out procedures to test and prove its systems, including rendezvous and berthing with the International Space Station. If the capsule performs as planned, the cargo and experiments it is carrying will be transferred to the station. The cargo includes food, water and provisions for the station’s Expedition crews, such as clothing, batteries and computer equipment. Under COTS, NASA has partnered with two aerospace companies to deliver cargo to the station. For more information, visit http://www.nasa.gov/spacex. Photo credit: NASA/Alan Ault

ksc-2012-2896

NASA Image and Video Library

2012-05-22

CAPE CANAVERAL, Fla. – The SpaceX Falcon 9 rocket lifts off Space Launch Complex-40 on Cape Canaveral Air Force Station in Florida at 3:44 a.m. EDT, carrying the Dragon capsule to orbit. The launch is the company's second demonstration test flight for NASA's Commercial Orbital Transportation Services, or COTS, Program. During the flight, the Dragon will conduct a series of check-out procedures to test and prove its systems, including rendezvous and berthing with the International Space Station. If the capsule performs as planned, the cargo and experiments it is carrying will be transferred to the station. The cargo includes food, water and provisions for the station’s Expedition crews, such as clothing, batteries and computer equipment. Under COTS, NASA has partnered with two aerospace companies to deliver cargo to the station. For more information, visit http://www.nasa.gov/spacex. Photo credit: NASA/Alan Ault

Structural Test Documentation and Results for the McDonnell Douglas All-Composite Wing Stub Box

NASA Technical Reports Server (NTRS)

Jegley, Dawn C.; Bush, Harold G.

1997-01-01

The results of a series of tests conducted at the NASA Langley Research Center to evaluate the behavior of an all-composite full-scale wing box are presented. The wing stub box is representative of a section of a commercial transport aircraft wing box and was designed and constructed by McDonnell Douglas Aerospace Company as part of the NASA Advanced Composites Technology (ACT) program. Tests were conducted with and without low-speed impact damage and repairs. The structure with nonvisible impact damage carried 140 percent of Design Limit Load prior to failure through an impact site.

(236)U and (239,)(240)Pu ratios from soils around an Australian nuclear weapons test site.

PubMed

Tims, S G; Froehlich, M B; Fifield, L K; Wallner, A; De Cesare, M

2016-01-01

The isotopes (236)U, (239)Pu and (240)Pu are present in surface soils as a result of global fallout from nuclear weapons tests carried out in the 1950's and 1960's. These isotopes potentially constitute artificial tracers of recent soil erosion and sediment movement. Only Accelerator Mass Spectrometry has the requisite sensitivity to measure all three isotopes at these environmental levels. Coupled with its relatively high throughput capabilities, this makes it feasible to conduct studies of erosion across the geographical extent of the Australian continent. In the Australian context, however, global fallout is not the only source of these isotopes. As part of its weapons development program the United Kingdom carried out a series of atmospheric and surface nuclear weapons tests at Maralinga, South Australia in 1956 and 1957. The tests have made a significant contribution to the Pu isotopic abundances present in the region around Maralinga and out to distances ∼1000 km, and impact on the assessment techniques used in the soil and sediment tracer studies. Quantification of the relative fallout contribution derived from detonations at Maralinga is complicated owing to significant contamination around the test site from numerous nuclear weapons safety trials that were also carried out around the site. We show that (236)U can provide new information on the component of the fallout that is derived from the local nuclear weapons tests, and highlight the potential of (236)U as a new fallout tracer. Crown Copyright © 2015. Published by Elsevier Ltd. All rights reserved.

Development of design, qualification, screening, and application requirements for plastic encapsulated solid-state devices for space applications

NASA Astrophysics Data System (ADS)

1981-12-01

Test data were collected on 1035 plastic encapsulated devices and 75 hermetically scaled control group devices that were purchased from each of five different manufacturers in the categories of (1) low power Schottsky TTL (bipolar) digital circuits; (2) CMOS digital circuits; (3) operational amplifier linear circuits; and (4) NPN transistors. These parts were subjected to three different initial screening conditions, then to extended life testing, to determine any possible advantages or trends for any particular screen. Several tests were carried out in the areas of flammability testing, humidity testing, high pressure steam (auroclave) testing, and high temperature storage testing. Test results are presented. Procurement and application considerations for use of plastic encapsulated semiconductors are presented and a statistical analysis program written to study the log normal distributions resulting from life testing is concluded.

Development of design, qualification, screening, and application requirements for plastic encapsulated solid-state devices for space applications

NASA Technical Reports Server (NTRS)

1981-01-01

Test data were collected on 1035 plastic encapsulated devices and 75 hermetically scaled control group devices that were purchased from each of five different manufacturers in the categories of (1) low power Schottsky TTL (bipolar) digital circuits; (2) CMOS digital circuits; (3) operational amplifier linear circuits; and (4) NPN transistors. These parts were subjected to three different initial screening conditions, then to extended life testing, to determine any possible advantages or trends for any particular screen. Several tests were carried out in the areas of flammability testing, humidity testing, high pressure steam (auroclave) testing, and high temperature storage testing. Test results are presented. Procurement and application considerations for use of plastic encapsulated semiconductors are presented and a statistical analysis program written to study the log normal distributions resulting from life testing is concluded.

Effects of two neuromuscular training programs on running biomechanics with load carriage: a study protocol for a randomised controlled trial.

PubMed

Liew, Bernard X W; Morris, Susan; Keogh, Justin W L; Appleby, Brendyn; Netto, Kevin

2016-10-22

In recent years, athletes have ventured into ultra-endurance and adventure racing events, which tests their ability to race, navigate, and survive. These events often require race participants to carry some form of load, to bear equipment for navigation and survival purposes. Previous studies have reported specific alterations in biomechanics when running with load which potentially influence running performance and injury risk. We hypothesize that a biomechanically informed neuromuscular training program would optimize running mechanics during load carriage to a greater extent than a generic strength training program. This will be a two group, parallel randomized controlled trial design, with single assessor blinding. Thirty healthy runners will be recruited to participate in a six weeks neuromuscular training program. Participants will be randomized into either a generic training group, or a biomechanically informed training group. Primary outcomes include self-determined running velocity with a 20 % body weight load, jump power, hopping leg stiffness, knee extensor and triceps-surae strength. Secondary outcomes include running kinetics and kinematics. Assessments will occur at baseline and post-training. To our knowledge, no training programs are available that specifically targets a runner's ability to carry load while running. This will provide sport scientists and coaches with a foundation to base their exercise prescription on. ANZCTR ( ACTRN12616000023459 ) (14 Jan 2016).

PRCC Aviation Students

NASA Image and Video Library

2007-01-26

Pratt & Whitney Rocketdyne's Jeff Hansell, right, explains functions of a space shuttle main engine to Pearl River Community College Aviation Maintenance Technology Program students. Christopher Bryon, left, of Bay St. Louis, Ret Tolar of Kiln, Dan Holston of Baxterville and Billy Zugg of Long Beach took a recent tour of the SSME Processing Facility and the E-1 Test Complex at Stennis Space Center in South Mississippi. The students attend class adjacent to the Stennis International Airport tarmac in Kiln, where they get hands-on experience. PRCC's program prepares students to be responsible for the inspection, repair and maintenance of technologically advanced aircraft. A contractor to NASA, Pratt & Whitney Rocketdyne in Canoga Park, Calif., manufactures the space shuttle main engine and its high-pressure turbo pumps. SSC was established in the 1960s to test the huge engines for the Saturn V moon rockets. Now 40 years later, the center tests every main engine for the space shuttle, and is America's largest rocket engine test complex. SSC will soon begin testing the rocket engines that will power spacecraft carrying Americans back to the moon and on to Mars.

PRCC Aviation Students

NASA Technical Reports Server (NTRS)

2007-01-01

Pratt & Whitney Rocketdyne's Jeff Hansell, right, explains functions of a space shuttle main engine to Pearl River Community College Aviation Maintenance Technology Program students. Christopher Bryon, left, of Bay St. Louis, Ret Tolar of Kiln, Dan Holston of Baxterville and Billy Zugg of Long Beach took a recent tour of the SSME Processing Facility and the E-1 Test Complex at Stennis Space Center in South Mississippi. The students attend class adjacent to the Stennis International Airport tarmac in Kiln, where they get hands-on experience. PRCC's program prepares students to be responsible for the inspection, repair and maintenance of technologically advanced aircraft. A contractor to NASA, Pratt & Whitney Rocketdyne in Canoga Park, Calif., manufactures the space shuttle main engine and its high-pressure turbo pumps. SSC was established in the 1960s to test the huge engines for the Saturn V moon rockets. Now 40 years later, the center tests every main engine for the space shuttle, and is America's largest rocket engine test complex. SSC will soon begin testing the rocket engines that will power spacecraft carrying Americans back to the moon and on to Mars.

KSC-2014-3938

NASA Image and Video Library

2014-09-15

SAN DIEGO, Calif. – John Casper, retired NASA astronaut and Special Assistant for Program Integration for the Orion Program, looks at the San Diego skyline from the deck of the USS Anchorage as the ship departs Naval Base San Diego on the first day of Orion Underway Recovery Test 3. The ship will head out to sea, off the coast of San Diego, in search of conditions to support test needs for a full dress rehearsal of recovery operations. NASA, Lockheed Martin and U.S. Navy personnel will conduct tests in the Pacific Ocean to prepare for recovery of the Orion crew module on its return from a deep space mission. The test will allow the teams to demonstrate and evaluate the recovery processes, procedures, hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery tests. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a United Launch Alliance Delta IV Heavy rocket and in 2018 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Cory Huston

The organization and financing of cervical cancer prevention carried out by midwives in primary health care.

PubMed

Sobczyk, Karolina; Woźniak-Holecka, Joanna; Holecki, Tomasz; Szałabska, Dorota

2016-01-01

The main objective of the project was the evaluation of the organizational and financial aspects of midwives in primary health care (PHC), functioning under The Population Program for the Early Detection of Cervical Cancer two years after the implementation of new law regulations, which enable this occupational group to collect cytological material for screening. Under this project, the data of the Program's Coordinating Centre, affecting midwives' postgraduate education in the field of pap smear tests, was taken into analysis. Furthermore, The National Health Fund (NFZ) reports on contracts entered in the field of the discussed topics, taking into consideration the value of health services performed within the Program in respect of ambulatory care and primary care units. NFZ concluded contracts for the provision of PHC service with 6124 service providers in 2016, including the contracts in the field of providing health services under the cervical cancer prevention program by PHC midwifes, which were entered into by 358 institutions (5.85%). The value of the basic services under the Program, carried out under NFZ contracts in 2014, amounted to approx. PLN 12.3 million, while the value of services performed by PHC midwives represented only 0.38% of this sum. The introduction of legislative changes, allowing PHC midwives to collect cytological material for screening, did not cause, in the period of the observation on a national scale, the expected growth of availability of basic stage services within the cervical cancer prevention program.

A Sub-Orbital Platform for Flight Tests of Small Space Capsules

NASA Astrophysics Data System (ADS)

Pereira, P. Moraes A. L., Jr.; Silva, C. R.; Villas Bôas, D. J.; Corrêa, F., Jr.; Miyoshi, J. H.; Loures da Costa, L. E.

2002-01-01

In the development of a small recoverable space capsule, flight tests using sub-orbital rockets are considered. For this test series, a platform for aerodynamic and thermal measurements as also for qualification tests of onboard sub-systems and equipment was specified and is actually under development. This platform, known as SARA Suborbital, is specified to withstand a sub-orbital flight with the high performance sounding rocket VS40 and to be recovered at the sea. To perform the testing program, a flight trajectory with adequate aeroballistic parameters, as for instance high velocities in dense atmosphere and average re-entry velocity, is considered. The testing program includes measurements of aerodynamic pressures and thermal characteristics, three- axis acceleration, acoustic pressure level inside the platform and vibration environment. Beside this, tests to characterise the performance of the data acquisition and transmission system, the micro-gravity environment and to qualify the recovery system will be carried out. During the return flight, the dynamics of parachutes deployment and platform water impact, as also rescue procedures will also be observed. The present article shows the concept of the platform, describes in detail the experiments, and concludes with a discussion on the flight trajectory and recovery procedure.

Development of a ROT22 - DATAMAP interface

NASA Technical Reports Server (NTRS)

Shenoy, K. R.; Waak, T.; Brieger, J. T.

1986-01-01

This report (Contract NAS2-10331- Mod 10), outlines the development and validation of an interface between the three-dimensional transonic analysis program ROT22 and the Data from Aeromechanics Test and Analytics-Management and Analysis Package (DATAMAP). After development of the interface, the validation is carried out as follows. First, the DATAMAP program is used to analyze a portion of the Tip Aerodynamics and Acoustics Test (TAAT) data. Specifically, records 2872 and 2873 are analyzed at an azimuth of 90 deg, and record 2806 is analyzed at 60 deg. Trim conditions for these flight conditions are then calculated using the Bell performance prediction program ARAM45. Equivalent shaft, pitch, and twist angles are calculated from ARAM45 results and used as input to the ROT22 program. The interface uses the ROT22 results and creates DATAMAP information files from which the surface pressure contours and sectional pressure coefficients are plotted. Twist angles input to ROT22 program are then iteratively modified in the tip region until the computed pressure coefficients closely match the measurements. In all cases studied, the location of the shock is well predicted. However, the negative pressure coefficients were underpredicted. This could be accounted for by blade vortex interaction effects.

Human in the Loop Integrated Life Support Systems Ground Testing

NASA Technical Reports Server (NTRS)

Henninger, Donald L.; Marmolejo, Jose A.; Seaman, Calvin H.

2012-01-01

Human exploration missions beyond low earth orbit will be long duration with abort scenarios of days to months. This necessitates provisioning the crew with all the things they will need to sustain themselves while carrying out mission objectives. Systems engineering and integration is critical to the point where extensive integrated testing of life support systems on the ground is required to identify and mitigate risks. Ground test facilities (human-rated altitude chambers) at the Johnson Space Center are being readied to integrate all the systems for a mission along with a human test crew. The relevant environment will include deep space habitat human accommodations, sealed atmosphere capable of 14.7 to 8 psi total pressure and 21 to 32% oxygen concentration, life support systems (food, air, and water), communications, crew accommodations, medical, EVA, tools, etc. Testing periods will approximate those of the expected missions (such as a near Earth asteroid, Earth-Moon L2 or L1, the moon, Mars). This type of integrated testing is needed for research and technology development as well as later during the mission design, development, test, and evaluation (DDT&E) phases of an approved program. Testing will evolve to be carried out at the mission level fly the mission on the ground . Mission testing will also serve to inform the public and provide the opportunity for active participation by international, industrial and academic partners.

Clementine, Deep Space Program Science Experiment

NASA Technical Reports Server (NTRS)

1993-01-01

Clementine, also called the Deep Space Program Science Experiment, is a joint Department of Defense (DoD)/National Aeronautics and Space Administration (NASA) mission with the dual goal of testing small spacecraft, subsystems, and sensors in the deep space environment and also providing a nominal science return. The Clementine mission will provide technical demonstrations of innovative lightweight spacecraft components and sensors, will be launced on a spacecraft developed within 2 years of program start, and will point a way for new planetary mission options under consideration by NASA. This booklet gives the background of the Clementine mission (including the agencies involved), the mission objectives, the mission scenario, the instruments that the mission will carry, and how the data will be analyzed and made accessible.

Allen Newell's Program of Research: The Video-Game Test.

PubMed

Gobet, Fernand

2017-04-01

Newell (1973) argued that progress in psychology was slow because research focused on experiments trying to answer binary questions, such as serial versus parallel processing. In addition, not enough attention was paid to the strategies used by participants, and there was a lack of theories implemented as computer models offering sufficient precision for being tested rigorously. He proposed a three-headed research program: to develop computational models able to carry out the task they aimed to explain; to study one complex task in detail, such as chess; and to build computational models that can account for multiple tasks. This article assesses the extent to which the papers in this issue advance Newell's program. While half of the papers devote much attention to strategies, several papers still average across them, a capital sin according to Newell. The three courses of action he proposed were not popular in these papers: Only two papers used computational models, with no model being both able to carry out the task and to account for human data; there was no systematic analysis of a specific video game; and no paper proposed a computational model accounting for human data in several tasks. It is concluded that, while they use sophisticated methods of analysis and discuss interesting results, overall these papers contribute only little to Newell's program of research. In this respect, they reflect the current state of psychology and cognitive science. This is a shame, as Newell's ideas might help address the current crisis of lack of replication and fraud in psychology. Copyright © 2017 The Author. Topics in Cognitive Science published by Wiley Periodicals, Inc. on behalf of Cognitive Science Society.

The influence of computer-generated path on the robot’s effector stability of motion

NASA Astrophysics Data System (ADS)

Foit, K.; Banaś, W.; Gwiazda, A.; Ćwikła, G.

2017-08-01

The off-line trajectory planning is often carried out due to economical and practical reasons: the robot is not excluded from the production process and the operator could benefit from testing programs in the virtual environment. On the other hand, the dedicated off-line programming and simulation software is often limited in features and is intended to roughly check the program. It should be expected that the arm of the real robot’s manipulator will realize the trajectory in different manner: the acceleration and deceleration phases may trigger the vibrations of the kinematic chain that could affect the precision of effector positioning and degrade the quality of process realized by the robot. The purpose of this work is the analysis of the selected cases, when the robot’s effector has been moved along the programmed path. The off-line generated, test trajectories have different arrangement of points: such approach has allowed evaluating the time needed to complete the each of the tasks, as well as measuring the level of the vibration of the robot’s wrist. All tests were performed without the load. The conclusions of the experiment may be useful during the trajectory planning in order to avoid the critical configuration of points.

Organizational determinants of efficiency and effectiveness in mental health partial care programs.

PubMed Central

Schinnar, A P; Kamis-Gould, E; Delucia, N; Rothbard, A B

1990-01-01

The use of partial care as a treatment modality for mentally ill patients, particularly the chronically mentally ill, has greatly increased. However, research into what constitutes a "good" program has been scant. This article reports on an evaluation study of staff productivity, cost efficiency, and service effectiveness of adult partial care programs carried out in New Jersey in fiscal year 1984/1985. Five program performance indexes are developed based on comparisons of multiple measures of resources, service activities, and client outcomes. These are used to test various hypotheses regarding the effect of organizational and fiscal variables on partial care program efficiency and effectiveness. The four issues explored are: auspices, organizational complexity, service mix, and fiscal control by the state. These were found to explain about half of the variance in program performance. In addition, partial care programs demonstrating midlevel performance with regard to productivity and efficiency were observed to be the most effective, implying a possible optimal level of efficiency at which effectiveness is maximized. PMID:2113046

B-52 Launch Aircraft in Flight

NASA Technical Reports Server (NTRS)

2001-01-01

NASA's venerable B-52 mothership is seen here photographed from a KC-135 Tanker aircraft. The X-43 adapter is visible attached to the right wing. The B-52, used for launching experimental aircraft and for other flight research projects, has been a familiar sight in the skies over Edwards for more than 40 years and is also both the oldest B-52 still flying and the aircraft with the lowest flight time of any B-52. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet.

25 CFR 163.36 - Tribal forestry program financial support.

Code of Federal Regulations, 2010 CFR

2010-04-01

... services to carry out forest land management activities and shall be based on levels of funding assistance... carrying out forest land management activities. Such financial support shall be made available through the... of carrying out forest land management activities may apply and qualify for tribal forestry program...

25 CFR 163.36 - Tribal forestry program financial support.

Code of Federal Regulations, 2011 CFR

2011-04-01

... services to carry out forest land management activities and shall be based on levels of funding assistance... carrying out forest land management activities. Such financial support shall be made available through the... of carrying out forest land management activities may apply and qualify for tribal forestry program...

Basic research for the geodynamics program

NASA Technical Reports Server (NTRS)

1991-01-01

The mathematical models of space very long base interferometry (VLBI) observables suitable for least squares covariance analysis were derived and estimatability problems inherent in the space VLBI system were explored, including a detailed rank defect analysis and sensitivity analysis. An important aim is to carry out a comparative analysis of the mathematical models of the ground-based VLBI and space VLBI observables in order to describe the background in detail. Computer programs were developed in order to check the relations, assess errors, and analyze sensitivity. In order to investigate the estimatability of different geodetic and geodynamic parameters from the space VLBI observables, the mathematical models for time delay and time delay rate observables of space VLBI were analytically derived along with the partial derivatives with respect to the parameters. Rank defect analysis was carried out both by analytical and numerical testing of linear dependencies between the columns of the normal matrix thus formed. Definite conclusions were formed about the rank defects in the system.

Hydrokinesitherapy program using the Halliwick method on strength endurance and flexibility in a person with poliomyelitis sequelae.

PubMed

Ochoa Martínez, Paulina Yesica; Hall Lopez, Javier Arturo; Mateos Valenzuela, Adriana Griselda

2014-09-12

This case study attempts to determine the effect of a hydrokinesitherapy program by means of the Halliwick method on physical fitness in a female aged 35 years with poliomyelitis sequelae. The intervention followed sixteen weeks of hydrokinesitherapy during 70 minutes, five times a week, where we carried out exercises from the Halliwick method. There was an assessment both before and after the application. Strength endurance and flexibility were determined according to a senior fitness test protocol. The results showed positive improvements when carrying out the exercises from the Halliwick method and the percentage change (Δ%) of strength endurance increase 361.5% in the right arm and 300% in the left arm. Flexibility increased 2 cm in the right shoulder and 10 cm in the left shoulder. In conclusion the subject was able to improve the performance of Halliwick exercises while showing an increase in strength endurance and flexibility. Copyright AULA MEDICA EDICIONES 2014. Published by AULA MEDICA. All rights reserved.

A Blanik L-23 glider carrying a microphone and a pressure transducer flies near a BADS sensor following flight under the path of the F-5E SSBE aircraft

NASA Image and Video Library

2004-01-13

A United States Air Force Test Pilot School Blanik L-23 glider carrying a microphone and a pressure transducer flies near a BADS (Boom Amplitudes Direction System) sensor following flight at an altitude of 10 thousand feet under the path of the F-5E SSBE aircraft. The SSBE (Shaped Sonic Boom Experiment) was formerly known as the Shaped Sonic Boom Demonstration, or SSBD, and is part of DARPA's Quiet Supersonic Platform (QSP) program. On August 27, 2003, the F-5E SSBD aircraft demonstrated a method to reduce the intensity of sonic booms.

KSC-07pd3537

NASA Image and Video Library

2007-12-03

KENNEDY SPACE CENTER, FLA. -- STS-122 Mission Specialist Leland Melvin tests his gloves for a final fitting before space shuttle Atlantis' launch scheduled for 4:31 p.m. EST on Dec. 6. Melvin will make his first shuttle flight. Atlantis will carry the Columbus Lab, Europe’s largest contribution to the construction of the International Space Station. It will support scientific and technological research in a microgravity environment. Columbus, a program of ESA, is a multifunctional, pressurized laboratory that will be permanently attached to Node 2 of the space station to carry out experiments in materials science, fluid physics and biosciences, as well as to perform a number of technological applications. Photo credit: NASA/Kim Shiflett

Laterally Loaded Partially Prestressed Concrete Piles

DTIC Science & Technology

1989-09-01

of an extensive test program onl laterali y ioadeu. partially pr- estressed concrete fender piles. The study Included service load range as well ats...12,000-psi design strength). Configura- tion G utilized 14 r:- estress strand, in an unsymmetric pattern. To provide a uniform concrete prestress of 540...sudden loss in load carrying capacity directly related to the loss of concrete area. The compression concrete fractured longitudinally and along the

Results of the 1978 NASA/JPL balloon flight solar cell calibration program

NASA Technical Reports Server (NTRS)

Seaman, C. H.; Sidwell, L. B.

1979-01-01

The 1978 scheduled solar cell calibration balloon flight was successfully completed. Thirty six modules were carried to an altitude of above 36 kilometers. Recovery of telemetry and flight packages was without incident. These calibrated standard cells are used as reference standards in simulator testing of cells and arrays with similar spectral response characteristics. The factors affecting the spectral transmission of the atmosphere at various altitudes are summarized.

Krypton-85 Powered Lights for Airfield Application.

DTIC Science & Technology

1981-11-01

Department of Energy.(DOE), and eight lights were fabricated for testing by actual observation under airfield conditions. Light is produced in the units...concepts of radionuclide-powered lights, the R&D program carried out, and fabrication constraints involved in the production of the experimental...visible light has been known for many years. Early use of radium mixed with zinc sulfide phosphors provided self-illuminated clock dials. The military has

Instructional multimedia program versus standard lecture: a comparison of two methods for teaching the undergraduate orthodontic curriculum.

PubMed

Aly, M; Elen, J; Willems, G

2004-02-01

To compare the effectiveness of an interactive multimedia courseware package versus standard lectures regarding knowledge, understanding, and transfer of content, as well as problem-solving skills in orthodontics. Pre- and post-test assessments of final-year dental students (n = 26), who either used an interactive multimedia courseware package (n = 15) or attended standard lectures (n = 11) on equivalent material of the undergraduate orthodontic curriculum were carried out. Both groups were tested by written and multiple-choice questions covering knowledge, understanding, and application areas in the curriculum. A one-way anova was carried out in order to check statistical difference between the two groups. The P-value was set at 0.05. There was no difference in prior knowledge between the groups at baseline. Generally, no significant difference was seen between the two groups in relation to answers to questions about knowledge, understanding, and application in the orthodontic curriculum. However, both groups improved their scores after the course. In one question investigating the extent of understanding the instructional content of the multidisciplinary orthodontic treatment, the multimedia courseware package group scored significantly better. In this study, the instructional interactive multimedia program was found to be at least as effective as the standard lecture of the orthodontic curriculum for undergraduate training in orthodontics.

Student Interns Work on Mars

NASA Technical Reports Server (NTRS)

Bowman, C. D.; Bebak, M.; Bollen, D. M.; Curtis, K.; Daniel, C.; Grigsby, B.; Herman, T.; Haynes, E.; Lineberger, D. H.; Pieruccini, S.

2004-01-01

The exceptional imagery and data acquired by the Mars Exploration Rovers since their January 2004 landing have captured the attention of scientists, the public, and students and teachers worldwide. One aspect of particular interest lies with a group of high school teachers and students actively engaged in the Athena Student Interns Program. The Athena Student Interns Program (ASIP) is a joint effort between NASA s Mars Public Engagement Office and the Athena Science Investigation that began in early 1999 as a pilot student-scientist research partnership program associated with the FIDO prototype Mars rover field test . The program is designed to actively engage high school students and their teachers in Mars exploration and scientific inquiry. In ASIP, groups of students and teachers from around the country work with mentors from the mission s Athena Science Team to carry out an aspect of the mission.

Field Quality Study of a 1-m-Long Single-Aperture 11-T Nb$$_3$$Sn Dipole Model for LHC Upgrades

DOE Office of Scientific and Technical Information (OSTI.GOV)

Chlachidze, G.; DiMarco, J.; Andreev, N.

2014-01-01

FNAL and CERN are carrying out a joint R&D program with the goal of building a 5.5-m-long twin-aperture 11-T Nb_3Sn dipole prototype that is suitable for installation in the LHC. An important part of the program is the development and test of a series of short single-aperture and twin-aperture dipole models with a nominal field of 11 T at the LHC operation current of 11.85 kA and 20% margin. This paper presents the results of magnetic measurements of a 1-m-long single-aperture Nb_3Sn dipole model fabricated and tested recently at FNAL, including geometrical field harmonics and effects of coil magnetization andmore » iron yoke saturation.« less

Multivisceral Transplantation Rehabilitation Program-Case Report.

PubMed

Loschi, T M; Cinacchi, M P R G; Baccan, M D T A; Marques, F; Pedroso, P T; Meira Filho, S P; Scacchetti, T; Pavão, D N

2018-04-01

Multivisceral transplantation is the treatment for multiple abdominal organ failure. The patient experiences reduced food intake and absorption of nutrients, contributing to weight loss and decreased muscle mass, reducing functional capacity. A physical and nutritional rehabilitation program based on adequate caloric intake associated with supervised physical exercise seems to support a gain of muscle mass, re-establishing its capacity and functional independence. A rehabilitation program was carried out, consisting of low-intensity aerobic exercise on treadmill, exercises of global strengthening (50% of 1 maximum repetition [1RM], with progressive increase), and nutritional monitoring (oral hypercaloric diet, hyperproteic supplementation daily and after exercise). Initial and final evaluation included weight, muscle mass index, brachial circumference (BC), tricipital cutaneous fold (TCF), hand grip strength (HGS), 6-minute walk test (6MWT), 1RM, vital capacity (VC), and respiratory muscle strength. After the program, functional capacity was evaluated through the 6MWT (92%), 1RM test, VC (55%), respiratory muscle strength, HGS at 5 kg, weight gain (4.75%), increase of BC in 2 cm, and TCF in 2 mm. The program contributed to functional independence, improved quality of life, and social reintegration, suggesting the importance of a supervised physical activity program associated with adequate nutritional intake after multivisceral transplantation. Copyright © 2018 Elsevier Inc. All rights reserved.

Feasibility and Efficacy of Mat Pilates on People with Mild-to-Moderate Parkinson's Disease: A Preliminary Study.

PubMed

Cancela, Jose Maria; Mollinedo Cardalda, Irimia; Ayán, Carlos; de Oliveira, Iris Machado

2018-04-01

This pilot study aimed at assessing the feasibility and efficacy of a Mat Pilates program in people with mild-to-moderate Parkinson's disease (PD). The participants carried out a Mat Pilates program twice a week for 12 weeks. The Senior Fitness Test battery and the 39-item PD Questionnaire were used to assess the effects of the program on the participants' fitness level and quality of life. A total of 16 patients with mild-to-moderate PD volunteered for and finished the study. The Mat Pilates program proved to be feasible. Adherence to the program was excellent, and no adverse effects were observed. The program had a positive effect on the participants' fitness levels, except for shoulder range of motion and dynamic balance, and on their quality of life. Assessments at follow-up indicated a regression in the improvements obtained by the end of the intervention, even though the sample still showed higher levels of fitness and quality of life than those tested at baseline. Mat Pilates is feasible and may be a beneficial rehabilitation strategy to improve fitness and quality of life in people with mild-to-moderate PD. Future randomized controlled trials might determine the extent of such benefits.

JaxoDraw: A graphical user interface for drawing Feynman diagrams

NASA Astrophysics Data System (ADS)

Binosi, D.; Theußl, L.

2004-08-01

JaxoDraw is a Feynman graph plotting tool written in Java. It has a complete graphical user interface that allows all actions to be carried out via mouse click-and-drag operations in a WYSIWYG fashion. Graphs may be exported to postscript/EPS format and can be saved in XML files to be used for later sessions. One of JaxoDraw's main features is the possibility to create ? code that may be used to generate graphics output, thus combining the powers of ? with those of a modern day drawing program. With JaxoDraw it becomes possible to draw even complicated Feynman diagrams with just a few mouse clicks, without the knowledge of any programming language. Program summaryTitle of program: JaxoDraw Catalogue identifier: ADUA Program summary URL:http://cpc.cs.qub.ac.uk/summaries/ADUA Program obtainable from: CPC Program Library, Queen's University of Belfast, N. Ireland Distribution format: tar gzip file Operating system: Any Java-enabled platform, tested on Linux, Windows ME, XP, Mac OS X Programming language used: Java License: GPL Nature of problem: Existing methods for drawing Feynman diagrams usually require some 'hard-coding' in one or the other programming or scripting language. It is not very convenient and often time consuming, to generate relatively simple diagrams. Method of solution: A program is provided that allows for the interactive drawing of Feynman diagrams with a graphical user interface. The program is easy to learn and use, produces high quality output in several formats and runs on any operating system where a Java Runtime Environment is available. Number of bytes in distributed program, including test data: 2 117 863 Number of lines in distributed program, including test data: 60 000 Restrictions: Certain operations (like internal latex compilation, Postscript preview) require the execution of external commands that might not work on untested operating systems. Typical running time: As an interactive program, the running time depends on the complexity of the diagram to be drawn.

Locatable-Body Temperature Monitoring Based on Semi-Active UHF RFID Tags

PubMed Central

Liu, Guangwei; Mao, Luhong; Chen, Liying; Xie, Sheng

2014-01-01

This paper presents the use of radio-frequency identification (RFID) technology for the real-time remote monitoring of body temperature, while an associated program can determine the location of the body carrying the respective sensor. The RFID chip's internal integrated temperature sensor is used for both the human-body temperature detection and as a measurement device, while using radio-frequency communication to broadcast the temperature information. The adopted RFID location technology makes use of reference tags together with a nearest neighbor localization algorithm and a multiple-antenna time-division multiplexing location system. A graphical user interface (GUI) was developed for collecting temperature and location data for the data fusion by using RFID protocols. With a puppy as test object, temperature detection and localization experiments were carried out. The measured results show that the applied method, when using a mercury thermometer for comparison in terms of measuring the temperature of the dog, has a good consistency, with an average temperature error of 0.283 °C. When using the associated program over the area of 12.25 m2, the average location error is of 0.461 m, which verifies the feasibility of the sensor-carrier location by using the proposed program. PMID:24675759

Locatable-body temperature monitoring based on semi-active UHF RFID tags.

PubMed

Liu, Guangwei; Mao, Luhong; Chen, Liying; Xie, Sheng

2014-03-26

This paper presents the use of radio-frequency identification (RFID) technology for the real-time remote monitoring of body temperature, while an associated program can determine the location of the body carrying the respective sensor. The RFID chip's internal integrated temperature sensor is used for both the human-body temperature detection and as a measurement device, while using radio-frequency communication to broadcast the temperature information. The adopted RFID location technology makes use of reference tags together with a nearest neighbor localization algorithm and a multiple-antenna time-division multiplexing location system. A graphical user interface (GUI) was developed for collecting temperature and location data for the data fusion by using RFID protocols. With a puppy as test object, temperature detection and localization experiments were carried out. The measured results show that the applied method, when using a mercury thermometer for comparison in terms of measuring the temperature of the dog, has a good consistency, with an average temperature error of 0.283 °C. When using the associated program over the area of 12.25 m2, the average location error is of 0.461 m, which verifies the feasibility of the sensor-carrier location by using the proposed program.

Bluetongue sentinel surveillance program and cross-sectional serological survey in cattle in Belgium in 2010-2011.

PubMed

Vangeel, I; De Leeuw, I; Méroc, E; Vandenbussche, F; Riocreux, F; Hooyberghs, J; Raemaekers, M; Houdart, P; Van der Stede, Y; De Clercq, K

2012-10-01

Bluetongue virus serotype 8 (BTV-8) emerged in Central Western Europe in 2006 causing a large scale epidemic in 2007 that involved several European Union (EU) countries including Belgium. As in several other EU member states, vaccination against BTV-8 with inactivated vaccines was initiated in Belgium in spring 2008 and appeared to be successful. Since 2009, no clinical cases of Bluetongue (BT) have been reported in Belgium and BTV-8 circulation seemed to have completely disappeared by spring 2010. Therefore, a series of repeated cross-sectional surveys, the BT sentinel surveillance program, based on virus detection in blood samples by means of real-time RT-PCR (RT-qPCR) were carried out in dairy cattle from the end of 2010 onwards with the aim to demonstrate the absence of BTV circulation in Belgium. This paper describes the results of the first two sampling rounds of this BT sentinel surveillance program carried out in October-November 2010 and January-February 2011. In addition, the level of BTV-specific maternal antibodies in young non-vaccinated animals was monitored and the level of herd immunity against BTV-8 after 3 consecutive years of compulsory BTV-8 vaccination was measured by ELISA. During the 1st sampling round of the BT sentinel surveillance program, 15 animals tested positive and 2 animals tested doubtful for BTV RNA by RT-qPCR. During the 2nd round, 17 animals tested positive and 5 animals tested doubtful. The positive/doubtful animals in both rounds were re-sampled 2-4 weeks after the original sampling and then all tested negative by RT-qPCR. These results demonstrate the absence of BTV circulation in Belgium in 2010 at a minimum expected prevalence of 2% and 95% confidence level. The study of the maternal antibodies in non-vaccinated animals showed that by the age of 7 months maternal antibodies against BTV had disappeared in most animals. The BTV seroprevalence at herd level after 3 years of compulsory BTV-8 vaccination was very high (97.4% [95% CI: 96.2-98.2]). The overall true within-herd BTV seroprevalence in 6-24 month old Belgian cattle in early 2011 was estimated at 73.4% (95% CI: 71.3-75.4). Copyright © 2012 Elsevier B.V. All rights reserved.

Isotherm Sensor Calibration Program for Mars Science Laboratory Heat Shield Flight Data Analysis

NASA Technical Reports Server (NTRS)

Santos, Jose A.; Oishi, Tomo; Martinez, Ed R.

2011-01-01

Seven instrumented sensor plugs were installed on the Mars Science Laboratory heat shield in December 2008 as part of the Mars Science Laboratory Entry, Descent, and Landing Instrumentation (MEDLI) project. These sensor plugs contain four in-depth thermocouples and one Hollow aErothermal Ablation and Temperature (HEAT) sensor. The HEAT sensor follows the time progression of a 700 C isotherm through the thickness of a thermal protection system (TPS) material. The data can be used to infer char depth and, when analyzed in conjunction with the thermocouple data, the thermal gradient through the TPS material can also be determined. However, the uncertainty on the isotherm value is not well defined. To address this uncertainty, a team at NASA Ames Research Center is carrying out a HEAT sensor calibration test program. The scope of this test program is described, and initial results from experiments conducted in the laboratory to study the isotherm temperature of the HEAT sensor are presented. Data from the laboratory tests indicate an isotherm temperature of 720 C 60 C. An overview of near term arc jet testing is also given, including preliminary data from 30.48cm 30.48cm PICA panels instrumented with two MEDLI sensor plugs and tested in the NASA Ames Panel Test Facility. Forward work includes analysis of the arc jet test data, including an evaluation of the isotherm value based on the instant in time when it reaches a thermocouple depth.

A novel virtual motor rehabilitation system for Guillain-Barré syndrome. Two single case studies.

PubMed

Albiol-Pérez, S; Forcano-García, M; Muñoz-Tomás, M T; Manzano-Fernández, P; Solsona-Hernández, S; Mashat, M A; Gil-Gómez, J A

2015-01-01

This article is part of the Focus Theme of Methods of Information in Medicine on "New Methodologies for Patients Rehabilitation". For Guillain-Barré patients, motor rehabilitation programs are helpful at the onset to prevent the complications of paralysis and in cases of persistent motor impairment. Traditional motor rehabilitation programs may be tedious and monotonous, resulting in low adherence to the treatments. A Virtual Motor Rehabilitation system has been tested in Guillain-Barré patients to increase patient adherence and to improve clinical results. Two people with Guillain-Barré performed 20 rehabilitation sessions. We tested a novel system based on Motor Virtual Rehabilitation in three periods of time (baseline evaluation, final evaluation, and follow-up. In the training program, the participants carried out a specific treatment using the Active Balance Rehabilitation system (ABAR). The system is composed of customizable virtual games to perform static and dynamic balance rehabilitation. Significant improvements in clinical results were obtained by both participants, with significant results in the static balance clinical test of the Anterior Reach test in the standing position and unipedal stance time. Other significant results were found in dynamic balance clinical tests in the Berg Balance Scale test and the 30-second Sit-to-Stand test. With regard to acceptance of the system, both patients enjoyed the experience, and both patients thought that this system was helpful for their rehabilitation. The results show that Virtual Motor Rehabilitation for Guillain-Barré patients provides clinical improvements in an entertaining way.

Damage tolerance certification of a fighter horizontal stabilizer

NASA Astrophysics Data System (ADS)

Huang, Jia-Yen; Tsai, Ming-Yang; Chen, Jong-Sheng; Ong, Ching-Long

1995-05-01

A review of the program for the damage tolerance certification test of a composite horizontal stabilizer (HS) of a fighter is presented. The object of this program is to certify that the fatigue life and damage tolerance strength of a damaged composite horizontal stabilizer meets the design requirements. According to the specification for damage tolerance certification, a test article should be subjected to two design lifetimes of flight-by-flight load spectra simulating the in-service fatigue loading condition for the aircraft. However, considering the effect of environmental change on the composite structure, one additional lifetime test was performed. In addition, to evaluate the possibilities for extending the service life of the structure, one more lifetime test was carried out with the spectrum increased by a factor of 1.4. To assess the feasibility and reliability of repair technology on a composite structure, two damaged areas were repaired after two lifetimes of damage tolerance test. On completion of four lifetimes of the damage tolerance test, the static residual strength was measured to check whether structural strength after repair met the requirements. Stiffness and static strength of the composite HS with and without damage were evaluated and compared.

KSC-2009-5342

NASA Image and Video Library

2009-10-06

CAPE CANAVERAL, Fla. – A banner inside NASA Kennedy Space Center's Vehicle Assembly Building captures the excitement building at Kennedy in anticipation of the flight test of the Ares I-X rocket, towering above it in High Bay 3. Part of the Constellation Program, the Ares I-X is the test vehicle for the Ares I, which is the essential core of a space transportation system designed to carry crewed missions back to the moon, on to Mars and out into the solar system. The Ares I-X flight test is targeted for Oct. 27. For information on the Ares I-X vehicle and flight test, visit http://www.nasa.gov/mission_pages/constellation/ares/flighttests/aresIx/index.html. Photo credit: NASA/Glenn Benson

Thermal-environmental testing of a 30-cm engineering model thruster

NASA Technical Reports Server (NTRS)

Mirtich, M. J.

1976-01-01

An experimental test program was carried out to document all 30-cm electron bombardment Hg ion bombardment thruster functions and characteristics over the thermal environment of several proposed missions. An engineering model thruster was placed in a thermal test facility equipped with -196 C walls and solar simulation. The thruster was cold soaked and exposed to simulated eclipses lasting in duration from 17 to 72 minutes. The thruster was operated at quarter, to full beam power in various thermal configurations which simulated multiple thruster operation, and was also exposed to 1 and 2 suns solar simulation. Thruster control characteristics and constraints; performance, including thrust magnitude and direction; and structural integrity were evaluated over the range of thermal environments tested.

Thermal-environment testing of a 30-cm engineering model thruster

NASA Technical Reports Server (NTRS)

Mirtich, M. J.

1976-01-01

An experimental test program was carried out to document all 30-cm electron bombardment Hg ion bombardment thruster functions and characteristics over the thermal environment of several proposed missions. An engineering model thruster was placed in a thermal test facility equipped with -196 C walls and solar simulation. The thruster was cold soaked and exposed to simulated eclipses lasting in duration from 17 to 72 minutes. The thruster was operated at quarter, to full beam power in various thermal configurations which simulated multiple thruster operation, and was also exposed to 1 and 2 suns solar simulation. Thruster control characteristics and constraints; performance, including thrust magnitude and direction; and structural integrity were evaluated over the range of thermal environments tested.

The Nature of Ultraluminous Galaxies: Infrared Space Observatory Analysis and Instrument Team

NASA Technical Reports Server (NTRS)

Satyapal, Shobita

2001-01-01

The scientific goal of the proposed research was to investigate the physical conditions in the nuclear regions of infrared luminous galaxies by carrying out detailed infrared spectroscopic observations of a large sample of infrared luminous galaxies. During the past year, these observations have been successfully analyzed and extensive modeling using photoionization and photodissociation codes has been carried out. Two first-author publications and a second-author publication have been submitted to the Astrophysical Journal and results were presented at two invited talks. Four additional journal papers are in preparation and will be submitted during year 2 of the grant. The secondary project included in this program was the development of a near-infrared cryogenic Fabry-Perot interferometer for use on future large aperture telescopes. System integration and room temperature testing was successfully carried out for this project during year 1.

34 CFR 676.18 - Use of funds.

Code of Federal Regulations, 2010 CFR

2010-07-01

... end of the award year that it transferred to the FSEOG program from the FWS program. (c) Carry forward funds. (1) An institution may carry forward and expend in the next award year up to 10 percent of the... institution may spend its current year FSEOG allocation, it must spend any funds carried forward from the...

Advanced multi-megawatt wind turbine design for utility application

NASA Technical Reports Server (NTRS)

Pijawka, W. C.

1984-01-01

A NASA/DOE program to develop a utility class multimegawatt wind turbine, the MOD-5A, is described. The MOD-5A features a 400 foot diameter rotor which is teetered and positioned upwind of the tower; a 7.3 megawatt power rating with a variable speed electric generating system; and a redundant rotor support and torque transmission structure. The rotor blades were fabricated from an epoxy-bonded wood laminate material which was a successful outgrowth of the MOD-OA airfoil design. Preliminary data from operational tests carried out at the NASA Plumbrook test facility are presented.

KSC-2009-2559

NASA Image and Video Library

2009-04-08

CAPE CANAVERAL, Fla. – The mockup Orion crew exploration vehicle is lowered into the water at the Trident Basin at Port Canaveral, Fla., for testing in open water. The goal of the operation, dubbed the Post-landing Orion Recovery Test, or PORT, is to determine what kind of motion astronauts can expect after landing, as well as outside conditions for recovery teams. Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. Orion, along with the Ares I and V rockets and the Altair lunar lander, are part of the Constellation Program. Photo credit: NASA/Kim Shiflett

KSC-2009-2557

NASA Image and Video Library

2009-04-08

CAPE CANAVERAL, Fla. – The mockup Orion crew exploration vehicle is on the dock at the Trident Basin at Port Canaveral, Fla., waiting to be tested in open water. The goal of the operation, dubbed the Post-landing Orion Recovery Test, or PORT, is to determine what kind of motion astronauts can expect after landing, as well as outside conditions for recovery teams. Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. Orion, along with the Ares I and V rockets and the Altair lunar lander, are part of the Constellation Program. Photo credit: NASA/Kim Shiflett

KSC-2009-2550

NASA Image and Video Library

2009-04-08

CAPE CANAVERAL, Fla. – The mockup Orion crew exploration vehicle is on the dock at the Trident Basin at Port Canaveral, Fla., waiting to be tested in open waters. Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. The goal of the operation, dubbed the Post-landing Orion Recovery Test, or PORT, is to determine what kind of motion astronauts can expect after landing, as well as outside conditions for recovery teams. Orion, along with the Ares I and V rockets and the Altair lunar lander, are part of the Constellation Program. Photo credit: NASA/Dimitri Gerondidakis

KSC-2009-2552

NASA Image and Video Library

2009-04-08

CAPE CANAVERAL, Fla. – The mockup Orion crew exploration vehicle is lowered toward the water at the Trident Basin at Port Canaveral, Fla., for testing. Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. The goal of the operation, dubbed the Post-landing Orion Recovery Test, or PORT, is to determine what kind of motion astronauts can expect after landing, as well as outside conditions for recovery teams. Orion, along with the Ares I and V rockets and the Altair lunar lander, are part of the Constellation Program. Photo credit: NASA/Dimitri Gerondidakis

KSC-2009-2553

NASA Image and Video Library

2009-04-08

CAPE CANAVERAL, Fla. – The mockup Orion crew exploration vehicle is lowered into the water at the Trident Basin at Port Canaveral, Fla., for testing. Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. The goal of the operation, dubbed the Post-landing Orion Recovery Test, or PORT, is to determine what kind of motion astronauts can expect after landing, as well as outside conditions for recovery teams. Orion, along with the Ares I and V rockets and the Altair lunar lander, are part of the Constellation Program. Photo credit: NASA/Dimitri Gerondidakis

KSC-2009-2551

NASA Image and Video Library

2009-04-08

CAPE CANAVERAL, Fla. – The mockup Orion crew exploration vehicle is prepared to be lifted into the water at the Trident Basin at Port Canaveral, Fla., for testing. Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. The goal of the operation, dubbed the Post-landing Orion Recovery Test, or PORT, is to determine what kind of motion astronauts can expect after landing, as well as outside conditions for recovery teams. Orion, along with the Ares I and V rockets and the Altair lunar lander, are part of the Constellation Program. Photo credit: NASA/Dimitri Gerondidakis

Advanced multi-megawatt wind turbine design for utility application

NASA Astrophysics Data System (ADS)

Pijawka, W. C.

1984-08-01

A NASA/DOE program to develop a utility class multimegawatt wind turbine, the MOD-5A, is described. The MOD-5A features a 400 foot diameter rotor which is teetered and positioned upwind of the tower; a 7.3 megawatt power rating with a variable speed electric generating system; and a redundant rotor support and torque transmission structure. The rotor blades were fabricated from an epoxy-bonded wood laminate material which was a successful outgrowth of the MOD-OA airfoil design. Preliminary data from operational tests carried out at the NASA Plumbrook test facility are presented.

High-pressure hydrogen testing of single crystal superalloys for advanced rocket engine turbopump turbine blades

NASA Technical Reports Server (NTRS)

Alter, W. S.; Parr, R. A.; Johnston, M. H.; Strizak, J. P.

1984-01-01

A screening program to determine the effects of high pressure hydrogen on selected candidate materials for advanced single crystal turbine blade applications is examined. The alloys chosen for the investigation are CM SX-2, CM SX-4C, Rene N-4, and PWA1480. Testing is carried out in hydrogen and helium at 34 MPa and room temperature, with both notched and unnotched single crystal specimens. Results show a significant variation in susceptibility to Hydrogen Environment Embrittlement (HEE) among the four alloys and a marked difference in fracture topography between hydrogen and helium environment specimens.

Medical Support and Findings of the Skylab Program

NASA Technical Reports Server (NTRS)

Johnston, Richard S.; Dietlein, Lawrence F.

1975-01-01

Specific equipment used in carrying out Skylab medical experiments is outlined and illustrated. Also included are reviews of the techniques, frequency, and protocols of the tests designed to study the long term effects of weightlessness on the human body. In-flight investigations were an evaluation of the cardiovascular system, a study of metabolic activity, investigations in the field of neurophysiology, the determination of changes in body fluids, a precise measurement of total body metabolism, and a study of crew performance by use of a time and motion experiment. Significant data obtained from in-flight and postflight tests are outlined.

Bio-media Citizenship and Chronic Kidney Disease of Unknown Etiology in Sri Lanka.

PubMed

de Silva, M W Amarasiri

2018-04-01

In this article, I examine the crucial role of the biomedical industry, epidemiological and biomedical research, and the media in forming attitudes to and the understanding of chronic kidney disease of unknown etiology (CKDu) in Sri Lanka. Local conceptions of CKDu have been shaped by the circulation in the media of epidemiological research findings pertaining to the disease, biomedical interventions in the management of the disease in hospitals and clinics, community programs involving mass blood surveys and the testing of well water, and local food and health education programs carried out through village health committees. This process of circulation I identify as bio-media citizenship.

Orion Versus Poseidon: Understanding How Nasa's Crewed Capsule Survives Nature's Fury

NASA Technical Reports Server (NTRS)

Barbre, Robert E., Jr.

2016-01-01

This presentation summarizes the Marshall Space Flight Center Natural Environments Terrestrial and Planetary Environments (TPE) Team support to the NASA Orion space vehicle. The Orion vehicle, part of the Multi-Purpose Crew Vehicle Program, is designed to carry astronauts beyond low-Earth orbit and is currently undergoing a series of tests including Exploration Flight Test (EFT)-1. This design must address the natural environment to which the capsule and launch vehicle are exposed during all mission phases. In addition, the design must, to the best extent possible, implement the same process and data to be utilized on launch day. The TPE utilizes meteorological data to assess the sensitivities of the vehicle due to the terrestrial environment. The presentation describes examples of TPE support for vehicle design and several tests, as well as support for EFT-1 and planning for upcoming Exploration Missions while emphasizing the importance of accounting for the natural environment's impact to the vehicle early in the vehicle's program.

Validation study and routine control monitoring of moist heat sterilization procedures.

PubMed

Shintani, Hideharu

2012-06-01

The proposed approach to validation of steam sterilization in autoclaves follows the basic life cycle concepts applicable to all validation programs. Understand the function of sterilization process, develop and understand the cycles to carry out the process, and define a suitable test or series of tests to confirm that the function of the process is suitably ensured by the structure provided. Sterilization of product and components and parts that come in direct contact with sterilized product is the most critical of pharmaceutical processes. Consequently, this process requires a most rigorous and detailed approach to validation. An understanding of the process requires a basic understanding of microbial death, the parameters that facilitate that death, the accepted definition of sterility, and the relationship between the definition and sterilization parameters. Autoclaves and support systems need to be designed, installed, and qualified in a manner that ensures their continued reliability. Lastly, the test program must be complete and definitive. In this paper, in addition to validation study, documentation of IQ, OQ and PQ concretely were described.

Alternative Approach to Vehicle Element Processing

NASA Technical Reports Server (NTRS)

Huether, Jacob E.; Otto, Albert E.

1995-01-01

The National Space Transportation Policy (NSTP), describes the challenge facing today's aerospace industry. 'Assuring reliable and affordable access to space through U.S. space transportation capabilities is a fundamental goal of the U.S. space program'. Experience from the Space Shuttle Program (SSP) tells us that launch and mission operations are responsible for approximately 45 % of the cost of each shuttle mission. Reducing these costs is critical to NSTP goals in the next generation launch vehicle. Based on this, an innovative alternative approach to vehicle element processing was developed with an emphasis on reduced launch costs. State-of-the-art upgrades to the launch processing system (LPS) will enhance vehicle ground operations. To carry this one step further, these upgrade could be implemented at various vehicle element manufacturing sites to ensure system compatibility between the manufacturing facility and the launch site. Design center vehicle stand alone testing will ensure system integrity resulting in minimized checkout and testing at the launch site. This paper will addresses vehicle test requirements, timelines and ground checkout procedures which enable concept implementation.

Computer system design description for SY-101 hydrogen mitigation test project data acquisition and control system (DACS-1)

DOE Office of Scientific and Technical Information (OSTI.GOV)

Ermi, A.M.

1997-05-01

Description of the Proposed Activity/REPORTABLE OCCURRENCE or PIAB: This ECN changes the computer systems design description support document describing the computers system used to control, monitor and archive the processes and outputs associated with the Hydrogen Mitigation Test Pump installed in SY-101. There is no new activity or procedure associated with the updating of this reference document. The updating of this computer system design description maintains an agreed upon documentation program initiated within the test program and carried into operations at time of turnover to maintain configuration control as outlined by design authority practicing guidelines. There are no new crediblemore » failure modes associated with the updating of information in a support description document. The failure analysis of each change was reviewed at the time of implementation of the Systems Change Request for all the processes changed. This document simply provides a history of implementation and current system status.« less

Effects of supportive-educative program on quality of life of adolescents living with a parent with cancer.

PubMed

Azarbarzin, Mehrdad; Malekian, Azadeh; Taleghani, Fariba

2015-01-01

Cancer has significant traumatic effects on the family members of the patients, particularly in Asia's tightly knitted families. Research evidence suggests a debilitating impact of cancer on the quality of life of the afflicted individuals, their spouses, and their families. Since a few studies have been carried out on the quality of life of adolescents living with parents diagnosed with cancer, especially in Iran, the research team decided to evaluate the quality of life of them and also investigate the effects of supportive-educative program on it. The present quasi-experimental, one-group study had a pre-test-post-test design and was performed in Esfahan in 2014. The sample of this study consisted of 30 adolescents. The data gathering tool was the short form of quality of life questionnaire (SF-36). Data were analyzed by descriptive statistics and paired sample t-test. P-value of 0.05 was considered significant. The paired sample t-test showed that before and after presenting the program, there were significant statistical differences in some aspects of quality of life, such as physical functioning (P = 0.01), energy/fatigue (P < 0.0001), emotional well-being (P < 0.0001), social functioning (P = 0.001), pain (P < 0.0001), and general health (P = 0.01). This research showed that supportive-educative program can enhance some aspects of quality of life. Therefore, nurses and other health professionals can use this scheme or similar programs for helping adolescents living with a parent with cancer.

Development and Testing of the Orion CEV Parachute Assembly System (CPAS)

NASA Technical Reports Server (NTRS)

Lichodziejewski, David; Taylor, Anthony P.; Sinclair, Robert; Olmstead, Randy; Kelley, Christopher; Johnson, Justin; Melgares, Michael; Morris, Aaron; Bledsoe, Kristin

2009-01-01

The Crew Exploration Vehicle (CEV) is an element of the Constellation Program that includes launch vehicles, spacecraft, and ground systems needed to embark on a robust space exploration program. As an anchoring capability of the Constellation Program, the CEV shall be human-rated and will carry human crews and cargo from Earth into space and back again. Coupled with transfer stages, landing vehicles, and surface exploration systems, the CEV will serve as an essential component of the architecture that supports human voyages to the Moon and beyond. In addition, the CEV will be modified, as required, to support International Space Station (ISS) mission requirements for crewed and pressurized cargo configurations. Headed by Johnson Space Center (JSC), NASA selected Jacobs Engineering as the support contractor to manage the overall CEV Parachute Assembly System (CPAS) program development. Airborne Systems was chosen to develop the parachute system components. General Dynamics Ordnance and Tactical Systems (GD-OTS) was subcontracted to Airborne Systems to provide the mortar systems. Thus the CPAS development team of JSC, Jacobs, Airborne Systems and GD-OTS was formed. The CPAS team has completed the first phase, or Generation I, of the design, fabrication, and test plan. This paper presents an overview of the CPAS program including system requirements and the development of the second phase, known as the Engineering Development Unit (EDU) architecture. We also present top level results of the tests completed to date. A significant number of ground and flight tests have been completed since the last CPAS presentation at the 2007 AIAA ADS Conference.

The hydrodynamic model testing for closed loop DP assisted mooring

DOE Office of Scientific and Technical Information (OSTI.GOV)

Aalbers, A.B.; Merchant, A.A.

1996-12-31

Far East Levingston Shipbuilding (FELS) is presently completing the construction of the Smedvig Production Unit SPU 380, which will be operated as FPSO for Esso Balder Field Offshore Norway. In good cooperation with FELS and ND and A Inc. of Houston an extensive model test program was carried out for approval and optimization of the DP assisted mooring system. The main aspects were: investigate the performance of the mooring in two water depths, i.e. 250 m and 70 m; optimization of DP control for the three azimuthing thrusters; measurement of motions and wave induced loads at e.g., the bilge keels,more » keel and deckhouse front; and determination of limit sea state for turning the vessel around against the weather. The tests were carried out in the Wave and Current Basin of MARIN, using a closed loop DP control system to steer the thrusters. The paper presents the findings with respect to the effect of DP control strategy on mooring loads and presents selected results of wave induced loads on bilge keels and deck house.« less

An experimental investigation of rubbing interaction in labyrinth seals at cryogenic temperature

NASA Technical Reports Server (NTRS)

Dolan, F. X.; Kennedy, F. E.; Schulson, E. M.

1985-01-01

An experimental program was carried out to address issues related to the observed cracking of the titanium knife edges on the labyrinth seals of the high pressure fuel pump (HPFP) in the Space Shuttle main engine (SSME). Thermal shock experiments were carried out using a jet specimen with geometry similar to the knife edge geometry. These tests demonstrate that cracking of the titanium alloy is possible in a situation involving repeated thermal cycles over a wide temperature range, as might be realized during a rub in the liquid hydrogen fuel pump. High speed rub interaction tests were conducted using a representative knife edge and seal geometry over a broad range of interaction rates. Alternative materials were also experimentally evaluated. These tests provide information which can be used to design improved labyrinth seals for the HPFP of the SSME. In particular, plasma-sprayed aluminum-graphite was found to be significantly better than aluminum alloy seals used at present from the standpoint of rub performance. Ion nitriding of the titanium alloy knife edges was also found to improve rub performance compared with the untreated baseline knife edge material.

KSC-2009-2561

NASA Image and Video Library

2009-04-08

CAPE CANAVERAL, Fla. – Flotation devices are attached to the top of the mockup Orion crew exploration vehicle before the testing in the open water at the Trident Basin at Port Canaveral, Fla. The mockup vehicle will undergo testing in open water. The goal of the operation, dubbed the Post-landing Orion Recovery Test, or PORT, is to determine what kind of motion astronauts can expect after landing, as well as outside conditions for recovery teams. Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. Orion, along with the Ares I and V rockets and the Altair lunar lander, are part of the Constellation Program. Photo credit: NASA/Kim Shiflett

KSC-2009-2506

NASA Image and Video Library

2009-04-02

CAPE CANAVERAL, Fla. – On display at the Kennedy Space Center Visitor Complex in Florida is the Orion crew exploration vehicle mockup, which will be moved onto the center before heading offshore to be tested in open water. The spacecraft mock-up traveled from the Naval Surface Warfare Center's Carderock Division in Bethesda, Md. The goal of the open water testing, dubbed the Post-landing Orion Recovery Test, or PORT, is to determine what kind of motion astronauts can expect after landing, as well as outside conditions for recovery teams. Part of the Constellation Program, Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. Photo credit: NASA/Jack Pfaller

KSC-2009-2503

NASA Image and Video Library

2009-04-02

CAPE CANAVERAL, Fla. – Visitors to the Visitor Complex at NASA's Kennedy Space Center in Florida get a look at the Orion crew exploration vehicle mockup, which is on display before heading offshore to be tested in open water. The spacecraft mock-up traveled from the Naval Surface Warfare Center's Carderock Division in Bethesda, Md. The goal of the open water testing, dubbed the Post-landing Orion Recovery Test, or PORT, is to determine what kind of motion astronauts can expect after landing, as well as outside conditions for recovery teams. Part of the Constellation Program, Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. Photo credit: NASA/Jack Pfaller

KSC-2009-2560

NASA Image and Video Library

2009-04-08

CAPE CANAVERAL, Fla. – Members of the 920th Rescue Wing help prepare the mockup Orion crew exploration vehicle for testing in the open water at the Trident Basin at Port Canaveral, Fla. The mockup vehicle will undergo testing in open water. The goal of the operation, dubbed the Post-landing Orion Recovery Test, or PORT, is to determine what kind of motion astronauts can expect after landing, as well as outside conditions for recovery teams. Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. Orion, along with the Ares I and V rockets and the Altair lunar lander, are part of the Constellation Program. Photo credit: NASA/Kim Shiflett

Orion Flight Test Preview Briefing

NASA Image and Video Library

2014-11-06

In the Kennedy Space Center’s Press Site auditorium, members of the news media are briefed on the upcoming Orion flight test by Bill Hill, NASA deputy associate administrator for Exploration Systems Development. Mark Geyer, NASA Orion Program manager, is on the right. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch Dec. 4, 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket.

Solar tests of aperture plate materials for solar thermal dish collectors

NASA Technical Reports Server (NTRS)

Jaffe, L. D.

1983-01-01

In parabolic dish solar collectors, walk-off of the spot of concentrated sunlight is a hazard if a malfunction causes the concentrator to stop following the Sun. Therefore, a test program was carried out to evaluate the behavior of various ceramics, metals, and polymers under solar irradiation of about 7000 kW/sq m. (peak) for 15 minutes. The only materials that did not slump or shatter were two grades of medium-grain extruded graphite. High purity, slip-cast silica might be satisfactory at somewhat lower flux. Oxidation of the graphite appeared acceptable during tests simulating walk-off, acquisition (2000 cycles on/off Sun), and spillage (continuous on-Sun operation).

DOE Office of Scientific and Technical Information (OSTI.GOV)

Sterndorff, M.J.; O`Brien, P.

ROLF (Retrievable Offshore Loading Facility) has been proposed as an alternative offshore oil export tanker loading system for the North Sea. The system consists of a flexible riser ascending from the seabed in a lazy wave configuration to the bow of a dynamically positioned tanker. In order to supplant and support the numerical analyses performed to design the system, an extensive model test program was carried out in a 3D offshore basin at scale 1:50. A model riser with properties equivalent to the properties of the oil filled prototype riser installed in seawater was tested in several combinations of wavesmore » and current. During the tests the forces at the bow of the tanker and at the pipeline end manifold were measured together with the motions of the tanker and the riser. The riser motions were measured by means of a video based 3D motion monitoring system. Of special importance was accurate determination of the minimum bending radius for the riser. This was derived based on the measured riser motions. The results of the model tests were compared to numerical analyses by an MCS proprietary riser analysis program.« less

Blade System Design Study. Part II, final project report (GEC).

DOE Office of Scientific and Technical Information (OSTI.GOV)

Griffin, Dayton A.

2009-05-01

As part of the U.S. Department of Energy's Low Wind Speed Turbine program, Global Energy Concepts LLC (GEC)1 has studied alternative composite materials for wind turbine blades in the multi-megawatt size range. This work in one of the Blade System Design Studies (BSDS) funded through Sandia National Laboratories. The BSDS program was conducted in two phases. In the Part I BSDS, GEC assessed candidate innovations in composite materials, manufacturing processes, and structural configurations. GEC also made recommendations for testing composite coupons, details, assemblies, and blade substructures to be carried out in the Part II study (BSDS-II). The BSDS-II contract periodmore » began in May 2003, and testing was initiated in June 2004. The current report summarizes the results from the BSDS-II test program. Composite materials evaluated include carbon fiber in both pre-impregnated and vacuum-assisted resin transfer molding (VARTM) forms. Initial thin-coupon static testing included a wide range of parameters, including variation in manufacturer, fiber tow size, fabric architecture, and resin type. A smaller set of these materials and process types was also evaluated in thin-coupon fatigue testing, and in ply-drop and ply-transition panels. The majority of materials used epoxy resin, with vinyl ester (VE) resin also used for selected cases. Late in the project, testing of unidirectional fiberglass was added to provide an updated baseline against which to evaluate the carbon material performance. Numerous unidirectional carbon fabrics were considered for evaluation with VARTM infusion. All but one fabric style considered suffered either from poor infusibility or waviness of fibers combined with poor compaction. The exception was a triaxial carbon-fiberglass fabric produced by SAERTEX. This fabric became the primary choice for infused articles throughout the test program. The generally positive results obtained in this program for the SAERTEX material have led to its being used in innovative prototype blades of 9-m and 30-m length, as well as other non-wind related structures.« less

Electroacoustic dewatering of food and other suspensions

DOE Office of Scientific and Technical Information (OSTI.GOV)

Kim, B.C.; Zelinski, M.S.; Criner, C.L.

1989-05-31

The food processing industry is a large user of energy for evaporative drying due to limited effectiveness of conventional mechanical dewatering machines. Battelle's Electroacoustic Dewatering (EAD) process improves the performance of mechanical dewatering machines by superimposing electric and ultrasonic fields. A two phase development program to demonstrate the benefits of EAD was carried out in cooperation with the food processing industry, the National Food Processors Association (NFPA) and two equipment vendors. In Phase I, laboratory scale studies were carried out on a variety of food suspensions. The process was scaled up to small commercial scale in Phase II. The technicalmore » feasibility of EAD for a variety of food materials, without adversely affecting the food properties, was successfully demonstrated during this phase, which is the subject of this report. Two Process Research Units (PRUs) were designed and built through joint efforts between Battelle and two equipment vendors. A 0.5-meter wide belt press was tested on apple mash, corn fiber, and corn gluten at sites provided by two food processors. A high speed citrus juice finisher (a hybrid form of screw press and centrifuge) was tested on orange pulp. These tests were carried out jointly by Battelle, equipment vendors, NFPA, and food processors. The apple and citrus juice products were analyzed by food processors and NFPA. 26 figs., 30 tabs.« less

A continuing program for technology transfer to the apparel industry

NASA Technical Reports Server (NTRS)

Clingman, W. H.

1971-01-01

A six month program has been carried out to investigate various mechanisms for transferring technology to industry. This program has focused on transfer to the apparel industry through the Apparel Research Foundation. The procedure was to analyze the problem, obtain potentially relevant aerospace technology, and then transfer this technology to the industry organization. This was done in a specific case. Technology was identified relevant to stitchless joining, and this technology was transferred to the Apparel Research Foundation. The feasibility and ground rules for carrying out such activities on a broader scale were established. A specific objective was to transfer new technology from the industry organization to the industry itself. This required the establishment of an application engineering program. Another transfer mechanism tested was publication of solutions to industry problems in a format familiar to the industry. This is to be distinguished from circulating descriptions of new technology. Focus is on the industry problem and the manager is given a formula for solving it that he can follow. It was concluded that this mechanism can complement the problem statement approach to technology transfer. It is useful in achieving transfer when a large amount of application engineering is not necessary. A wide audience is immediately exposed to the technology. On the other hand, the major manufacturing problems which require a sophisticated technical solution integrating many innovations are less likely to be helped.

Near-Term Electric Vehicle Program. Phase II: Mid-Term Summary Report.

DOE Office of Scientific and Technical Information (OSTI.GOV)

None

1978-08-01

The Near Term Electric Vehicle (NTEV) Program is a constituent elements of the overall national Electric and Hybrid Vehicle Program that is being implemented by the Department of Energy in accordance with the requirements of the Electric and Hybrid Vehicle Research, Development, and Demonstration Act of 1976. Phase II of the NTEV Program is focused on the detailed design and development, of complete electric integrated test vehicles that incorporate current and near-term technology, and meet specified DOE objectives. The activities described in this Mid-Term Summary Report are being carried out by two contractor teams. The prime contractors for these contractormore » teams are the General Electric Company and the Garrett Corporation. This report is divided into two discrete parts. Part 1 describes the progress of the General Electric team and Part 2 describes the progress of the Garrett team.« less

An Inquiry-Based Microbiology Short Course in the SUMS Program at Hartnell College

NASA Astrophysics Data System (ADS)

Dorighi, K. M.; Petrella, L.; McCann, S.; Metevier, A. J.

2010-12-01

In this paper, we describe our design and implementation of inquiry-based biology units for the Summer Undergraduate Math and Science (SUMS) program at Hartnell College. The SUMS bridge program is designed to encourage local minority students with unrealized potential to enter and excel in Math and Science college curricula. The inquiry activities we designed prompted students to investigate where bacteria live in the students' environment and how effective different cleaning products are at killing these bacteria. These investigations required students to create their own testable questions and design and carry out experiments to test them. By the end of the program the students demonstrated a command of the scientific method and reported feeling like real scientists. While this unit was taught in four consecutive days, it could easily be translated to a more traditional weekly college lab schedule.

Post-game analysis: An initial experiment for heuristic-based resource management in concurrent systems

NASA Technical Reports Server (NTRS)

Yan, Jerry C.

1987-01-01

In concurrent systems, a major responsibility of the resource management system is to decide how the application program is to be mapped onto the multi-processor. Instead of using abstract program and machine models, a generate-and-test framework known as 'post-game analysis' that is based on data gathered during program execution is proposed. Each iteration consists of (1) (a simulation of) an execution of the program; (2) analysis of the data gathered; and (3) the proposal of a new mapping that would have a smaller execution time. These heuristics are applied to predict execution time changes in response to small perturbations applied to the current mapping. An initial experiment was carried out using simple strategies on 'pipeline-like' applications. The results obtained from four simple strategies demonstrated that for this kind of application, even simple strategies can produce acceptable speed-up with a small number of iterations.

75 FR 36120 - Proposed Information Collection Request Submitted for Public Comment and Recommendations; Program...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-06-24

... Submitted for Public Comment and Recommendations; Program To Prevent Smoking Underground and in Hazardous... Act), 30 U.S.C. 877(c), and 30 CFR 75.1702 prohibit persons from smoking or carrying smoking materials... mine operators are required to develop programs to prevent persons from carrying smoking materials...

Mutual coupling effects in antenna arrays, volume 1

NASA Technical Reports Server (NTRS)

Collin, R. E.

1986-01-01

Mutual coupling between rectangular apertures in a finite antenna array, in an infinite ground plane, is analyzed using the vector potential approach. The method of moments is used to solve the equations that result from setting the tangential magnetic fields across each aperture equal. The approximation uses a set of vector potential model functions to solve for equivalent magnetic currents. A computer program was written to carry out this analysis and the resulting currents were used to determine the co- and cross-polarized far zone radiation patterns. Numerical results for various arrays using several modes in the approximation are presented. Results for one and two aperture arrays are compared against published data to check on the agreement of this model with previous work. Computer derived results are also compared against experimental results to test the accuracy of the model. These tests of the accuracy of the program showed that it yields valid data.

Operational plans for life science payloads - From experiment selection through postflight reporting

NASA Technical Reports Server (NTRS)

Mccollum, G. W.; Nelson, W. G.; Wells, G. W.

1976-01-01

Key features of operational plans developed in a study of the Space Shuttle era life science payloads program are presented. The data describes the overall acquisition, staging, and integration of payload elements, as well as program implementation methods and mission support requirements. Five configurations were selected as representative payloads: (a) carry-on laboratories - medical emphasis experiments, (b) mini-laboratories - medical/biology experiments, (c) seven-day dedicated laboratories - medical/biology experiments, (d) 30-day dedicated laboratories - Regenerative Life Support Evaluation (RLSE) with selected life science experiments, and (e) Biomedical Experiments Scientific Satellite (BESS) - extended duration primate (Type I) and small vertebrate (Type II) missions. The recommended operational methods described in the paper are compared to the fundamental data which has been developed in the life science Spacelab Mission Simulation (SMS) test series. Areas assessed include crew training, experiment development and integration, testing, data-dissemination, organization interfaces, and principal investigator working relationships.

[The effects of an environmental education with newspaper in education (NIE) on the environmental concern and practice].

PubMed

Sung, Ki-Wol

2008-12-01

The purpose of this study was to develop an environmental education program using newspaper articles in education (NIE) and to evaluate changes in concern and practice for environmental protection after NIE. The design was a nonequivalent control group pretest-posttest design. The participants were university students in nursing, of which 31 were assigned to the experimental group and 43 to the control group. The education was carried out for 2 hr, once a week for 7 weeks. Data were analyzed with SPSS WIN 14 program, and included chi2 test, independent t-test, and repeated measure ANOVA. NIE showed significant differences in the changes of attitude toward environment (F=4.461, p=.036). Findings suggest that this NIE in environmental education was effective in changing students' attitudes toward the environment. Therefore this NIE is recommended for inclusion in education for university students in nursing.

Winged cargo return vehicle. Volume 1: Conceptual design

NASA Technical Reports Server (NTRS)

1990-01-01

The Advanced Design Project (ADP) allows an opportunity for students to work in conjunction with NASA and other aerospace companies on NASA Advanced Design Projects. The following volumes represent the design report: Volume 1 Conceptual Design; Volume 2 Wind Tunnel Tests; Volume 3 Structural Analysis; and Volume 4 Water Tunnel Tests. The project chosen by the University of Minnesota in conjunction with NASA Marshall Space Flight Center for this year is a Cargo Return Vehicle (CRV) to support the Space Station Freedom. The vehicle is the third generation of vehicles to be built by NASA, the first two being the Apollo program, and the Space Shuttle program. The CRV is to work in conjunction with a personnel launch system (PLS) to further subdivide and specialize the vehicles that NASA will operate in the year 2000. The cargo return vehicle will carry payload to and from the Space Station Freedom (SSF).

Life review based on remembering specific positive events in active aging.

PubMed

Latorre, José M; Serrano, Juan P; Ricarte, Jorge; Bonete, Beatriz; Ros, Laura; Sitges, Esther

2015-02-01

The aim of this study is to evaluate the effectiveness of life review (LR) based on specific positive events in non-depressed older adults taking part in an active aging program. Fifty-five older adults were randomly assigned to an experimental group or an active control (AC) group. A six-session individual training of LR based on specific positive events was carried out with the experimental group. The AC group undertook a "media workshop" of six sessions focused on learning journalistic techniques. Pre-test and post-test measures included life satisfaction, depressive symptoms, experiencing the environment as rewarding, and autobiographical memory (AM) scales. LR intervention decreased depressive symptomatology, improved life satisfaction, and increased specific memories. The findings suggest that practice in AM for specific events is an effective component of LR that could be a useful tool in enhancing emotional well-being in active aging programs, thus reducing depressive symptoms. © The Author(s) 2014.

Magnetic Cleanliness Program Under Control of Electromagnetic Compatibility for the SELENE (Kaguya) Spacecraft

NASA Astrophysics Data System (ADS)

Matsushima, Masaki; Tsunakawa, Hideo; Iijima, Yu-Ichi; Nakazawa, Satoru; Matsuoka, Ayako; Ikegami, Shingo; Ishikawa, Tomoaki; Shibuya, Hidetoshi; Shimizu, Hisayoshi; Takahashi, Futoshi

2010-07-01

To achieve the scientific objectives related to the lunar magnetic field measurements in a polar orbit at an altitude of 100 km, strict electromagnetic compatibility (EMC) requirements were applied to all components and subsystems of the SELENE (Kaguya) spacecraft. The magnetic cleanliness program was defined as one of the EMC control procedures, and magnetic tests were carried out for most of the engineering and flight models. The EMC performance of all components was systematically controlled and examined through a series of EMC tests. As a result, the Kaguya spacecraft was made to be very clean, magnetically. Hence reliable scientific data related to the magnetic field around the Moon were obtained by the LMAG (Lunar MAGnetometer) and the PACE (Plasma energy Angle and Composition Experiment) onboard the Kaguya spacecraft. These data have been available for lunar science use since November 2009.

Testing and Analytical Modeling for Purging Process of a Cryogenic Line

NASA Technical Reports Server (NTRS)

Hedayat, A.; Mazurkivich, P. V.; Nelson, M. A.; Majumdar, A. K.

2013-01-01

The purging operations for cryogenic main propulsion systems of upper stage are usually carried out for the following cases: 1) Purging of the Fill/Drain line after completion of propellant loading. This operation allows the removal of residual propellant mass; and 2) Purging of the Feed/Drain line if the mission is scrubbed. The lines would be purged by connections to a ground high-pressure gas storage source. The flowrate of purge gas should be regulated such that the pressure in the line will not exceed the required maximum allowable value. Exceeding the maximum allowable pressure may lead to structural damage in the line. To gain confidence in analytical models of the purge process, a test series was conducted. The test article, a 20-cm incline line, was filled with liquid hydrogen and then purged with gaseous helium (GHe). The influences of GHe flowrates and initial temperatures were evaluated. The Generalized Fluid System Simulation Program, an in-house general-purpose computer program for flow network analysis, was utilized to model and simulate the testing. The test procedures, modeling descriptions, and the results will be presented in the final paper.

Testing and Analytical Modeling for Purging Process of a Cryogenic Line

NASA Technical Reports Server (NTRS)

Hedayat, A.; Mazurkivich, P. V.; Nelson, M. A.; Majumdar, A. K.

2015-01-01

The purging operations for cryogenic main propulsion systems of upper stage are usually carried out for the following cases: 1) Purging of the Fill/Drain line after completion of propellant loading. This operation allows the removal of residual propellant mass; and 2) Purging of the Feed/Drain line if the mission is scrubbed. The lines would be purged by connections to a ground high-pressure gas storage source. The flow-rate of purge gas should be regulated such that the pressure in the line will not exceed the required maximum allowable value. Exceeding the maximum allowable pressure may lead to structural damage in the line. To gain confidence in analytical models of the purge process, a test series was conducted. The test article, a 20-cm incline line, was filled with liquid hydrogen and then purged with gaseous helium (GHe). The influences of GHe flow-rates and initial temperatures were evaluated. The Generalized Fluid System Simulation Program, an in-house general-purpose computer program for flow network analysis, was utilized to model and simulate the testing. The test procedures, modeling descriptions, and the results will be presented in the final paper.

Free Enterprise: Contributions of the Approach and Landing Test (ALT) Program to the Development of the Space Shuttle Orbiter

NASA Technical Reports Server (NTRS)

Merlin, Peter W.

2006-01-01

The space shuttle orbiter was the first spacecraft designed with the aerodynamic characteristics and in-atmosphere handling qualities of a conventional airplane. In order to evaluate the orbiter's flight control systems and subsonic handling characteristics, a series of flight tests were undertaken at NASA Dryden Flight Research Center in 1977. A modified Boeing 747 Shuttle Carrier Aircraft carried the Enterprise, a prototype orbiter, during eight captive tests to determine how well the two vehicles flew together and to test some of the orbiter s systems. The free-flight phase of the ALT program allowed shuttle pilots to explore the orbiter's low-speed flight and landing characteristics. The Enterprise provided realistic, in-flight simulations of how subsequent space shuttles would be flown at the end of an orbital mission. The fifth free flight, with the Enterprise landing on a concrete runway for the first time, revealed a problem with the space shuttle flight control system that made it susceptible to pilot-induced oscillation, a potentially dangerous control problem. Further research using various aircraft, particularly NASA Dryden's F-8 Digital-Fly-By-Wire testbed, led to correction of the problem before the first Orbital Test Flight.

The combined use of heat-pulse flowmeter logging and packer testing for transmissive fracture recognition

NASA Astrophysics Data System (ADS)

Lo, Hung-Chieh; Chen, Po-Jui; Chou, Po-Yi; Hsu, Shih-Meng

2014-06-01

This paper presents an improved borehole prospecting methodology based on a combination of techniques in the hydrogeological characterization of fractured rock aquifers. The approach is demonstrated by on-site tests carried out in the Hoshe Experimental Forest site and the Tailuge National Park, Taiwan. Borehole televiewer logs are used to obtain fracture location and distribution along boreholes. The heat-pulse flow meter log is used to measure vertical velocity flow profiles which can be analyzed to estimate fracture transmissivity and to indicate hydraulic connectivity between fractures. Double-packer hydraulic tests are performed to determine the rock mass transmissivity. The computer program FLASH is used to analyze the data from the flowmeter logs. The FLASH program is confirmed as a useful tool which quantitatively predicts the fracture transmissivity in comparison to the hydraulic properties obtained from packer tests. The location of conductive fractures and their transmissivity is identified, after which the preferential flow paths through the fracture network are precisely delineated from a cross-borehole test. The results provide robust confirmation of the use of combined flowmeter and packer methods in the characterization of fractured-rock aquifers, particularly in reference to the investigation of groundwater resource and contaminant transport dynamics.

Development of website for studying modern physics

NASA Astrophysics Data System (ADS)

Saehana, S.; Wahyono, U.; Darmadi, I. W.; Kendek, Y.; Widyawati, W.

2018-03-01

The purpose of this study is to produce a website in modern physics courses in order to increase student interest in physics learning. To determine the feasibility level of learning media then feasibility test to the product. The feasibility test carried out on the product is divided into three parts: material feasibility test, media feasibility test, and student response test. Based on the results of the test conducted the material obtained an average score of 3.72 and categorized very well. The result of media test that was obtained got the average score of 3.25 and categorized well. The result of the analysis of student's response to the twenty students of class A (fifth semester) of physics education program FKIP UniversitasTadulako obtained an average score of 3.16 with the good category. The results showed that the website developed can be used as one of the learning media that can support the learning process of students.

Fine urban and precursor emissions control for diesel urban transit buses.

PubMed

Lanni, Thomas

2003-01-01

Particulate emission from diesel engines is one of the most important pollutants in urban areas. As a result, particulate emission control from urban bus diesel engines using particle filter technology is being evaluated at several locations in the US. A project entitled "Clean Diesel Air Quality Demonstration Program" has been initiated by the New York City Metropolitan Transit Authority (MTA) under the supervision of New York State Department of Environmental Conservation and with active participation from Johnson Matthey, Corning, Equilon, Environment Canada and RAD Energy. Under this program, several MTA transit buses with DDC Series 50 engines were equipped with Continuously Regenerating Technology (CRTTM) particulate filter systems and have been operated with ultra low sulfur diesel (<30 ppm S) in transit service in Manhattan since February 2000. These buses were evaluated over a 9-month period for durability and maintainability of the particulate filter. In addition, an extensive emissions testing program was carried out using transient cycles on a chassis dynamometer to evaluate the emissions reductions obtained with the particle filter. In this paper, the emissions testing data from the Clean Diesel Air Quality Demonstration Program are discussed in detail.

Effectiveness of a first-aid intervention program applied by undergraduate nursing students to preparatory school children.

PubMed

Wafik, Wagida; Tork, Hanan

2014-03-01

Childhood injuries constitute a major public health problem worldwide. First aid is an effective life-preservation tool at work, school, home, and in public locations. In this study, the effectiveness of a first-aid program delivered by undergraduate nursing students to preparatory school children was examined. This quasi-experimental study was carried out on 100 school children in governmental preparatory schools in Egypt. The researchers designed a program for first-aid training, and this was implemented by trained nursing students. The evaluation involved immediate post-test and follow-up assessment after two months. The results showed generally low levels of satisfactory knowledge and inadequate situational practice among the school students before the intervention. Statistically-significant improvements were shown at the post- and follow-up tests. Multivariate regression analysis identified the intervention and the type of school as the independent predictors of the change in students' knowledge score, while the intervention and the knowledge score were the predictors of the practice score. The study concluded that a first-aid training program delivered by nursing students to preparatory school children is effective in improving their knowledge and practice. © 2013 Wiley Publishing Asia Pty Ltd.

Processing eutectics in space

NASA Technical Reports Server (NTRS)

Douglas, F. C.; Galasso, F. S.

1974-01-01

Studies which have been done in an earth-based laboratory environment have generally not yielded specimens with the degree of perfection required of the eutectic microstructure to provide test data to evaluate their nonstructural applications. It has been recognized that the low-g environment of an orbiting space laboratory provides a unique environment to re-examine the process of solidification with the goal of producing better microstructures. The objective of this program is to evaluate the feasibility of using the space environment for producing eutectics with microstructures which can be of value on earth. In carrying out this objective, evaluative investigations were carried out on the technology of solidification in a 1-g environment to provide sound baseline data for planning space laboratory experiments.

Ground crewmen help guide the alignment of the X-40A as the experimental craft is gently lowered to

NASA Technical Reports Server (NTRS)

2000-01-01

Ground crewmen help guide the alignment of the X-40 technology demonstrator as the experimental craft is gently lowered to the ground by a U.S. Army CH-47 Chinook cargo helicopter following a captive-carry test flight at NASA's Dryden Flight Research Center, Edwards, California. The X-40 is an unpowered 82 percent scale version of the X-37, a Boeing-developed spaceplane designed to demonstrate various advanced technologies for development of future lower-cost access to space vehicles. The X-37 will be carried into space aboard a space shuttle and then released to perform various maneuvers and a controlled re-entry through the Earth's atmosphere to an airplane-style landing on a runway, controlled entirely by pre-programmed computer software. Following a series of captive-carry flights, the X-40 made several free flights from a launch altitude of about 15,000 feet above ground, gliding to a fully autonomous landing. The captive carry flights helped verify the X-40's navigation and control systems, rigging angles for its sling, and stability and control of the helicopter while carrying the X-40 on a tether.

Permutation tests for goodness-of-fit testing of mathematical models to experimental data.

PubMed

Fişek, M Hamit; Barlas, Zeynep

2013-03-01

This paper presents statistical procedures for improving the goodness-of-fit testing of theoretical models to data obtained from laboratory experiments. We use an experimental study in the expectation states research tradition which has been carried out in the "standardized experimental situation" associated with the program to illustrate the application of our procedures. We briefly review the expectation states research program and the fundamentals of resampling statistics as we develop our procedures in the resampling context. The first procedure we develop is a modification of the chi-square test which has been the primary statistical tool for assessing goodness of fit in the EST research program, but has problems associated with its use. We discuss these problems and suggest a procedure to overcome them. The second procedure we present, the "Average Absolute Deviation" test, is a new test and is proposed as an alternative to the chi square test, as being simpler and more informative. The third and fourth procedures are permutation versions of Jonckheere's test for ordered alternatives, and Kendall's tau(b), a rank order correlation coefficient. The fifth procedure is a new rank order goodness-of-fit test, which we call the "Deviation from Ideal Ranking" index, which we believe may be more useful than other rank order tests for assessing goodness-of-fit of models to experimental data. The application of these procedures to the sample data is illustrated in detail. We then present another laboratory study from an experimental paradigm different from the expectation states paradigm - the "network exchange" paradigm, and describe how our procedures may be applied to this data set. Copyright © 2012 Elsevier Inc. All rights reserved.

A constitutive model and numerical simulation of sintering processes at macroscopic level

NASA Astrophysics Data System (ADS)

Wawrzyk, Krzysztof; Kowalczyk, Piotr; Nosewicz, Szymon; Rojek, Jerzy

2018-01-01

This paper presents modelling of both single and double-phase powder sintering processes at the macroscopic level. In particular, its constitutive formulation, numerical implementation and numerical tests are described. The macroscopic constitutive model is based on the assumption that the sintered material is a continuous medium. The parameters of the constitutive model for material under sintering are determined by simulation of sintering at the microscopic level using a micro-scale model. Numerical tests were carried out for a cylindrical specimen under hydrostatic and uniaxial pressure. Results of macroscopic analysis are compared against the microscopic model results. Moreover, numerical simulations are validated by comparison with experimental results. The simulations and preparation of the model are carried out by Abaqus FEA - a software for finite element analysis and computer-aided engineering. A mechanical model is defined by the user procedure "Vumat" which is developed by the first author in Fortran programming language. Modelling presented in the paper can be used to optimize and to better understand the process.

Spectroscopic investigations using density functional theory on 2-methoxy- 4(phenyliminomethyl)phenol: A non linear optical material

NASA Astrophysics Data System (ADS)

Hijas, K. M.; Madan Kumar, S.; Byrappa, K.; Geethakrishnan, T.; Jeyaram, S.; Nagalakshmi, R.

2018-03-01

Single crystals of 2-methoxy-4(phenyliminomethyl)phenol were grown from ethanol by slow evaporation solution growth technique. Single crystal X-ray diffraction experiment reveals the crystallization in orthorhombic system having non-centrosymmetric space group C2221. Geometrical optimization by density functional theory method was carried out using Gaussian program and compared with experimental results. Detailed experimental and theoretical vibrational analyses were carried out and the results were correlated to find close agreement. Thermal analyses show the material is thermally stable with a melting point of 159 °C. Natural bond orbital analysis was carried out to explain charge transfer interactions through hydrogen bonding. Relatively smaller HOMO-LUMO band gap favors the non linear optical activity of the molecule. Natural population analysis and molecular electrostatic potential calculations visualize the charge distribution in an isolated molecule. Calculated first-order molecular hyperpolarizability and preliminary second harmonic generation test carried out using Kurtz-Perry technique establish 2-methoxy-4(phenyliminomethyl)phenol crystal as a good non linear optical material. Z-scan proposes the material for reverse saturable absorption.

Durability Tests of Ball Valve Prototype with Flowmeter Operation

NASA Astrophysics Data System (ADS)

Rogula, J.; Romanik, G.

2018-02-01

The results of the investigation of the prototypical ball valve are presented in this article. The innovation of the tested valve is a ball with a built-in measuring orifice. The valve has been subjected to durability tests. Leakage under three temperatures: ambient, -30°C and +100°C was analyzed. Sealing elements of the valve were tested for roughness and deviation of shape before and after the cycles of operation. Ball valve operation means cycles of open/close. It was planned to perform 1000 cycles at each temperature condition accordingly. Tests of the valve were performed under gas pressure equal to 10 MPa. The research was carried out under the Operational Program "Intelligent Development" (POIR 01.01.01-00-0013 / 15 "Development of devices for measurement of media flow on industrial trunk-lines".

The comparative effectiveness of a team-based versus group-based physical activity intervention for cancer survivors.

PubMed

Carter, Cindy L; Onicescu, Georgiana; Cartmell, Kathleen B; Sterba, Katherine R; Tomsic, James; Alberg, Anthony J

2012-08-01

Physical activity benefits cancer survivors, but the comparative effectiveness of a team-based delivery approach remains unexplored. The hypothesis tested was that a team-based physical activity intervention delivery approach has added physical and psychological benefits compared to a group-based approach. A team-based sport accessible to survivors is dragon boating, which requires no previous experience and allows for diverse skill levels. In a non-randomized trial, cancer survivors chose between two similarly structured 8-week programs, a dragon boat paddling team (n = 68) or group-based walking program (n = 52). Three separate intervention rounds were carried out in 2007-2008. Pre-post testing measured physical and psychosocial outcomes. Compared to walkers, paddlers had significantly greater (all p < 0.01) team cohesion, program adherence/attendance, and increased upper-body strength. For quality-of-life outcomes, both interventions were associated with pre-post improvements, but with no clear-cut pattern of between-intervention differences. These hypothesis-generating findings suggest that a short-term, team-based physical activity program (dragon boat paddling) was associated with increased cohesion and adherence/attendance. Improvements in physical fitness and psychosocial benefits were comparable to a traditional, group-based walking program. Compared to a group-based intervention delivery format, the team-based intervention delivery format holds promise for promoting physical activity program adherence/attendance in cancer survivors.

Family leader empowerment program using participatory learning process for dengue vector control.

PubMed

Pengvanich, Veerapong

2011-02-01

Assess the performance of the empowerment program using participatory learning process for the control of Dengue vector The program focuses on using the leaders of families as the main executer of the vector control protocol. This quasi-experimental research utilized the two-group pretest-posttest design. The sample group consisted of 120 family leaders from two communities in Mueang Municipality, Chachoengsao Province. The research was conducted during an 8-week period between April and June 2010. The data were collected and analyzed based on frequency, percentage, mean, paired t-test, and independent t-test. The result was evaluated by comparing the difference between the mean prevalence index of mosquito larvae before and after the process implementation in terms of the container index (CI) and the house index (HI). After spending eight weeks in the empowerment program, the family leader's behavior in the aspect of Dengue vector control has improved. The Container Index and the House Index were found to decrease with p = 0.05 statistical significance. The reduction of CI and HI suggested that the program worked well in the selected communities. The success of the Dengue vector control program depended on cooperation and participation of many groups, especially the families in the community When the family leaders have good attitude and are capable of carrying out the vector control protocol, the risk factor leading to the incidence of Dengue rims infection can be reduced.

Massachusetts Beryllium Screening Program for Former Workers of Wyman-Gordon, Norton Abrasives, and MIT/Nuclear Metals

DOE Office of Scientific and Technical Information (OSTI.GOV)

Pepper, L. D.

2008-05-21

The overall objective of this project was to provide medical screening to former workers of Wyman-Gordon Company, Norton Abrasives, and MIT/Nuclear Metals (NMI) in order to prevent and minimize the health impact of diseases caused by site related workplace exposures to beryllium. The program was developed in response to a request by the U.S. Department of Energy (DOE) that had been authorized by Congress in Section 3162 of the 1993 Defense Authorization Act, urging the DOE to carry out a program for the identification and ongoing evaluation of current and former DOE employees who are subjected to significant health risksmore » during such employment." This program, funded by the DOE, was an amendment to the medical surveillance program for former DOE workers at the Nevada Test Site (NTS). This program's scope included workers who had worked for organizations that provided beryllium products or materials to the DOE as part of their nuclear weapons program. These organizations have been identified as Beryllium Vendors.« less

The Application of Problem-Based Learning in Mechanical Engineering

NASA Astrophysics Data System (ADS)

Putra, Z. A.; Dewi, M.

2018-02-01

The course of Technology and Material Testing prepare students with the ability to do a variety of material testing in the study of mechanical engineering. Students find it difficult to understand the materials to make them unable to carry out the material testing in accordance with the purpose of study. This happens because they knowledge is not adequately supported by the competence to find and construct learning experience. In this study, quasy experiment research method with pre-post-test with control group design was used. The subjects of the study were students divided in two groups; control and experiment with twenty-two students in each group. Study result: their grades showed no difference in between the pre-test or post-test in control group, but the difference in grade existed between the pre-test and post-test in experiment group. Yet, there is no significant difference in the study result on both groups. The researcher recommend that it is necessary to develop Problem-Based Learning that suits need analysis on D3 Program for Mechanical Engineering Department at the State University of Padang, to ensure the compatibility between Model of Study and problems and need. This study aims to analyze how Problem-Based Learning effects on the course of Technology and Material Testing for the students of D3 Program of Mechanical Engineering of the State University of Padang.

Design optimization of first wall and breeder unit module size for the Indian HCCB blanket module

NASA Astrophysics Data System (ADS)

Deepak, SHARMA; Paritosh, CHAUDHURI

2018-04-01

The Indian test blanket module (TBM) program in ITER is one of the major steps in the Indian fusion reactor program for carrying out the R&D activities in the critical areas like design of tritium breeding blankets relevant to future Indian fusion devices (ITER relevant and DEMO). The Indian Lead–Lithium Cooled Ceramic Breeder (LLCB) blanket concept is one of the Indian DEMO relevant TBM, to be tested in ITER as a part of the TBM program. Helium-Cooled Ceramic Breeder (HCCB) is an alternative blanket concept that consists of lithium titanate (Li2TiO3) as ceramic breeder (CB) material in the form of packed pebble beds and beryllium as the neutron multiplier. Specifically, attentions are given to the optimization of first wall coolant channel design and size of breeder unit module considering coolant pressure and thermal loads for the proposed Indian HCCB blanket based on ITER relevant TBM and loading conditions. These analyses will help proceeding further in designing blankets for loads relevant to the future fusion device.

A History of Satellite Reconnaissance. Volume 1. CORONA (REDACTED)

DTIC Science & Technology

1973-10-01

occurring in the Physics Research Lab, which had become more of an industrial research facility than a campus estab- lishment through the instrumentation...General Electric), and that spin stabilization had inherent disadvantages when BYE 17017-74 52 Handle via Byeman/Talent • Keyhole Controls Only —TOP...transfer to "other" ARPA programs. In the remainder, the first two were to be vehicle development tests, the next two were to carry mice , eight were to

Semiconductor millimeter wavelength electronics

NASA Astrophysics Data System (ADS)

Rosenbaum, F. J.

1985-12-01

This final report summarizes the results of research carried out on topics in millimeter wavelength semiconductor electronics under an ONR Selected Research Opportunity program. Study areas included III-V compound semiconductor growth and characterization, microwave and millimeter wave device modeling, fabrication and testing, and the development of new device concepts. A new millimeter wave mixer and detector, the Gap diode was invented. Topics reported on include ballistic transport, Zener oscillations, impurities in GaAs, electron velocity-electric field calculation and measurements, etc., calculations.

KSC-2009-3207

NASA Image and Video Library

2009-05-18

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building's high bay, technicians test how to put the "skins" on the outer mold of the simulator Orion crew module. Part of NASA's Constellation Program, the Orion spacecraft will return humans to the moon and prepare for future voyages to Mars and other destinations in our solar system. Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. Photo credit: NASA/Kim Shiflett

KSC-2009-3204

NASA Image and Video Library

2009-05-18

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building's high bay, technicians begin testing how to put the "skins" on the outer mold of the simulator Orion crew module.Part of NASA's Constellation Program, the Orion spacecraft will return humans to the moon and prepare for future voyages to Mars and other destinations in our solar system. Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. Photo credit: NASA/Kim Shiflett

KSC-2009-3208

NASA Image and Video Library

2009-05-18

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building's high bay, technicians test how to put the "skins" on the outer mold of the simulator Orion crew module. Part of NASA's Constellation Program, the Orion spacecraft will return humans to the moon and prepare for future voyages to Mars and other destinations in our solar system. Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. Photo credit: NASA/Kim Shiflett

Frequency of Usher syndrome in two pediatric populations: Implications for genetic screening of deaf and hard of hearing children.

PubMed

Kimberling, William J; Hildebrand, Michael S; Shearer, A Eliot; Jensen, Maren L; Halder, Jennifer A; Trzupek, Karmen; Cohn, Edward S; Weleber, Richard G; Stone, Edwin M; Smith, Richard J H

2010-08-01

Usher syndrome is a major cause of genetic deafness and blindness. The hearing loss is usually congenital and the retinitis pigmentosa is progressive and first noticed in early childhood to the middle teenage years. Its frequency may be underestimated. Newly developed molecular technologies can detect the underlying gene mutation of this disorder early in life providing estimation of its prevalence in at risk pediatric populations and laying a foundation for its incorporation as an adjunct to newborn hearing screening programs. A total of 133 children from two deaf and hard of hearing pediatric populations were genotyped first for GJB2/6 and, if negative, then for Usher syndrome. Children were scored as positive if the test revealed > or =1 pathogenic mutations in any Usher gene. Fifteen children carried pathogenic mutations in one of the Usher genes; the number of deaf and hard of hearing children carrying Usher syndrome mutations was 15/133 (11.3%). The population prevalence was estimated to be 1/6000. Usher syndrome is more prevalent than has been reported before the genome project era. Early diagnosis of Usher syndrome has important positive implications for childhood safety, educational planning, genetic counseling, and treatment. The results demonstrate that DNA testing for Usher syndrome is feasible and may be a useful addition to newborn hearing screening programs.

Frequency of Usher Syndrome in Two Pediatric Populations: Implications for genetic screening of Deaf and Hard of Hearing Children

PubMed Central

Kimberling, William J.; Hildebrand, Michael S.; Shearer, A. Eliot; Jensen, Maren L.; Halder, Jennifer A.; Cohn, Edward S.; Weleber, Richard G.; Stone, Edwin M.; Smith, Richard J. H.

2011-01-01

Purpose Usher syndrome is a major cause of genetic deafblindness. The hearing loss is usually congenital and the retinitis pigmentosa is progressive and first noticed in early childhood to the middle teenage years. Its frequency may be underestimated. Newly developed molecular technologies can detect the underlying gene mutation of this disorder early in life providing estimation of its prevalence in at risk pediatric populations and laying a foundation for its incorporation as an adjunct to newborn hearing screening programs. Methods A total of 133 children from two deaf and hard of hearing pediatric populations were genotyped first for GJB2/6 and, if negative, then for Usher syndrome. Children were scored as positive if the test revealed ≥1 pathogenic mutations in any Usher gene. Results Fifteen children carried pathogenic mutations in one of the Usher genes; the number of deaf and hard of hearing children carrying Usher syndrome mutations was 15/133 (11.3%). The population prevalence was estimated to be 1/6000. Conclusion Usher syndrome is more prevalent than has been reported prior to the genome project era. Early diagnosis of Usher syndrome has important positive implications for childhood safety, educational planning, genetic counseling, and treatment. The results demonstrate that DNA testing for Usher syndrome is feasible and may be a useful addition to newborn hearing screening programs. PMID:20613545

Health education to increase screening for cervical cancer among Lumbee Indian women in North Carolina.

PubMed

Dignan, M B; Michielutte, R; Wells, H B; Sharp, P; Blinson, K; Case, L D; Bell, R; Konen, J; Davis, S; McQuellon, R P

1998-12-01

Although age-adjusted mortality rates from cancer among Native-Americans are generally lower than for the US population as a whole, cervical cancer mortality rates are higher. This report presents results from a National Cancer Institute-funded health education program conducted among the Lumbee tribe in North Carolina that was designed to increase the proportion of women, age 18 and older, who receive Pap smears to screen for cervical cancer. The Solomon Four Group research design was used for this project. Participants were selected at random from the enrollment records of the Lumbee tribe and data collection was carried out during face-to-face interviews. The health education program was provided one-on-one in women's homes by a trained lay health educator and included verbal, print and videotape information. A total of 979 women were enrolled in the study, and 125 were lost to follow-up between the pre-test and post-test. Women who received the education program were found to be more likely to have knowledge of the Pap smear and to report a Pap smear in the past year at the post-test than those in the control group, regardless of whether they received the pre-test interview, P < 0.05. Women most likely to respond to the education program were also likely to have reported that they receive an annual physical examination. Women with better knowledge of the Pap smear tended to have more education, higher income and greater identification with Native-American culture than those with less knowledge. We conclude that the health education program was associated with greater knowledge about cervical cancer prevention and higher proportions of Lumbee women obtaining Pap smears in the past year.

Environmental test program for superconducting materials and devices

NASA Technical Reports Server (NTRS)

Haertling, Gene; Randolph, Henry; Hsi, Chi-Shiung; Verbelyi, Darren

1992-01-01

A systematic approach to obtaining real time, superconducting YBa2Cu30(7-x) materials is presented. The work was carried out under the overall direction of Clemson University with tasks being performed at both Clemson and Westinghouse (Aiken, SC). Clemson prepared the tapecast superconducting 123 material and fabricated in into substrate-supported, environmentally-protected conducting links. Following this, all of the elements were individually tested for resistance vs. temperature and Tc; and then a portion of them were kept at Clemson for further testing while a randomly selected group was delivered to Westinghouse for specialized testing and evaluation in their low temperature/high vacuum and radiation facilities. In addition, a number of control samples (12 ea.) were put on the shelf at Clemson for further reference at the end of the testing period. The specific tests conducted at Clemson and Westinghouse/SRC are presented with a summary of the results.

Orion Underway Recovery Test 5 (URT-5)

NASA Image and Video Library

2016-11-01

The USS San Diego approaches the coast of San Diego, California after completion of Underway Recovery Test 5 in the Pacific Ocean. NASA's Ground Systems Development and Operations Program and the U.S. Navy conducted a series of tests, called Underway Recovery Test 5, using the ship's well deck and a test version of the Orion crew module to prepare for recovery of Orion on its return from deep space missions. The testing allowed the team to demonstrate and evaluate recovery processes, procedures, hardware and personnel in open waters. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and NASA's Journey to Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. Orion is scheduled to launch on NASA's Space Launch System in late 2018. For more information, visit http://www.nasa.gov/orion.

Screening of redox couples and electrode materials

NASA Technical Reports Server (NTRS)

Giner, J.; Swette, L.; Cahill, K.

1976-01-01

Electrochemical parameters of selected redox couples that might be potentially promising for application in bulk energy storage systems were investigated. This was carried out in two phases: a broad investigation of the basic characteristics and behavior of various redox couples, followed by a more limited investigation of their electrochemical performance in a redox flow reactor configuration. In the first phase of the program, eight redox couples were evaluated under a variety of conditions in terms of their exchange current densities as measured by the rotating disk electrode procedure. The second phase of the program involved the testing of four couples in a redox reactor under flow conditions with a varity of electrode materials and structures.

Results of the 1996 JPL Balloon Flight Solar Cell Calibration Program

NASA Technical Reports Server (NTRS)

Anspaugh, B. E.; Weiss, R. S.

1996-01-01

The 1996 solar cell calibration balloon flight campaign was completed with the first flight on June 30, 1996 and a second flight on August 8, 1996. All objectives of the flight program were met. Sixty-four modules were carried to an altitude of 120,000 ft (36.6 km). Full 1-5 curves were measured on 22 of these modules, and output at a fixed load was measured on 42 modules. This data was corrected to 28 C and to 1 AU (1.496 x 10(exp 8) km). The calibrated cells have been returned to the participants and can now be used as reference standards in simulator testing of cells and arrays.

Neutronic Calculation Analysis for CN HCCB TBM-Set

NASA Astrophysics Data System (ADS)

Cao, Qixiang; Zhao, Fengchao; Zhao, Zhou; Wu, Xinghua; Li, Zaixin; Wang, Xiaoyu; Feng, Kaiming

2015-07-01

Using the Monte Carlo transport code MCNP, neutronic calculation analysis for China helium cooled ceramic breeder test blanket module (CN HCCB TBM) and the associated shield block (together called TBM-set) has been carried out based on the latest design of HCCB TBM-set and C-lite model. Key nuclear responses of HCCB TBM-set, such as the neutron flux, tritium production rate, nuclear heating and radiation damage, have been obtained and discussed. These nuclear performance data can be used as the basic input data for other analyses of HCCB TBM-set, such as thermal-hydraulics, thermal-mechanics and safety analysis. supported by the Major State Basic Research Development Program of China (973 Program) (No. 2013GB108000)

KSC-2009-2554

NASA Image and Video Library

2009-04-08

CAPE CANAVERAL, Fla. – The mockup Orion crew exploration vehicle floats in the water at the Trident Basin at Port Canaveral, Fla. Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. The mockup vehicle will undergo testing in open water. The goal of the operation, dubbed the Post-landing Orion Recovery Test, or PORT, is to determine what kind of motion astronauts can expect after landing, as well as outside conditions for recovery teams. Orion, along with the Ares I and V rockets and the Altair lunar lander, are part of the Constellation Program. Photo credit: NASA/Dimitri Gerondidakis

KSC-2009-2558

NASA Image and Video Library

2009-04-08

CAPE CANAVERAL, Fla. – The mockup Orion crew exploration vehicle is prepared to be lifted into the water at the Trident Basin at Port Canaveral, Fla., for testing in open water. The goal of the operation, dubbed the Post-landing Orion Recovery Test, or PORT, is to determine what kind of motion astronauts can expect after landing, as well as outside conditions for recovery teams. Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. Orion, along with the Ares I and V rockets and the Altair lunar lander, are part of the Constellation Program. Photo credit: NASA/Kim Shiflett

Computer simulation of thermal modeling of primary lithium cells

NASA Technical Reports Server (NTRS)

Young, I. Cho; Frank, Harvey; Halpert, Gersid

1987-01-01

The objective was to gain a better understanding of the safety problem of primary Li-SOCl2 and Li-SO2 cells by carrying out detailed thermal modeling work. In particular, the transient heat generation rates during moderate and extermely high discharge rate tests of Li-SOCl2 cells were predicted and compared with those from the electrochemical heating. The difference between the two may be attributed to the lithium corrosion and other chemical reactions. The present program was also tested for charging of Li-SO2. In addition, the present methodology should be applicable to other primary cylindrical cells as well as rechargeable battery analyses with minor modifications.

The DARWIN breadboard cryogenic optical delay line

NASA Astrophysics Data System (ADS)

van den Dool, T. C.; Gielesen, W.; Kamphues, F.; Loix, N.; Kooijman, P. P.; de Vries, C.; van Weers, H.; Fleury, K.; Stockman, Y.; Velsink, G.; Benoit, J.; Poupinet, A.; Sève, F.

2017-11-01

TNO, in cooperation with Micromega-Dynamics, SRON, Dutch Space and CSL, has designed a compact breadboard cryogenic delay line (figure 1) for use in future space interferometry missions. The work is performed under ESA contract 17.747/03 in preparation for the DARWIN mission. The breadboard (BB) delay line is representative of a flight mechanism. The delay line has a single stage voice coil actuator for Optical Path Difference (OPD) control, driving a twomirror cat's eye. Magnetic bearings provide frictionless and wear free operation with zero-hysteresis. The design of the BB delay line has been completed. The development test program, including operation at 100 K has been completed. The verification test programme is currently being carried out and will include functional testing at 40 K.

The effect of microstructure and strength on the fracture toughness of an 18 ni, 300 grade maraging steel

NASA Technical Reports Server (NTRS)

Psioda, J. A.; Low, J. R., Jr.

1974-01-01

Methods for increasing the strength of maraging steels are discussed. An investigation was conducted to systematically vary the strength of 18 weight percent nickel, 300 grade maraging steel, to isolate any attending microstructural changes, and to study the effects of these changes on the fracture toughness of the alloy. A study aimed at determining the aging behavior of the program alloy was carried out to provide data by which to estimate yield strength. The effects of various alloying materials on the strength of the maraging steel are examined. The mechanical properties of the 300 grade maraging steel were determined by tension tests, fatigue precracked Charpy impact tests, and plane strain fracture toughness tests.

VEGA Launch Vehicle Vibro-Acoustic Approach for Multi Payload Configuration Qualification

NASA Astrophysics Data System (ADS)

Bartoccini, D.; Di Trapani, C.; Fotino, D.; Bonnet, M.

2014-06-01

Acoustic loads are one of the principal source of structural vibration and internal noise during a launch vehicle flight but do not generally present a critical design condition for the main load-carrying structure. However, acoustic loads may be critical to the proper functioning of vehicle components and their supporting structures, which are otherwise lightly loaded. Concerning the VEGA program, in order to demonstrate VEGA Launch Vehicle (LV) on-ground qualification, prior to flight, to the acoustic load, the following tests have been performed: small-scale acoustic test intended for the determination of the acoustic loading of the LV and its nature and full-scale acoustic chamber test to determine the vibro-acoustic response of the structures as well as of the acoustic cavities.

KSC-2013-3016

NASA Image and Video Library

2013-05-30

Edwards, Calif. – ED13-161-35 - Sierra Nevada Corporation SNC Space Systems' team members tow the Dream Chaser flight vehicle out to a concrete runway at NASA's Dryden Flight Research Center in California for range and taxi tow tests. The ground testing will validate the performance of the spacecraft's nose skid, brakes, tires and other systems prior to captive-carry and free-flight tests scheduled for later this year. SNC is one of three companies working with NASA's Commercial Crew Program, or CCP, during the agency's Commercial Crew Integrated Capability, or CCiCap, initiative, which is intended to lead to the availability of commercial human spaceflight services for government and commercial customers. To learn more about CCP and its industry partners, visit www.nasa.gov/commercialcrew. Image credit: NASA/Ken Ulbrich

KSC-2013-3022

NASA Image and Video Library

2013-05-31

Edwards, Calif. – ED13-164-34 - Sierra Nevada Corporation SNC Space Systems' team members tow the Dream Chaser flight vehicle out to a concrete runway at NASA's Dryden Flight Research Center in California for range and taxi tow tests. The ground testing will validate the performance of the spacecraft's nose skid, brakes, tires and other systems prior to captive-carry and free-flight tests scheduled for later this year. SNC is one of three companies working with NASA's Commercial Crew Program, or CCP, during the agency's Commercial Crew Integrated Capability, or CCiCap, initiative, which is intended to lead to the availability of commercial human spaceflight services for government and commercial customers. To learn more about CCP and its industry partners, visit www.nasa.gov/commercialcrew. Image credit: NASA/Ken Ulbrich

KSC-2013-3021

NASA Image and Video Library

2013-05-31

Edwards, Calif. – ED13-164-34 - Sierra Nevada Corporation SNC Space Systems' team members tow the Dream Chaser flight vehicle out to a concrete runway at NASA's Dryden Flight Research Center in California for range and taxi tow tests. The ground testing will validate the performance of the spacecraft's nose skid, brakes, tires and other systems prior to captive-carry and free-flight tests scheduled for later this year. SNC is one of three companies working with NASA's Commercial Crew Program, or CCP, during the agency's Commercial Crew Integrated Capability, or CCiCap, initiative, which is intended to lead to the availability of commercial human spaceflight services for government and commercial customers. To learn more about CCP and its industry partners, visit www.nasa.gov/commercialcrew. Image credit: NASA/Ken Ulbrich

KSC-2013-3025

NASA Image and Video Library

2013-06-27

Edwards, Calif. – ED13-0215-072 - Sierra Nevada Corporation SNC Space Systems' team members tow the Dream Chaser flight vehicle along a concrete runway at NASA's Dryden Flight Research Center in California for range and taxi tow tests. The ground testing will validate the performance of the spacecraft's nose skid, brakes, tires and other systems prior to captive-carry and free-flight tests scheduled for later this year. SNC is one of three companies working with NASA's Commercial Crew Program, or CCP, during the agency's Commercial Crew Integrated Capability, or CCiCap, initiative, which is intended to lead to the availability of commercial human spaceflight services for government and commercial customers. To learn more about CCP and its industry partners, visit www.nasa.gov/commercialcrew. Image credit: NASA/Ken Ulbrich

KSC-2013-3020

NASA Image and Video Library

2013-05-31

Edwards, Calif. – ED13-164-33 - Sierra Nevada Corporation SNC Space Systems' team members tow the Dream Chaser flight vehicle out to a concrete runway at NASA's Dryden Flight Research Center in California for range and taxi tow tests. The ground testing will validate the performance of the spacecraft's nose skid, brakes, tires and other systems prior to captive-carry and free-flight tests scheduled for later this year. SNC is one of three companies working with NASA's Commercial Crew Program, or CCP, during the agency's Commercial Crew Integrated Capability, or CCiCap, initiative, which is intended to lead to the availability of commercial human spaceflight services for government and commercial customers. To learn more about CCP and its industry partners, visit www.nasa.gov/commercialcrew. Image credit: NASA/Ken Ulbrich

KSC-2013-3019

NASA Image and Video Library

2013-05-31

Edwards, Calif. – ED13-164-32 - Sierra Nevada Corporation SNC Space Systems' team members tow the Dream Chaser flight vehicle out to a concrete runway at NASA's Dryden Flight Research Center in California for range and taxi tow tests. The ground testing will validate the performance of the spacecraft's nose skid, brakes, tires and other systems prior to captive-carry and free-flight tests scheduled for later this year. SNC is one of three companies working with NASA's Commercial Crew Program, or CCP, during the agency's Commercial Crew Integrated Capability, or CCiCap, initiative, which is intended to lead to the availability of commercial human spaceflight services for government and commercial customers. To learn more about CCP and its industry partners, visit www.nasa.gov/commercialcrew. Image credit: NASA/Ken Ulbrich

Orion Flight Test Preview Briefing

NASA Image and Video Library

2014-11-06

In the Kennedy Space Center’s Press Site auditorium, members of the news media are briefed on the upcoming Orion flight test by Mark Geyer, NASA Orion Program manager. Also participating in the news conference are Bill Hill, NASA deputy associate administrator for Exploration Systems Development, left, and Bryan Austin, Lockheed Martin mission manager. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch Dec. 4, 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket.

Soil runway friction evaluation in support of USAF C-17 transport aircraft operations

NASA Technical Reports Server (NTRS)

Yager, Thomas J.

1995-01-01

A series of NASA Diagonal-Braked Vehicle (DBV) test runs were performed on the soil runway 7/25 at Holland landing zone, Fort Bragg, North Carolina, near Pope Air Force Base in March 1995 at the request of the Air Force C-17 System Program Office. These ground vehicle test results indicated that the dry runway friction level was suitable for planned C-17 transport aircraft landing and take-off operations at various gross weights. These aircraft operations were successfully carried out. On-board aircraft deceleration measurements were comparable to NASA DBV measurements. Additional tests conducted with an Army High Mobility Multi-Purpose Wheeled Vehicle equipped with a portable decelerometer, showed good agreement with NASA DBV data.

Overview of the 2006-2008 JOGMEC/NRCan/Aurora Mallik Gas Hydrate Production Test Program

NASA Astrophysics Data System (ADS)

Yamamoto, K.; Dallimore, S. R.

2008-12-01

During the winters of 2007 and 2008 the Japan Oil, Gas and Metals National Corporation (JOGMEC) and Natural Resources Canada (NRCan), with Aurora Research Institute as the operator, carried out an on-shore gas hydrate production test program at the Mallik site, Mackenzie Delta, Northwest Territories, Canada. The prime objective of the program was to verify the feasibility of depressurization technique by drawing down the formation pressure across a 12m perforated gas hydrate bearing section. This project was the second full scale production test at this site following the 2002 Japex/JNOC/GSC et al Mallik research program in which seven participants organizatinos from five countries undertook a thermal test using hot water circulation Field work in 2007 was devoted to establishing a production test well, installing monitoring devices outside of casing, conducting base line geophysical studies and undertaking a short test to gain practical experience prior to longer term testing planned for 2008 . Hydrate-dissociated gas was produced to surface by depressurization achieved by lowering the fluid level with a dowhole pump. However, the operation was terminated 60 hours after the start of the pumping mainly due to sand production problems. In spite of the short period (12.5 hours of ellapsed pumping time), at least 830m3 of the gas was produced and accumulated in the borehole. Sand screens were installed across the perforated interval at the bottom hole for the 2008 program to overcome operational problems encountered in 2007 and achieve sustainable gas production. Stable bottom hole flowing pressures were successfully achieved during a 6 day test with continuous pump operation. Sustained gas production was achieved with rates between 2000- 4000m3/day and cummulative gas volume in the surface of approximately 13,000m3. Temperature and pressure data measured at the bottom hole and gas and water production rates gave positive evidence for the high efficiency of gas production through depressurization method. Pre and post produciton testing geophysical logging program, geochemical analyses and monitoring tools outside of the casing also derived the supporting data for the formation responses to the depressurization. Acknowledgements: METI, MH21, JOGMEC and NRCan, Government of NWT, 2002 partners, IPM, R&D team members.

Improving balance, mobility, and dual-task performance in an adolescent with cerebral palsy: A case report.

PubMed

Fisher-Pipher, Sarah; Kenyon, Lisa K; Westman, Marci

2017-07-01

Improving functional mobility is often a desired outcome for adolescents with cerebral palsy (CP). Traditional neurorehabilitation approaches are frequently directed at impairments; however, improvements may not be carried over into functional mobility. The purpose of this case report was to describe the examination, intervention, and outcomes of a task-oriented physical therapy intervention program to improve dynamic balance, functional mobility, and dual-task performance in an adolescent with CP. The participant was a 15-year-old girl with spastic triplegic CP (Gross Motor Classification System Level II). Examination procedures included the Canadian Occupational Performance Measure, 6-minute walk test, Muscle Power Sprint Test, 10 x 5-meter sprint test, Timed Up and Down Stairs Test, Gross Motor Function Measure, Gillette Functional Assessment Questionnaire, and functional lower extremity strength tests. Intervention focused on task-oriented dynamic balance and mobility tasks that incorporated coordination and speed demands as well as task-specific lower extremity and trunk strengthening activities. Dual task demands were integrated into all intervention activities. Post-intervention testing revealed improvements in cardiovascular endurance, anaerobic power, agility, stair climbing, gross motor skills, and mobility. The participant appeared to benefit from a task-oriented program to improve dynamic balance, functional mobility, and dual-task performance.

Full-scale transmission testing to evaluate advanced lubricants

NASA Technical Reports Server (NTRS)

Lewicki, David G.; Decker, Harry J.; Shimski, John T.

1992-01-01

Experimental tests were performed on the OH-58A helicopter main rotor transmission in the NASA Lewis 500 hp helicopter transmission test stand. The testing was part of a lubrication program. The objectives are to develop and show a separate lubricant for gearboxes with improved performance in life and load carrying capacity. The goal was to develop a testing procedure to fail certain transmission components using a MIL-L-23699 based reference oil and then to run identical tests with improved lubricants and show improved performance. The tests were directed at parts that failed due to marginal lubrication from Navy field experience. These failures included mast shaft bearing micropitting, sun gear and planet bearing fatigue, and spiral bevel gear scoring. A variety of tests were performed and over 900 hrs of total run time accumulated for these tests. Some success was achieved in developing a testing procedure to produce sun gear and planet bearing fatigue failures. Only marginal success was achieved in producing mast shaft bearing micropitting and spiral bevel gear scoring.

Coping, stress, and personality in Spanish nursing students: A longitudinal study.

PubMed

Fornés-Vives, Joana; Garcia-Banda, Gloria; Frias-Navarro, Dolores; Rosales-Viladrich, Gerard

2016-01-01

The purpose of this study was to examine the dominant stress coping style in nursing students, its relationships with stressful life events and personality traits, and the students' changes during their academic training. A non-experimental two-wave longitudinal design was carried out in 199 nursing students recruited from three Spanish nursing schools. The Stressful Life Events Scale, NEO-FFI, and COPE questionnaire were administered at the beginning (T1) and end (T2) of their nursing studies. Descriptive statistics, Anova(s), NPar tests, and Pearson correlations were carried out. Results show that nursing students' dominant coping style was emotion-focused coping, both at T1 and T2. Highly significant correlations between emotional coping and the neuroticism trait were found. Coping, stress, and personality changed positively during the training program. At T2, the use of problem-focused strategies increased, and participants became more extroverted, agreeable, and conscientious. Coping and personality changes experienced by nursing students throughout their degree program seem to mirror the professional competences needed by future licensed nurses. Copyright © 2015 Elsevier Ltd. All rights reserved.

Study protocol: an early intervention program to improve motor outcome in preterm infants: a randomized controlled trial and a qualitative study of physiotherapy performance and parental experiences

PubMed Central

2012-01-01

Abstract Background Knowledge about early physiotherapy to preterm infants is sparse, given the risk of delayed motor development and cerebral palsy. Methods/Design A pragmatic randomized controlled study has been designed to assess the effect of a preventative physiotherapy program carried out in the neonatal intensive care unit. Moreover, a qualitative study is carried out to assess the physiotherapy performance and parents' experiences with the intervention. The aim of the physiotherapy program is to improve motor development i.e. postural control and selective movements in these infants. 150 infants will be included and randomized to either intervention or standard follow-up. The infants in the intervention group will be given specific stimulation to facilitate movements based on the individual infant's development, behavior and needs. The physiotherapist teaches the parents how to do the intervention and the parents receive a booklet with photos and descriptions of the intervention. Intervention is carried out twice a day for three weeks (week 34, 35, 36 postmenstrual age). Standardized tests are carried out at baseline, term age and at three, six, 12 and 24 months corrected age. In addition eight triads (infant, parent and physiotherapist) are observed and videotaped in four clinical encounters each to assess the process of physiotherapy performance. The parents are also interviewed on their experiences with the intervention and how it influences on the parent-child relationship. Eight parents from the follow up group are interviewed about their experience. The interviews are performed according to the same schedule as the standardized measurements. Primary outcome is at two years corrected age. Discussion The paper presents the protocol for a randomized controlled trial designed to study the effect of physiotherapy to preterm infants at neonatal intensive care units. It also studies physiotherapy performance and the parent's experiences with the intervention. Trial registration ClinicalTrials.gov NCT01089296 PMID:22336194

An atomistic geometrical model of the B-DNA configuration for DNA-radiation interaction simulations

NASA Astrophysics Data System (ADS)

Bernal, M. A.; Sikansi, D.; Cavalcante, F.; Incerti, S.; Champion, C.; Ivanchenko, V.; Francis, Z.

2013-12-01

In this paper, an atomistic geometrical model for the B-DNA configuration is explained. This model accounts for five organization levels of the DNA, up to the 30 nm chromatin fiber. However, fragments of this fiber can be used to construct the whole genome. The algorithm developed in this work is capable to determine which is the closest atom with respect to an arbitrary point in space. It can be used in any application in which a DNA geometrical model is needed, for instance, in investigations related to the effects of ionizing radiations on the human genetic material. Successful consistency checks were carried out to test the proposed model. Catalogue identifier: AEPZ_v1_0 Program summary URL:http://cpc.cs.qub.ac.uk/summaries/AEPZ_v1_0.html Program obtainable from: CPC Program Library, Queen’s University, Belfast, N. Ireland Licensing provisions: Standard CPC licence, http://cpc.cs.qub.ac.uk/licence/licence.html No. of lines in distributed program, including test data, etc.: 1245 No. of bytes in distributed program, including test data, etc.: 6574 Distribution format: tar.gz Programming language: FORTRAN. Computer: Any. Operating system: Multi-platform. RAM: 2 Gb Classification: 3. Nature of problem: The Monte Carlo method is used to simulate the interaction of ionizing radiation with the human genetic material in order to determine DNA damage yields per unit absorbed dose. To accomplish this task, an algorithm to determine if a given energy deposition lies within a given target is needed. This target can be an atom or any other structure of the genetic material. Solution method: This is a stand-alone subroutine describing an atomic-resolution geometrical model of the B-DNA configuration. It is able to determine the closest atom to an arbitrary point in space. This model accounts for five organization levels of the human genetic material, from the nucleotide pair up to the 30 nm chromatin fiber. This subroutine carries out a series of coordinate transformations to find which is the closest atom containing an arbitrary point in space. Atom sizes are according to the corresponding van der Waals radii. Restrictions: The geometrical model presented here does not include the chromosome organization level but it could be easily build up by using fragments of the 30 nm chromatin fiber. Unusual features: To our knowledge, this is the first open source atomic-resolution DNA geometrical model developed for DNA-radiation interaction Monte Carlo simulations. In our tests, the current model took into account the explicit position of about 56×106 atoms, although the user may enhance this amount according to the necessities. Running time: This subroutine can process about 2 million points within a few minutes in a typical current computer.

45 CFR 309.150 - What start-up costs are allowable for Tribal IV-D programs carried out under § 309.65(b) of this...

Code of Federal Regulations, 2010 CFR

2010-10-01

... 45 Public Welfare 2 2010-10-01 2010-10-01 false What start-up costs are allowable for Tribal IV-D... ENFORCEMENT (IV-D) PROGRAM Tribal IV-D Program Funding § 309.150 What start-up costs are allowable for Tribal IV-D programs carried out under § 309.65(b) of this part? Federal funds are available for costs of...

Including the Copenhagen Adduction Exercise in the FIFA 11+ Provides Missing Eccentric Hip Adduction Strength Effect in Male Soccer Players: A Randomized Controlled Trial.

PubMed

Harøy, Joar; Thorborg, Kristian; Serner, Andreas; Bjørkheim, André; Rolstad, Linn E; Hölmich, Per; Bahr, Roald; Andersen, Thor Einar

2017-11-01

The FIFA 11+ was developed as a complete warm-up program to prevent injuries in soccer players. Although reduced hip adduction strength is associated with groin injuries, none of the exercises included in the FIFA 11+ seem to specifically target hip adduction strength. To investigate the effect on eccentric hip adduction strength of the FIFA 11+ warm-up program with or without the Copenhagen adduction exercise. Randomized controlled trial; Level of evidence, 1. We recruited 45 eligible players from 2 U19 elite male soccer teams. Players were randomized into 2 groups; 1 group carried out the standard FIFA 11+ program, while the other carried out the FIFA 11+ but replaced the Nordic hamstring exercise with the Copenhagen adduction exercise. Both groups performed the intervention 3 times weekly for 8 weeks. Players completed eccentric strength and sprint testing before and after the intervention. Per-protocol analyses were performed, and 12 players were excluded due to low compliance (<67% of sessions completed). The main outcome was eccentric hip adduction strength (N·m/kg). Between-group analyses revealed a significantly greater increase in eccentric hip adduction strength of 0.29 Nm/kg (8.9%; P = .01) in favor of the group performing the Copenhagen adduction exercise, whereas no within-group change was noted in the group that used the standard FIFA 11+ program (-0.02 N·m/kg [-0.7%]; P = .69). Including the Copenhagen adduction exercise in the FIFA 11+ program increases eccentric hip adduction strength, while the standard FIFA 11+ program does not. Registration: Registration: ISRCTN13731446 (International Standard Randomised Controlled Trial Number registry).

A Fully Non-Metallic Gas Turbine Engine Enabled by Additive Manufacturing

NASA Technical Reports Server (NTRS)

Grady, Joseph E.; Halbig, Michael C.; Singh, Mrityunjay

2015-01-01

In a NASA Aeronautics Research Institute (NARI) sponsored program entitled "A Fully Non-Metallic Gas Turbine Engine Enabled by Additive Manufacturing," evaluation of emerging materials and additive manufacturing technologies was carried out. These technologies may enable fully non-metallic gas turbine engines in the future. This paper highlights the results of engine system trade studies which were carried out to estimate reduction in engine emissions and fuel burn enabled due to advanced materials and manufacturing processes. A number of key engine components were identified in which advanced materials and additive manufacturing processes would provide the most significant benefits to engine operation. In addition, feasibility of using additive manufacturing technologies to fabricate gas turbine engine components from polymer and ceramic matrix composite were demonstrated. A wide variety of prototype components (inlet guide vanes (IGV), acoustic liners, engine access door, were additively manufactured using high temperature polymer materials. Ceramic matrix composite components included first stage nozzle segments and high pressure turbine nozzle segments for a cooled doublet vane. In addition, IGVs and acoustic liners were tested in simulated engine conditions in test rigs. The test results are reported and discussed in detail.

A Fully Non-Metallic Gas Turbine Engine Enabled by Additive Manufacturing

NASA Technical Reports Server (NTRS)

Grady, Joseph E.; Halbig, Michael C.; Singh, Mrityunjay

2015-01-01

In a NASA Aeronautics Research Institute (NARI) sponsored program entitled "A Fully Non-Metallic Gas Turbine Engine Enabled by Additive Manufacturing", evaluation of emerging materials and additive manufacturing technologies was carried out. These technologies may enable fully non-metallic gas turbine engines in the future. This paper highlights the results of engine system trade studies which were carried out to estimate reduction in engine emissions and fuel burn enabled due to advanced materials and manufacturing processes. A number of key engine components were identified in which advanced materials and additive manufacturing processes would provide the most significant benefits to engine operation. In addition, feasibility of using additive manufacturing technologies to fabricate gas turbine engine components from polymer and ceramic matrix composite were demonstrated. A wide variety of prototype components (inlet guide vanes (IGV), acoustic liners, engine access door) were additively manufactured using high temperature polymer materials. Ceramic matrix composite components included first stage nozzle segments and high pressure turbine nozzle segments for a cooled doublet vane. In addition, IGVs and acoustic liners were tested in simulated engine conditions in test rigs. The test results are reported and discussed in detail.

Automated Array Assembly, Phase 2

NASA Technical Reports Server (NTRS)

Carbajal, B. G.

1979-01-01

The solar cell module process development activities in the areas of surface preparation are presented. The process step development was carried out on texture etching including the evolution of a conceptual process model for the texturing process; plasma etching; and diffusion studies that focused on doped polymer diffusion sources. Cell processing was carried out to test process steps and a simplified diode solar cell process was developed. Cell processing was also run to fabricate square cells to populate sample minimodules. Module fabrication featured the demonstration of a porcelainized steel glass structure that should exceed the 20 year life goal of the low cost silicon array program. High efficiency cell development was carried out in the development of the tandem junction cell and a modification of the TJC called the front surface field cell. Cell efficiencies in excess of 16 percent at AM1 have been attained with only modest fill factors. The transistor-like model was proposed that fits the cell performance and provides a guideline for future improvements in cell performance.

Static tests of excess ground attenuation at Wallops Flight Center

NASA Astrophysics Data System (ADS)

Sutherland, L. C.; Brown, R.

1981-06-01

An extensive experimental measurement program which evaluated the attenuation of sound for close to horizontal propagation over the ground was designed to replicate, under static conditions, results of the flight measurements carried out earlier by NASA at the same site (Wallops Flight Center). The program consisted of a total of 41 measurement runs of attenuation, in excess of spreading and air absorption losses, for one third octave bands over a frequency range of 50 to 4000 Hz. Each run consisted of measurements at 10 locations up to 675 m, from a source located at nominal elevations of 2.5, or 10 m over either a grassy surface or an adjacent asphalt concrete runway surface. The tests provided a total of over 8100 measurements of attenuation under conditions of low wind speed averaging about 1 m/s and, for most of the tests, a slightly positive temperature gradient, averaging about 0.3 C/m from 1.2 to 7 m. The results of the measurements are expected to provide useful experimental background for the further development of prediction models of near grazing incidence sound propagation losses.

KSC-2014-3449

NASA Image and Video Library

2014-08-10

LOS ANGELES, Calif. – Andy Quiett, Detachment 3 deputy operations lead for the Orion program and DoD liaison for NASA, answers questions about the Orion boilerplate test vehicle from visitors touring the well deck of the USS Anchorage during the Science, Technology, Engineering and Mathematics, or STEM, Expo for L.A. Navy Days at the Port of Los Angeles in California. A combined team from NASA’s Ground Systems Development and Operations Program and the U.S. Navy were in San Diego to practice recovering Orion from the ocean, as they will do in December following the spacecraft's first trip to space during Exploration Flight Test-1. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep-space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-3448

NASA Image and Video Library

2014-08-10

LOS ANGELES, Calif. – Andy Quiett, Detachment 3 deputy operations lead for the Orion program and DoD liaison for NASA, answers questions about the Orion boilerplate test vehicle from visitors touring the well deck of the USS Anchorage during the Science, Technology, Engineering and Mathematics, or STEM, Expo for L.A. Navy Days at the Port of Los Angeles in California. A combined team from NASA’s Ground Systems Development and Operations Program and the U.S. Navy were in San Diego to practice recovering Orion from the ocean, as they will do in December following the spacecraft's first trip to space during Exploration Flight Test-1. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep-space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-3447

NASA Image and Video Library

2014-08-10

LOS ANGELES, Calif. – Andy Quiett, Detachment 3 deputy operations lead for the Orion program and DoD liaison for NASA, answers questions about the Orion boilerplate test vehicle from visitors touring the well deck of the USS Anchorage during the Science, Technology, Engineering and Mathematics, or STEM, Expo for L.A. Navy Days at the Port of Los Angeles in California. A combined team from NASA’s Ground Systems Development and Operations Program and the U.S. Navy were in San Diego to practice recovering Orion from the ocean, as they will do in December following the spacecraft's first trip to space during Exploration Flight Test-1. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep-space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

Static tests of excess ground attenuation at Wallops Flight Center

NASA Technical Reports Server (NTRS)

Sutherland, L. C.; Brown, R.

1981-01-01

An extensive experimental measurement program which evaluated the attenuation of sound for close to horizontal propagation over the ground was designed to replicate, under static conditions, results of the flight measurements carried out earlier by NASA at the same site (Wallops Flight Center). The program consisted of a total of 41 measurement runs of attenuation, in excess of spreading and air absorption losses, for one third octave bands over a frequency range of 50 to 4000 Hz. Each run consisted of measurements at 10 locations up to 675 m, from a source located at nominal elevations of 2.5, or 10 m over either a grassy surface or an adjacent asphalt concrete runway surface. The tests provided a total of over 8100 measurements of attenuation under conditions of low wind speed averaging about 1 m/s and, for most of the tests, a slightly positive temperature gradient, averaging about 0.3 C/m from 1.2 to 7 m. The results of the measurements are expected to provide useful experimental background for the further development of prediction models of near grazing incidence sound propagation losses.

Comparative Optical Measurements of Airspeed and Aerosols on a DC-8 Aircraft

NASA Technical Reports Server (NTRS)

Bogue, Rodney; McGann, Rick; Wagener, Thomas; Abbiss, John; Smart, Anthony

1997-01-01

NASA Dryden supported a cooperative flight test program on the NASA DC-8 aircraft in November 1993. This program evaluated optical airspeed and aerosol measurement techniques. Three brassboard optical systems were tested. Two were laser Doppler systems designed to measure free-stream-referenced airspeed. The third system was designed to characterize the natural aerosol statistics and airspeed. These systems relied on optical backscatter from natural aerosols for operation. The DC-8 aircraft carried instrumentation that provided real-time flight situation information and reference data on the aerosol environment. This test is believed to be the first to include multiple optical airspeed systems on the same carrier aircraft, so performance could be directly compared. During 23 hr of flight, a broad range of atmospheric conditions was encountered, including aerosol-rich layers, visible clouds, and unusually clean (aerosol-poor) regions. Substantial amounts of data were obtained. Important insights regarding the use of laser-based systems of this type in an aircraft environment were gained. This paper describes the sensors used and flight operations conducted to support the experiments. The paper also briefly describes the general results of the experiments.

KSC-2013-2917

NASA Image and Video Library

2013-06-27

CAPE CANAVERAL, Fla. – Inside the Operations and Checkout Building high bay at NASA’s Kennedy Space Center in Florida, members of the media receive an on activities in NASA’s Ground Systems Development and Operations, or GSDO, Program, Space Launch System and Orion crew module for Exploration Test Flight 1. Speaking to the media, from left are Scott Wilson, manager of Orion Production Operations at Kennedy Larry Price, Lockheed Martin deputy program manager for Orion Tom Erdman, from Marshall Space Flight Center’s Kennedy resident office Jules Schneider, Lockheed Martin manager of Orion Production Operations and Jeremy Parsons, chief of the GSDO Operations Integration Office at Kennedy. Orion is the exploration spacecraft designed to carry crews to space beyond low Earth orbit. It will provide emergency abort capability, sustain the crew during the space travel and provide safe re-entry from deep space return velocities. Orion’s first unpiloted test flight is scheduled to launch in 2014 atop a Delta IV rocket. A second uncrewed flight test is scheduled for 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Jim Grossmann

UKIRT fast guide system improvements

NASA Astrophysics Data System (ADS)

Balius, Al; Rees, Nicholas P.

1997-09-01

The United Kingdom Infra-Red Telescope (UKIRT) has recently undergone the first major upgrade program since its construction. One part of the upgrade program was an adaptive tip-tilt secondary mirror closed with a CCD system collectively called the fast guide system. The installation of the new secondary and associated systems was carried out in the first half of 1996. Initial testing of the fast guide system has shown great improvement in guide accuracy. The initial installation included a fixed integration time CCD. In the first part of 1997 an integration time controller based on computed guide star luminosity was implemented in the fast guide system. Also, a Kalman type estimator was installed in the image tracking loop based on a dynamic model and knowledge of the statistical properties of the guide star position error measurement as a function of computed guide star magnitude and CCD integration time. The new configuration was tested in terms of improved guide performance nd graceful degradation when tracking faint guide stars. This paper describes the modified fast guide system configuration and reports the results of performance tests.

Response of Microtermes mycophagus (Isoptera: Termitidae) to twenty one wood species

PubMed Central

Saeed, Shafqat

2015-01-01

The responses of termite species to bait depend upon the quality of the food used in the stations. Woods are the most common food sources for termites but different termite species behave differently to different wood species and types. The knowledge of the preference status of different wood species to a termite species helps in effective monitoring and baiting program. The current study was carried out to evaluate the preference of 21 wood species to the termite, Microtermes mycophagus in the field by no-choice and choice feeding tests. The results indicated silk cotton tree and sacred fig woods as the most preferred wood species with mean mass losses of 71.21 ± 5.09% and 68.38 ± 7.27% in no-choice test and 95.02 ± 1.65% and 91.69 ± 2.07% in choice tests, respectively. White cedar was the least preferred wood species with mean mass losses of 7.49 ± 1.64% and 13.92 ± 1.89% in no choice and choice feeding tests, respectively. Based on present studies, sapwood of silk cotton tree and sacred fig may be used in effective monitoring and baiting program against M. mycophagus. PMID:26312171

Construction of a Thermal Vacuum Chamber for Environment Test of Triple CubeSat Mission TRIO-CINEMA

NASA Astrophysics Data System (ADS)

Jeon, Jeheon; Lee, Seongwhan; Yoon, Seyoung; Seon, Jongho; Jin, Ho; Lee, Donghun; Lin, Robert P.

2013-12-01

TRiplet Ionospheric Observatory-CubeSat for Ion, Neutron, Electron & MAgnetic fields (TRIO-CINEMA) is a CubeSat with 3.14 kg in weight and 3-U (10 × 10 × 30 cm) in size, jointly developed by Kyung Hee University and UC Berkeley to measure magnetic fields of near Earth space and detect plasma particles. When a satellite is launched into orbit, it encounters ultrahigh vacuum and extreme temperature. To verify the operation and survivability of the satellite in such an extreme space environment, experimental tests are conducted on the ground using thermal vacuum chamber. This paper describes the temperature control device and monitoring system suitable for CubeSat test environment using the thermal vacuum chamber of the School of Space Research, Kyung Hee University. To build the chamber, we use a general purpose thermal analysis program and NX 6.0 TMG program. We carry out thermal vacuum tests on the two flight models developed by Kyung Hee University based on the thermal model of the TRIO-CINEMA satellite. It is expected from this experiment that proper operation of the satellite in the space environment will be achieved.

Pressurized fluidized bed combustion of coal for electric power generation the AEP approach

DOE Office of Scientific and Technical Information (OSTI.GOV)

Markowsky J.J.; Wickstrom, B.

1982-08-01

American Electric Power (AEP), STAL-LAVAL Turbine A.B. (SL), and Deutsche Babcock Anlagen AG (DBA) are working on a program estimated to cost $250 million that will lead toward the construction of a large (170,000 KW) commercial demonstration of an advanced electric power plant incorporating Pressurized Fluidized Bed Combustion (PFBC) of coal. A pilot plant test program carried out during 1977-1980 verified combustor performance and demonstrated long gas turbine blade life. Parallel efforts during this period involved the design of the 170,000 kW Commercial Demonstration Plant (CDP) and a 500,000 kW Commercial Plant which essentially consists of two CDP combustors-gas turbinemore » modules and a larger capacity steam cycle. These efforts showed considerable economic advantages of PFBC-combined cycle power generation over other alternative technologies. A 15,000 KW (thermal) component test facility (CTF) is presently under construction in Sweden. Extensive testing is scheduled to begin in early 1982. Upon successful completion of these tests, AEP intends to start construction of the CDP in 1983; the plant is expected to supply power to the AEP network by 1986.« less

KSC-2009-2556

NASA Image and Video Library

2009-04-08

CAPE CANAVERAL, Fla. – Members of the 920th Rescue Wing release a flotation collar around the mockup Orion crew exploration vehicle at the Trident Basin at Port Canaveral, Fla. On top of Orion are additional flotation devices. The goal of the operation, dubbed the Post-landing Orion Recovery Test, or PORT, is to determine what kind of motion astronauts can expect after landing, as well as outside conditions for recovery teams. Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. Orion, along with the Ares I and V rockets and the Altair lunar lander, are part of the Constellation Program. Photo credit: NASA/Dimitri Gerondidakis

Friendly protection of houses by affordable isolation

DOE Office of Scientific and Technical Information (OSTI.GOV)

Mazzolani, Federico M.; Mandara, Alberto; Froncillo, Salvatore

2008-07-08

The paper deals with a case of seismic isolation carried out in Campania (Italy), referring to the construction of a house building. The concerned case is a three-storey reinforced concrete frame building, in which the isolation system has been applied between the basement top and the first floor deck. The paper reports the main steps of this work, starting from the design, carried out according to the latest Italian seismic code, going throughout the construction stage, up to the extensive on-site testing program performed to evaluate the dynamic response of the building. Relevant technological solutions are illustrated and discussed. Bothmore » theoretical calculation and experimental measurements demonstrate the effectiveness of the solution adopted, not only from the technical point of view, but also in an economic perspective.« less

Obstetric team simulation program challenges.

PubMed

Bullough, A S; Wagner, S; Boland, T; Waters, T P; Kim, K; Adams, W

2016-12-01

To describe the challenges associated with the development and assessment of an obstetric emergency team simulation program. The goal was to develop a hybrid, in-situ and high fidelity obstetric emergency team simulation program that incorporated weekly simulation sessions on the labor and delivery unit, and quarterly, education protected sessions in the simulation center. All simulation sessions were video-recorded and reviewed. Labor and delivery unit and simulation center. Medical staff covering labor and delivery, anesthesiology and obstetric residents and obstetric nurses. Assessments included an on-line knowledge multiple-choice questionnaire about the simulation scenarios. This was completed prior to the initial in-situ simulation session and repeated 3 months later, the Clinical Teamwork Scale with inter-rater reliability, participant confidence surveys and subjective participant satisfaction. A web-based curriculum comprising modules on communication skills, team challenges, and team obstetric emergency scenarios was also developed. Over 4 months, only 6 labor and delivery unit in-situ sessions out of a possible 14 sessions were carried out. Four high-fidelity sessions were performed in 2 quarterly education protected meetings in the simulation center. Information technology difficulties led to the completion of only 18 pre/post web-based multiple-choice questionnaires. These test results showed no significant improvement in raw score performance from pre-test to post-test (P=.27). During Clinical Teamwork Scale live and video assessment, trained raters and program faculty were in agreement only 31% and 28% of the time, respectively (Kendall's W=.31, P<.001 and W=.28, P<.001). Participant confidence surveys overall revealed confidence significantly increased (P<.05), from pre-scenario briefing to after post-scenario debriefing. Program feedback indicates a high level of participant satisfaction and improved confidence yet further program refinement is required. Copyright © 2016 Elsevier Inc. All rights reserved.

Effects of supportive-educative program on quality of life of adolescents living with a parent with cancer

PubMed Central

Azarbarzin, Mehrdad; Malekian, Azadeh; Taleghani, Fariba

2015-01-01

Background: Cancer has significant traumatic effects on the family members of the patients, particularly in Asia's tightly knitted families. Research evidence suggests a debilitating impact of cancer on the quality of life of the afflicted individuals, their spouses, and their families. Since a few studies have been carried out on the quality of life of adolescents living with parents diagnosed with cancer, especially in Iran, the research team decided to evaluate the quality of life of them and also investigate the effects of supportive-educative program on it. Materials and Methods: The present quasi-experimental, one-group study had a pre-test–post-test design and was performed in Esfahan in 2014. The sample of this study consisted of 30 adolescents. The data gathering tool was the short form of quality of life questionnaire (SF-36). Data were analyzed by descriptive statistics and paired sample t-test. P-value of 0.05 was considered significant. Results: The paired sample t-test showed that before and after presenting the program, there were significant statistical differences in some aspects of quality of life, such as physical functioning (P = 0.01), energy/fatigue (P < 0.0001), emotional well-being (P < 0.0001), social functioning (P = 0.001), pain (P < 0.0001), and general health (P = 0.01). Conclusions: This research showed that supportive-educative program can enhance some aspects of quality of life. Therefore, nurses and other health professionals can use this scheme or similar programs for helping adolescents living with a parent with cancer. PMID:26457095

Enhancing Diabetes Self-care Among Rural African Americans With Diabetes

PubMed Central

Williams, Ishan C.; Utz, Sharon W.; Hinton, Ivora; Yan, Guofen; Jones, Randy; Reid, Kathryn

2015-01-01

Purpose The purpose of this study is to test the feasibility of conducting a community-based randomized controlled trial evaluating a culturally tailored community-based group diabetes self-management education (DSME) program among rural African Americans. Methods Thirty-two African American rural adults with type 2 diabetes were recruited and 25 adults were retained and participated in an interventional study designed to test the effectiveness of the “Taking Care of Sugar” DSME program for the 2-year follow-up. Participants were selected from rural central Virginia. Primary outcomes variables included average blood sugar levels, cardiovascular risk factors, and general physical and mental health. These outcomes were assessed at baseline, 3 months, 6 months, and 12 months post baseline. Results From baseline to 3-month follow-up assessment, participants exhibited significant improvement on several physiological and behavioral measures. Given the small sample size, hypothesis testing was limited. Results show change from baseline over time, illustrating that the primary outcome of A1C decreased, although not significant. Additionally, participants reported more knowledge about diabetes self-management and personal care skills (ie, exercise and foot care) that persisted over time. The feasibility of the culturally tailored DSME was established, and participation with the program was high. Conclusions A community-based group DSME program using storytelling is feasible. This research will help to inform clinicians and health policymakers as to the types of interventions that are feasible in a larger rural population. If such a program is carried out, we can improve knowledge, reduce complications, and improve quality of life among rural African Americans. PMID:24478047

Superallowed Fermi β decay studies at TRIUMF-ISAC

NASA Astrophysics Data System (ADS)

Svensson, C. E.; Dunlop, R.; Finlay, P.; Ball, G. C.; Ettenauer, S.; Leslie, J. R.; Towner, I. S.; Andreoiu, C.; Austin, R. A. E.; Bandyopadhyay, D.; Chagnon-Lessard, S.; Chester, A.; Cross, D. S.; Demand, G.; Djongolov, M.; Garnsworthy, A. B.; Garrett, P. E.; Green, K. L.; Glister, J.; Grinyer, G. F.; Hackman, G.; Hadinia, B.; Leach, K. G.; Pearson, C. J.; Phillips, A. A.; Rand, E. T.; Starosta, K.; Sumithrarachchi, C. S.; Tardiff, E. R.; Triambak, S.; Williams, S. J.; Wong, J.; Yates, S. W.; Zganjar, E. F.

2013-10-01

A program of high-precision superallowed Fermi β decay studies is being carried out at the Isotope Separator and Accelerator (ISAC) radioactive ion beam facility at TRIUMF. Recent high-precision branching ratio measurements for the superallowed decays of 74Rb and 26Alm, as well as a half-life measurement for 26Alm that is the most precise half-life measurement for any superallowed emitter to date, are reported. These results provide demanding tests of the theoretical isospin symmetry breaking corrections in superallowed Fermi β decays.

Crawler Transporter 2 Trek

NASA Image and Video Library

2016-03-23

NASA’s upgraded crawler-transporter 2 (CT-2) begins its trek from the Vehicle Assembly Building (VAB) at the agency’s Kennedy Space Center in Florida to Launch Pad 39B to test recently completed upgrades and modifications for NASA’s journey to Mars. The Ground Systems Development and Operations Program at Kennedy oversaw upgrades to the crawler in the VAB. The crawler will carry the mobile launcher with Orion atop the Space Launch System rocket to Pad 39B for Exploration Mission-1, scheduled for 2018.

Crawler Transporter 2 Trek

NASA Image and Video Library

2016-03-23

NASA’s upgraded crawler-transporter 2 (CT-2) has exited the Vehicle Assembly Building (VAB) at the agency’s Kennedy Space Center in Florida for its trek along the crawlerway to Launch Pad 39B to test recently completed upgrades and modifications for NASA’s journey to Mars. The Ground Systems Development and Operations Program at Kennedy oversaw upgrades to the crawler in the VAB. The crawler will carry the mobile launcher with Orion atop the Space Launch System rocket to Pad 39B for Exploration Mission-1, scheduled for 2018.

Crawler Transporter 2 Trek

NASA Image and Video Library

2016-03-23

NASA’s upgraded crawler-transporter 2 (CT-2) travels along the crawlerway from the Vehicle Assembly Building (VAB) at the agency’s Kennedy Space Center in Florida on its trek to Launch Pad 39B to test recently completed upgrades and modifications for NASA’s journey to Mars. The Ground Systems Development and Operations Program at Kennedy oversaw upgrades to the crawler in the VAB. The crawler will carry the mobile launcher with Orion atop the Space Launch System rocket to Pad 39B for Exploration Mission-1, scheduled for 2018.

Crawler Transporter 2 Trek

NASA Image and Video Library

2016-03-23

NASA’s upgraded crawler-transporter 2 (CT-2) travels along the crawlerway during its trek to Launch Pad 39B at the agency’s Kennedy Space Center in Florida, to test recently completed upgrades and modifications for NASA’s journey to Mars. The Ground Systems Development and Operations Program at Kennedy oversaw upgrades to the crawler in the Vehicle Assembly Building. The crawler will carry the mobile launcher with Orion atop the Space Launch System rocket to Pad 39B for Exploration Mission-1, scheduled for 2018.

VSP - Discussion: The Common Interest on Planning Hulls and Plan for Collaboration Studies between NSWC and KRISO - Washington DC

DTIC Science & Technology

2016-03-07

planning hulls and plan for N62909-15-1-2052 collaboration studies between NSWC and KRISO - Washington DC Sb. GRANT NUMBER N62909-15-1-2052 Sc. PROGRAM...be carried out in MASK’s facilities. We discussed common interests on planing hulls , and made plans for collaboration studies between NSWC and KRISO... hull forms for satisfying the requirements of the project. Model tests and analyses are required to assess the maneuvering and seakeeping performance

KSC-2009-3202

NASA Image and Video Library

2009-05-18

CAPE CANAVERAL, Fla. – In the Operations and Checkout Building's high bay, technicians are preparing to start testing how to put the "skins" on the outer mold of the simulator Orion crew module. Part of NASA's Constellation Program, the Orion spacecraft will return humans to the moon and prepare for future voyages to Mars and other destinations in our solar system. Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. Photo credit: NASA/Kim Shiflett

Effects of surface chemistry on hot corrosion life: Overview

NASA Technical Reports Server (NTRS)

Merutka, J.

1982-01-01

This program concentrates on analyzing a limited number of hot corroded components from the field and the carrying out of a series of controlled laboratory experiments to establish the effects of oxide scale and coating chemistry on hot corrosion life. This is to be determined principally from the length of the incubation period, the investigation of the mechanisms of hot corrosion attack, and the fitting of the data generated from the test exposure experiments to an empirical life prediction model.

Defense Acquisitions: Assessments of Selected Weapon Programs

DTIC Science & Technology

2012-03-01

knowledge-based practices. As a result , most of these programs will carry technology, design, and production risks into subsequent phases of the...acquisition process that could result in cost growth or schedule delays. GAO also assessed the implementation of selected acquisition reforms and found...knowledge-based practices. As a result , most of these programs will carry technology, design, and production risks into subsequent phases of the

Acoustic Noise Test Report for the U.S. Department of Energy 1.5-Megawatt Wind Turbine

DOE Office of Scientific and Technical Information (OSTI.GOV)

Roadman, Jason; Huskey, Arlinda

2015-07-01

A series of tests were conducted to characterize the baseline properties and performance of the U.S. Department of Energy (DOE) 1.5-megawatt wind turbine (DOE 1.5) to enable research model development and quantify the effects of future turbine research modifications. The DOE 1.5 is built on the platform of GE's 1.5-MW SLE commercial wind turbine model. It was installed in a nonstandard configuration at the NWTC with the objective of supporting DOE Wind Program research initiatives such as A2e. Therefore, the test results may not represent the performance capabilities of other GE 1.5-MW SLE turbines. The acoustic noise test documented inmore » this report is one of a series of tests carried out to establish a performance baseline for the DOE 1.5 in the NWTC inflow environment.« less

Testing of Environmental Satellite Bus-Instrument Interfaces Using Engineering Models

NASA Technical Reports Server (NTRS)

Gagnier, Donald; Hayner, Rick; Nosek, Thomas; Roza, Michael; Hendershot, James E.; Razzaghi, Andrea I.

2004-01-01

This paper discusses the formulation and execution of a laboratory test of the electrical interfaces between multiple atmospheric scientific instruments and the spacecraft bus that carries them. The testing, performed in 2002, used engineering models of the instruments and the Aura spacecraft bus electronics. Aura is one of NASA s Earth Observatory System missions. The test was designed to evaluate the complex interfaces in the command and data handling subsystems prior to integration of the complete flight instruments on the spacecraft. A problem discovered during the flight integration phase of the observatory can cause significant cost and schedule impacts. The tests successfully revealed problems and led to their resolution before the full-up integration phase, saving significant cost and schedule. This approach could be beneficial for future environmental satellite programs involving the integration of multiple, complex scientific instruments onto a spacecraft bus.

Review of NASA's Hypersonic Research Engine Project

NASA Technical Reports Server (NTRS)

Andrews, Earl H.; Mackley, Ernest A.

1993-01-01

The goals of the NASA Hypersonic Research Engine (HRE) Project, which began in 1964, were to design, develop, and construct a hypersonic research ramjet/scramjet engine for high performance and to flight-test the developed concept over the speed range from Mach 3 to 8. The project was planned to be accomplished in three phases: project definition, research engine development, and flight test using the X-15A-2 research aircraft, which was modified to carry hydrogen fuel for the research engine. The project goal of an engine flight test was eliminated when the X-15 program was canceled in 1968. Ground tests of engine models then became the focus of the project. Two axisymmetric full-scale engine models having 18-inch-diameter cowls were fabricated and tested: a structural model and a combustion/propulsion model. A brief historical review of the project with salient features, typical data results, and lessons learned is presented.

Experimental and finite element investigation of the buckling characteristics of a beaded skin panel for a hypersonic aircraft. Ph.D. Thesis. Final Report

NASA Technical Reports Server (NTRS)

Siegel, W. H.

1978-01-01

As part of NASA's continuing research into hypersonics and 85 square foot hypersonic wing test section of a proposed hypersonic research airplane was laboratory tested. The project reported on in this paper has carried the hypersonic wing test structure project one step further by testing a single beaded panel to failure. The primary interest was focused upon the buckling characteristics of the panel under pure compression with boundary conditions similar to those found in a wing mounted condition. Three primary phases of analysis are included in the report. These phases include: experimental testing of the beaded panel to failure; finite element structural analysis of the beaded panel with the computer program NASTRAN; a summary of the semiclassical buckling equations for the beaded panel under purely compressive loads. Comparisons between each of the analysis methods are also included.

Orion Underway Recovery Test 5 (URT-5)

NASA Image and Video Library

2016-11-01

The USS San Diego approaches Naval Base San Diego in California after completion of Underway Recovery Test 5 in the Pacific Ocean. NASA's Ground Systems Development and Operations Program and the U.S. Navy conducted a series of tests using the ship's well deck and a test version of the Orion crew module to prepare for recovery of Orion on its return from deep space missions. The testing allowed the team to demonstrate and evaluate recovery processes, procedures, hardware and personnel in open waters. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and NASA's Journey to Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. Orion is scheduled to launch on NASA's Space Launch System in late 2018. For more information, visit http://www.nasa.gov/orion.

Numerical analysis and experimental verification of elastomer bending process with different material models

NASA Astrophysics Data System (ADS)

Kut, Stanislaw; Ryzinska, Grazyna; Niedzialek, Bernadetta

2016-01-01

The article presents the results of tests in order to verifying the effectiveness of the nine selected elastomeric material models (Neo-Hookean, Mooney with two and three constants, Signorini, Yeoh, Ogden, Arruda-Boyce, Gent and Marlow), which the material constants were determined in one material test - the uniaxial tension testing. The convergence assessment of nine analyzed models were made on the basis of their performance from an experimental bending test of the elastomer samples from the results of numerical calculations FEM for each material models. To calculate the material constants for the analyzed materials, a model has been generated by the stressstrain characteristics created as a result of experimental uniaxial tensile test with elastomeric dumbbell samples, taking into account the parameters received in its 18th cycle. Using such a calculated material constants numerical simulation of the bending process of a elastomeric, parallelepipedic sampleswere carried out using MARC / Mentat program.

Performance testing and module monitoring at the EC Necessary steps to develop cost-effective PV modules

NASA Astrophysics Data System (ADS)

Krebs, K.

Testing programs carried out by the European Communities to establish testing techniques and standards for verifying the reliability and integrity of solar cells intended for the marketplace are described. The efforts are being expended to assure quality control and certification for photovoltaic (PV) products manufactured in any of the member nations. The failure rate for PV modules was lowered to 0.5 pct/year by 1981, and single cell failures are projected to be lowered to 0.00001/yr, connectors to 0.001/yr, and batteries to 0.01/yr. Day/night thermal cycling causes the most dominant type of failures, i.e., cracked cells and interconnect defects. Tests have been standardized for inspection, verification, performance, mechanical loading, hail impact, damp heat, high temperature long exposure, hot-spot heating, thermal cycling, and humidity-freezing tolerance.

Shop test of the 501F; A 150 MW combustion turbine

DOE Office of Scientific and Technical Information (OSTI.GOV)

Entenmann, D.T.; North, W.E.; Fukue, I.

1991-10-01

The 501F is a 150 MW-class 60 Hz engine jointly developed by Westinghouse Electric Corporation and Mitsubishi Heavy Industries, Ltd. This paper describes the full-load shop test program for the prototype engine, as carried out in Takasago, Japan. The shop test included a full range of operating conditions, from startup through full load at the 1260{degrees} C (2300{degrees} F) design turbine inlet temperature. The engine was prepared with more than 1500 instrumentation points to monitor flow path characteristics, metal temperatures, displacements, pressures, cooling circuit characteristics, strains, sound pressure levels, and exhaust emissions. The results of this shop test indicate themore » new 501F engine design and development effort to be highly successful. The engine exceeds power and overall efficiency expectations, thus verifying the new concepts and design improvements.« less

[Early detection of bowel cancer in occupational surveillance examinations: switching from a guaiak-based to an immunochemical fecal occult blood test].

PubMed

Webendörfer, S; Riemann, J F

2014-01-01

If the diagnosis is made early the cure rate of bowel cancer is more than 90 %. Occupational preventative medical care required by law and carried out by company physicians can be supplemented by a medical consultation and by simple screenings to interest employees in cancer prevention and refer them to registered general practitioners and specialist doctors for further diagnosis and treatment. Since 2001, BASF SE in Ludwigshafen, Germany offers its employees aged 45 and more a program to detect intestinal cancer early. The employees receive personal invitations for this program once a year. The participants answer a standard questionnaire about risk factors for bowel cancer and an endoscopic diagnosis, if this has already been carried out, and receive a FOBT. Since 2010 an immunological test system was used. We compare the results from two consecutive years with a Guajacum test system (g-FOBT) and an immunological test (i-FOBT). The German Association of Digestive and Metabolic Diseases, DGVS, recommends a colonoscopy if test results are positive or a family member has suffered from bowel cancer. Between 2008 and 2011, a total of 52,797 invitations were sent to employees aged 45 and over. Overall, 16,730 men (37.7 % of 46,245) and 1,585 women (24.4 % of 6,552) took part (in some cases more than once). The return rate of the FOBT increased from 66.7 % in 2008 to 79.5 % in 2011. Due to positive results and/or suspicious information in the questionnaire, 2,441 colonoscopies were recommended, 849 of them because of a positive FOBT. The medical department was informed of 224 endoscopy diagnoses. In 8 cases, manifested cancer (6 × colon, 2 × rectum) and in 57 cases adenomatous polyps were diagnosed as preliminary stages of cancer. Most of these diagnoses were made using the i-FOBT, the simultaneous increase in positive test results and therefore more frequent recommendations for a colonoscopy. The additional offer of a program for early detection of bowel cancer as part of an occupational surveillance examination helps detecting bowel cancer early in employees who show no symptoms. Since men on average fall ill earlier, it makes sense to offer these tests at the age of 45.  Personal invitations lead to consistently high participant rates and the simplicity of the i-FOBT leads to high return rates of tests. The rate of positive test results is higher compared to g-FOBT. In our follow-up, significantly more intestinal cancer and possible preliminary stages were detected through screening with the immunological test. © Georg Thieme Verlag KG Stuttgart · New York.

Setting up chronic disease programs: perspectives from Aboriginal Australia.

PubMed

Hoy, Wendy E; Kondalsamy-Chennakesavan, S; Smith, J; Sharma, S; Davey, R; Gokel, G

2006-01-01

To share some perspectives on setting up programs to improve management of hypertension, renal disease, and diabetes in high-risk populations, derived from experience in remote Australian Aboriginal settings. Regular integrated checks for chronic disease and their risk factors and appropriate treatment are essential elements of regular adult health care. Programs should be run by local health workers, following algorithms for testing and treatment, with back up from nurses. Constant evaluation is essential. COMPONENTS: Theses include testing, treatment, education for individuals and communities, skills and career development for staff, ongoing evaluation, program modification, and advocacy. Target groups, elements, and frequency of testing, as well as the reagents and treatment modalities must be designed for local circumstances, which include disease burden and impact, competing priorities, and available resources. Pilot surveys or record reviews can define target groups and conditions. Opportunistic testing will suffice if people are seen with some regularity for other conditions; otherwise, systematic screening is needed, preferably embedded in primary care streams. The chief goal of treatment is to lower blood pressure, and if the patient is diabetic, to control hyperglycemia. Many people will need multiple drugs for many years. Challenges include lack of resources, competing demands of acute care, the burden of treatment when disease rates are high, problems with information systems, and in our setting, health worker absenteeism. Businesses, altruistic organizations, and pharmaceutical and biotechnology companies might fund feasibility studies. Where governments or insurance companies already support health services, they must ultimately commit to chronic disease services over the long- term. Effective advocacy requires the presentation of an integrated view of chronic disease and a single cross-disciplinary program for its containment. Arguments based on preserving the economic base of societies by preventing or delaying premature death will carry most weight, as will the costs of dialysis avoided in countries that already support open-access programs.

Developmental Programming: Contribution of Prenatal Androgen and Estrogen to Estradiol Feedback Systems and Periovulatory Hormonal Dynamics in Sheep1

PubMed Central

Veiga-Lopez, Almudena; Astapova, Olga I.; Aizenberg, Esther F.; Lee, James S.; Padmanabhan, Vasantha

2009-01-01

Prenatal testosterone excess leads to neuroendocrine and periovulatory disruptions in the offspring culminating in progressive loss of cyclicity. It is unknown whether the mediary of these disruptions is androgen or estrogen, because testosterone can be aromatized to estrogen. Taking a reproductive life span approach of studying control, prenatal testosterone, and dihydrotestosterone-treated offspring, this study tested the hypothesis that disruptions in estradiol-negative but not -positive feedback effects are programmed by androgenic actions of testosterone and that these disruptions in turn will have an impact on the periovulatory hormonal dynamics. The approach was to test estradiol-negative and -positive feedback responses of all three groups of ovary-intact females during prepubertal age and then compare the periovulatory dynamics of luteinizing hormone, follicle-stimulating hormone, estradiol, and progesterone during the first breeding season. The findings show that estradiol-negative but not estradiol-positive feedback disruptions in prenatal testosterone-treated females are programmed by androgenic actions of prenatal testosterone excess and that follicular phase estradiol and gonadotropins surge disruptions during reproductive life are consistent with estrogenic programming. Additional studies carried out testing estradiol-positive feedback response over time found progressive deterioration of estradiol-positive feedback in prenatal testosterone-treated sheep until the time of puberty. Together, these findings provide insight into the mechanisms by which prenatal testosterone disrupts the reproductive axis. The findings may be of translational relevance since daughters of mothers with hyperandrogenism are at risk of increased exposure to androgens. PMID:19122183

Developmental programming: contribution of prenatal androgen and estrogen to estradiol feedback systems and periovulatory hormonal dynamics in sheep.

PubMed

Veiga-Lopez, Almudena; Astapova, Olga I; Aizenberg, Esther F; Lee, James S; Padmanabhan, Vasantha

2009-04-01

Prenatal testosterone excess leads to neuroendocrine and periovulatory disruptions in the offspring culminating in progressive loss of cyclicity. It is unknown whether the mediary of these disruptions is androgen or estrogen, because testosterone can be aromatized to estrogen. Taking a reproductive life span approach of studying control, prenatal testosterone, and dihydrotestosterone-treated offspring, this study tested the hypothesis that disruptions in estradiol-negative but not -positive feedback effects are programmed by androgenic actions of testosterone and that these disruptions in turn will have an impact on the periovulatory hormonal dynamics. The approach was to test estradiol-negative and -positive feedback responses of all three groups of ovary-intact females during prepubertal age and then compare the periovulatory dynamics of luteinizing hormone, follicle-stimulating hormone, estradiol, and progesterone during the first breeding season. The findings show that estradiol-negative but not estradiol-positive feedback disruptions in prenatal testosterone-treated females are programmed by androgenic actions of prenatal testosterone excess and that follicular phase estradiol and gonadotropins surge disruptions during reproductive life are consistent with estrogenic programming. Additional studies carried out testing estradiol-positive feedback response over time found progressive deterioration of estradiol-positive feedback in prenatal testosterone-treated sheep until the time of puberty. Together, these findings provide insight into the mechanisms by which prenatal testosterone disrupts the reproductive axis. The findings may be of translational relevance since daughters of mothers with hyperandrogenism are at risk of increased exposure to androgens.

The effectiveness of a community health program in improving diabetes knowledge in the Hispanic population: Salud y Bienestar (Health and Wellness).

PubMed

Cruz, Yanira; Hernandez-Lane, Maria-Eugenia; Cohello, Janet I; Bautista, Christian T

2013-12-01

We evaluated the effectiveness of the Salud y Bienestar program to deliver diabetes education in the Hispanic population in the United States. This program uses a community outreach model where community health promoters are trained and then they deliver education to other community members regarding diabetes disease, risk factors, and ways to prevent and control disease. This intervention applies a one-group pre- and post-test design to improve diabetes knowledge. The intervention carried out in the states of California, Texas, and Washington DC. A total of 1,413 participants were enrolled. Of these, 73% were females, 46% were 65 years or older, 59% were Mexican, 64% had at least elementary education, 56% had lived in the US for more than 20 years, and 38% participants were self-reported diabetic. Among diabetic participants, a significant improvement was observed on diabetes knowledge when comparing pre- and post-test scores (13.7 vs. 18.6, P < 0.001; Cohen's d = 1.2). Among non-diabetic participants, diabetes knowledge also increased significantly after one-single training session (12.9 vs. 18.2, P < 0.001; Cohen's d = 1.2). The Salud y Bienestar program conducted by community health workers was effective approach to improving diabetes knowledge in the Hispanic population.

Flight Qualification of the NASA's Super Pressure Balloon

NASA Astrophysics Data System (ADS)

Cathey, Henry; Said, Magdi; Fairbrother, Debora

Designs of new balloons to support space science require a number of actual flights under various flight conditions to qualify them to as standard balloon flight offerings to the science community. Development of the new Super Pressure Balloon for the National Aeronautics and Space Administration’s Balloon Program Office has entailed employing new design, analysis, and production techniques to advance the state of the art. Some of these advances have been evolutionary steps and some have been revolutionary steps requiring a maturing understanding of the materials, designs, and manufacturing approaches. The NASA Super Pressure Balloon development end goal is to produce a flight vehicle that is qualified to carry a ton of science instrumentation, at an altitude greater than 33 km while maintaining a near constant pressure altitude for extended periods of up to 100 days, and at any latitude on the globe. The NASA’s Balloon Program Office has pursued this development in a carefully executed incremental approach by gradually increasing payload carrying capability and increasing balloon volume to reach these end goal. A very successful test flight of a ~200,700 m3 balloon was launch in late 2008 from Antarctica. This balloon flew for over 54 days at a constant altitude and circled the Antarctic continent almost three times. A larger balloon was flown from Antarctica in early 2011. This ~422,400 m3 flew at a constant altitude for 22 days making one circuit around Antarctica. Although the performance was nominal, the flight was terminated via command to recover high valued assets from the payload. The balloon designed to reach the program goals is a ~532,200 m3 pumpkin shaped Super Pressure Balloon. A test flight of this balloon was launched from the Swedish Space Corporation’s Esrange Balloon Launch Facilities near Kiruna, Sweden on 14 August, 2012. This flight was another success for this development program. Valuable information was gained from this short test flight by successfully demonstrated balloon vehicle performance, obtained a large amount of videos, measured balloon differential pressure, obtained temperature and altitude data, assessed structure strength through pressurization, and demonstrated the balloon vehicles altitude stability. This flight was the first of several to qualify this design for the science community. Results of the most recent flights will be presented. Some of the related material characterization testing which is vital to the balloon design development for the balloon will also be presented. Additionally, this paper will provide a current overview of the development and qualification approach pursued for the NASA’s Super Pressure Balloon. Future plans and goals of future test flights will also be presented. This will include the projected balloon volumes, payload capabilities, test flight locations, and proposed flight schedule.

[National Antimicrobial Resistance Surveillance System (NAMRSS) external quality assessment studies: 2011-2016].

PubMed

Süzük Yıldız, Serap; Şimşek, Hüsniye; Çöplü, Nilay; Gülay, Zeynep

2017-07-01

Establishment of sustainable and evidence-based surveillance systems are recommended for prevention of microbial resistance by the World Health Organization (WHO). As a necessity of these surveillance systems, participants are recommended to implement an external quality assessment (EQA) program. In this scope, National Antimicrobial Resistance Surveillance System (NARSS) has been established within the Public Health Institute of Turkey (PHIT) in our country since 2011. In the scope of this surveillance, NARSS EQA program has been implemented in a cycle per year and four isolates were sent to participants per cycle every year since 2011. In this study, it was aimed to evaluate the six years results of the EQA programs being implemented on NARSS participants between 2011 and 2016. The surveillance system consisted of 118 laboratories. Escherichia coli, Klebsiella pneumoniae, Pseudomonas aeruginosa, Staphylococcus aureus, Streptococcus pneumoniae, Enterococcus faecium/faecalis and Acinetobacter baumannii bacteria included in scope of the surveillance were sent to participants. Identification of bacteria to the species level, verification of the antibiotic susceptibility test results and existence of specified resistance of the isolates performed with valid test methods required from the participants. Identified isolates were cultured with routine microbiological methods and sent to participants in ambient temperature in triple carrying pouches inside suitable carrying media via PTT Cargo. The results were entered by means of passwords prepared by PHIT and sent to the web based system. The analysis of results were made with SPSS program. A total of twenty-three isolates were sent to participants between 2011 and 2016. It was determined that participants commonly preferred automated systems for bacterial identification and antibiotic sensitivity test results. The use of MALDI TOF MS system was determined to be raised up to 15.65% in 2016. It has been determined that usually little mistakes were done in bacterial identification but the error rate was high especially in antimicrobial susceptibility test results with close clinical threshold values. Although not required for antibiotic susceptibility test results, it was determined that phenotypic tests have been used more widely in determining the specific resistance mechanisms that are important for epidemiological data. It was determined that 80% of participants have used EUCAST standards in 2016. As a result of this research, we have observed that EQA studies of NARSS EQA are a good performance tool for sustainable and evidence based surveillance studies, that the national antimicrobial resistance data quality is sufficiently good and that the data can be shared on international platforms. In addition, the regular maintenance of national surveillance studies shown that laboratories have positive reflections on self improvement in achieving up to date and accurate results.

7 CFR 3403.4 - Three-phase program.

Code of Federal Regulations, 2012 CFR

2012-01-01

... AGRICULTURE SMALL BUSINESS INNOVATION RESEARCH GRANTS PROGRAM Program Description § 3403.4 Three-phase program. The Small Business Innovation Research Grants Program is carried out in three separate phases...

7 CFR 3403.4 - Three-phase program.

Code of Federal Regulations, 2014 CFR

2014-01-01

... AGRICULTURE SMALL BUSINESS INNOVATION RESEARCH GRANTS PROGRAM Program Description § 3403.4 Three-phase program. The Small Business Innovation Research Grants Program is carried out in three separate phases...

7 CFR 3403.4 - Three-phase program.

Code of Federal Regulations, 2013 CFR

2013-01-01

... AGRICULTURE SMALL BUSINESS INNOVATION RESEARCH GRANTS PROGRAM Program Description § 3403.4 Three-phase program. The Small Business Innovation Research Grants Program is carried out in three separate phases...

Cavity BPM System Tests for the ILC Spectrometer

DOE Office of Scientific and Technical Information (OSTI.GOV)

Slater, M.

2007-12-21

The main physics program of the International Linear Collider (ILC) requires a measurement of the beam energy at the interaction point with an accuracy of 10{sup -4} or better. To achieve this goal a magnetic spectrometer using high resolution beam position monitors (BPMs) has been proposed. This paper reports on the cavity BPM system that was deployed to test this proposal. We demonstrate sub-micron resolution and micron level stability over 20 hours for a 1 m long BPM triplet. We find micron-level stability over 1 hour for 3 BPM stations distributed over a 30 m long baseline. The understanding ofmore » the behavior and response of the BPMs gained from this work has allowed full spectrometer tests to be carried out.« less

KSC-2013-3024

NASA Image and Video Library

2013-06-27

Edwards, Calif. – ED13-0215-024 - Sierra Nevada Corporation SNC Space Systems' team members prepare to tow the Dream Chaser flight vehicle along a concrete runway at NASA's Dryden Flight Research Center in California for range and taxi tow tests. The ground testing will validate the performance of the spacecraft's nose skid, brakes, tires and other systems prior to captive-carry and free-flight tests scheduled for later this year. SNC is one of three companies working with NASA's Commercial Crew Program, or CCP, during the agency's Commercial Crew Integrated Capability, or CCiCap, initiative, which is intended to lead to the availability of commercial human spaceflight services for government and commercial customers. To learn more about CCP and its industry partners, visit www.nasa.gov/commercialcrew. Image credit: NASA/Ken Ulbrich

KSC-2013-3023

NASA Image and Video Library

2013-06-27

Edwards, Calif. – ED13-0215-016 - Sierra Nevada Corporation SNC Space Systems' team members prepare to tow the Dream Chaser flight vehicle along a concrete runway at NASA's Dryden Flight Research Center in California for range and taxi tow tests. The ground testing will validate the performance of the spacecraft's nose skid, brakes, tires and other systems prior to captive-carry and free-flight tests scheduled for later this year. SNC is one of three companies working with NASA's Commercial Crew Program, or CCP, during the agency's Commercial Crew Integrated Capability, or CCiCap, initiative, which is intended to lead to the availability of commercial human spaceflight services for government and commercial customers. To learn more about CCP and its industry partners, visit www.nasa.gov/commercialcrew. Image credit: NASA/Ken Ulbrich

Preliminary flight prototype waste collection subsystem. [performance of waste disposal system in weightless environment

NASA Technical Reports Server (NTRS)

Swider, J. E., Jr.

1974-01-01

The zero gravity test program demonstrated the feasibility and practicability of collecting urine from both male and female crew members in a zero gravity environment in an earthlike manner not requiring any manual handling of urine containers. In addition, the testing demonstrated that a seat which is comfortable in both regimes of operation could be designed for use on the ground and in zero-gravity. Further, the tests showed that the vortex liquid/air separator is an effective liquid/air separation method in zero gravity. Visual observations indicate essentially zero liquid carry over. The system also demonstrated its ability to handle post elimination wipes without difficulty. The designs utilized in the WCS were verified as acceptable for usage in the space shuttle or other space vehicles.

Orion Flight Test Preview Briefing

NASA Image and Video Library

2014-11-06

In the Kennedy Space Center’s Press Site auditorium, members of the news media are briefed on the upcoming Orion flight test by Mark Geyer, NASA Orion Program manager. Also participating in the news conference are Bryan Austin, Lockheed Martin mission manager, center, and Jeremy Graeber, Orion Recovery Director in Ground Systems Development and Operations at Kennedy. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch Dec. 4, 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket.

Design of the central region in the Warsaw K-160 cyclotron

NASA Astrophysics Data System (ADS)

Toprek, Dragan; Sura, Josef; Choinski, Jaroslav; Czosnyka, Tomas

2001-08-01

This paper describes the design of the central region for h=2 and 3 modes of acceleration in the Warsaw K-160 cyclotron. The central region is unique and compatible with the two above-mentioned harmonic modes of operation. Only one spiral type inflector will be used. The electric field distribution in the inflector and in the four acceleration gaps has been numerically calculated from an electric potential map produced by the program RELAX3D. The geometry of the central region has been tested with the computations of orbits carried out by means of the computer code CYCLONE. The optical properties of the spiral inflector and the central region were studied by using the programs CASINO and CYCLONE, respectively.

Results of the 1999 JPL Balloon Flight Solar Cell Calibration Program

NASA Technical Reports Server (NTRS)

Anspaugh, B. E.; Mueller, R. L.; Weiss, R. S.

2000-01-01

The 1999 solar cell calibration balloon flight campaign consisted of two flights, which occurred on June 14, 1999, and July 6, 1999. All objectives of the flight program were met. Fifty-seven modules were carried to an altitude of approximately equal to 120,000 ft (36.6 km). Full I-V curves were measured on five of these modules, and output at a fixed load was measured on forty-three modules (forty-five cells), with some modules repeated on the second flight. This data was corrected to 28 C and to 1 AU (1.496 x 10 (exp 8) km). The calibrated cells have been returned to their owners and can now be used as reference standards in simulator testing of cells and arrays.

Salton Sea Scientific Drilling Program

USGS Publications Warehouse

Sass, J.H.

1988-01-01

The Salton Sea Scientific Drilling Program (SSSDP) was the first large-scale drilling project undertaken by the U.S Continental Scientific Drilling Program. The objectives of the SSSDP were (1) to drill a deep well into the Salton Sea Geothermal Field in the Imperial Valley of California, (2) to retrieve a high percentage of core and cuttings along the entire depth of the well, (3) to obtain a comprehensive suite of geophysical logs, (4) to conduct flow tests at two depths  (and to take fluid samples therefrom), and (5) to carry out several downhole experiments. These activites enabled the U.S Geological Survey and cooperating agencies to study the physical and chemical processes involved in an active hydrothermal system driven by a molten-rock heat source. This program, orginally conceived by Wilfred A. Elders, professor of geology at the University of California at Riverside, was coordinated under an inter-agency accord among the Geological Survey, the U.S Department of Energy, and the National Science Foundation. 

Professional quality of life, wellness education, and coping strategies among emergency physicians.

PubMed

El-Shafei, Dalia A; Abdelsalam, Amira E; Hammam, Rehab A M; Elgohary, Hayam

2018-03-01

Professional quality of life (ProQOL) is affected by and affects professional well-being and performance. The objectives of this study are to identify risk factors of ProQOL among EM physicians in Zagazig University hospitals (ZUHs), to detect the relationship between ProQOL and coping strategies, and to measure the implication of the Worksite Wellness Education (WWE) program on improving knowledge skills, ProQOL, and coping. An intervention study was conducted among 108 EM physicians at ZUHs through two stages: assessing ProQOL subscales (CS, BO, and STS) and coping strategies and conducting the WWE program. A pre-post-test design was used in the evaluation. CS was higher among the older age group, smokers, nighttime sleepers, and hobbies' practitioners. Coping strategies carried out by EM physicians to overcome stress and their ProQOL scores were improved significantly post program. ProQOL has multiple factors that affect it. Applying the WWE program will address this concept and may raise awareness about how to cope with work stressors.

URT-3 At Sea Recovery Operation with Bolden

NASA Image and Video Library

2014-09-15

Underway Recovery Test team members help secure the Orion boilerplate test vehicle in the well deck of the USS Anchorage during the first day of Underway Recovery Test 3 in the Pacific Ocean. NASA, Lockheed Martin and U.S. Navy personnel are conducting the recovery test to prepare for recovery of the Orion crew module on its return from a deep space mission. The test allows the teams to demonstrate and evaluate the recovery processes, procedures, hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery tests. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a United Launch Alliance Delta IV Heavy rocket and in 2018 on NASA’s Space Launch System rocket.

Collaborative Testing in Practical Laboratories: An Effective Teaching-Learning Method in Histology.

PubMed

Guo, Yuping; Li, Enzhong

2016-01-01

This article presents an experimental teaching and learning program used in histology with first-year students in the second term in the Faculty of Biology at Huanghuai University, China. Eighty-six students were divided randomly into two groups (n=43 per group). Tests were conducted at the end of each practical laboratory (10 laboratories in total) in which collaborative testing was used in the experimental group and traditional testing in the control group. To assess achievement, a final examination in histology was carried out at the end of the course. To determine students' attitude to the teaching styles, a questionnaire survey was conducted at the end of the term. Results showed that students preferred the collaborative testing format. In the experimental group, students' scores were significantly higher than those of students in the control group in final examinations. These findings indicate that collaborative testing enhances student learning and understanding of the material taught, and suggest that collaborative testing is an effective teaching-learning method in histology.

DOE Office of Scientific and Technical Information (OSTI.GOV)

Jens Korsgaard

The main conclusions from the work carried out under this contract are: An ordinary seafarer can learn by training on a simulator, to moor large tanker vessels to the Hydrostatic Mooring, safely and quickly, in all weather conditions up to storms generating waves with a significant wave height of 8 m. Complete conceptual design of the Hydrostatic Mooring buoy was carried out which proved that the buoy could be constructed entirely from commercially available standard components and materials. The design is robust, and damage resistant. The mooring tests had a 100% success rate from the point of view of themore » buoy being securely attached and moored to the vessel following every mooring attempt. The tests had an 80% success rate from the point of view of the buoy being adequately centered such that petroleum transfer equipment on the vessel could be attached to the corresponding equipment on the buoy. The results given in Table 3-2 of the mooring tests show a consistently improving performance from test to test by the Captain that performed the mooring operations. This is not surprising, in view of the fact that the Captain had only three days of training on the simulator prior to conducting the tests, that the maneuvering required is non-standard, and the test program itself lasted four days. One conclusion of the test performance is that the Captain was not fully trained at the initiation of the test. It may therefore be concluded that a thoroughly trained navigator would probably be able to make the mooring such that the fluid transfer equipment can be connected with reliability in excess of 90%. Considering that the typical standard buoy has enough power aboard to make eight mooring attempts, this implies that the probability that the mooring attempt should fail because of the inability to connect the fluid transfer equipment is of the order of 10{sup {minus}8}. It may therefore be concluded that the mooring operation between a Hydrostatic Mooring and a large tanker vessel can be carried out with near absolute reliability in all sea states up to a sea state where the significant wave height is 8 m.« less

KSC-2009-2566

NASA Image and Video Library

2009-04-08

CAPE CANAVERAL, Fla. – The mockup Orion crew exploration vehicle floats in the water at the Trident Basin at Port Canaveral, Fla. On top of Orion are additional flotation devices. Orion is targeted to begin carrying humans to the International Space Station in 2015 and to the moon by 2020. The mockup vehicle is undergoing testing in open water. The goal of the operation, dubbed the Post-landing Orion Recovery Test, or PORT, is to determine what kind of motion astronauts can expect after landing, as well as outside conditions for recovery teams. Orion, along with the Ares I and V rockets and the Altair lunar lander, are part of the Constellation Program. Photo credit: NASA/Kim Shiflett

Nonmetallic materials handbook. Volume 2: Epoxy and silicone materials

NASA Technical Reports Server (NTRS)

Podlaseck, S. E.

1982-01-01

Chemical and physical property test data obtained during qualification and receiving inspection testing of nonmetallic materials for the Viking Mars Lander program is presented. Thermochemical data showing degradation as a function of temperature from room temperature through 773 K is included. These data include activation energies for thermal degradation, rate constants, and exo- and/or endotherms. Thermal degradations carried out under vacuum include mass spectral data taken simultaneously during the decomposition. Many materials have supporting data such as condensation rates of degassed products and isothermal weight loss. Changes in mechanical, electrical, and thermal properties after exposure to 408 K in nitrogen for times ranging from 380 to 570 hours are included for many materials.

Aero Spacelines B377PG Pregnant Guppy on ramp in preparation for flight tests and pilot evaluation

NASA Technical Reports Server (NTRS)

1962-01-01

The Aero Spacelines B377PG Pregnant Guppy was flown by Aero Spacelines pilots to Dryden for tests and evaluation by pilots Joe Vensel and Stan Butchart in October 1962. The outsized cargo aircraft incorporated the wings, engines, lower fuselage and tail from a Boeing 377 Stratocruiser with a huge upper fuselage more than 20 feet in diameter. The modified aircraft was built to transport outsized cargo for NASA's Apollo program, primarily to carry portions of the Saturn V rockets from the manufacturer to Cape Canaveral. Later versions of the aircraft, including the Super Guppy and the Super Guppy Turbine, are still in use.

A space standards application to university-class microsatellites: The UNISAT experience

NASA Astrophysics Data System (ADS)

Graziani, Filippo; Piergentili, Fabrizio; Santoni, Fabio

2010-05-01

Hands-on education is recognized as an invaluable tool to improve students' skills, to stimulate their enthusiasm and to educate them to teamwork. University class satellite programs should be developed keeping in mind that education is the main goal and that university satellites are a unique opportunity to make involved students familiar with all the phases of space missions. Moreover university budgets for education programs are much lower than for industrial satellites programs. Therefore two main constraints must be respected: a time schedule fitting with the student course duration and a low economic budget. These have an impact on the standard which can be followed in university class satellite programs. In this paper university-class satellite standardization is discussed on the basis of UNISAT program experience, reporting successful project achievements and lessons learned through unsuccessful experiences. The UNISAT program was established at the Scuola di Ingegneria Aerospaziale by the Group of Astrodynamics of the University of Rome "La Sapienza" (GAUSS) as a research and education program in which Ph.D. and graduate students have the opportunity to gain hands-on experience on small space missions. Four university satellites (UNISAT, UNISAT-2, UNISAT-3, UNISAT-4), weighing about 10 kg, have been designed, manufactured, tested and launched every two years since 2000 in the framework of this program In the paper, after a brief overview of new GAUSS programs, an analysis of the UNISAT satellites ground test campaign is carried out, identifying the most critical procedures and requirements to be fulfilled. Moreover a device for low earth orbit low-cost satellite end-of-life disposal is presented; this system (SIRDARIA) complies with the international guidelines on space debris.

Challenges faced by cervical cancer prevention programs in developing countries: a situational analysis of program organization in Argentina.

PubMed

Arrossi, Silvina; Paolino, Melisa; Sankaranarayanan, Rengaswamy

2010-10-01

to carry out a situational analysis of cervical cancer prevention activities in Argentina, specifically regarding (a) the organizational framework of cervical cancer prevention activities; (b) Pap-smear coverage; (c) cytology laboratory organization; and (d) follow-up/treatment of women with abnormal lesions. a situational analysis of provincial cervical cancer programs using data from an ad-hoc questionnaire sent to the leaders of cervical cancer prevention programs in Argentina's 24 provinces. In addition, the provinces' program guidelines, statistical reports, laws, and program regulations were reviewed and certain key leaders were personally interviewed. data were obtained for 19 of Argentina's 24 provinces. Four of the 19 provinces had no formal program framework. Conventional cytology was the most commonly used screening test. Screening was mainly opportunistic. The recommended interval between normal tests was 3 years in most provinces. The eligible age for screening ranged from 10-70 years of age; however, annual or biannual screening was the usual practice after becoming sexually active. None of the provincial programs had data available regarding Pap-smear coverage. Most of the cytology laboratories did not have a quality control policy. The number of smears read varied greatly by laboratory (650-24 000 per year). A log of events related to screening and treatment did not exist in most provinces. screening in Argentina is mainly opportunistic, characterized by an estimated low coverage, coexisting with over-screening of women with access to health services, and an absence of quality control procedures. Policies for cervical cancer screening in the provinces vary and, most often, deviate from the national recommendation of one Pap smear every 3 years for women 35-64 years of age. Ensuring compliance with national program guidelines is an essential step toward significantly reducing the burden of cervical cancer.

Iowa state information handbook: formerly utilized sites remedial action program

DOE Office of Scientific and Technical Information (OSTI.GOV)

None

This volume is one of a series produced under contract with the DOE, By Politech Corporation to develop a legislative and regulatory data base to assist the FUSRAP management in addressing the institutional and socioeconomic issues involved in carrying out the Formerly Utilized Sites Remedial Action Program. This Information Handbook series contains information about all relevant government agencies at the Federal and state levels, the pertinent programs they administer, each affected state legislature, and current Federal and state legislative and regulatory initiatives. This volume is a compilation of information about the state of Iowa. It contains: a description of themore » state executive branch structure; a summary of relevant state statutes and regulations; a description of the structure of the state legislature, identification of the officers and committee chairmen, and a summary of recent relevant legislative action; the full test of relevant statutes and regulations.« less

Effects of an intervention with teachers in the physical education context: A Self-Determination Theory approach

PubMed Central

2017-01-01

Framed within Self-Determination Theory, the purpose of the present study was to test the effects of a training program with physical education (PE) teachers. Participants were 21 high school PE teachers (experimental group, n = 10; control group, n = 11), and their 836 students, aged 12 to 16 years. Teachers in the experimental group received a training program consisting of strategies to support autonomy, competence, and relatedness need satisfaction. A repeated measures ANCOVA was carried out for each dependent variable. After the intervention, students in the experimental group significantly increased their scores on autonomy support, relatedness support, autonomy satisfaction, autonomous motivation, controlled motivation, and intention to be physically active, as compared to the control group. These findings emphasize the utility of a training program with PE teachers to promote the students’ psychological need satisfaction, and hence, self-determined motivation toward PE classes. PMID:29284027

Testing by artificial intelligence: computational alternatives to the determination of mutagenicity.

PubMed

Klopman, G; Rosenkranz, H S

1992-08-01

In order to develop methods for evaluating the predictive performance of computer-driven structure-activity methods (SAR) as well as to determine the limits of predictivity, we investigated the behavior of two Salmonella mutagenicity data bases: (a) a subset from the Genetox Program and (b) one from the U.S. National Toxicology Program (NTP). For molecules common to the two data bases, the experimental concordance was 76% when "marginals" were included and 81% when they were excluded. Three SAR methods were evaluated: CASE, MULTICASE and CASE/Graph Indices (CASE/GI). The programs "learned" the Genetox data base and used it to predict NTP molecules that were not present in the Genetox compilation. The concordances were 72, 80 and 47% respectively. Obviously, the MULTICASE version is superior and approaches the 85% interlaboratory variability observed for the Salmonella mutagenicity assays when the latter was carried out under carefully controlled conditions.

Beam orbit simulation in the central region of the RIKEN AVF cyclotron

NASA Astrophysics Data System (ADS)

Toprek, Dragan; Goto, Akira; Yano, Yasushige

1999-04-01

This paper describes the modification design of the central region for h=2 mode of acceleration in the RIKEN AVF cyclotron. we made a small modification to the electrode shape in the central region for optimization of the beam transmission. The central region is equipped with an axial injection system. The spiral type inflector is used for axial injection. The electric field distribution in the inflector and in four acceleration gaps has been numerically calculated from an electric potential map produced by the program RELAX3D. The magnetic field is measured. The geometry of the central region has been tested with the computations of orbits carried out by means of the computer code CYCLONE. The optical properties of the spiral inflector and the central region are studied by using the program CASINO and CYCLONE, respectively. We have also made an effort to minimize the inflector fringe field effects using the RELAX3D program.

A novel heuristic for optimization aggregate production problem: Evidence from flat panel display in Malaysia

NASA Astrophysics Data System (ADS)

Al-Kuhali, K.; Hussain M., I.; Zain Z., M.; Mullenix, P.

2015-05-01

Aim: This paper contribute to the flat panel display industry it terms of aggregate production planning. Methodology: For the minimization cost of total production of LCD manufacturing, a linear programming was applied. The decision variables are general production costs, additional cost incurred for overtime production, additional cost incurred for subcontracting, inventory carrying cost, backorder costs and adjustments for changes incurred within labour levels. Model has been developed considering a manufacturer having several product types, which the maximum types are N, along a total time period of T. Results: Industrial case study based on Malaysia is presented to test and to validate the developed linear programming model for aggregate production planning. Conclusion: The model development is fit under stable environment conditions. Overall it can be recommended to adapt the proven linear programming model to production planning of Malaysian flat panel display industry.

High-temperature behavior of advanced spacecraft TPS

NASA Technical Reports Server (NTRS)

Pallix, Joan

1994-01-01

The objective of this work has been to develop more efficient, lighter weight, and higher temperature thermal protection systems (TPS) for future reentry space vehicles. The research carried out during this funding period involved the design, analysis, testing, fabrication, and characterization of thermal protection materials to be used on future hypersonic vehicles. This work is important for the prediction of material performance at high temperature and aids in the design of thermal protection systems for a number of programs including programs such as the National Aerospace Plane (NASP), Pegasus and Pegasus/SWERVE, the Comet Rendezvous and Flyby Vehicle (CRAF), and the Mars mission entry vehicles. Research has been performed in two main areas including development and testing of thermal protection systems (TPS) and computational research. A variety of TPS materials and coatings have been developed during this funding period. Ceramic coatings were developed for flexible insulations as well as for low density ceramic insulators. Chemical vapor deposition processes were established for the fabrication of ceramic matrix composites. Experimental testing and characterization of these materials has been carried out in the NASA Ames Research Center Thermophysics Facilities and in the Ames time-of-flight mass spectrometer facility. By means of computation, we have been better able to understand the flow structure and properties of the TPS components and to estimate the aerothermal heating, stress, ablation rate, thermal response, and shape change on the surfaces of TPS. In addition, work for the computational surface thermochemistry project has included modification of existing computer codes and creating new codes to model material response and shape change on atmospheric entry vehicles in a variety of environments (e.g., earth and Mars atmospheres).