Locomotive cab design development. Volume 5 : performance evaluation tests

DOT National Transportation Integrated Search

1976-09-01

This document reports on a preiiminary evaluation o f the Buman : Factors design proposed for a line haul freight locomotive : cab . The program was conducted using a full scale hard mock-up : o f the proposed design and the evaluation was provided b...

Cyber Space--with Elbow Room.

ERIC Educational Resources Information Center

Milshtein, Amy

1998-01-01

Describes how the Hammond School District (Indiana) solved the problem of fitting the correct amount of space needed for students, teachers, and technology. Examines the district's solutions for furniture needs through the use of full-scale mockups of classroom arrangements; and the wiring, power needs, and lighting. (GR)

Participatory ergonomics simulation of hospital work systems: The influence of simulation media on simulation outcome.

PubMed

Andersen, Simone Nyholm; Broberg, Ole

2015-11-01

Current application of work system simulation in participatory ergonomics (PE) design includes a variety of different simulation media. However, the actual influence of the media attributes on the simulation outcome has received less attention. This study investigates two simulation media: full-scale mock-ups and table-top models. The aim is to compare, how the media attributes of fidelity and affordance influence the ergonomics identification and evaluation in PE design of hospital work systems. The results illustrate, how the full-scale mock-ups' high fidelity of room layout and affordance of tool operation support ergonomics identification and evaluation related to the work system entities space and technologies & tools. The table-top models' high fidelity of function relations and affordance of a helicopter view support ergonomics identification and evaluation related to the entity organization. Furthermore, the study addresses the form of the identified and evaluated conditions, being either identified challenges or tangible design criteria. Copyright © 2015 Elsevier Ltd and The Ergonomics Society. All rights reserved.

A NASA technician paints NASA's first Orion full-scale abort flight test crew module.

NASA Image and Video Library

2008-03-31

A full-scale flight-test mockup of the Constellation program's Orion crew vehicle arrived at NASA's Dryden Flight Research Center in late March 2008 to undergo preparations for the first short-range flight test of the spacecraft's astronaut escape system later that year. Engineers and technicians at NASA's Langley Research Center fabricated the structure, which precisely represents the size, outer shape and mass characteristics of the Orion space capsule. The Orion crew module mockup was ferried to NASA Dryden on an Air Force C-17. After painting in the Edwards Air Force Base paint hangar, the conical capsule was taken to Dryden for installation of flight computers, instrumentation and other electronics prior to being sent to the U.S. Army's White Sands Missile Range in New Mexico for integration with the escape system and the first abort flight test in late 2008. The tests were designed to ensure a safe, reliable method of escape for astronauts in case of an emergency.

Sporting a fresh paint job, NASA's first Orion full-scale abort flight test crew module awaits avionics and other equipment installation.

NASA Image and Video Library

2008-04-01

A full-scale flight-test mockup of the Constellation program's Orion crew vehicle arrived at NASA's Dryden Flight Research Center in late March 2008 to undergo preparations for the first short-range flight test of the spacecraft's astronaut escape system later that year. Engineers and technicians at NASA's Langley Research Center fabricated the structure, which precisely represents the size, outer shape and mass characteristics of the Orion space capsule. The Orion crew module mockup was ferried to NASA Dryden on an Air Force C-17. After painting in the Edwards Air Force Base paint hangar, the conical capsule was taken to Dryden for installation of flight computers, instrumentation and other electronics prior to being sent to the U.S. Army's White Sands Missile Range in New Mexico for integration with the escape system and the first abort flight test in late 2008. The tests were designed to ensure a safe, reliable method of escape for astronauts in case of an emergency.

Large scale particle image velocimetry with helium filled soap bubbles

NASA Astrophysics Data System (ADS)

Bosbach, Johannes; Kühn, Matthias; Wagner, Claus

2009-03-01

The application of Particle Image Velocimetry (PIV) to measurement of flows on large scales is a challenging necessity especially for the investigation of convective air flows. Combining helium filled soap bubbles as tracer particles with high power quality switched solid state lasers as light sources allows conducting PIV on scales of the order of several square meters. The technique was applied to mixed convection in a full scale double aisle aircraft cabin mock-up for validation of Computational Fluid Dynamics simulations.

ASTP fluid transfer measurement experiment. [using breadboard model

NASA Technical Reports Server (NTRS)

Fogal, G. L.

1974-01-01

The ASTP fluid transfer measurement experiment flight system design concept was verified by the demonstration and test of a breadboard model. In addition to the breadboard effort, a conceptual design of the corresponding flight system was generated and a full scale mockup fabricated. A preliminary CEI specification for the flight system was also prepared.

Development and Testing of a Completely Passive, Air Suspended, Air Propelled Personal Rapid Transit Vehicle

DOT National Transportation Integrated Search

1973-04-01

A prototype Uniflo vehicle base with mock-up superstructure was tested on 55 ft. of full-scale track. Sound treatment to meet NCA 60 at 25 ft. from the guideway enclosure and within the vehicle was proposed and the costs determined. A heating and coo...

NASA's first Orion full-scale abort flight test crew module was placed in NASA Dryden's Abort Flight Test integration area for equipment installation.

NASA Image and Video Library

2008-04-01

A full-scale flight-test mockup of the Constellation program's Orion crew vehicle arrived at NASA's Dryden Flight Research Center in late March 2008 to undergo preparations for the first short-range flight test of the spacecraft's astronaut escape system later that year. Engineers and technicians at NASA's Langley Research Center fabricated the structure, which precisely represents the size, outer shape and mass characteristics of the Orion space capsule. The Orion crew module mockup was ferried to NASA Dryden on an Air Force C-17. After painting in the Edwards Air Force Base paint hangar, the conical capsule was taken to Dryden for installation of flight computers, instrumentation and other electronics prior to being sent to the U.S. Army's White Sands Missile Range in New Mexico for integration with the escape system and the first abort flight test in late 2008. The tests were designed to ensure a safe, reliable method of escape for astronauts in case of an emergency.

NASA Dryden Flight Research Center personnel accompany NASA's first Orion full-scale abort flight test crew module as it heads to its new home.

NASA Image and Video Library

2008-04-01

A full-scale flight-test mockup of the Constellation program's Orion crew vehicle arrived at NASA's Dryden Flight Research Center in late March 2008 to undergo preparations for the first short-range flight test of the spacecraft's astronaut escape system later that year. Engineers and technicians at NASA's Langley Research Center fabricated the structure, which precisely represents the size, outer shape and mass characteristics of the Orion space capsule. The Orion crew module mockup was ferried to NASA Dryden on an Air Force C-17. After painting in the Edwards Air Force Base paint hangar, the conical capsule was taken to Dryden for installation of flight computers, instrumentation and other electronics prior to being sent to the U.S. Army's White Sands Missile Range in New Mexico for integration with the escape system and the first abort flight test in late 2008. The tests were designed to ensure a safe, reliable method of escape for astronauts in case of an emergency.

A NASA painter applies the first primer coat to NASA's Orion full-scale abort flight test crew module in the Edwards Air Force Base paint hangar.

NASA Image and Video Library

2008-03-29

A full-scale flight-test mockup of the Constellation program's Orion crew vehicle arrived at NASA's Dryden Flight Research Center in late March 2008 to undergo preparations for the first short-range flight test of the spacecraft's astronaut escape system later that year. Engineers and technicians at NASA's Langley Research Center fabricated the structure, which precisely represents the size, outer shape and mass characteristics of the Orion space capsule. The Orion crew module mockup was ferried to NASA Dryden on an Air Force C-17. After painting in the Edwards Air Force Base paint hangar, the conical capsule was taken to Dryden for installation of flight computers, instrumentation and other electronics prior to being sent to the U.S. Army's White Sands Missile Range in New Mexico for integration with the escape system and the first abort flight test in late 2008. The tests were designed to ensure a safe, reliable method of escape for astronauts in case of an emergency.

Paint shop technicians carefully apply masking prior to painting the Orion full-scale abort flight test crew module in the Edwards Air Force Base paint hangar.

NASA Image and Video Library

2008-03-29

A full-scale flight-test mockup of the Constellation program's Orion crew vehicle arrived at NASA's Dryden Flight Research Center in late March 2008 to undergo preparations for the first short-range flight test of the spacecraft's astronaut escape system later that year. Engineers and technicians at NASA's Langley Research Center fabricated the structure, which precisely represents the size, outer shape and mass characteristics of the Orion space capsule. The Orion crew module mockup was ferried to NASA Dryden on an Air Force C-17. After painting in the Edwards Air Force Base paint hangar, the conical capsule was taken to Dryden for installation of flight computers, instrumentation and other electronics prior to being sent to the U.S. Army's White Sands Missile Range in New Mexico for integration with the escape system and the first abort flight test in late 2008. The tests were designed to ensure a safe, reliable method of escape for astronauts in case of an emergency.

NASA paint shop technicians prepare the Orion full-scale flight test crew module for painting in the Edwards Air Force Base paint hangar.

NASA Image and Video Library

2008-03-29

A full-scale flight-test mockup of the Constellation program's Orion crew vehicle arrived at NASA's Dryden Flight Research Center in late March 2008 to undergo preparations for the first short-range flight test of the spacecraft's astronaut escape system later that year. Engineers and technicians at NASA's Langley Research Center fabricated the structure, which precisely represents the size, outer shape and mass characteristics of the Orion space capsule. The Orion crew module mockup was ferried to NASA Dryden on an Air Force C-17. After painting in the Edwards Air Force Base paint hangar, the conical capsule was taken to Dryden for installation of flight computers, instrumentation and other electronics prior to being sent to the U.S. Army's White Sands Missile Range in New Mexico for integration with the escape system and the first abort flight test in late 2008. The tests were designed to ensure a safe, reliable method of escape for astronauts in case of an emergency.

Experimental Plan for Crystal Accumulation Studies in the WTP Melter Riser

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

Miller, D.; Fowley, M.

2015-04-28

This experimental plan defines crystal settling experiments to be in support of the U.S. Department of Energy – Office of River Protection crystal tolerant glass program. The road map for development of crystal-tolerant high level waste glasses recommends that fluid dynamic modeling be used to better understand the accumulation of crystals in the melter riser and mechanisms of removal. A full-scale version of the Hanford Waste Treatment and Immobilization Plant (WTP) melter riser constructed with transparent material will be used to provide data in support of model development. The system will also provide a platform to demonstrate mitigation or recoverymore » strategies in off-normal events where crystal accumulation impedes melter operation. Test conditions and material properties will be chosen to provide results over a variety of parameters, which can be used to guide validation experiments with the Research Scale Melter at the Pacific Northwest National Laboratory, and that will ultimately lead to the development of a process control strategy for the full scale WTP melter. The experiments described in this plan are divided into two phases. Bench scale tests will be used in Phase 1 (using the appropriate solid and fluid simulants to represent molten glass and spinel crystals) to verify the detection methods and analytical measurements prior to their use in a larger scale system. In Phase 2, a full scale, room temperature mockup of the WTP melter riser will be fabricated. The mockup will provide dynamic measurements of flow conditions, including resistance to pouring, as well as allow visual observation of crystal accumulation behavior.« less

A SCALE-UP Mock-Up: Comparison of Student Learning Gains in High- and Low-Tech Active-Learning Environments.

PubMed

Soneral, Paula A G; Wyse, Sara A

2017-01-01

Student-centered learning environments with upside-down pedagogies (SCALE-UP) are widely implemented at institutions across the country, and learning gains from these classrooms have been well documented. This study investigates the specific design feature(s) of the SCALE-UP classroom most conducive to teaching and learning. Using pilot survey data from instructors and students to prioritize the most salient SCALE-UP classroom features, we created a low-tech "Mock-up" version of this classroom and tested the impact of these features on student learning, attitudes, and satisfaction using a quasi--experimental setup. The same instructor taught two sections of an introductory biology course in the SCALE-UP and Mock-up rooms. Although students in both sections were equivalent in terms of gender, grade point average, incoming ACT, and drop/fail/withdraw rate, the Mock-up classroom enrolled significantly more freshmen. Controlling for class standing, multiple regression modeling revealed no significant differences in exam, in-class, preclass, and Introduction to Molecular and Cellular Biology Concept Inventory scores between the SCALE-UP and Mock-up classrooms. Thematic analysis of student comments highlighted that collaboration and whiteboards enhanced the learning experience, but technology was not important. Student satisfaction and attitudes were comparable. These results suggest that the benefits of a SCALE-UP experience can be achieved at lower cost without technology features. © 2017 P. A. G. Soneral and S. A. Wyse. CBE—Life Sciences Education © 2017 The American Society for Cell Biology. This article is distributed by The American Society for Cell Biology under license from the author(s). It is available to the public under an Attribution–Noncommercial–Share Alike 3.0 Unported Creative Commons License (http://creativecommons.org/licenses/by-nc-sa/3.0).

A SCALE-UP Mock-Up: Comparison of Student Learning Gains in High- and Low-Tech Active-Learning Environments

PubMed Central

Soneral, Paula A. G.; Wyse, Sara A.

2017-01-01

Student-centered learning environments with upside-down pedagogies (SCALE-UP) are widely implemented at institutions across the country, and learning gains from these classrooms have been well documented. This study investigates the specific design feature(s) of the SCALE-UP classroom most conducive to teaching and learning. Using pilot survey data from instructors and students to prioritize the most salient SCALE-UP classroom features, we created a low-tech “Mock-up” version of this classroom and tested the impact of these features on student learning, attitudes, and satisfaction using a quasi-­experimental setup. The same instructor taught two sections of an introductory biology course in the SCALE-UP and Mock-up rooms. Although students in both sections were equivalent in terms of gender, grade point average, incoming ACT, and drop/fail/withdraw rate, the Mock-up classroom enrolled significantly more freshmen. Controlling for class standing, multiple regression modeling revealed no significant differences in exam, in-class, preclass, and Introduction to Molecular and Cellular Biology Concept Inventory scores between the SCALE-UP and Mock-up classrooms. Thematic analysis of student comments highlighted that collaboration and whiteboards enhanced the learning experience, but technology was not important. Student satisfaction and attitudes were comparable. These results suggest that the benefits of a SCALE-UP experience can be achieved at lower cost without technology features. PMID:28213582

Pipe crawler development for duct elbow removal

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

Zollinger, W.T.; Treanor, R.C.

1992-01-01

This paper describes the development of equipment for removing an elbow in a 36 inch diameter ventilation line by cutting from the inside. Radiation levels, high air flow and physical constraints preclude any manual rework of the ventilation system. A remotely operated pipe crawler was developed. Testing has been performed in a full-scale mockup which models the ventilation duct configuration with the exception of radiation levels. The results gathered from the testing are discussed, and illustrate the strengths and weaknesses of the crawler and plasma arc torch system. To date, the equipment has successfully completed the tasks of maneuvering throughmore » the duct geometry, performing the two required cuts, and backing out of the duct mockup. The elbow successfully fell away from the main duct, showing that the line would be clear of obstructions.« less

Pipe crawler development for duct elbow removal

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

Zollinger, W.T.; Treanor, R.C.

1992-11-01

This paper describes the development of equipment for removing an elbow in a 36 inch diameter ventilation line by cutting from the inside. Radiation levels, high air flow and physical constraints preclude any manual rework of the ventilation system. A remotely operated pipe crawler was developed. Testing has been performed in a full-scale mockup which models the ventilation duct configuration with the exception of radiation levels. The results gathered from the testing are discussed, and illustrate the strengths and weaknesses of the crawler and plasma arc torch system. To date, the equipment has successfully completed the tasks of maneuvering throughmore » the duct geometry, performing the two required cuts, and backing out of the duct mockup. The elbow successfully fell away from the main duct, showing that the line would be clear of obstructions.« less

Astronauts Thomas D. Akers and Kathryn C. Thornton during WETF training

NASA Image and Video Library

1993-03-05

S93-30238 (5 Mar 1993) --- Wearing training versions of Space Shuttle Extravehicular Mobility Units (EMU), astronauts Thomas D. Akers (red stripe) and Kathryn C. Thornton use the spacious pool of the Johnson Space Center's (JSC) Weightless Environment Training Facility (WET-F) to rehearse for the Hubble Space Telescope (HST) repair mission. They are working with a full scale mockup of a solar array fixture.

The lightcraft project

NASA Technical Reports Server (NTRS)

Messitt, Don G.; Myrabo, Leik N.

1991-01-01

Rensselaer Polytechnic Institute has been developing a transatmospheric 'Lightcraft' technology which uses beamed laser energy to propel advanced shuttle craft to orbit. In the past several years, Rensselaer students have analyzed the unique combined-cycle Lightcraft engine, designed a small unmanned Lightcraft Technology Demonstrator, and conceptualized larger manned Lightcraft - to name just a few of the interrelated design projects. The 1990-91 class carried out preliminary and detailed design efforts for a one-person 'Mercury' Lightcraft, using computer-aided design and finite-element structural modeling techniques. In addition, they began construction of a 2.6 m-diameter, full-scale engineering prototype mockup. The mockup will be equipped with three robotic legs that 'kneel' for passenger entry and exit. More importantly, the articulated tripod gear is crucial for accurately pointing at, and tracking the laser relay mirrors, a maneuver that must be performed just prior to liftoff. Also accomplished were further design improvements on a 6-inch-diameter Lightcraft model (for testing in RPI's hypersonic tunnel), and new laser propulsion experiments. The resultant experimental data will be used to calibrate Computational Fluid Dynamic (CFD) codes and analytical laser propulsion models that can simulate vehicle/engine flight conditions along a transatmospheric boost trajectory. These efforts will enable the prediction of distributed aerodynamic and thruster loads over the entire full-scale spacecraft.

Analysis of Photogrammetry Data from ISIM Mockup

NASA Technical Reports Server (NTRS)

Nowak, Maria; Hill, Mike

2007-01-01

During ground testing of the Integrated Science Instrument Module (ISIM) for the James Webb Space Telescope (JWST), the ISIM Optics group plans to use a Photogrammetry Measurement System for cryogenic calibration of specific target points on the ISIM composite structure and Science Instrument optical benches and other GSE equipment. This testing will occur in the Space Environmental Systems (SES) chamber at Goddard Space Flight Center. Close range photogrammetry is a 3 dimensional metrology system using triangulation to locate custom targets in 3 coordinates via a collection of digital photographs taken from various locations and orientations. These photos are connected using coded targets, special targets that are recognized by the software and can thus correlate the images to provide a 3 dimensional map of the targets, and scaled via well calibrated scale bars. Photogrammetry solves for the camera location and coordinates of the targets simultaneously through the bundling procedure contained in the V-STARS software, proprietary software owned by Geodetic Systems Inc. The primary objectives of the metrology performed on the ISIM mock-up were (1) to quantify the accuracy of the INCA3 photogrammetry camera on a representative full scale version of the ISIM structure at ambient temperature by comparing the measurements obtained with this camera to measurements using the Leica laser tracker system and (2), empirically determine the smallest increment of target position movement that can be resolved by the PG camera in the test setup, i.e., precision, or resolution. In addition, the geometrical details of the test setup defined during the mockup testing, such as target locations and camera positions, will contribute to the final design of the photogrammetry system to be used on the ISIM Flight Structure.

Advanced Spacesuit Portable Life Support System Packaging Concept Mock-Up Design & Development

NASA Technical Reports Server (NTRS)

O''Connell, Mary K.; Slade, Howard G.; Stinson, Richard G.

1998-01-01

A concentrated development effort was begun at NASA Johnson Space Center to create an advanced Portable Life Support System (PLSS) packaging concept. Ease of maintenance, technological flexibility, low weight, and minimal volume are targeted in the design of future micro-gravity and planetary PLSS configurations. Three main design concepts emerged from conceptual design techniques and were carried forth into detailed design, then full scale mock-up creation. "Foam", "Motherboard", and "LEGOtm" packaging design concepts are described in detail. Results of the evaluation process targeted maintenance, robustness, mass properties, and flexibility as key aspects to a new PLSS packaging configuration. The various design tools used to evolve concepts into high fidelity mock ups revealed that no single tool was all encompassing, several combinations were complimentary, the devil is in the details, and, despite efforts, many lessons were learned only after working with hardware.

KSC-2009-1661

NASA Image and Video Library

2009-02-16

CAPE CANAVERAL, Fla. – In high bay 4 of the Vehicle Assembly Building at NASA's Kennedy Space Center, workers lift the Ares I-X crew module mock-up during a fit check with a mock-up of the service module. When fully developed, the 16-foot diameter crew module will furnish living space and reentry protection for future astronauts, and the service module’s main engine will be used to break out of lunar orbit for the return trip to Earth. Ares I-X is the test flight for the Ares I, which is part of the Constellation Program to return men to the moon and beyond. The I-X flight will provide NASA an early opportunity to test and prove hardware, facilities and ground operations associated with Ares I launches. Targeted for the summer of 2009, the launch of the full-scale Ares I-X will be the first in a series of unpiloted rocket launches from Kennedy. Photo credit: NASA/Jack Pfaller

STS-122 Crew Members during Post Insertion / Deorbit Prepreparation in Building 9 NW

NASA Image and Video Library

2007-03-20

JSC2007-E-14482 (20 March 2007) --- Jerry L. Ross (center), chief, vehicle integration test office, poses for a photo with astronauts Stanley G. Love (left), European Space Agency's (ESA) Hans Schlegel, Leland D. Melvin and Rex J. Walheim, STS-122 mission specialists, as they prepare for a post insertion/de-orbit training session in one of the full-scale trainers (out of frame) in the Space Vehicle Mockup Facility at Johnson Space Center.

NASA Deputy Administrator Tours Bigelow Aerospace

NASA Image and Video Library

2011-02-04

NASA Deputy Administrator Lori Garver views the inside of a full scale mockup of Bigelow Aerospace's Space Station Alpha during a tour of the Bigelow Aerospace facilities by the company's President Robert Bigelow on Friday, Feb. 4, 2011, in Las Vegas. NASA has been discussing potential partnership opportunities with Bigelow for its inflatable habitat technologies as part of NASA's goal to develop innovative technologies to ensure that the U.S. remains competitive in future space endeavors. Photo Credit: (NASA/Bill Ingalls)

ORNL Pre-test Analyses of A Large-scale Experiment in STYLE

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

Williams, Paul T; Yin, Shengjun; Klasky, Hilda B

Oak Ridge National Laboratory (ORNL) is conducting a series of numerical analyses to simulate a large scale mock-up experiment planned within the European Network for Structural Integrity for Lifetime Management non-RPV Components (STYLE). STYLE is a European cooperative effort to assess the structural integrity of (non-reactor pressure vessel) reactor coolant pressure boundary components relevant to ageing and life-time management and to integrate the knowledge created in the project into mainstream nuclear industry assessment codes. ORNL contributes work-in-kind support to STYLE Work Package 2 (Numerical Analysis/Advanced Tools) and Work Package 3 (Engineering Assessment Methods/LBB Analyses). This paper summarizes the current statusmore » of ORNL analyses of the STYLE Mock-Up3 large-scale experiment to simulate and evaluate crack growth in a cladded ferritic pipe. The analyses are being performed in two parts. In the first part, advanced fracture mechanics models are being developed and performed to evaluate several experiment designs taking into account the capabilities of the test facility while satisfying the test objectives. Then these advanced fracture mechanics models will be utilized to simulate the crack growth in the large scale mock-up test. For the second part, the recently developed ORNL SIAM-PFM open-source, cross-platform, probabilistic computational tool will be used to generate an alternative assessment for comparison with the advanced fracture mechanics model results. The SIAM-PFM probabilistic analysis of the Mock-Up3 experiment will utilize fracture modules that are installed into a general probabilistic framework. The probabilistic results of the Mock-Up3 experiment obtained from SIAM-PFM will be compared to those results generated using the deterministic 3D nonlinear finite-element modeling approach. The objective of the probabilistic analysis is to provide uncertainty bounds that will assist in assessing the more detailed 3D finite-element solutions and to also assess the level of confidence that can be placed in the best-estimate finiteelement solutions.« less

Design and development of a Space Station proximity operations research and development mockup

NASA Technical Reports Server (NTRS)

Haines, Richard F.

1986-01-01

Proximity operations (Prox-Ops) on-orbit refers to all activities taking place within one km of the Space Station. Designing a Prox-Ops control station calls for a comprehensive systems approach which takes into account structural constraints, orbital dynamics including approach/departure flight paths, myriad human factors and other topics. This paper describes a reconfigurable full-scale mock-up of a Prox-Ops station constructed at Ames incorporating an array of windows (with dynamic star field, target vehicle(s), and head-up symbology), head-down perspective display of manned and unmanned vehicles, voice- actuated 'electronic checklist', computer-generated voice system, expert system (to help diagnose subsystem malfunctions), and other displays and controls. The facility is used for demonstrations of selected Prox-Ops approach scenarios, human factors research (work-load assessment, determining external vision envelope requirements, head-down and head-up symbology design, voice synthesis and recognition research, etc.) and development of engineering design guidelines for future module interiors.

KSC-2009-1660

NASA Image and Video Library

2009-02-16

CAPE CANAVERAL, Fla. – In high bay 4 of the Vehicle Assembly Building at NASA's Kennedy Space Center, workers lift the Ares I-X crew module mock-up from a work stand for a fit check with a mock-up of the service module. When fully developed, the 16-foot diameter crew module will furnish living space and reentry protection for future astronauts, and the service module’s main engine will be used to break out of lunar orbit for the return trip to Earth. Ares I-X is the test flight for the Ares I, which is part of the Constellation Program to return men to the moon and beyond. The I-X flight will provide NASA an early opportunity to test and prove hardware, facilities and ground operations associated with Ares I launches. Targeted for the summer of 2009, the launch of the full-scale Ares I-X will be the first in a series of unpiloted rocket launches from Kennedy. Photo credit: NASA/Jack Pfaller

KSC-2009-1664

NASA Image and Video Library

2009-02-16

CAPE CANAVERAL, Fla. – In high bay 4 of the Vehicle Assembly Building at NASA's Kennedy Space Center, workers position the Ares I-X crew module mock-up onto a mock-up of the service module during a fit check of the hardware. When fully developed, the 16-foot diameter crew module will furnish living space and reentry protection for future astronauts, and the service module’s main engine will be used to break out of lunar orbit for the return trip to Earth. Ares I-X is the test flight for the Ares I, which is part of the Constellation Program to return men to the moon and beyond. The I-X flight will provide NASA an early opportunity to test and prove hardware, facilities and ground operations associated with Ares I launches. Targeted for the summer of 2009, the launch of the full-scale Ares I-X will be the first in a series of unpiloted rocket launches from Kennedy. Photo credit: NASA/Jack Pfaller

KSC-2009-1663

NASA Image and Video Library

2009-02-16

CAPE CANAVERAL, Fla. – In high bay 4 of the Vehicle Assembly Building at NASA's Kennedy Space Center, workers lower the Ares I-X crew module mock-up onto a mock-up of the service module during a fit check of the hardware. When fully developed, the 16-foot diameter crew module will furnish living space and reentry protection for future astronauts, and the service module’s main engine will be used to break out of lunar orbit for the return trip to Earth. Ares I-X is the test flight for the Ares I, which is part of the Constellation Program to return men to the moon and beyond. The I-X flight will provide NASA an early opportunity to test and prove hardware, facilities and ground operations associated with Ares I launches. Targeted for the summer of 2009, the launch of the full-scale Ares I-X will be the first in a series of unpiloted rocket launches from Kennedy. Photo credit: NASA/Jack Pfaller

KSC-2009-1662

NASA Image and Video Library

2009-02-16

CAPE CANAVERAL, Fla. – In high bay 4 of the Vehicle Assembly Building at NASA's Kennedy Space Center, the Ares I-X crew module mock-up hangs suspended from a crane as it is moved for a fit check with a mock-up of the service module. When fully developed, the 16-foot diameter crew module will furnish living space and reentry protection for future astronauts, and the service module’s main engine will be used to break out of lunar orbit for the return trip to Earth. Ares I-X is the test flight for the Ares I, which is part of the Constellation Program to return men to the moon and beyond. The I-X flight will provide NASA an early opportunity to test and prove hardware, facilities and ground operations associated with Ares I launches. Targeted for the summer of 2009, the launch of the full-scale Ares I-X will be the first in a series of unpiloted rocket launches from Kennedy. Photo credit: NASA/Jack Pfaller

KSC-2009-1665

NASA Image and Video Library

2009-02-16

CAPE CANAVERAL, Fla. – In high bay 4 of the Vehicle Assembly Building at NASA's Kennedy Space Center, the Ares I-X crew module mock-up is positioned onto a mock-up of the service module to determine that the pieces of hardware are a perfect fit. When fully developed, the 16-foot diameter crew module will furnish living space and reentry protection for future astronauts, and the service module’s main engine will be used to break out of lunar orbit for the return trip to Earth. Ares I-X is the test flight for the Ares I, which is part of the Constellation Program to return men to the moon and beyond. The I-X flight will provide NASA an early opportunity to test and prove hardware, facilities and ground operations associated with Ares I launches. Targeted for the summer of 2009, the launch of the full-scale Ares I-X will be the first in a series of unpiloted rocket launches from Kennedy. Photo credit: NASA/Jack Pfaller

STS-131 crew training during FFT CCTV Lighting 91019 ( Lights Out).

NASA Image and Video Library

2009-11-16

JSC2009-E-240951 (16 Nov. 2009) --- Japan Aerospace Exploration Agency (JAXA) astronaut Naoko Yamazaki (foreground) and NASA astronaut Stephanie Wilson, both STS-131 mission specialists, participate in a Full Fuselage Trainer (FFT) mock-up training session in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center. United Space Alliance (USA) instructor David L. Williams assisted the crew members.

NASA Enterprise Visual Analysis

NASA Technical Reports Server (NTRS)

Lopez-Tellado, Maria; DiSanto, Brenda; Humeniuk, Robert; Bard, Richard, Jr.; Little, Mia; Edwards, Robert; Ma, Tien-Chi; Hollifield, Kenneith; White, Chuck

2007-01-01

NASA Enterprise Visual Analysis (NEVA) is a computer program undergoing development as a successor to Launch Services Analysis Tool (LSAT), formerly known as Payload Carrier Analysis Tool (PCAT). NEVA facilitates analyses of proposed configurations of payloads and packing fixtures (e.g. pallets) in a space shuttle payload bay for transport to the International Space Station. NEVA reduces the need to use physical models, mockups, and full-scale ground support equipment in performing such analyses. Using NEVA, one can take account of such diverse considerations as those of weight distribution, geometry, collision avoidance, power requirements, thermal loads, and mechanical loads.

STS-115 crew during suited egress training on the Full Fuselage Trainer (FFT) mockup.

NASA Image and Video Library

2005-04-05

JSC2005-E-13817 (5 April 2005) --- Astronaut Steven G. MacLean, STS-115 mission specialist representing the Canadian Space Agency, attired in a training version of the shuttle launch and entry suit, awaits the start of an emergency egress training session in the Space Vehicle Mockup Facility at the Johnson Space Center. Astronaut Heidemarie M. Stefanyshyn-Piper, mission specialist, is visible in the background.

Simulating clefts in pumpkin balloons

NASA Astrophysics Data System (ADS)

Baginski, Frank; Brakke, Kenneth

2010-02-01

The geometry of a large axisymmetric balloon with positive differential pressure, such as a sphere, leads to very high film stresses. These stresses can be significantly reduced by using a tendon re-enforced lobed pumpkin-like shape. A number of schemes have been proposed to achieve a cyclically symmetric pumpkin shape, including the constant bulge angle (CBA) design, the constant bulge radius (CBR) design, CBA/CBR hybrids, and NASA’s recent constant stress (CS) design. Utilizing a hybrid CBA/CBR pumpkin design, Flight 555-NT in June 2006 formed an S-cleft and was unable to fully deploy. In order to better understand the S-cleft phenomenon, a series of inflation tests involving four 27-m diameter 200-gore pumpkin balloons were conducted in 2007. One of the test vehicles was a 1/3-scale mockup of the Flight 555-NT balloon. Using an inflation procedure intended to mimic ascent, the 1/3-scale mockup developed an S-cleft feature strikingly similar to the one observed in Flight 555-NT. Our analysis of the 1/3-scale mockup found it to be unstable. We compute asymmetric equilibrium configurations of this balloon, including shapes with an S-cleft feature.

Safety divers prepare HST mockup in the Neutral Buoyancy Simulator at MSFC

NASA Image and Video Library

1993-06-01

Safety divers in the Neutral Buoyancy Simulator (NBS) at the Marshall Space Flight Center (MSFC) prepare a mockup of the Hubble Space Telescope (HST) for one of 32 separate training sessions conducted by four of the STS-61 crew members in June. The three-week process allowed mission trainers to refine the timelines for the five separate spacewalks scheduled to be conducted on the actual mission scheduled for December 1993. The HST is separated into two pieces since the water tank depth cannot support the entire structure in one piece. The full length payload bay mockup shows the Solar Array Carrier in the foreground and the various containers that will house replacement hardware that will be carried on the mission.

Comfort and Accessibility Evaluation of Light Rail Vehicles

NASA Astrophysics Data System (ADS)

Hirasawa, Takayuki; Matsuoka, Shigeki; Suda, Yoshihiro

A quantitative evaluation method for passenger rooms of light rail vehicles from viewpoint of comfort and accessibility is proposed as the result of physical modeling of in-vehicle behavior of passengers upon Gibson's ecological psychology approach. The model parameters are identified from experiments at real vehicles at the depot of Kumamoto municipal transport and at the full-scale mockup of the University of Tokyo. The developed model has realized quantitative evaluation of floor lowering effects by abolishing internal steps at passenger doorways and door usage restriction scenarios from viewpoint of both passengers and operators in comparison to commuter railway vehicles.

Crystal accumulation in the Hanford Waste Treatment Plant high level waste melter: Summary of 2017 experiments

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

Fox, K.; Fowley, M.

A full-scale, transparent mock-up of the Hanford Tank Waste Treatment and Immobilization Project High Level Waste glass melter riser and pour spout has been constructed to allow for testing with visual feedback of particle settling, accumulation, and resuspension when operating with a controlled fraction of crystals in the glass melt. Room temperature operation with silicone oil and magnetite particles simulating molten glass and spinel crystals, respectively, allows for direct observation of flow patterns and settling patterns. The fluid and particle mixture is recycled within the system for each test.

James Webb Space Telescope (JWST): The First Light Machine

NASA Technical Reports Server (NTRS)

Stahl, Philip

2009-01-01

This slide presentation review the mission objective, the organization of the mission planning, the design, and testing of the James Webb Space Telescope (JWST). There is also information about the orbit, in comparison to the Hubble Space Telescope, the mirror design, and the science instruments. Pictures of the full scale mockup of the JWST are given. A brief history of the universe is also presented from the big bang through the formation of galaxies, and the planets, to life itself. One of the goals of the JWST is to search for extra solar planets and then to search for signs of life.

Refurbishment cost study of the thermal protection system of a space shuttle vehicle, phase 2

NASA Technical Reports Server (NTRS)

Haas, D. W.

1972-01-01

The labor costs and techniques associated with the refurbishment and maintenance of representative thermal protection system (TPS) components and their attachment concepts suitable for space shuttle application are defined, characterized, and evaluated from the results of an experimental test program. This program consisted of designing selected TPS concepts, fabricating and assembling test hardware, and performing a time and motion study of specific maintenance functions of the test hardware on a full-scale- mockup. Labor requirements and refurbishment techniques, as they relate to the maintenance functions of inspection, repair, removal, and replacement were identified.

Final Report: Characterization of Canister Mockup Weld Residual Stresses

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

Enos, David; Bryan, Charles R.

2016-12-01

Stress corrosion cracking (SCC) of interim storage containers has been indicated as a high priority data gap by the Department of Energy (DOE) (Hanson et al., 2012), the Electric Power Research Institute (EPRI, 2011), the Nuclear Waste Technical Review Board (NWTRB, 2010a), and the Nuclear Regulatory Commission (NRC, 2012a, 2012b). Uncertainties exist in terms of the environmental conditions that prevail on the surface of the storage containers, the stress state within the container walls associated both with weldments as well as within the base metal itself, and the electrochemical properties of the storage containers themselves. The goal of the workmore » described in this document is to determine the stress states that exists at various locations within a typical storage canister by evaluating the properties of a full-diameter cylindrical mockup of an interim storage canister. This mockup has been produced using the same manufacturing procedures as the majority of the fielded spent nuclear fuel interim storage canisters. This document describes the design and procurement of the mockup and the characterization of the stress state associated with various portions of the container. It also describes the cutting of the mockup into sections for further analyses, and a discussion of the potential impact of the results from the stress characterization effort.« less

STS-29 MS Bagian during post landing egress exercises in JSC FFT mockup

NASA Image and Video Library

1988-05-26

S88-38355 (27 May 1988) --- Astronaut James P. Bagian lowers himself from the top of one of the full-fuselage trainer in JSC's Shuttle mockup and integration laboratory during a post-landing, over-the-top emergency egress test. Bagian, a M.D., and one of three mission specialists assigned to NASA STS-29 flight of the Discovery, is working with engineers evaluating egress using the new crew escape equipment that includes a parachute harness.

STS-48 Commander Creighton, in LES, stands at JSC FFT side hatch

NASA Technical Reports Server (NTRS)

1991-01-01

STS-48 Discovery, Orbiter Vehicle (OV) 103, Commander John O. Creighton, wearing a launch and entry suit (LES), stands at the side hatch of JSC's full fuselage trainer (FFT). Creighton will enter the FFT shuttle mockup through the side hatch and take his assigned position on the forward flight deck. Creighton, along with the other crewmembers, is participating in a post-landing emergency egress exercise. The FFT is located in the Mockup and Integration Laboratory (MAIL) Bldg 9A.

Documentation of STS-88 Node evaluation

NASA Image and Video Library

1997-09-08

S97-11949 (8 Sept 1997) --- Wearing training versions of the Shuttle Extravehicular Mobility Unit (EMU) space suit, astronauts Jerry L. Ross (left), and James Newman perform the first training session in the Neutral Buoyancy Laboratory (NBL) of the Sonny Carter Training Facility. The training was actually a dress rehearsal of three Extravehicular Activity?s (EVA) the pair will conduct during the July 1998 flight (STS-88) -- the first International Space Station (ISS) assembly mission. During the six-hour training session, the crew practiced hooking up power and data cables between full-scale mockups of the Functional Cargo Block and the United States-built Node 1 (foreground).

KSC-2009-1529

NASA Image and Video Library

2009-02-10

CAPE CANAVERAL, Fla. – In high bay 4 of the Vehicle Assembly Building at NASA's Kennedy Space Center, the Ares I-X mock-up crew module displays the newly applied window decals. Ares I-X is the test flight for the Ares I. The I-X flight will provide NASA an early opportunity to test and prove hardware, facilities and ground operations associated with Ares I. The launch of full-scale Ares I-X, targeted for July 2009, will be the first in a series of unpiloted rocket launches from Kennedy. When fully developed, the 16-foot diameter crew module will furnish living space and reentry protection for the astronauts. Photo credit: NASA/Tim Jacobs

KSC-2009-1528

NASA Image and Video Library

2009-02-10

CAPE CANAVERAL, Fla. – In high bay 4 of the Vehicle Assembly Building at NASA's Kennedy Space Center, a worker applies a window decal on the Ares I-X mock-up crew module. Ares I-X is the test flight for the Ares I. The I-X flight will provide NASA an early opportunity to test and prove hardware, facilities and ground operations associated with Ares I. The launch of full-scale Ares I-X, targeted for July 2009, will be the first in a series of unpiloted rocket launches from Kennedy. When fully developed, the 16-foot diameter crew module will furnish living space and reentry protection for the astronauts. Photo credit: NASA/Tim Jacobs

KSC-2009-1527

NASA Image and Video Library

2009-02-10

CAPE CANAVERAL, Fla. – In high bay 4 of the Vehicle Assembly Building at NASA's Kennedy Space Center, a worker applies a window decal on the Ares I-X mock-up crew module. Ares I-X is the test flight for the Ares I. The I-X flight will provide NASA an early opportunity to test and prove hardware, facilities and ground operations associated with Ares I. The launch of full-scale Ares I-X, targeted for July 2009, will be the first in a series of unpiloted rocket launches from Kennedy. When fully developed, the 16-foot diameter crew module will furnish living space and reentry protection for the astronauts. Photo credit: NASA/Tim Jacobs

Development of ECT/UT inspection system for bottom mounted instrumentation nozzle of PWR reactor vessels

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

Tanaka, H.; Fukui, S.; Iwahashi, Y.

1994-12-31

The development of inspection technique and tool for Bottom Mounted Instrument (BMI) nozzle of PWR plant was performed for countermeasure of leakage accident at incore instrument nozzle of Hamaoka-1 (BWR). MHI achieved the following development, of which object was PWR Plant R/V: (1) development of ECT/UT Multi-sensored Probe; (2) development of Inspection System (3) development of Data Processing System. The Inspection System had been functionally tested using full scale mock-up. As the result of the functional test, this system was confirmed to be very effective, and assumed to be hopeful for the actual application on site.

Experimental evaluation of the Skylab orbital workshop ventilation system concept

NASA Technical Reports Server (NTRS)

Allums, S. L.; Hastings, L. J.; Ralston, J. T.

1972-01-01

Extensive testing was conducted to evaluate the Orbital Workshop ventilation concept. Component tests were utilized to determine the relationship between operating characteristics at 1 and 0.34 atm. System tests were conducted at 1 atm within the Orbital Workshop full-scale mockup to assess delivered volumetric flow rate and compartment air velocities. Component tests with the Anemostat circular diffusers (plenum- and duct-mounted) demonstrated that the diffuser produced essentially equivalent airflow patterns and velocities in 1- and 0.34-atm environments. The tests also showed that the pressure drop across the diffuser could be scaled from 1 to 0.34 atm using the atmosphere pressure ratio. Fan tests indicated that the performance of a multiple, parallel-mounted fan cluster could be predicted by summing the single-fan flow rates at a given delta P.

A SCALE-UP Mock-Up: Comparison of Student Learning Gains in High- and Low-Tech Active-Learning Environments

ERIC Educational Resources Information Center

Soneral, Paula A. G.; Wyse, Sara A.

2017-01-01

Student-centered learning environments with upside-down pedagogies (SCALE-UP) are widely implemented at institutions across the country, and learning gains from these classrooms have been well documented. This study investigates the specific design feature(s) of the SCALE-UP classroom most conducive to teaching and learning. Using pilot survey…

STS-48 Pilot Reightler and MS Brown, in LESs, stand at JSC FFT side hatch

NASA Technical Reports Server (NTRS)

1991-01-01

STS-48 Discovery, Orbiter Vehicle (OV) 103, Pilot Kenneth S. Reightler, Jr (left) and Mission Specialist (MS) Mark N. Brown, wearing launch and entry suits (LESs), stand at the side hatch of JSC's full fuselage trainer (FFT). The crewmembers will enter the FFT shuttle mockup through the side hatch and take their assigned descent (landing) positions in the crew cabin. Reightler and Brown, along with the other crewmembers, are participating in a post-landing emergency egress exercise. The FFT is located in the Mockup and Integration Laboratory (MAIL) Bldg 9A.

Simulation of the human-telerobot interface on the Space Station

NASA Technical Reports Server (NTRS)

Stuart, Mark A.; Smith, Randy L.

1993-01-01

Many issues remain unresolved concerning the components of the human-telerobot interface presented in this work. It is critical that these components be optimally designed and arranged to ensure, not only that the overall system's goals are met, but but that the intended end-user has been optimally accommodated. With sufficient testing and evaluation throughout the development cycle, the selection of the components to use in the final telerobotic system can promote efficient, error-free performance. It is recommended that whole-system simulation with full-scale mockups be used to help design the human-telerobot interface. It is contended that the use of simulation can facilitate this design and evaluation process.

Investigation of wellbore microannulus permeability under stress via experimental wellbore mock-up and finite element modeling

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

Gomez, Steven P.; Sobolik, Steve R.; Matteo, Edward N.

This research aims to describe the microannulus region of the cement sheath-steel casing interface in terms of its compressibility and permeability. Here, a wellbore system mock-up was used for lab-scale testing, and was subjected to confining and casing pressures in a pressure vessel while measuring gas flow along the specimen’s axis. The flow was interpreted as the hydraulic aperture of the microannuli. Numerical joint models were used to calculate stress and displacement conditions of the microannulus region, where the mechanical stiffness and hydraulic aperture were altered in response to the imposed stress state and displacement across the joint interface.

Investigation of wellbore microannulus permeability under stress via experimental wellbore mock-up and finite element modeling

DOE PAGES

Gomez, Steven P.; Sobolik, Steve R.; Matteo, Edward N.; ...

2016-11-16

This research aims to describe the microannulus region of the cement sheath-steel casing interface in terms of its compressibility and permeability. Here, a wellbore system mock-up was used for lab-scale testing, and was subjected to confining and casing pressures in a pressure vessel while measuring gas flow along the specimen’s axis. The flow was interpreted as the hydraulic aperture of the microannuli. Numerical joint models were used to calculate stress and displacement conditions of the microannulus region, where the mechanical stiffness and hydraulic aperture were altered in response to the imposed stress state and displacement across the joint interface.

The design, fabrication and installation of cable routing mockups in support of Spacelab 2

NASA Technical Reports Server (NTRS)

1981-01-01

From flight and mockup drawings of Spacelab 2 (SL 2) experiments and hardware, shop ready mockup drawings were produced. Floor panels were the first items considered for fabrication. Cold plate and orthogrid mockups were designed and fabricated. Experiment and other hardware mockups were fabricated of aluminum or plywood, depending on size and configuration. Eighty-three cable routing bracket mockups were fabricated of aluminum and delivered for painting.

Simulation research: A vital step for human missions to Mars

NASA Astrophysics Data System (ADS)

Perino, Maria Antonietta; Apel, Uwe; Bichi, Alessandro

The complex nature of the challenge as humans embark on exploration missions beyond Earth orbit will require that, in the early stages, simulation facilities be established at least on Earth. Suitable facilities in Low Earth Orbit and on the Moon surface would provide complementary information of critical importance for the overall design of a human mission to Mars. A full range of simulation campaigns is required, in fact, to reach a better understanding of the complexities involved in exploration missions that will bring humans back to the Moon and then outward to Mars. The corresponding simulation means may range from small scale environmental simulation chambers and/or computer models that will aid in the development of new materials, to full scale mock-ups of spacecraft and planetary habitats and/or orbiting infrastructues. This paper describes how a suitable simulation campaign will contribute to the definition of the required countermeasures with respect to the expected duration of the flight. This will allow to be traded contermeasure payload and astronaut time against effort in technological development of propulsion systems.

Electro-osmotic fluxes in multi-well electro-remediation processes.

PubMed

López-Vizcaíno, Rubén; Sáez, Cristina; Mena, Esperanza; Villaseñor, Jose; Cañizares, Pablo; Rodrigo, Manuel A

2011-01-01

In recent years, electrokinetic techniques on a laboratory scale have been studied but few applications have been assessed at full-scale. In this work, a mock-up plant with two rows of three electrodes positioned in semipermeable electrolyte wells has been used to study the electro-osmotic flux distribution. Water accumulated in the cathodic wells when an electric voltage gradient was applied between the two electrode-well rows. Likewise, slight differences in the water flux were observed depending on the position and number of electrodes used and on the voltage gradient applied. Results show that the electro-osmotic flow did not increase proportionally with the number of electrodes used. During the start-up of the study, there was an abrupt change in the current density, pH and conductivity of the soil portions closest to electrodic wells due to electrokinetic processes. These differences can be explained in terms of the complex current distributions from anode and cathode rows.

MMU development at the Martin Marietta plant in Denver, Colorado

NASA Image and Video Library

1980-07-25

S80-36889 (24 July 1980) --- Astronaut Bruce McCandless II uses a simulator at Martin Marietta?s space center near Denver to develop flight techniques for a backpack propulsion unit that will be used on Space Shuttle flights. The manned maneuvering unit (MMU) training simulator allows astronauts to "fly missions" against a full scale mockup of a portion of the orbiter vehicle. Controls of the simulator are like those of the actual MMU. Manipulating them allows the astronaut to move in three straight-line directions and in pitch, yaw and roll. One possible application of the MMU is for an extravehicular activity chore to repair damaged tiles on the vehicle. McCandless is wearing an extravehicular mobility unit (EMU).

Engineering the Future: Cell 6

NASA Technical Reports Server (NTRS)

Stahl, P. H.

2010-01-01

This slide presentation reviews the development of the James Webb Space Telescope (JWST), explaining the development using a systems engineering methodology. Included are slides showing the organizational chart, the JWST Science Goals, the size of the primary mirror, and full scale mockups of the JSWT. Also included is a review of the JWST Optical Telescope Requirements, a review of the preliminary design and analysis, the technology development required to create the JWST, with particular interest in the specific mirror technology that was required, and views of the mirror manufacturing process. Several slides review the process of verification and validation by testing and analysis, including a diagram of the Cryogenic Test Facility at Marshall, and views of the primary mirror while being tested in the cryogenic facility.

Technology demonstration of space intravehicular automation and robotics

NASA Technical Reports Server (NTRS)

Morris, A. Terry; Barker, L. Keith

1994-01-01

Automation and robotic technologies are being developed and capabilities demonstrated which would increase the productivity of microgravity science and materials processing in the space station laboratory module, especially when the crew is not present. The Automation Technology Branch at NASA Langley has been working in the area of intravehicular automation and robotics (IVAR) to provide a user-friendly development facility, to determine customer requirements for automated laboratory systems, and to improve the quality and efficiency of commercial production and scientific experimentation in space. This paper will describe the IVAR facility and present the results of a demonstration using a simulated protein crystal growth experiment inside a full-scale mockup of the space station laboratory module using a unique seven-degree-of-freedom robot.

Project M: Scale Model of Lunar Landing Site of Apollo 17: Focus on Lighting Conditions and Analysis

NASA Technical Reports Server (NTRS)

Vanik, Christopher S.; Crain, Timothy P.

2010-01-01

This document captures the research and development of a scale model representation of the Apollo 17 landing site on the moon as part of the NASA INSPIRE program. Several key elements in this model were surface slope characteristics, crater sizes and locations, prominent rocks, and lighting conditions. This model supports development of Autonomous Landing and Hazard Avoidance Technology (ALHAT) and Project M for the GN&C Autonomous Flight Systems Branch. It will help project engineers visualize the landing site, and is housed in the building 16 Navigation Systems Technology Lab. The lead mentor was Dr. Timothy P. Crain. The purpose of this project was to develop an accurate scale representation of the Apollo 17 landing site on the moon. This was done on an 8'2.5"X10'1.375" reduced friction granite table, which can be restored to its previous condition if needed. The first step in this project was to research the best way to model and recreate the Apollo 17 landing site for the mockup. The project required a thorough plan, budget, and schedule, which was presented to the EG6 Branch for build approval. The final phase was to build the model. The project also required thorough research on the Apollo 17 landing site and the topography of the moon. This research was done on the internet and in person with Dean Eppler, a space scientist, from JSC KX. This data was used to analyze and calculate the scale of the mockup and the ratio of the sizes of the craters, ridges, etc. The final goal was to effectively communicate project status and demonstrate the multiple advantages of using our model. The conclusion of this project was that the mockup was completed as accurately as possible, and it successfully enables the Project M specialists to visualize and plan their goal on an accurate three dimensional surface representation.

Tritium, deuterium, and helium permeation through EPDM O-rings

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

Swansiger, W.A.

1992-03-01

This paper discusses tritium permeabilities determined at room temperature, 1.0 MPa (150 psia) tritium for three 23.4 cm diameter EPDM (ethylene-propylene-diene monomer) O-rings using a full-scale mock-up of the Al-SX shipping container seal geometry. The AL-SX container is being developed by Sandia National Laboratories for shipping tritium reservoirs. To determine the tritium permeation rate as a function of temperature, a 50.8 mm diameter EPDM O-ring was tested from room temperature to 150{degrees}C at a pressure of 1.0 MPa. Additional permeation measurements were made under the following test conditions: deuterium and helium-4 at room temperature and a pressure of 1.0 MPamore » using the full-scale AL-SX fixture, tritium from 0.1 MPa to 1.0 MPa at 142{degrees}C using the 50.8 mm fixture, and deuterium form room temperature to 150{degrees}C at a pressure of 1.0 MPa using the three full-scale O-rings showed the average room temperature, 1.0 MPa steady state tritium permeation rate to be about 1 {times} 10{sup {minus}2} Pa-liter/sec (7.6 {times} 10{sup {minus}5} torr-liter/sec or 1 {times} 10{sup {minus}4} std cc/sec), well within the allowable limit of 7.1 {times} 10{sup {minus}2} Pa-liter/sec for tritium release form the AL-SX container.« less

Digitally-bypassed transducers: interfacing digital mockups to real-time medical equipment.

PubMed

Sirowy, Scott; Givargis, Tony; Vahid, Frank

2009-01-01

Medical device software is sometimes initially developed by using a PC simulation environment that executes models of both the device and a physiological system, and then later by connecting the actual medical device to a physical mockup of the physiological system. An alternative is to connect the medical device to a digital mockup of the physiological system, such that the device believes it is interacting with a physiological system, but in fact all interaction is entirely digital. Developing medical device software by interfacing with a digital mockup enables development without costly or dangerous physical mockups, and enables execution that is faster or slower than real time. We introduce digitally-bypassed transducers, which involve a small amount of hardware and software additions, and which enable interfacing with digital mockups.

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

Miller, N. J.; Koltai, R. N.; McGowan, T. K.

The GATEWAY program followed two pedestrian-scale lighting projects that required multiple mockups – one at Stanford University in California and the other at Chautauqua Institution in upstate New York. The report provides insight into pedestrian lighting criteria, how they differ from street and area lighting criteria, and how solid-state lighting can be better applied in pedestrian applications.

Human Factors Evaluations of Two-Dimensional Spacecraft Conceptual Layouts

NASA Technical Reports Server (NTRS)

Kennedy, Kriss J.; Toups, Larry D.; Rudisill, Marianne

2010-01-01

Much of the human factors work done in support of the NASA Constellation lunar program has been with low fidelity mockups. These volumetric replicas of the future lunar spacecraft allow researchers to insert test subjects from the engineering and astronaut population and evaluate the vehicle design as the test subjects perform simulations of various operational tasks. However, lunar outpost designs must be evaluated without the use of mockups, creating a need for evaluation tools that can be performed on two-dimension conceptual spacecraft layouts, such as floor plans. A tool based on the Cooper- Harper scale was developed and applied to one lunar scenario, enabling engineers to select between two competing floor plan layouts. Keywords: Constellation, human factors, tools, processes, habitat, outpost, Net Habitable Volume, Cooper-Harper.

In-pile testing of ITER first wall mock-ups at relevant thermal loading conditions

NASA Astrophysics Data System (ADS)

Litunovsky, N.; Gervash, A.; Lorenzetto, P.; Mazul, I.; Melder, R.

2009-04-01

The paper describes the experimental technique and preliminary results of thermal fatigue testing of ITER first wall (FW) water-cooled mock-ups inside the core of the RBT-6 experimental fission reactor (RIAR, Dimitrovgrad, Russia). This experiment has provided simultaneous effect of neutron fluence and thermal cycling damages on the mock-ups. A PC-controlled high-temperature graphite ohmic heater was applied to provide cyclic thermal load onto the mock-ups surface. This experiment lasted for 309 effective irradiation days with a final damage level (CuCrZr) of 1 dpa in the mock-ups. About 3700 thermal cycles with a heat flux of 0.4-0.5 MW/m 2 onto the mock-ups were realized before the heater fails. Then, irradiation was continued in a non-cycling mode.

Experimental detailed power distribution in a fast spectrum thermionic reactor fuel element at the core/BeO reflector interface region

NASA Technical Reports Server (NTRS)

Klann, P. G.; Lantz, E.

1973-01-01

A zero-power critical assembly was designed, constructed, and operated for the prupose of conducting a series of benchmark experiments dealing with the physics characteristics of a UN-fueled, Li-7-cooled, Mo-reflected, drum-controlled compact fast reactor for use with a space-power conversion system. The critical assembly was modified to simulate a fast spectrum advanced thermionics reactor by: (1) using BeO as a reflector in place of some of the existing molybdenum, (2) substituting Nb-1Zr tubing for some of the existing Ta tubing, and (3) inserting four full-scale mockups of thermionic type fuel elements near the core and BeO reflector boundary. These mockups were surrounded with a buffer zone having the equivalent thermionic core composition. In addition to measuring the critical mass of this thermionic configuration, a detailed power distribution in one of the thermionic element stages in the mixed spectrum region was measured. A power peak to average ratio of two was observed for this fuel stage at the midplane of the core and adjacent to the reflector. Also, the power on the outer surface adjacent to the BeO was slightly more than a factor of two larger than the power on the inside surface of a 5.08 cm (2.0 in.) high annular fuel segment with a 2.52 cm (0.993 in. ) o.d. and a 1.86 cm (0.731 in.) i.d.

Technicians complete assembly of Hubble Space Telescope (HST) mockup at JSC

NASA Technical Reports Server (NTRS)

1989-01-01

Technicians complete assembly of the Hubble Space Telescope (HST) mockup at JSC's Mockup and Integration Laboratory (MAIL) Bldg 9A. In the foreground, a technician holds the controls for an overhead crane attached to one of the HST's high gain antennas (HGAs). Technicians on the ground prepare the HGA to be hoisted into position on the mockup's Support System Module (SSM) forward shell as others work on SSM from a cherry picker.

Heritage Gallery

NASA Technical Reports Server (NTRS)

2002-01-01

Marshall Space Flight Center's (MSFC's) building 4200 hosts a new spaceflight history museum referred to as the Heritage Gallery, allowing employees and visitors alike to have the opportunity to experience history first hand. On display are many models of launch vehicles and spacecraft that have made the center famous. It features a full-scale mockup of the lunar roving vehicle, three built-in multimedia displays, a large theater screen, and two glass cases that house memorabilia such as personal items belonging to Wernher von Braun, MSFC's first Center Director. The new Heritage Gallery features the accomplishments of several past and present members of the Marshall team. Attending the ribbon cutting ceremony are: (left to right) Gerhard Reisig; Cort Durocher, executive director of the American Institute of Aeronautics and Astronautics; Ernst Stuhlinger; Konrad Darnenburg; Werner Dahm; Walter Jacobi; and host of event, Center Director Art Stephenson.

Thermoelectric temperature control system for the pushbroom microwave radiometer (PBMR)

NASA Technical Reports Server (NTRS)

Dillon-Townes, L. A.; Averill, R. D.

1984-01-01

A closed loop thermoelectric temperature control system is developed for stabilizing sensitive RF integrated circuits within a microwave radiometer to an accuracy of + or - 0.1 C over a range of ambient conditions from -20 C to +45 C. The dual mode (heating and cooling) control concept utilizes partial thermal isolation of the RF units from an instrument deck which is thermally controlled by thermoelectric coolers and thin film heaters. The temperature control concept is simulated with a thermal analyzer program (MITAS) which consists of 37 nodes and 61 conductors. A full scale thermal mockup is tested in the laboratory at temperatures of 0 C, 21 C, and 45 C to confirm the validity of the control concept. A flight radiometer and temperature control system is successfully flight tested on the NASA Skyvan aircraft.

Around Marshall

NASA Image and Video Library

2002-10-30

Marshall Space Flight Center's (MSFC's) building 4200 hosts a new spaceflight history museum referred to as the Heritage Gallery, allowing employees and visitors alike to have the opportunity to experience history first hand. On display are many models of launch vehicles and spacecraft that have made the center famous. It features a full-scale mockup of the lunar roving vehicle, three built-in multimedia displays, a large theater screen, and two glass cases that house memorabilia such as personal items belonging to Wernher von Braun, MSFC's first Center Director. The new Heritage Gallery features the accomplishments of several past and present members of the Marshall team. Attending the ribbon cutting ceremony are: (left to right) Gerhard Reisig; Cort Durocher, executive director of the American Institute of Aeronautics and Astronautics; Ernst Stuhlinger; Konrad Darnenburg; Werner Dahm; Walter Jacobi; and host of event, Center Director Art Stephenson.

Technicians assembly the Hubble Space Telescope (HST) mockup at JSC

NASA Technical Reports Server (NTRS)

1989-01-01

At JSC's Mockup and Integration Laboratory (MAIL) Bldg 9A, technicians install a high gain antenna (HGA) on the Hubble Space Telescope (HST) mockup. On the ground a technician operates the controls for the overhead crane that is lifting the HGA into place on the Support System Module (SSM) forward shell. Others in a cherry picker basket wait for the HGA to near its final position so they can secure it on the mockup.

Recent High Heat Flux Tests on W-Rod-Armored Mockups

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

NYGREN,RICHARD E.; YOUCHISON,DENNIS L.; MCDONALD,JIMMIE M.

2000-07-18

In the authors initial high heat flux tests on small mockups armored with W rods, done in the small electron beam facility (EBTS) at Sandia National Laboratories, the mockups exhibited excellent thermal performance. However, to reach high heat fluxes, they reduced the heated area to only a portion ({approximately}25%) of the sample. They have now begun tests in their larger electron beam facility, EB 1200, where the available power (1.2 MW) is more than enough to heat the entire surface area of the small mockups. The initial results indicate that, at a given power, the surface temperatures of rods inmore » the EB 1200 tests is somewhat higher than was observed in the EBTS tests. Also, it appears that one mockup (PW-10) has higher surface temperatures than other mockups with similar height (10mm) W rods, and that the previously reported values of absorbed heat flux on this mockup were too high. In the tests in EB 1200 of a second mockup, PW-4, absorbed heat fluxes of {approximately}22MW/m{sup 2} were reached but the corresponding surface temperatures were somewhat higher than in EBTS. A further conclusion is that the simple 1-D model initially used in evaluating some of the results from the EBTS testing was not adequate, and 3-D thermal modeling will be needed to interpret the results.« less

NASA Dryden technicians work on a fit-check mockup in preparation for systems installation work on an Orion boilerplate crew capsule for launch abort testing.

NASA Image and Video Library

2008-01-24

NASA Dryden technicians work on a fit-check mockup in preparation for systems installation work on an Orion boilerplate crew capsule for launch abort testing. A mockup Orion crew module has been constructed by NASA Dryden Flight Research Center's Fabrication Branch. The mockup is being used to develop integration procedures for avionics and instrumentation in advance of the arrival of the first abort flight test article.

NASA Dryden technicians take measurements inside a fit-check mockup for prior to systems installation on a boilerplate Orion launch abort test crew capsule.

NASA Image and Video Library

2008-01-24

NASA Dryden technicians take measurements inside a fit-check mockup for prior to systems installation on a boilerplate Orion launch abort test crew capsule. A mockup Orion crew module has been constructed by NASA Dryden Flight Research Center's Fabrication Branch. The mockup is being used to develop integration procedures for avionics and instrumentation in advance of the arrival of the first abort flight test article.

Technicians complete assembly of Hubble Space Telescope (HST) mockup at JSC

NASA Technical Reports Server (NTRS)

1989-01-01

A technician listens to instructions as he operates the controls for the overhead crane that is lifting one of the Hubble Space Telescope (HST) high gain antennas (HGAs) into place on the HST Support System Module (SSM) forward shell. Others in a cherry picker basket wait to install the HGA on the SSM mockup. The HST mockup will be used for astronaut training and is being assembled in JSC's Mockup and Integration Laboratory (MAIL) Bldg 9A.

Characterization of flaws in a tube bundle mock-up for reliability studies

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

Kupperman, D.S.; Bakhtiari, S.

1997-02-01

As part of an assessment of in-service inspection of steam generator tubes, the authors will assemble a steam generator mock-up for round robin studies and use as a test bed in evaluating emerging technologies. Progress is reported on the characterization of flaws that will be part of the mock-up. Eddy current and ultrasonic techniques are being evaluated as a means to characterize the flaws in the mock-up tubes before final assembly. Twenty Inconel 600 tubes with laboratory-grown cracks, typical of those to be used in the mock-up, were provided by Pacific Northwest National Laboratory for laboratory testing. After the tubesmore » were inspected with eddy current and ultrasonic techniques, they were destructively analyzed to establish the actual depths, lengths, and profiles of the cracks. The analysis of the results will allow the best techniques to be used for characterizing the flaws in the mock-up tubes.« less

Experimental investigation of MHD pressure losses in a mock-up of a liquid metal blanket

NASA Astrophysics Data System (ADS)

Mistrangelo, C.; Bühler, L.; Brinkmann, H.-J.

2018-03-01

Experiments have been performed to investigate the influence of a magnetic field on liquid metal flows in a scaled mock-up of a helium cooled lead lithium (HCLL) blanket. During the experiments pressure differences between points on the mock-up have been recorded for various values of flow rate and magnitude of the imposed magnetic field. The main contributions to the total pressure drop in the test-section have been identified as a function of characteristic flow parameters. For sufficiently strong magnetic fields the non-dimensional pressure losses are practically independent on the flow rate, namely inertia forces become negligible. Previous experiments on MHD flows in a simplified test-section for a HCLL blanket showed that the main contributions to the total pressure drop in a blanket module originate from the flow in the distributing and collecting manifolds. The new experiments confirm that the largest pressure drops occur along manifolds and near the first wall of the blanket module, where the liquid metal passes through small openings in the stiffening plates separating two breeder units. Moreover, the experimental data shows that with the present manifold design the flow does not distribute homogeneously among the 8 stacked boxes that form the breeding zone.

Quantifying air distribution, ventilation effectiveness and airborne pollutant transport in an aircraft cabin mockup

NASA Astrophysics Data System (ADS)

Wang, Aijun

The health, safety and comfort of passengers during flight inspired this research into cabin air quality, which is closely related to its airflow distribution, ventilation effectiveness and airborne pollutant transport. The experimental facility is a full-scale aircraft cabin mockup. A volumetric particle tracking velocimetry (VPTV) technique was enhanced by incorporating a self-developed streak recognition algorithm. Two stable recirculation regions, the reverse flows above the seats and the main air jets from the air supply inlets formed the complicated airflow patterns inside the cabin mockup. The primary air flow was parallel to the passenger rows. The small velocity component in the direction of the cabin depth caused less net air exchange between the passenger rows than that parallel to the passenger rows. Different total air supply rate changed the developing behaviors of the main air jets, leading to different local air distribution patterns. Two indices, Local mean age of air and ventilation effectiveness factor (VEF), were measured at five levels of air supply rate and two levels of heating load. Local mean age of air decreased linearly with an increase in the air supply rate, while the VEF remained consistent when the air supply rate varied. The thermal buoyancy force from the thermal plume generated the upside plume flow, opposite to the main jet flow above the boundary seats and thus lowered the local net air exchange. The airborne transport dynamics depends on the distance between the source and the receptors, the relative location of pollutant source, and air supply rate. Exposure risk was significantly reduced with increased distance between source and receptors. Another possible way to decrease the exposure risk was to position the release source close to the exhaust outlets. Increasing the air supply rate could be an effective solution under some emergency situations. The large volume of data regarding the three-dimensional air velocities was visualized in the CAVE virtual environment. ShadowLight, a virtual reality application was used to import and navigate the velocity vectors through the virtual airspace. A real world demonstration and an active interaction with the three-dimensional air velocity data have been established.

STS_135_PostInsertion

NASA Image and Video Library

2011-03-24

JSC2011-E-040273 (24 March 2011) --- NASA astronaut Chris Ferguson, STS-135 commander, is reflected in a mirror before participating in a post-insertion training session in the Full-Fuselage Trainer in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center in Houston March 24, 2011. Photo credit: NASA Photo/Houston Chronicle, Smiley N. Pool

Student experimenter stands near middeck lockers in JSC Bldg 9A mockup

NASA Technical Reports Server (NTRS)

1991-01-01

Student experimenter Constantine Costes, STS-42 Commander Ronald J. Grabe, STS-42 Mission Specialist (MS) William F. Readdy, and Integration Engineer Neal Christie discuss Coates' student experiment 83-02 (SE 83-02) entitled 'Zero-G Capillary Rise of Liquid through Granular Porous Media' in JSC Mockup and Integration Laboratory Bldg 9A Full Fuselage Trainer (FFT). On FFT middeck, Costes stands behind Readdy (kneeling) as Christie demonstrates experiment setup and Grabe looks on (47326). The team also examines experiment components at middeck stowage locker (47323) and at FFT open side hatch (47324, 47325). The experiment is designed to investigate the capillary and forced flow characteristics of blue-tinted water in three glass tubes with three sizes of glass beads. SE 83-02 is scheduled to be flown on STS-42 aboard Discovery, Orbiter Vehicle (OV) 103.

ITER-FEAT vacuum vessel and blanket design features and implications for the R&D programme

NASA Astrophysics Data System (ADS)

Ioki, K.; Dänner, W.; Koizumi, K.; Krylov, V. A.; Cardella, A.; Elio, F.; Onozuka, M.; ITER Joint Central Team; ITER Home Teams

2001-03-01

A configuration in which the vacuum vessel (VV) fits tightly to the plasma aids the passive plasma vertical stability, and ferromagnetic material in the VV reduces the toroidal field ripple. The blanket modules are supported directly by the VV. A full scale VV sector model has provided critical information related to fabrication technology and for testing the magnitude of welding distortions and achievable tolerances. This R&D validated the fundamental feasibility of the double wall VV design. The blanket module configuration consists of a shield body to which a separate first wall is mounted. The separate first wall has a facet geometry consisting of multiple flat panels, where 3-D machining will not be required. A configuration with deep slits minimizes the induced eddy currents and loads. The feasibility and robustness of solid hot isostatic pressing joining were demonstrated in the R&D by manufacturing and testing several small and medium scale mock-ups and finally two prototypes. Remote handling tests and assembly tests of a blanket module have demonstrated the basic feasibility of its installation and removal.

IVA the robot: Design guidelines and lessons learned from the first space station laboratory manipulation system

NASA Technical Reports Server (NTRS)

Konkel, Carl R.; Powers, Allen K.; Dewitt, J. Russell

1991-01-01

The first interactive Space Station Freedom (SSF) lab robot exhibit was installed at the Space and Rocket Center in Huntsville, AL, and has been running daily since. IntraVehicular Activity (IVA) the robot is mounted in a full scale U.S. Lab (USL) mockup to educate the public on possible automation and robotic applications aboard the SSF. Responding to audio and video instructions at the Command Console, exhibit patrons may prompt IVA to perform a housekeeping task or give a speaking tour of the module. Other exemplary space station tasks are simulated and the public can even challenge IVA to a game of tic tac toe. In anticipation of such a system being built for the Space Station, a discussion is provided of the approach taken, along with suggestions for applicability to the Space Station Environment.

Retired Astronaut John Blaha at opening of new International Space Station Center at KSC

NASA Technical Reports Server (NTRS)

1998-01-01

Retired Astronaut John Blaha celebrates the official opening of the new International Space Station (ISS) Center at Kennedy Space Center as he steps out of a full-scale mockup of one of the station modules. Modules through which visitors can walk that are included in the new tour attraction are the Habitation Unit, where station crew members will live, sleep, and work; a Laboratory Module; and the Pressurized Logistics Module, where racks and supplies will be transported back and forth from KSC to space. Guests also can take an elevated walkway to a gallery overlooking the work area where actual ISS hardware is prepared for flight into space. This new tour site, in addition to a new Launch Complex 39 Observation Gantry, are part of a comprehensive effort by NASA and Delaware North to expand and improve the KSC public tour and visitor facilities.

Fast Ion Effects During Test Blanket Module Simulation Experiments in DIII-D

NASA Astrophysics Data System (ADS)

Kramer, G. J.; Budny, R.; Nazikian, R.; Heidbrink, W. W.; Kurki-Suonio, T.; Salmi, A.; Schaffer, M. J.; van Zeeland, M. A.; Shinohara, K.; Snipes, J. A.; Spong, D.

2010-11-01

The fast beam-ion confinement in the presence of a scaled mock-up of two Test Blanket Modules (TBM) for ITER was studied in DIII-D. The TBM on DIII-D has four vertically arranged protective carbon tiles with thermocouples placed at the back of each tile. Temperature increases of up to 200^oC were measured for the two tiles closest to the midplane when the TBM fields were present. These measurements agree qualitatively with results from the full orbit-following beam-ion code, SPIRAL, that predict beam-ion losses to be localized on the central two carbon tiles when the TBM fields present. Within the experimental uncertainties no significant change in the fast-ion population was found in the core of these plasmas which is consistent with SPIRAL analysis. These experiments indicate that the TBM fields do not affect the fast-ion confinement in a harmful way which is good news for ITER.

Design, fabrication and test of a trace contaminant control system

NASA Technical Reports Server (NTRS)

1975-01-01

A trace contaminant control system was designed, fabricated, and evaluated to determine suitability of the system concept to future manned spacecraft. Two different models were considered. The load model initially required by the contract was based on the Space Station Prototype (SSP) general specifications SVSK HS4655, reflecting a change from a 9 man crew to a 6 man crew of the model developed in previous phases of this effort. Trade studies and a system preliminary design were accomplished based on this contaminant load, including computer analyses to define the optimum system configuration in terms of component arrangements, flow rates and component sizing. At the completion of the preliminary design effort a revised contaminant load model was developed for the SSP. Additional analyses were then conducted to define the impact of this new contaminant load model on the system configuration. A full scale foam-core mock-up with the appropriate SSP system interfaces was also fabricated.

Emergency in-flight egress opening for general aviation aircraft

NASA Technical Reports Server (NTRS)

Bement, L. J.

1980-01-01

In support of a stall/spin research program, an emergency in-flight egress system is being installed in a light general aviation airplane. To avoid a major structural redesign for a mechanical door, an add-on 11.2 kg pyrotechnic-actuated system was developed to create an opening in the existing structure. The airplane skin will be explosively severed around the side window, across a central stringer, and down to the floor, creating an opening of approximately 76 by 76 cm. The severed panel will be jettisoned at an initial velocity of approximately 13.7 m/sec. System development included a total of 68 explosive severance tests on aluminum material using small samples, small and full scale flat panel aircraft structural mock-ups, and an actual aircraft fuselage. These tests proved explosive sizing/severance margins, explosive initiation, explosive product containment, and system dynamics.

The heat removal capability of actively cooled plasma-facing components for the ITER divertor

NASA Astrophysics Data System (ADS)

Missirlian, M.; Richou, M.; Riccardi, B.; Gavila, P.; Loarer, T.; Constans, S.

2011-12-01

Non-destructive examination followed by high-heat-flux testing was performed for different small- and medium-scale mock-ups; this included the most recent developments related to actively cooled tungsten (W) or carbon fibre composite (CFC) armoured plasma-facing components. In particular, the heat-removal capability of these mock-ups manufactured by European companies with all the main features of the ITER divertor design was investigated both after manufacturing and after thermal cycling up to 20 MW m-2. Compliance with ITER requirements was explored in terms of bonding quality, heat flux performances and operational compatibility. The main results show an overall good heat-removal capability after the manufacturing process independent of the armour-to-heat sink bonding technology and promising behaviour with respect to thermal fatigue lifetime under heat flux up to 20 MW m-2 for the CFC-armoured tiles and 15 MW m-2 for the W-armoured tiles, respectively.

STS_135_PostInsertion

NASA Image and Video Library

2011-03-24

JSC2011-E-040277 (24 March 2011) --- NASA astronaut Sandy Magnus, STS-135 mission specialist, practices the use of a digital camera with a long telephoto lens as she participates in a post-insertion training session in the Full-Fuselage Trainer in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center in Houston March 24, 2011. Photo credit: NASA Photo/Houston Chronicle, Smiley N. Pool

Sub-Scale Analysis of New Large Aircraft Pool Fire-Suppression

DTIC Science & Technology

2016-01-01

discrete ordinates radiation and single step Khan and Greeves soot model provided radiation and soot interaction. Agent spray dynamics were...Notable differences observed showed a modeled increase in the mockup surface heat-up rate as well as a modeled decreased rate of soot production...488 K SUPPRESSION STARTED  Large deviation between sensors due to sensor alignment challenges and asymmetric fuel surface ignition  Unremarkable

STS-117 Crew Training during suited PI/DO Prep in CCT-II mockup

NASA Image and Video Library

2006-08-03

JSC2006-E-32682 (3 Aug. 2006) --- Attired in training versions of their shuttle launch and landing suits, astronauts Patrick G. Forrester (left) and Frederick W. (Rick) Sturckow, STS-117 mission specialist and commander, respectively, participate in a training session in the high fidelity mockup/trainers in the Space Vehicle Mockup Facility at Johnson Space Center. Trainer Robert H. Tomaro assisted Forrester and Sturckow.

Design guidelines for robotically serviceable hardware

NASA Technical Reports Server (NTRS)

Gordon, Scott A.

1988-01-01

Research being conducted at the Goddard Space Flight Center into the development of guidelines for the design of robotically serviceable spaceflight hardware is described. A mock-up was built based on an existing spaceflight system demonstrating how these guidelines can be applied to actual hardware. The report examines the basic servicing philosophy being studied and how this philosophy is reflected in the formulation of design guidelines for robotic servicing. A description of the mock-up is presented with emphasis on the design features that make it robot friendly. Three robotic servicing schemes fulfilling the design guidelines were developed for the mock-up. These servicing schemes are examined as to how their implementation was affected by the constraints of the spacecraft system on which the mock-up is based.

Building 9 ISS mock-ups and trainers

NASA Image and Video Library

1999-08-02

Photographic documentation showing the bldg. 9 ISS module mock-ups and trainers. Views include: various overall views of the configuration of the ISS module trainers on the floor of bldg. 9 (08445-46, 08449-51, 08458-61, 08464-65, 08469, 08471, 08476); various portions of the mock-ups (08447-48, 08470); views of the Node 2, Experiment Module and Logistics Module (08452); Node 2 (08453, 08466); Destiny and Node 2 (08454); Destiny, Unity and Airlock (08455); Zarya, Service Module and shuttle mock-ups (08456); Logistics Module and Experiment Module (08457, 08468); various views of Columbia, Node 2 and Destiny (08462-63); Columbus, Node 2, Experiment Module and Logistics Module (08467); U.S. Laboratory module (08472); Logistics Module (08473); module layout (08474); Logistics Module and Experiment Module (08475).

STS-58 crewmembers prepare for a training exercise

NASA Image and Video Library

1993-07-20

S93-38672 (20 July 1993) --- Wearing training versions of the partial pressure launch and entry garment, the STS-58 crewmembers prepare for a training exercise. After being briefed by astronaut John E. Blaha (right), mission commander, the group rehearsed contingency evacuation procedures. Most of the training session took part in the crew compartment and full fuselage trainers in the Space Shuttle mockup and integration laboratory.

Neutron Tomography Using Mobile Neutron Generators for Assessment of Void Distributions in Thermal Hydraulic Test Loops

NASA Astrophysics Data System (ADS)

Andersson, P.; Bjelkenstedt, T.; Sundén, E. Andersson; Sjöstrand, H.; Jacobsson-Svärd, S.

Detailed knowledge of the lateral distribution of steam (void) and water in a nuclear fuel assembly is of great value for nuclear reactor operators and fuel manufacturers, with consequences for both reactor safety and economy of operation. Therefore, nuclear relevant two-phase flows are being studied at dedicated thermal-hydraulic test loop, using two-phase flow systems ranging from simplified geometries such as heated circular pipes to full scale mock-ups of nuclear fuel assemblies. Neutron tomography (NT) has been suggested for assessment of the lateral distribution of steam and water in such test loops, motivated by a good ability of neutrons to penetrate the metallic structures of metal pipes and nuclear fuel rod mock-ups, as compared to e.g. conventional X-rays, while the liquid water simultaneously gives comparatively good contrast. However, these stationary test loops require the measurement setup to be mobile, which is often not the case for NT setups. Here, it is acknowledged that fast neutrons of 14 MeV from mobile neutron generators constitute a viable option for a mobile NT system. We present details of the development of neutron tomography for this purpose at the division of Applied Nuclear Physics at Uppsala University. Our concept contains a portable neutron generator, exploiting the fusion reaction of deuterium and tritium, and a detector with plastic scintillator elements designed to achieveadequate spatial and energy resolution, all mounted in a light-weight frame without collimators or bulky moderation to allow for a mobile instrument that can be moved about the stationary thermal hydraulic test sections. The detector system stores event-to-event pulse-height information to allow for discrimination based on the energy deposition in the scintillator elements.

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

Carter, E.E.; Welty, B.D.

Molten wax shows considerable promise as a fixative and dust control agent in demolition of radioactively contaminated facilities. Sticky molten wax, modified with special surfactants and wetting agents, is capable of not only coating materials but also penetrating into friable or dusty materials and making them incapable of becoming airborne during demolition. Wax also shows significant promise for stabilization of waste residuals that may be contained in buildings undergoing demolition. Some of the building materials that have been tested to date include concrete, wood, sheet rock, fiber insulation, lime, rock, and paper. Protective clothing, clay, sand, sulfur, and bentonite claymore » have been tested as surrogates for certain waste materials that may be encountered during building demolition. The paper describes several potential applications of molten wax for dust control in demolition of radioactive contaminated facilities. As a case-study, this paper describes a research test performed for a pipeline closure project being completed by the Idaho Cleanup Project at the Idaho National Laboratory. The project plans to excavate and remove a section of buried Duriron drain piping containing highly radioactive and friable and 'flighty' waste residuals. A full-scale pipeline mockup containing simulated waste was buried in sand to simulate the direct buried subsurface condition of the subject piping. The pipeline was pre-heated by drawing hot air through the line with a HEPA vacuum blower unit. Molten wax was pumped into the line and allowed to cool. The line was then broken apart in various places to evaluate the permeation performance of the wax. The wax fully permeated all the surrogate materials rendering them non-friable with a consistency similar to modeling clay. Based on the performance during the mockup, it is anticipated that the wax will be highly effective in controlling the spread of radiological contamination during pipe demolition activities. (authors)« less

Spacecraft Internal Acoustic Environment Modeling

NASA Technical Reports Server (NTRS)

Chu, Shao-Sheng R.; Allen Christopher S.

2010-01-01

Acoustic modeling can be used to identify key noise sources, determine/analyze sub-allocated requirements, keep track of the accumulation of minor noise sources, and to predict vehicle noise levels at various stages in vehicle development, first with estimates of noise sources, later with experimental data. This paper describes the implementation of acoustic modeling for design purposes by incrementally increasing model fidelity and validating the accuracy of the model while predicting the noise of sources under various conditions. During FY 07, a simple-geometry Statistical Energy Analysis (SEA) model was developed and validated using a physical mockup and acoustic measurements. A process for modeling the effects of absorptive wall treatments and the resulting reverberation environment were developed. During FY 08, a model with more complex and representative geometry of the Orion Crew Module (CM) interior was built, and noise predictions based on input noise sources were made. A corresponding physical mockup was also built. Measurements were made inside this mockup, and comparisons were made with the model and showed excellent agreement. During FY 09, the fidelity of the mockup and corresponding model were increased incrementally by including a simple ventilation system. The airborne noise contribution of the fans was measured using a sound intensity technique, since the sound power levels were not known beforehand. This is opposed to earlier studies where Reference Sound Sources (RSS) with known sound power level were used. Comparisons of the modeling result with the measurements in the mockup showed excellent results. During FY 10, the fidelity of the mockup and the model were further increased by including an ECLSS (Environmental Control and Life Support System) wall, associated closeout panels, and the gap between ECLSS wall and mockup wall. The effect of sealing the gap and adding sound absorptive treatment to ECLSS wall were also modeled and validated.

STS-47 MS Jemison extends side hatch mockup CES pole during JSC training

NASA Technical Reports Server (NTRS)

1992-01-01

STS-47 Endeavour, Orbiter Vehicle (OV) 105, Mission Specialist (MS) Mae C. Jemison extends crew escape system (CES) pole through a side hatch mockup during launch emergency egress (bailout) training in JSC's Mockup and Integration Laboratory (MAIL) Bldg 9A. MS Jerome Apt (right) looks on. The crewmembers practiced extending the CES pole prior to donning their launch and entry suits (LESs) and conducting the simulation in the Crew Compartment Trainer (CCT).

STS-56 Commander Cameron & Pilot Oswald at CCT hatch during JSC training

NASA Image and Video Library

1992-12-01

STS-56 Discovery, Orbiter Vehicle (OV) 103, Commander Kenneth Cameron (right) and Pilot Stephen S. Oswald, wearing launch and entry suits (LESs), stand at the side hatch of the crew compartment trainer (CCT), a shuttle mockup, prior to entering the mockup. Once inside the CCT, they will don their launch and entry helmets (LEHs) and participate in emergency egress (bailout) procedures. The CCT is located in JSC's Mockup and Integration Laboratory (MAIL) Bldg 9NE.

Servicers system demonstration plan and capability development

NASA Technical Reports Server (NTRS)

Bulboaca, M. A.; Cuseo, J. A.; Derocher, W. L., Jr.; Maples, R. W.; Reynolds, P. C.; Sterrett, R. A.

1985-01-01

A plan for the demonstration of the exchange of Multi-Mission Modular Spacecraft (MMS) modules using the servicer mechanism Engineering Test Unit (ETU) was prepared and executed. The plan included: establishment of requirements, conceptual design, selection of MMS spacecraft mockup configuration, selection of MMS module mockup configuration, evaluation of adequacy of ETU load capability, and selection of a stowage rack arrangement. The MMS module exchange demonstration mockup equipment was designed, fabricated, checked out, shipped, installed, and demonstrated.

Skylab

NASA Image and Video Library

1967-09-01

This September 1967 photograph shows workmen removing a mockup of the Saturn V S-IVB stage that housed the Skylab Orbital Workshop (OWS) from the Marshall Space Flight Center (MSFC), building 4755. The mockup was shipped to McDornell Douglas in Huntington, California for design modifications. NASA used the mockup as an engineering design tool to plan structures, equipment, and experiments for Skylab, an orbiting space laboratory. The MSFC had program management responsibility for the development of Skylab hardware and experiments, including the OWS.

Student experimenter stands near middeck lockers in JSC Bldg 9A mockup

NASA Image and Video Library

1991-09-18

S91-47323 (18 Sept 1991) --- Constantine Costes, left, a student experimenter sponsored by United Space Boosters Inc, in Huntsville, Alabama, discusses his student experiment, "Zero-G Rise of Liquid Through Porous Media" with astronauts Ronald J. Grabe (right), STS 42 mission commander; and William Readdy, mission specialist. The student experimenter and crew members are in the Full Fuselage Trainer (FFT) in the Shuttle Mockup and Integration Laboratory. While attending Randolph School, a high school in Huntsville, Alabama, Costes was chosen in the national competition to participate in the Shuttle Student Involvement Program (SSIP). The experiment, contained in a middeck locker, involves the investigation of the effects of gravity on the flow characteristics of a fluid. Both pure capillary and forced flow behavior will be investigated. A ground based experiment was conducted so that gravity influenced data can be compared to that gathered in weightlessness. Costes is now a candidate for a Ph.D in mathematics at Harvard University.

Evaluation of NDE Round-Robin Exercises Using the NRC Steam Generator Mockup at Argonne National Laboratory

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

Muscara, Joseph; Kupperman, David S.; Bakhtiari, Sasab

2002-07-01

This paper discusses round-robin exercises using the NRC steam generator (SG) mock-up at Argonne National Laboratory to assess inspection reliability. The purpose of the round robins was to assess the current reliability of SG tubing inservice inspection, determine the probability of detection (POD) as function of flaw size or severity, and assess the capability for sizing of flaws. For the round robin and subsequent evaluation completed in 2001, eleven teams participated. Bobbin and rotating coil mock-up data collected by qualified industry personnel were evaluated. The mock-up contains hundreds of cracks and simulations of artifacts such as corrosion deposits and tubemore » support plates that make detection and characterization of cracks more difficult in operating steam generators than in most laboratory situations. An expert Task Group from industry, Argonne National Laboratory, and the NRC have reviewed the signals from the laboratory-grown cracks used in the mock-up to ensure that they provide reasonable simulations of those obtained in the field. The mock-up contains 400 tube openings. Each tube contains nine 22.2-mm (7/8-in.) diameter, 30.5-cm (1-ft) long, Alloy 600 test sections. The flaws are located in the tube sheet near the roll transition zone (RTZ), in the tube support plate (TSP), and in the free-span. The flaws are primarily intergranular stress corrosion cracks (axial and circumferential, ID and OD) though intergranular attack (IGA) wear and fatigue cracks are also present, as well as cracks in dents. In addition to the simulated tube sheet and TSP the mock-up has simulated sludge and magnetite deposits. A multiparameter eddy current algorithm, validated for mock-up flaws, provided a detailed isometric plot for every flaw and was used to establish the reference state of defects in the mock-up. The detection results for the 11 teams were used to develop POD curves as a function of maximum depth, voltage and the parameter m p, for the various types of flaws. The POD curves were represented as linear logistic curves, and the curve parameters were determined by the method of Maximum Likelihood. The effect of both statistical uncertainties inherent in sampling from distributions and the uncertainties due to errors in the estimates of maximum depth and m p was investigated. The 95% one-sided confidence limits (OSL), which include errors in maximum depth estimates, are presented along with the POD curves. For the second round robin a reconfigured mock-up is being used to evaluate the effectiveness of eddy current array probes. The primary emphasis is on the X-Probe. Progress with the X-Probe round robin is discussed in this paper. (authors)« less

Time-to-burnout data for a prototypical ITER divertor tube during a simulated loss of flow accident

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

Marshall, T.D.; Watson, R.D.; McDonald, J.M.

The Loss of Flow Accident (LOFA) is a serious safety concern for the International Thermonuclear Experimental Reactor (ITER) as it has been suggested that greater than 100 seconds are necessary to safely shutdown the plasma when ITER is operating at full power. In this experiment, the thermal response of a prototypical ITER divertor tube during a simulated LOFA was studied. The divertor tube was fabricated from oxygen-free high-conductivity copper to have a square geometry with a circular coolant channel. The coolant channel inner diameter was 0.77 cm, the heated length was 4.0 cm, and the heated width was 1.6 cm.more » The mockup did not feature any flow enhancement techniques, i.e., swirl tape, helical coils, or internal fins. One-sided surface heating of the mockup was accomplished through the use of the 30 kW Sandia Electron Beam Test System. After reaching steady state temperatures in the mockup, as determined by two Type-K thermocouples installed 0.5 mm beneath the heated surface, the coolant pump was manually tripped off and the coolant flow allowed to naturally coast down. Electron beam heating continued after the pump trip until the divertor tube`s heated surface exhibited the high temperature transient normally indicative of rapidly approaching burnout. Experimental data showed that time-to-burnout increases proportionally with increasing inlet velocity and decreases proportionally with increasing incident heat flux.« less

Plasma cleaning of ITER edge Thomson scattering mock-up mirror in the EAST tokamak

NASA Astrophysics Data System (ADS)

Yan, Rong; Moser, Lucas; Wang, Baoguo; Peng, Jiao; Vorpahl, Christian; Leipold, Frank; Reichle, Roger; Ding, Rui; Chen, Junling; Mu, Lei; Steiner, Roland; Meyer, Ernst; Zhao, Mingzhong; Wu, Jinhua; Marot, Laurent

2018-02-01

First mirrors are the key element of all optical and laser diagnostics in ITER. Facing the plasma directly, the surface of the first mirrors could be sputtered by energetic particles or deposited with contaminants eroded from the first wall (tungsten and beryllium), which would result in the degradation of the reflectivity. The impurity deposits emphasize the necessity of the first mirror in situ cleaning for ITER. The mock-up first mirror system for ITER edge Thomson scattering diagnostics has been cleaned in EAST for the first time in a tokamak using radio frequency capacitively coupled plasma. The cleaning properties, namely the removal of contaminants and homogeneity of cleaning were investigated with molybdenum mirror insets (25 mm diameter) located at five positions over the mock-up plate (center to edge) on which 10 nm of aluminum oxide, used as beryllium proxy, were deposited. The cleaning efficiency was evaluated using energy dispersive x-ray spectroscopy, reflectivity measurements and x-ray photoelectron spectroscopy. Using argon or neon plasma without magnetic field in the laboratory and with a 1.7 T magnetic field in the EAST tokamak, the aluminum oxide films were homogeneously removed. The full recovery of the mirrors’ reflectivity was attained after cleaning in EAST with the magnetic field, and the cleaning efficiency was about 40 times higher than that without the magnetic field. All these results are promising for the plasma cleaning baseline scenario of ITER.

Placement of direct composite veneers utilizing a silicone buildup guide and intraoral mock-up.

PubMed

Behle, C

2000-04-01

The indications for direct composite resins have recently been expanded to include predictable and convenient application in the aesthetic zone. The availability of composite materials with improved physical and optical characteristics facilitates the development of enhanced aesthetics while maintaining vital function. This article presents a simplified technique that combines function with aesthetics by utilizing an intraoral composite mock-up for initial communication and a lingual/incisal silicone stent of the mock-up to transfer the information to the definitive restorative buildup.

STS-56 Commander Cameron and Pilot Oswald at CCT hatch during JSC training

NASA Technical Reports Server (NTRS)

1993-01-01

STS-56 Discovery, Orbiter Vehicle (OV) 103, Commander Kenneth Cameron (right) and Pilot Stephen S. Oswald, wearing launch and entry suits (LESs), stand at the side hatch of the crew compartment trainer (CCT), a shuttle mockup, prior to entering the mockup. Once inside the CCT, they will don their launch and entry helmets (LEHs) and participate in emergency egress (bailout) procedures. The CCT is located in JSC's Mockup and Integration Laboratory (MAIL) Bldg 9NE.

Design concepts for the Centrifuge Facility Life Sciences Glovebox

NASA Technical Reports Server (NTRS)

Sun, Sidney C.; Horkachuck, Michael J.; Mckeown, Kellie A.

1989-01-01

The Life Sciences Glovebox will provide the bioisolated environment to support on-orbit operations involving non-human live specimens and samples for human life sceinces experiments. It will be part of the Centrifuge Facility, in which animal and plant specimens are housed in bioisolated Habitat modules and transported to the Glovebox as part of the experiment protocols supported by the crew. At the Glovebox, up to two crew members and two habitat modules must be accommodated to provide flexibility and support optimal operations. This paper will present several innovative design concepts that attempt to satisfy the basic Glovebox requirements. These concepts were evaluated for ergonomics and ease of operations using computer modeling and full-scale mockups. The more promising ideas were presented to scientists and astronauts for their evaluation. Their comments, and the results from other evaluations are presented. Based on the evaluations, the authors recommend designs and features that will help optimize crew performance and facilitate science accommodations, and specify problem areas that require further study.

Illuminance and luminance distributions of a prototype ambient illumination system for Space Station Freedom

NASA Technical Reports Server (NTRS)

Mullican, R. C.; Hayes, B. C.

1991-01-01

Preliminary results of research conducted in the late 1970's indicate that perceptual qualities of an enclosure can be influenced by the distribution of illumination within the enclosure. Subjective impressions such as spaciousness, perceptual clarity, and relaxation or tenseness, among others, appear to be related to different combinations of surface luminance. A prototype indirect ambient illumination system was developed which will allow crew members to alter surface luminance distributions within an enclosed module, thus modifying perceptual cues to match crew preferences. A traditional lensed direct lighting system was compared to the prototype utilizing the full-scale mockup of Space Station Freedom developed by Marshall Space Flight Center. The direct lensed system was installed in the habitation module with the indirect prototype deployed in the U.S. laboratory module. Analysis centered on the illuminance and luminance distributions resultant from these systems and the implications of various luminaire spacing options. All test configurations were evaluated for compliance with NASA Standard 3000, Man-System Integration Standards.

Design Concept for a Minimal Volume Spacecraft Cabin to Serve as a Mars Ascent Vehicle Cabin and Other Alternative Pressurized Vehicle Cabins

NASA Technical Reports Server (NTRS)

Howard, Robert L., Jr.

2016-01-01

The Evolvable Mars Campaign is developing concepts for human missions to the surface of Mars. These missions are round-trip expeditions, thereby requiring crew launch via a Mars Ascent Vehicle (MAV). A study to identify the smallest possible pressurized cabin for this mission has developed a conceptual vehicle referred to as the minimal MAV cabin. The origin of this concept will be discussed as well as its initial concept definition. This will lead to a description of possible configurations to integrate the minimal MAV cabin with ascent vehicle engines and propellant tanks. Limitations of this concept will be discussed, in particular those that argue against the use of the minimal MAV cabin to perform the MAV mission. However, several potential alternative uses for the cabin are identified. Finally, recommended forward work will be discussed, including current work in progress to develop a full scale mockup and conduct usability evaluations.

KSC-98pc156

NASA Image and Video Library

1998-01-16

Celebrating the official opening of the new International Space Station (ISS) Center at Kennedy Space Center are, left to right, James Ball, chief, NASA Public Services, KSC; KSC Director Roy D. Bridges Jr.; Hugh Harris, director, NASA Public Affairs, KSC; and Rick Abramson, president and chief operating officer, Delaware North Parks Services of Spaceport Inc. Center Director Bridges cuts the ribbon to the new tour attraction where full-scale mockups of station modules, through which visitors can walk, are on display. These include the Habitation Unit, where station crew members will live, sleep, and work; a Laboratory Module; and the Pressurized Logistics Module, where racks and supplies will be transported back and forth from KSC to space. Guests also can take an elevated walkway to a gallery overlooking the work are where actual ISS hardware is prepared for flight into space. This new tour site, in addition to a new Launch Complex 39 Observation Gantry, are part of a comprehensive effort by NASA and Delaware North to expand and improve the KSC public tour and visitor facilities

Emergency in-flight egress opening for general aviation aircraft. [pilot bailout

NASA Technical Reports Server (NTRS)

Bement, L. J.

1980-01-01

An emergency in-flight egress system was installed in a light general aviation airplane. The airplane had no provision for egress on the left side. To avoid a major structural redesign for a mechanical door, an add on 11.2 kg (24.6 lb) pyrotechnic-actuated system was developed to create an opening in the existing structure. The skin of the airplane was explosively severed around the side window, across a central stringer, and down to the floor, creating an opening of approximately 76 by 76 cm. The severed panel was jettisoned at an initial velocity of approximately 13.7 m/sec. System development included a total of 68 explosive severance tests on aluminum material using small samples, small and full scale flat panel aircraft structural mockups, and an actual aircraft fuselage. These tests proved explosive sizing/severance margins, explosive initiation, explosive product containment, and system dynamics. This technology is applicable to any aircraft of similar construction.

John Glenn during preflight training for STS-95

NASA Image and Video Library

1998-04-14

S98-06949 (28 April 1998) --- U.S. Sen. John H. Glenn Jr. (D.-Ohio), talks with crew trainer Sharon Jones prior to simulating procedures for egressing from a troubled space shuttle. This training mockup is called the full fuselage trainer (FFT). Glenn has been named as a payload specialist for STS-95, scheduled for launch later this year. Photo Credit: Joe McNally, National Geographic, for NASA

STS-104 crewmembers in Building 9NW

NASA Image and Video Library

2001-01-17

JSC2001-00083 (January 2001) --- Several members of the STS-104 crew, assisted by suit technician Jim Cheatham, don training versions of the full-pressure launch and entry suit prior to a training session in one of the trainer/mockups (out of frame) in the Johnson Space Center’s Systems Integration Facility. Pictured (from right foreground) are astronauts James F. Reilly, Janet L. Kavandi, Michael L. Gernhardt, and Charles O. Hobaugh.

CHARACTERIZATION OF DEFECTS IN ALLOY 152, 52 AND 52M WELDS

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

Bruemmer, Stephen M.; Toloczko, Mychailo B.; Olszta, Matthew J.

2009-08-27

Defect distributions have been documented by optical metallography, scanning electron microscopy and electron backscatter diffraction in alloy 152 and 52 mockups welds, alloy 52 and 52M overlay mockups and an alloy 52M inlay. Primary defects were small cracks at grain boundaries except for more extensive cracking in the dilution zone of an alloy 52 overlay on 304SS. Detailed characterizations of the dilution zone cracks were performed by analytical transmission electron microscopy identifying grain boundary titanium-nitride precipitation associated with the intergranular separations. I. INTRODUCTION Weldments continue to be a primary location of stress-corrosion cracking (SCC) in light-water reactor systems. While problemsmore » related to heat-affected-zone (HAZ) sensitization and intergranular (IG) SCC of austenitic stainless alloys in boiling-water reactors (BWRs) have been significantly reduced, SCC has now been observed in HAZs of non-sensitized materials and in dissimilar metal welds where Ni-base alloy weld metals are used. IGSCC in weld metals has been observed in both BWRs and pressurized water reactors (PWRs) with recent examples for PWR pressure vessel penetrations producing the most concern. This has led to the replacement of alloy 600/182/82 welds with higher Cr, more corrosion-resistant replacement materials (alloy 690/152/52/52M). Complicating this issue has been a known susceptibility to cracking during welding [1-7] of these weld metals. There is a critical need for an improved understanding of the weld metal metallurgy and defect formation in Ni-base alloy welds to effectively assess long-term performance. A series of macroscopic to microscopic examinations were performed on available mockup welds made with alloy 52 or alloy 152 plus selected overlay and inlay mockups. The intent was to expand our understanding of weld metal structures in simulated LWR service components with a focus on as-welded defects. Microstructural features, defect distributions, defect characteristics and weld residual strains were examined by optical metallography, scanning electron microscopy, electron backscatter diffraction and transmission electron microscopy. Industry-supplied mock-up welds were characterized including alloy 52 and 152 weldments, alloy 52M overlay and inlay welds, and an alloy 52 overlay. II. WELDMENTS II.A. Alloy 52 and 152 Weld Mockups The alloy 52 and 152 weld mockups were fabricated by MHI for the Kewaunee reactor and were obtained from the EPRI NDE Center. The mockups were U-groove welds joining two plates of 304SS as shown in Figure 1. Alloy 152 butter (heat 307380) was placed on the U-groove surface for both mockups by shielded metal arc welding (SMAW). For the alloy 152 weld mockup, the alloy 152 fill (heat 307380) was also applied using SMAW while for the alloy 52 weld mockup, the alloy 52 fill (heat NX2686JK) was applied using gas tungsten arc welding (GTAW). Welding parameters for the fill materials were substantially different with the alloy 152 SMAW having a deposition speed of 4-25 cm/min with a current of 95-145 A and the alloy 52 GTAW having a deposition speed of 4-10 cm/min with a current of 150-300 A. One prominent feature in these mockup welds is the presence of a crack starting at the 304SS butt joint at the bottom of the U-groove and extending up into the weld. It appears that the 304SS plate on either side of the butt joint acted as an anchor for the weld resulting in a stress rise across the slit that drove crack formation and extension up into the fill weld. As will be shown in the next section, the extent of the cracking around this stress riser was much greater in the MHI 52 weld mockup.« less

Size Contrast for Mars CubeSat

NASA Image and Video Library

2015-06-12

The full-scale mock-up of NASA's MarCO CubeSat held by Farah Alibay, a systems engineer at NASA's Jet Propulsion Laboratory, is dwarfed by the one-half-scale model of NASA's Mars Reconnaissance Orbiter behind her. MarCO, short for Mars Cube One, is the first interplanetary use of CubeSat technologies for small spacecraft. JPL is preparing two MarCO twins for launch in March 2016. They will ride along on an Atlas V launch vehicle lifting off from Vandenberg Air Force Base, California, with NASA's next Mars lander, InSight. MarCO is a technology demonstration aspect of the InSight mission. The mock-up in the photo is in a configuration to show the deployed position of components that correspond to MarCO's two solar panels and two antennas. During launch, those components will be stowed for a total vehicle size of about 14.4 inches (36.6 centimeters) by 9.5 inches (24.3 centimeters) by 4.6 inches (11.8 centimeters). After launch, the two MarCO CubeSats and InSight will be navigated separately to Mars. The MarCO twins will fly past the planet in September 2016 just as InSight is descending through the atmosphere and landing on the surface. MarCO is a technology demonstration to relay communications from InSight to Earth during InSight's descent and landing. InSight communications during that critical period will also be recorded by NASA's Mars Reconnaissance Orbiter for delayed transmission to Earth. InSight -- an acronym for Interior Exploration using Seismic Investigations, Geodesy and Heat Transport -- will study the interior of Mars to improve understanding of the processes that formed and shaped rocky planets, including Earth. Note: After thorough examination, NASA managers have decided to suspend the planned March 2016 launch of the Interior Exploration using Seismic Investigations Geodesy and Heat Transport (InSight) mission. The decision follows unsuccessful attempts to repair a leak in a section of the prime instrument in the science payload. http://photojournal.jpl.nasa.gov/catalog/PIA19671

Mechanical Characterization of the Iter Mock-Up Insulation after Reactor Irradiation

NASA Astrophysics Data System (ADS)

Prokopec, R.; Humer, K.; Fillunger, H.; Maix, R. K.; Weber, H. W.

2010-04-01

The ITER mock-up project was launched in order to demonstrate the feasibility of an industrial impregnation process using the new cyanate ester/epoxy blend. The mock-up simulates the TF winding pack cross section by a stainless steel structure with the same dimensions as the TF winding pack at a length of 1 m. It consists of 7 plates simulating the double pancakes, each of them is wrapped with glass fiber/Kapton sandwich tapes. After stacking the 7 plates, additional insulation layers are wrapped to simulate the ground insulation. This paper presents the results of the mechanical quality tests on the mock-up pancake insulation. Tensile and short beam shear specimens were cut from the plates extracted from the mock-up and tested at 77 K using a servo-hydraulic material testing device. All tests were repeated after reactor irradiation to a fast neutron fluence of 1×1022 m-2 (E>0.1 MeV). In order to simulate the pulsed operation of ITER, tension-tension fatigue measurements were performed in the load controlled mode. Initial results show a high mechanical strength as expected from the high number of thin glass fiber layers, and an excellent homogeneity of the material.

A proposal to demonstrate production of salad crops in the Space Station Mockup facility with particular attention to space, energy, and labor constraints

NASA Technical Reports Server (NTRS)

Brooks, Carolyn

1992-01-01

This research has continued along two lines, one at Marshall Space Flight Center with Salad Machine Rack development and the design and construction of a mockup for placement in the Huntsville Space Station Freedom mockup. The second avenue of research has addressed issues of relevance to the operation of the Salad Machine and Bioregenerative systems. These issues include plant species compatibility when grown on shared hydroponic systems and microbial populations of mixed species hydroponic systems. Significant progress is reported.

STS-133 crew during CCT II Flight Communications plan

NASA Image and Video Library

2010-02-04

JSC2010-E-023636 (4 Feb. 2010) --- NASA astronaut Tim Kopra, STS-133 mission specialist, participates in training session in a shuttle mock-up in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center.

STS-133 crew during CCT II Flight Communications plan

NASA Image and Video Library

2010-02-04

JSC2010-E-023637 (4 Feb. 2010) --- NASA astronaut Alvin Drew, STS-133 mission specialist, participates in training session in a shuttle mock-up in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center.

STS-133 crew during CCT II Flight Communications plan

NASA Image and Video Library

2010-02-04

JSC2010-E-023639 (4 Feb. 2010) --- NASA astronaut Steve Lindsey, STS-133 commander, participates in training session in a shuttle mock-up in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center.

Progress on performance assessment of ITER enhanced heat flux first wall technology after neutron irradiation

NASA Astrophysics Data System (ADS)

Hirai, T.; Bao, L.; Barabash, V.; Chappuis, Ph; Eaton, R.; Escourbiac, F.; Giqcuel, S.; Merola, M.; Mitteau, R.; Raffray, R.; Linke, J.; Loewenhoff, Th; Pintsuk, G.; Wirtz, M.; Boomstra, D.; Magielsen, A.; Chen, J.; Wang, P.; Gervash, A.; Safronov, V.

2016-02-01

ITER first wall (FW) panels are irradiated by energetic neutrons during the nuclear phase. Thus, an irradiation and high heat flux testing programme is undertaken by the ITER organization in order to evaluate the effects of neutron irradiation on the performance of enhanced heat flux (EHF) FW components. The test campaign includes neutron irradiation (up to 0.6-0.8 dpa at 200 °C-250 °C) of mock-ups that are representative of the final EHF FW panel design, followed by thermal fatigue tests (up to 4.7 MW m-2). Mock-ups were manufactured by the same manufacturing process as proposed for the series production. After a pre-irradiation thermal screening, eight mock-ups will be selected for the irradiation campaigns. This paper reports the preparatory work of HHF tests and neutron irradiation, assessment results as well as a brief description of mock-up manufacturing and inspection routes.

KSC-08pd1901

NASA Image and Video Library

2008-07-02

CAPE CANAVERAL, Fla. – Professor Peter Voci, NYIT MOCAP (Motion Capture) team director, (left) hands a component of the Orion Crew Module mockup to one of three technicians inside the mockup. The technicians wear motion capture suits. The motion tracking aims to improve efficiency of assembly processes and identify potential ergonomic risks for technicians assembling the mockup. The work is being performed in United Space Alliance's Human Engineering Modeling and Performance Lab in the RLV Hangar at NASA's Kennedy Space Center. The motion tracking aims to improve efficiency of assembly processes and identify potential ergonomic risks for technicians assembling the mockup. The work is being performed in United Space Alliance's Human Engineering Modeling and Performance Lab in the RLV Hangar at NASA's Kennedy Space Center. 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.

KSC-08pd1902

NASA Image and Video Library

2008-07-02

CAPE CANAVERAL, Fla. – A United Space Alliance technician (right) hands off a component of the Orion Crew Module mockup to one of the other technicians inside the mockup. The technicians wear motion capture suits. The motion tracking aims to improve efficiency of assembly processes and identify potential ergonomic risks for technicians assembling the mockup, which was created and built at the New York Institute of Technology by a team led by Prof. Peter Voci, MFA Director at the College of Arts and Sciences. The motion tracking aims to improve efficiency of assembly processes and identify potential ergonomic risks for technicians assembling the mockup. The work is being performed in United Space Alliance's Human Engineering Modeling and Performance Lab in the RLV Hangar at NASA's Kennedy Space Center. 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.

Tour by Saudi prince Salman Abdelazize Al-Saud prior to mission

NASA Technical Reports Server (NTRS)

1985-01-01

Tour by Saudi prince Salman Abdelazize Al-Saud, payload specialists for STS 51-G mission, prior to mission. Al-Saud and Abdulmohsen Hamad Al-Bassam, the backup payload specialist, man the controls on the flight deck of the crew compartment trainer in the Shuttle mockup and integration laboratory (29788); the Saudi payload specialists share the hatch of the crew compartment trainer (29789); Portrait view of Abdulmohsen Hamad Al-Bassam during a visit to the Shuttle mockup and integraion laboratory (29790); Don Sirroco, left, explains the middeck facilities in the Shuttle mockup and integration laboratory (29791); Portrait view of Sultan Salman Abdelazize Al-Saud in the Shuttle Mockup and Integration laboratory (29792); The Saudi payload specialists witness a space food demonstration in the life sciences laboratory at JSC. Al-Saud (left) and Al-Bassam (second left) listen as Rita M. Rapp, food specialist, discusses three preparations of re-hydratable food for space travelers. Lynn S. Coll

STS_135_PostInsertion

NASA Image and Video Library

2011-03-24

JSC2011-E-040284 (24 March 2011) --- NASA astronauts Doug Hurley and Sandy Magnus set up the middeck in the Full-Fuselage Trainer as the crew of STS-135 participates in a post insertion training session March 24, 2011 in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center in Houston. Hurley is the pilot and Magnus is one of two mission specialists assigned to the flight. Photo credit: NASA Photo/Houston Chronicle, Smiley N. Pool

Nuclear Waste Package Mockups: A Study of In-situ Redox State

NASA Astrophysics Data System (ADS)

Helean, K.; Anderson, B.; Brady, P. V.

2006-05-01

The Yucca Mountain Repository (YMR), located in southern Nevada, is to be the first facility in the U.S. for the permanent disposal of high-level radioactive waste and spent nuclear fuels. Total system performance assessment(TSPA) has indicated that among the major radionuclides contributing to dose are Np, Tc, and I. These three radionuclides are mobile in most geochemical settings, and therefore sequestering them within the repository horizon is a priority for the Yucca Mountain Project (YMP). Corroding steel may offset radionuclide transport processes within the proposed waste packages at YMR by retaining radionuclides, creating locally reducing conditions, and reducing porosity. Ferrous iron has been shown to reduce UO22+ to UO2s, and some ferrous iron-bearing ion-exchange materials have been shown to adsorb radionuclides and heavy metals. Locally reducing conditions may lead to the reduction and subsequent immobilization of problematic dissolved species such as TcO4-, NpO2+, and UO22+ and can also inhibit corrosion of spent nuclear fuel. Water occluded during corrosion produces bulky corrosion products, and consequently less porosity is available for water and radionuclide transport. The focus of this study is on the nature of Yucca Mountain waste package corrosion products and their effects on local redox conditions, radionuclide transport, and porosity. In order to measure in-situ redox, six small-scale (1:40) waste package mockups were constructed using A516 and 316 stainless steel, the same materials as the proposed Yucca Mountain waste packages. The mockups are periodically injected with a simulated groundwater and the accumulated effluent and corrosion products are evaluated for their Fe(II)/Fe(III) content and mineralogy. Oxygen fugacities are then calculated and, thus, in-situ redox conditions are determined. Early results indicate that corrosion products are largely amorphous Fe-oxyhydroxides, goethite and magnetite. That information together with the measured Fe(II)/Fe(III) ratios in the mockup effluent constrain the oxygen fugacity to approximately 10-38 atm, many orders of magnitude below ambient. These results and their impact on radionuclide migration from YMR will be discussed.

STS-133 crew during CCT II Flight Communications plan

NASA Image and Video Library

2010-02-04

JSC2010-E-023629 (4 Feb. 2010) --- NASA astronauts Michael Barratt and Nicole Stott, both STS-133 mission specialists, participate in training session in a shuttle mock-up in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center.

Visualization of the contact line during the water exit of flat plates

NASA Astrophysics Data System (ADS)

Tassin, A.; Breton, T.; Forest, B.; Ohana, J.; Chalony, S.; Le Roux, D.; Tancray, A.

2017-08-01

We investigate experimentally the time evolution of the wetted surface during the lifting of a body initially floating at the water surface. This phenomenon is referred to as the water exit problem. The water exit experiments were conducted with transparent (PMMA) mock-ups of two different shapes: a circular disc and a square flat plate. Two different lighting systems were used to diffuse light in the mock-up material: a central high-power LED light normal to the surface and an edge-lighting system featuring an array of LED lights. These setups make it possible to illuminate the contact line, which delimits the surface of contact between the mock-up and the water. The characteristic size of the mock-ups is about 20 cm and the acceleration of the mock-up oscillates between 0 and 25 m/s^2. We show that the central light setup gives satisfactory results for the circular disc and that the edge lighting technique makes it possible to follow a contact line with a time-evolving complex shape (strong changes of convexity) up to 1000 fps. The observations presented in the paper support the possibility of extending this promising technique to more general three-dimensional bodies with arbitrary motion (e.g., including pitch motion).

Locomotive cab design development. volume 2 : operator's manual - Interim Report

DOT National Transportation Integrated Search

1976-10-01

Locomotive Cab 913 designed as a result of Contract DOT-TSC- 913 has been built as a hard mock-up. This Operator's Manual is to familiarize the user with the mock-up. Normal and emergency procedures and cab facilities are described.

A stratospheric balloon experiment to test the Huygens atmospheric structure instrument (HASI)

NASA Astrophysics Data System (ADS)

Fulchignoni, M.; Aboudan, A.; Angrilli, F.; Antonello, M.; Bastianello, S.; Bettanini, C.; Bianchini, G.; Colombatti, G.; Ferri, F.; Flamini, E.; Gaborit, V.; Ghafoor, N.; Hathi, B.; Harri, A.-M.; Lehto, A.; Lion Stoppato, P. F.; Patel, M. R.; Zarnecki, J. C.

2004-08-01

We developed a series of balloon experiments parachuting a 1:1 scale mock-up of the Huygens probe from an altitude just over 30 km to simulate at planetary scale the final part of the descent of the probe through Titan's lower atmosphere. The terrestrial atmosphere represents a natural laboratory where most of the physical parameters meet quite well the bulk condition of Titan's environment, in terms of atmosphere composition, pressure and mean density ranges, though the temperature range will be far higher. The probe mock-up consists of spares of the HASI sensor packages, housekeeping sensors and other dedicated sensors, and also incorporates the Huygens Surface Science Package (SSP) Tilt sensor and a modified version of the Beagle 2 UV sensor, for a total of 77 acquired sensor channels, sampled during ascent, drift and descent phase. An integrated data acquisition and instrument control system, simulating the HASI data-processing unit (DPU), has been developed, based on PC architecture and soft-real-time application. Sensor channels were sampled at the nominal HASI data rates, with a maximum rate of 1 kHz. Software has been developed for data acquisition, onboard storage and telemetry transmission satisfying all requests for real-time monitoring, diagnostic and redundancy. The mock-up of the Huygens probe mission was successfully launched for the second time (first launch in summer 2001, see Gaborit et al., 2001) with a stratospheric balloon from the Italian Space Agency Base "Luigi Broglio" in Sicily on May 30, 2002, and recovered with all sensors still operational. The probe was lifted to an altitude of 32 km and released to perform a parachuted descent lasting 53 min, to simulate the Huygens mission at Titan. Preliminary aerodynamic study of the probe has focused upon the achievement of a descent velocity profile reproducing the expected profile of Huygens probe descent into Titan. We present here the results of this experiment discussing their relevance in the analysis of the data which will be obtained during the Huygens mission at Titan.

Orbital docking system centerline color television camera system test

NASA Technical Reports Server (NTRS)

Mongan, Philip T.

1993-01-01

A series of tests was run to verify that the design of the centerline color television camera (CTVC) system is adequate optically for the STS-71 Space Shuttle Orbiter docking mission with the Mir space station. In each test, a mockup of the Mir consisting of hatch, docking mechanism, and docking target was positioned above the Johnson Space Center's full fuselage trainer, which simulated the Orbiter with a mockup of the external airlock and docking adapter. Test subjects viewed the docking target through the CTVC under 30 different lighting conditions and evaluated target resolution, field of view, light levels, light placement, and methods of target alignment. Test results indicate that the proposed design will provide adequate visibility through the centerline camera for a successful docking, even with a reasonable number of light failures. It is recommended that the flight deck crew have individual switching capability for docking lights to provide maximum shadow management and that centerline lights be retained to deal with light failures and user preferences. Procedures for light management should be developed and target alignment aids should be selected during simulated docking runs.

Pretreatment Engineering Platform Phase 1 Final Test Report

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

Kurath, Dean E.; Hanson, Brady D.; Minette, Michael J.

2009-12-23

Pacific Northwest National Laboratory (PNNL) was tasked by Bechtel National Inc. (BNI) on the River Protection Project, Hanford Tank Waste Treatment and Immobilization Plant (RPP-WTP) project to conduct testing to demonstrate the performance of the WTP Pretreatment Facility (PTF) leaching and ultrafiltration processes at an engineering-scale. In addition to the demonstration, the testing was to address specific technical issues identified in Issue Response Plan for Implementation of External Flowsheet Review Team (EFRT) Recommendations - M12, Undemonstrated Leaching Processes.( ) Testing was conducted in a 1/4.5-scale mock-up of the PTF ultrafiltration system, the Pretreatment Engineering Platform (PEP). Parallel laboratory testing wasmore » conducted in various PNNL laboratories to allow direct comparison of process performance at an engineering-scale and a laboratory-scale. This report presents and discusses the results of those tests.« less

NASA Photographer Prepares to Film a Mercury Capsule

NASA Image and Video Library

1959-06-21

National Aeronautics and Space Administration (NASA) photographer Arthur Laufman sets up a camera to film a Mercury capsule that was constructed by the Lewis Research Center staff. Lewis engineers and mechanics built two of the capsules for the upcoming Big Joe launches in September 1959. Big Joe was an attempt early in Project Mercury to use a full-scale Atlas booster to simulate the reentry of a mock-up Mercury capsule without actually placing it in orbit. The Photographic Branch, referred to as the Photo Lab, was part of the center’s Technical Reports Division. Originally the group performed normal and high-speed still image and motion picture photography. The photographers documented construction, performed publicity work, created images for reports, photographed data on manometer boards, and recorded test footage. Laufman joined the Photo Lab staff in 1948 and began producing full-length technical films as a tool to educate those outside of the agency on the research being conducted at Lewis. He worked with engineers to determine proper subjects for these films and develop a script. Laufman not only filmed tests, but also supporting footage of facilities, models, and staff members. He then edited the footage and added audio, visuals, and narration. The film masters were assigned standard identification numbers and add to the Photo Lab’s catalogue.

Pretest reference calculation for the 18-W/m/sup 2/ Mockup for Defense High-Level Waste (WIPP Room A in situ experiment)

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

Morgan, H.S.; Stone, C.M.

A pretest reference calculation for the 18-W/m/sup 2/ Mockup for Defense High-Level Waste (DHLW) or Room A experiment is presented in this report. The mockup is one of several large scale in situ experiments currently under construction near Carlsbad, New Mexico, at the site of the Waste Isolation Pilot Plant (WIPP). The 18-W/m/sup 2/ test is an in situ experiment developed to simulate closely the Reference Repository Conditions (RRC) for DHLW in salt. The test consists of three long, parallel rooms (A1, A2, A3) which are heated by canister heaters placed in the floor of each room. These heaters producemore » thermal loading which simulates an areal heat output of 18-W/m/sup 2/ for Room A2, which is the focus of the experiment. This load will be supplied for a period of three years. Rooms A1, A2, and A3 are heavily instrumented for monitoring both temperature increases due to the thermal loading and deformations due to creep of the salt. Data from the experiment are not available at the present time, but the measurements for Room A2 will eventually be compared to the results for Room A2 presented here to assess and improve thermal and mechanical modeling capabilities for the WIPP. The thermal/structural model used here represents the state-of-the-art at the present time. A large number of plots are included since an appropriate result is presented for every Room A2 gauge location. 55 refs., 70 figs., 4 tabs.« less

STS-133 crew during CCT II Flight Communications plan

NASA Image and Video Library

2010-02-04

JSC2010-E-023633 (4 Feb. 2010) --- NASA astronaut Nicole Stott (right), STS-133 mission specialist, participates in training session in a shuttle mock-up in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center. Instructors Shanna Andrew and James Gaustad assisted Stott.

A new test environment for the SOFIA secondary mirror assembly to reduce the required time for in-flight testing

NASA Astrophysics Data System (ADS)

Lammen, Yannick; Reinacher, Andreas; Brewster, Rick; Greiner, Benjamin; Graf, Friederike; Krabbe, Alfred

2016-07-01

The Stratospheric Observatory For Infrared Astronomy (SOFIA) reached its full operational capability in 2014 and takes off from the NASA Armstrong Flight Research Center to explore the universe about three times a week. Maximizing the program's scientific output naturally leaves very little flight time for implementation and test of improved soft- and hardware. Consequently, it is very important to have a comparable test environment and infrastructure to perform troubleshooting, verifications and improvements on ground without interfering with science missions. SOFIA's Secondary Mirror Mechanism is one of the most complex systems of the observatory. In 2012 a first simple laboratory mockup of the mechanism was built to perform basic controller tests in the lower frequency band of up to 50Hz. This was a first step to relocate required engineering tests from the active observatory into the laboratory. However, to test and include accurate filters and damping methods as well as to evaluate hardware modifications a more precise mockup is required that represents the system characteristics over a much larger frequency range. Therefore the mockup has been improved in several steps to a full test environment representing the system dynamics with high accuracy. This new ground equipment allows moving almost the entire secondary mirror test activities away from the observatory. As fast actuator in the optical path, the SMM also plays a major role in SOFIA's pointing stabilization concept. To increase the steering bandwidth, hardware changes are required that ultimately need to be evaluated using the telescope optics. One interesting concept presented in this contribution is the in- stallation of piezo stack actuators between the mirror and the chopping mechanism. First successful baseline tests are presented. An outlook is given about upcoming performance tests of the actively controlled piezo stage with local metrology and optical feedback. To minimize the impact on science time, the laboratory test setup will be expanded with an optical measurement system so that it can be used for the vast majority of testing.

STS-125 Crew during Post Insertion/Deorbit Prep training in CCT II mockup.

NASA Image and Video Library

2008-01-29

JSC2008-E-008417 (29 Jan. 2008) --- Astronaut Michael T. Good (left), STS-125 mission specialist, participates in a training session in the Space Vehicle Mockup Facility at the Johnson Space Center. United Space Alliance (USA) instructor David L. Williams (center) assisted Good.

Astronaut William McArthur prepares for a training exercise

NASA Image and Video Library

1993-07-20

S93-38686 (20 July 1993) --- Wearing a training version of the partial pressure launch and entry garment, astronaut William S. McArthur prepares to rehearse emergency egress procedures for the STS-58 mission. McArthur, along with the five other NASA astronauts and a visiting payload specialist assigned to the seven-member crew, later simulated contingency evacuation procedures. Most of the training session took place in the crew compartment and full fuselage trainers of the Space Shuttle mockup and integration laboratory.

Astronaut William McArthur prepares for a training exercise

NASA Image and Video Library

1993-07-20

S93-38679 (20 July 1993) --- Wearing a training version of the partial pressure launch and entry garment, astronaut William S. McArthur listens to a briefing on emergency egress procedures for the STS-58 mission. McArthur, along with five other NASA astronauts and a visiting payload specialist assigned to the seven member crew, later rehearsed contingency evacuation procedures. Most of the training session took place in the crew compartment and full fuselage trainers of the Space Shuttle mockup and integration laboratory.

Disposition of feedwater nozzle UT indications in a BWR

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

Leshnoff, S.D.; Orski, M.A.

A technical logic is developed, which justifies the disposition of feedwater nozzle ultrasonic testing (UT) indications in order to return to operation without visual inspection of the vessel inside surface. Present regulatory guidance is to inspect the inside surface from the inside if a reportable indication is found. A highly sensitive, tomographic UT technique, developed by Kraftwerk Union, is used to detect and size machined notches in the blend radius and bore regions of a full-sized feedwater nozzle mock-up.

NEEMO 14: Evaluation of Human Performance for Rover, Cargo Lander, Crew Lander, and Exploration Tasks in Simulated Partial Gravity

NASA Technical Reports Server (NTRS)

Chappell, Steven P.; Abercromby, Andrew F.; Gernhardt, Michael L.

2011-01-01

The ultimate success of future human space exploration missions is dependent on the ability to perform extravehicular activity (EVA) tasks effectively, efficiently, and safely, whether those tasks represent a nominal mode of operation or a contingency capability. To optimize EVA systems for the best human performance, it is critical to study the effects of varying key factors such as suit center of gravity (CG), suit mass, and gravity level. During the 2-week NASA Extreme Environment Mission Operations (NEEMO) 14 mission, four crewmembers performed a series of EVA tasks under different simulated EVA suit configurations and used full-scale mockups of a Space Exploration Vehicle (SEV) rover and lander. NEEMO is an underwater spaceflight analog that allows a true mission-like operational environment and uses buoyancy effects and added weight to simulate different gravity levels. Quantitative and qualitative data collected during NEEMO 14, as well as from spacesuit tests in parabolic flight and with overhead suspension, are being used to directly inform ongoing hardware and operations concept development of the SEV, exploration EVA systems, and future EVA suits. OBJECTIVE: To compare human performance across different weight and CG configurations. METHODS: Four subjects were weighed out to simulate reduced gravity and wore either a specially designed rig to allow adjustment of CG or a PLSS mockup. Subjects completed tasks including level ambulation, incline/decline ambulation, standing from the kneeling and prone position, picking up objects, shoveling, ladder climbing, incapacitated crewmember handling, and small and large payload transfer. Subjective compensation, exertion, task acceptability, and duration data as well as photo and video were collected. RESULTS: There appear to be interactions between CG, weight, and task. CGs nearest the subject s natural CG are the most predictable in terms of acceptable performance across tasks. Future research should focus on understanding the interactions between CG, mass, and subject differences.

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

Carter, E.E.

Molten wax shows considerable promise as a fixative and dust control agent in demolition of radioactively contaminated facilities. Sticky molten wax, modified with special surfactants and wetting agents, is capable of not only coating materials but also penetrating into friable or dusty materials and making them incapable of becoming airborne during demolition. Wax also shows significant promise for stabilization of waste residuals that may be contained in buildings undergoing demolition. Some of the building materials that have been tested to date include concrete, wood, sheet-rock, fiber insulation, lime, rock, and paper. Protective clothing, clay, sand, sulfur, and bentonite clay havemore » been tested as surrogates for certain waste materials that may be encountered during building demolition. The paper describes several potential applications of molten wax for dust control in demolition of radioactive contaminated facilities. As a case-study, this paper describes a research test performed for a pipeline closure project being completed by the Idaho Cleanup Project at the Idaho National Laboratory. The project plans to excavate and remove a section of buried Duriron drain piping containing highly radioactive and friable and 'flighty' waste residuals. A full-scale pipeline mockup containing simulated waste was buried in sand to simulate the direct-buried subsurface condition of the subject piping. The pipeline was pre-heated by drawing hot air through the line with a HEPA vacuum blower unit. Molten wax was pumped into the line and allowed to cool. The line was then broken apart in various places to evaluate the permeation performance of the wax. The wax fully permeated all the surrogate materials rendering them non-friable with a consistency similar to modeling clay. Based on the performance during the mockup, it is anticipated that the wax will be highly effective in controlling the spread of radiological contamination during pipe demolition activities. A larger test was completed this year to simulate the work in more realistic conditions. (authors)« less

Fine water spray for fire extinguishing. Phase 2: Turbine hood

NASA Astrophysics Data System (ADS)

Aune, P.; Wighus, R.; Drangsholt, G.; Stensaas, J. P.

1994-12-01

SINTEF has carried out tests of a Fine Water Spray fire suppression system intended to be used as a replacement for Halon systems in turbine hoods on offshore platforms operated by British Petroleum Norway. The tests were carried out in a 70 cu m full scale model representing a turbine hood of the Ula platform in the North Sea. A mock-up of a gas turbine was installed in the model. The scope of work in Phase 2 was to verify the efficiency of fire suppression in realistic fire scenarios using a Fine Water Spray system, and to find an optimum procedure for water application in a fire situation. Two reports have been made from the experiments in Phase 2, one Main Report, STF25 A94036, and the present Technical Report, STF25 A94037. The discussion and conclusions are given in the Main Report while this Technical Report gives a more thorough presentation of the experimental setup and methods used for calibration and calculation of measured values. In addition, a complete set of curves for each experiment is included.

Ribbon-cutting ceremony occurs at grand opening of new International Space Station Center at KSC

NASA Technical Reports Server (NTRS)

1998-01-01

Celebrating the official opening of the new International Space Station (ISS) Center at Kennedy Space Center are, left to right, James Ball, chief, NASA Public Services, KSC; KSC Director Roy D. Bridges Jr.; Hugh Harris, director, NASA Public Affairs, KSC; and Rick Abramson, president and chief operating officer, Delaware North Parks Services of Spaceport Inc. Center Director Bridges cuts the ribbon to the new tour attraction where full-scale mockups of station modules, through which visitors can walk, are on display. These include the Habitation Unit, where station crew members will live, sleep, and work; a Laboratory Module; and the Pressurized Logistics Module, where racks and supplies will be transported back and forth from KSC to space. Guests also can take an elevated walkway to a gallery overlooking the work are where actual ISS hardware is prepared for flight into space. This new tour site, in addition to a new Launch Complex 39 Observation Gantry, are part of a comprehensive effort by NASA and Delaware North to expand and improve the KSC public tour and visitor facilities.

Countercurrent flow limited (CCFL) heat flux in the high flux isotope reactor (HFIR) fuel element

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

Ruggles, A.E.

1990-10-12

The countercurrent flow (CCF) performance in the fuel element region of the HFIR is examined experimentally and theoretically. The fuel element consists of two concentric annuli filled with aluminum clad fuel plates of 1.27 mm thickness separated by 1.27 mm flow channels. The plates are curved as they go radially outward to accomplish constant flow channel width and constant metal-to-coolant ratio. A full-scale HFIR fuel element mock-up is studied in an adiabatic air-water CCF experiment. A review of CCF models for narrow channels is presented along with the treatment of CCFs in system of parallel channels. The experimental results aremore » related to the existing models and a mechanistic model for the annular'' CCF in a narrow channel is developed that captures the data trends well. The results of the experiment are used to calculate the CCFL heat flux of the HFIR fuel assembly. It was determined that the HFIR fuel assembly can reject 0.62 Mw of thermal power in the CCFL situation. 31 refs., 17 figs.« less

Thermal mock-up studies of the Belle II vertex detector

NASA Astrophysics Data System (ADS)

Ye, H.; Niebuhr, C.; Stever, R.; Gadow, K.; Camien, C.

2018-07-01

The ongoing upgrade of the asymmetric electron-positron collider SuperKEKB at the KEK laboratory, Japan aims at a 40-fold increase of the peak luminosity to 8 × 1035 cm-2s-1. At the same time the complex Belle II detector is being significantly upgraded to be able to cope with the higher background level and trigger rates and to improve overall performance. The goal of the experiment is to explore physics beyond the standard model with a target integrated luminosity of 50 ab-1 in the next decade. The new vertex detector (VXD), comprising two layers of DEPFET pixel detectors (PXD) surrounded by 4 layers of double sided silicon strip detectors (SVD), is indispensable for vertex determination as well as for reconstruction of low momentum tracks that do not reach the central drift chamber (CDC). Within the confined VXD volume the front-end electronics of the two detectors will dissipate about 1 kW of heat. The VXD cooling system has been designed to remove this heat with the constraint to minimize extra dead material in the physics acceptance region. Taking into account additional heat intake from the environment the cooling system must have a cooling capacity of 2-3 kW. To achieve this goal evaporative two-phase CO2 cooling in combination with forced N2 flow is used in the VXD cooling system. In order to verify and optimize the cooling concept and to demonstrate that acceptable operation conditions for the VXD system as well as the surrounding CDC can be obtained, a full size VXD thermal mock-up has been built at DESY. Various thermal and mechanical tests carried out with this mock-up are reported.

Absolute determination of power density in the VVER-1000 mock-up on the LR-0 research reactor.

PubMed

Košt'ál, Michal; Švadlenková, Marie; Milčák, Ján

2013-08-01

The work presents a detailed comparison of calculated and experimentally determined net peak areas of selected fission products gamma lines. The fission products were induced during a 2.5 h irradiation on the power level of 9.5 W in selected fuel pins of the VVER-1000 Mock-Up. The calculations were done with deterministic and stochastic (Monte Carlo) methods. The effects of different nuclear data libraries used for calculations are discussed as well. The Net Peak Area (NPA) may be used for the determination of fission density across the mock-up. This fission density is practically identical to power density. Copyright © 2013 Elsevier Ltd. All rights reserved.

Space station wardroom habitability and equipment study

NASA Technical Reports Server (NTRS)

Nixon, David; Miller, Christopher; Fauquet, Regis

1989-01-01

Experimental designs in life-size mock-up form for the wardroom facility for the Space Station Habitability Module are explored and developed. In Phase 1, three preliminary concepts for the wardroom configuration are fabricated and evaluated. In Phase 2, the results of Phase 1 are combined with a specific range of program design requirements to provide the design criteria for the fabrication of an innovative medium-fidelity mock-up of a wardrobe configuration. The study also focuses on the design and preliminary prototyping of selected equipment items including crew exercise compartments, a meal/meeting table and a portable workstation. Design criteria and requirements are discussed and documented. Preliminary and final mock-ups and equipment prototypes are described and illustrated.

KSC00padig121

NASA Image and Video Library

2000-12-08

KENNEDY SPACE CENTER, FLA. -- Astronaut John Herrington (left) shows a mockup of the U.S. Lab to Norm Abram, master carpenter of television’s "This Old House" and "The New Yankee Workshop." Abram is at KSC to film an episode of "This Old House." The mockup lab is in the International Space Station Center, a tour facility

KSC-00padig121

NASA Image and Video Library

2000-12-08

KENNEDY SPACE CENTER, FLA. -- Astronaut John Herrington (left) shows a mockup of the U.S. Lab to Norm Abram, master carpenter of television’s "This Old House" and "The New Yankee Workshop." Abram is at KSC to film an episode of "This Old House." The mockup lab is in the International Space Station Center, a tour facility

STS-135 crew during Ingress/Egress Timeline training in building 9NW space station mockups

NASA Image and Video Library

2011-04-29

JSC2011-E-043875 (29 April 2011) --- NASA astronaut Rex Walheim, STS-135 mission specialist, participates in an EVA Thermal Protection System (TPS) overview training session in the TPS/Precision Air Bearing Facility in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center. Photo credit: NASA

STS-117 Crew Training during suited PI/DO Prep in CCT-II mockup

NASA Image and Video Library

2006-08-03

JSC2006-E-32665 (3 Aug. 2006) --- Astronaut Steven R. Swanson, STS-117 mission specialist, participates in a training session in the crew compartment trainer (CCT-2) in the Space Vehicle Mockup Facility at Johnson Space Center. Swanson is wearing a training version of his shuttle launch and landing suit.

STS-133 crew during CCT II Flight Communications plan

NASA Image and Video Library

2010-02-04

JSC2010-E-023632 (4 Feb. 2010) --- NASA astronauts Michael Barratt (left) and Nicole Stott, both STS-133 mission specialists, participate in training session in a shuttle mock-up in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center. United Space Alliance instructor James Gaustad assisted Barratt and Stott.

Re-analysis of HCPB/HCLL Blanket Mock-up Experiments Using Recent Nuclear Data Libraries

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

Kondo, K., E-mail: keitaro.kondo@kit.edu; Fischer, U.; Klix, A.

2014-06-15

We have re-analysed the two breeding blankets experiments performed previously in the frame of the European fusion program on two mock-ups of the European Helium-Cooled-Lithiium Lead (HCLL) and Helium-Cooled-Pebble-Bed (HCPB) test blanket modules for ITER. The tritium production rate and the neutron and photon spectra measured in these mock-ups were compared with calculations using FENDL-3 Starter Library, release 4 and state-of-the-art nuclear data evaluations, JEFF-3.1.2, JENDL-4.0 and ENDF/B-VII.0. The tritium production calculated for the HCPB mock-up underestimates the experimental result by about 10%. The result calculated with FENDL-3/SLIB4 gives slightly smaller tritium production by 2% than the one with FENDL-2.1.more » The difference attributes to the slight modification of the total and elastic scattering cross section of Be. For the HCLL experiment, all libraries reproduce the experimental results well. FENDL-3/SLIB4 gives better result both for the measured spectra and the tritium production compared to FENDL-2.1.« less

Achievements in the development of the Water Cooled Solid Breeder Test Blanket Module of Japan to the milestones for installation in ITER

NASA Astrophysics Data System (ADS)

Tsuru, Daigo; Tanigawa, Hisashi; Hirose, Takanori; Mohri, Kensuke; Seki, Yohji; Enoeda, Mikio; Ezato, Koichiro; Suzuki, Satoshi; Nishi, Hiroshi; Akiba, Masato

2009-06-01

As the primary candidate of ITER Test Blanket Module (TBM) to be tested under the leadership of Japan, a water cooled solid breeder (WCSB) TBM is being developed. This paper shows the recent achievements towards the milestones of ITER TBMs prior to the installation, which consist of design integration in ITER, module qualification and safety assessment. With respect to the design integration, targeting the detailed design final report in 2012, structure designs of the WCSB TBM and the interfacing components (common frame and backside shielding) that are placed in a test port of ITER and the layout of the cooling system are presented. As for the module qualification, a real-scale first wall mock-up fabricated by using the hot isostatic pressing method by structural material of reduced activation martensitic ferritic steel, F82H, and flow and irradiation test of the mock-up are presented. As for safety milestones, the contents of the preliminary safety report in 2008 consisting of source term identification, failure mode and effect analysis (FMEA) and identification of postulated initiating events (PIEs) and safety analyses are presented.

Spacecraft Internal Acoustic Environment Modeling

NASA Technical Reports Server (NTRS)

Chu, SShao-sheng R.; Allen, Christopher S.

2009-01-01

Acoustic modeling can be used to identify key noise sources, determine/analyze sub-allocated requirements, keep track of the accumulation of minor noise sources, and to predict vehicle noise levels at various stages in vehicle development, first with estimates of noise sources, later with experimental data. In FY09, the physical mockup developed in FY08, with interior geometric shape similar to Orion CM (Crew Module) IML (Interior Mode Line), was used to validate SEA (Statistical Energy Analysis) acoustic model development with realistic ventilation fan sources. The sound power levels of these sources were unknown a priori, as opposed to previous studies that RSS (Reference Sound Source) with known sound power level was used. The modeling results were evaluated based on comparisons to measurements of sound pressure levels over a wide frequency range, including the frequency range where SEA gives good results. Sound intensity measurement was performed over a rectangular-shaped grid system enclosing the ventilation fan source. Sound intensities were measured at the top, front, back, right, and left surfaces of the and system. Sound intensity at the bottom surface was not measured, but sound blocking material was placed tinder the bottom surface to reflect most of the incident sound energy back to the remaining measured surfaces. Integrating measured sound intensities over measured surfaces renders estimated sound power of the source. The reverberation time T6o of the mockup interior had been modified to match reverberation levels of ISS US Lab interior for speech frequency bands, i.e., 0.5k, 1k, 2k, 4 kHz, by attaching appropriately sized Thinsulate sound absorption material to the interior wall of the mockup. Sound absorption of Thinsulate was modeled in three methods: Sabine equation with measured mockup interior reverberation time T60, layup model based on past impedance tube testing, and layup model plus air absorption correction. The evaluation/validation was carried out by acquiring octave band microphone data simultaneously at ten fixed locations throughout the mockup. SPLs (Sound Pressure Levels) predicted by our SEA model match well with measurements for our CM mockup, with a more complicated shape. Additionally in FY09, background NC noise (Noise Criterion) simulation and MRT (Modified Rhyme Test) were developed and performed in the mockup to determine the maximum noise level in CM habitable volume for fair crew voice communications. Numerous demonstrations of simulated noise environment in the mockup and associated SIL (Speech Interference Level) via MRT were performed for various communities, including members from NASA and Orion prime-/sub-contractors. Also, a new HSIR (Human-Systems Integration Requirement) for limiting pre- and post-landing SIL was proposed.

KSC00padig122

NASA Image and Video Library

2000-12-08

KENNEDY SPACE CENTER, FLA. -- Astronaut John Herrington (left) and Norm Abram, master carpenter of television’s "This Old House" and "The New Yankee Workshop," talk in front of a mockup of the U.S. Lab. Abram is at KSC to film an episode of "This Old House." The mockup lab is in the International Space Station Center, a tour facility

KSC-00padig122

NASA Image and Video Library

2000-12-08

KENNEDY SPACE CENTER, FLA. -- Astronaut John Herrington (left) and Norm Abram, master carpenter of television’s "This Old House" and "The New Yankee Workshop," talk in front of a mockup of the U.S. Lab. Abram is at KSC to film an episode of "This Old House." The mockup lab is in the International Space Station Center, a tour facility

Astronaut Curtis Brown on flight deck mockup during training

NASA Technical Reports Server (NTRS)

1994-01-01

Astronaut Curtis L. Brown, STS-66 pilot, mans the pilot's station during a rehearsal of procedures to be followed during the launch and entry phases of their scheduled November 1994 flight. This rehearsal, held in the crew compartment trainer (CCT) of JSC's Shuttle mockup and integration laboratory, was followed by a training session on emergency egress procedures.

Design and fabrication of the NASA HL-20 support cradle and interior mockup

NASA Technical Reports Server (NTRS)

Exum, Thurman

1991-01-01

An extensive test program involving analysis in both the horizontal and vertical attitudes of the HL-20 will be conducted by NASA-Langley. This necessitated the fabrication of a steel support cradle for the composite Personnel Launch System (PLS) model and an internal mockup to simulate the pilot and passenger compartments.

REACTOR SERVICE BUILDING, TRA635. CROWDED MOCKUP AREA. CAMERA FACES EAST. ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

REACTOR SERVICE BUILDING, TRA-635. CROWDED MOCK-UP AREA. CAMERA FACES EAST. PHOTOGRAPHER'S NOTE SAYS "PICTURE REQUESTED BY IDO IN SUPPORT OF FY '58 BUILDING PROJECTS." INL NEGATIVE NO. 56-3025. R.G. Larsen, Photographer, 9/13/1956 - Idaho National Engineering Laboratory, Test Reactor Area, Materials & Engineering Test Reactors, Scoville, Butte County, ID

Norm Abram of 'This Old House'visits KSC to film for show

NASA Technical Reports Server (NTRS)

2000-01-01

Astronaut John Herrington (left) and Norm Abram, master carpenter of television's This Old House and The New Yankee Workshop, talk in front of a mockup of the U.S. Lab. Abram is at KSC to film an episode of This Old House. The mockup lab is in the International Space Station Center, a tour facility.

Norm Abram of 'This Old House' visits KSC to film for show

NASA Technical Reports Server (NTRS)

2000-01-01

Astronaut John Herrington (left) shows a mockup of the U.S. Lab to Norm Abram, master carpenter of television's This Old House and The New Yankee Workshop. Abram is at KSC to film an episode of This Old House. The mockup lab is in the International Space Station Center, a tour facility.

Microgravity

NASA Image and Video Library

2000-01-31

Students from Albuquerque, MN, tour through the mockup of the U.S. Destiny laboratory module that will be attached to the International Space Station (ISS). Behind them are the racks for the Fluids and Combustion Facility being developed by Glenn Research Center. The mockup was on display at the Space Tehnology International Forum in Albuquerque, MN. Photo credit: NASA/Marshall Space Flight Center

STS-131 crew during SSMTF Ingress/Egress Timeline training

NASA Image and Video Library

2010-02-10

JSC2010-E-024620 (10 Feb. 2010) --- NASA astronaut Stephanie Wilson, STS-131 mission specialist, participates in an ingress/egress timeline training session in a shuttle mock-up in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center. United Space Alliance (USA) instructors David L. Williams (left) and Gary W. Kilgo assisted Wilson.

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-2009-2562

NASA Image and Video Library

2009-04-08

CAPE CANAVERAL, Fla. – Members of the 920th Rescue Wing make their way toward the mockup Orion crew exploration vehicle floating in the open water of the Trident Basin at Port Canaveral, Fla. They will place a flotation collar around the mockup vehicle. 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-2009-2505

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

Soft tissue waxup and mock-up as key factors in a treatment plan: case presentation.

PubMed

Viana, Pedro Couto; Correia, André; Neves, Manuel; Kovacs, Zsolt; Neugbauer, Rudiger

2012-01-01

Rehabilitation of edentulous spaces in esthetic areas is a challenge to the clinician due to the loss of soft tissues. In these clinical situations, it would be desirable to evaluate and predict the gingival architecture to recover in the oral rehabilitation. To fulfill this need, the diagnostic wax should anticipate the final rehabilitation with the integration of hard and soft tissue. Thus, it is essential to produce a diagnostic waxup that integrates these two components that are simultaneously seeking to recreate the harmony of white and pink esthetic. This diagnostic waxup will be the basis for the creation of the provisional prosthesis and a soft tissue mock-up. After placing the provisional prosthesis in the mouth, the soft tissue mock-up can be applied to assess its esthetic impact at facial and intraoral level. Dentist and patient should objectively assess the appearance of the final result. After approval of this rehabilitation concept, the virtual surgical planning can be performed and the surgical guide can be designed, allowing the treatment to take place. This protocol allows the development of a rigorous treatment plan based on the integration of teeth and gingiva component. The waxup and the soft tissue mock-up play a significant role, since they allow an earlier evaluation of the esthetic result, better prosthetic and surgical planning, and it allows us to anticipate the need for gingiva-colored ceramics use. The authors present a clinical case report of the importance of the wax-up and soft tissue mock-up in the treatment plan.

Handbook for Implementing Agile in Department of Defense Information Technology Acquisition

DTIC Science & Technology

2010-12-15

Wire-frame Mockup of iTunes Cover Flow Feature (source: http://www.balsamiq.com/products/mockups/examples#mytunez...programming. The JOPES customer was included early in the development process in order to understand requirements management (story cards ), observe...transition by teaching the new members Agile processes, such as story card development, refactoring, and pair programming. Additionally, the team worked to

STS-117 Crew Training during suited PI/DO Prep in CCT-II mockup

NASA Image and Video Library

2006-08-03

JSC2006-E-32656 (3 Aug. 2006) --- While seated at the pilot's station, astronaut Lee J. Archambault, STS-117 pilot, participates in a training session in the crew compartment trainer (CCT-2) in the Space Vehicle Mockup Facility at Johnson Space Center. Archambault is wearing a training version of his shuttle launch and landing suit.

STS-117 Crew Training during suited PI/DO Prep in CCT-II mockup

NASA Image and Video Library

2006-08-03

JSC2006-E-32653 (3 Aug. 2006) --- While seated at the pilot's station, astronaut Lee J. Archambault, STS-117 pilot, participates in a training session in the crew compartment trainer (CCT-2) in the Space Vehicle Mockup Facility at Johnson Space Center. Archambault is wearing a training version of his shuttle launch and landing suit.

STS-117 Crew Training during suited PI/DO Prep in CCT-II mockup

NASA Image and Video Library

2006-08-03

JSC2006-E-32647 (3 Aug. 2006) --- While seated at the commander's station, astronaut Frederick W. (Rick) Sturckow, STS-117 commander, participates in a training session in the crew compartment trainer (CCT-2) in the Space Vehicle Mockup Facility at Johnson Space Center. Sturckow is wearing a training version of his shuttle launch and landing suit.

Experiments of multichannel least-square methods for sound field reproduction inside aircraft mock-up: Objective evaluations

NASA Astrophysics Data System (ADS)

Gauthier, P.-A.; Camier, C.; Lebel, F.-A.; Pasco, Y.; Berry, A.; Langlois, J.; Verron, C.; Guastavino, C.

2016-08-01

Sound environment reproduction of various flight conditions in aircraft mock-ups is a valuable tool for the study, prediction, demonstration and jury testing of interior aircraft sound quality and annoyance. To provide a faithful reproduced sound environment, time, frequency and spatial characteristics should be preserved. Physical sound field reproduction methods for spatial sound reproduction are mandatory to immerse the listener's body in the proper sound fields so that localization cues are recreated at the listener's ears. Vehicle mock-ups pose specific problems for sound field reproduction. Confined spaces, needs for invisible sound sources and very specific acoustical environment make the use of open-loop sound field reproduction technologies such as wave field synthesis (based on free-field models of monopole sources) not ideal. In this paper, experiments in an aircraft mock-up with multichannel least-square methods and equalization are reported. The novelty is the actual implementation of sound field reproduction with 3180 transfer paths and trim panel reproduction sources in laboratory conditions with a synthetic target sound field. The paper presents objective evaluations of reproduced sound fields using various metrics as well as sound field extrapolation and sound field characterization.

Tungsten joining with copper alloy and its high heat load performance

NASA Astrophysics Data System (ADS)

Liu, Xiang; Lian, Youyun; Chen, Lei; Cheng, Zengkui; Chen, Jiming; Duan, Xuru; Song, Jioupeng; Yu, Yang

2014-12-01

W-CuCrZr joining technology by using low activation Cu-Mn filler metal was developed at Southwestern Institute of Physics (SWIP) for the manufacturing of divertor components of fusion experiment devices. In addition, a fast W coating technology by chemical vapor deposition (CVD) was also developed and CVD-W/CuCrZr and CVD-W/C mockups with a W coating thickness of 2 mm were prepared. In order to assess their high heat flux (HHF) performances, a 60 kW Electron-beam Material testing Scenario (EMS-60) equipped with a 150 keV electron beam welding gun was constructed at SWIP. Experimental results indicated that brazed W/CuCrZr mockups can withstand 8 MW/m2 heat flux for 1000 cycles without visible damages and CVD-W/CuCrZr mockups with W-Cu gradient interface can survive 1000 cycles under 11 MW/m2 heat flux. An ultrasonic inspection method for non-destructive tests (NDT) of brazed W/CuCrZr mockups was established and 2 mm defect can be detected. Infinite element analysis and heat load tests indicated that 5 mm defect had less noticeable influence on the heat transfer.

Integral measurements of neutron and gamma-ray leakage fluxes from the Little Boy replica

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

Muckenthaler, F.J.

This report presents integral measurements of neutron and gamma-ray leakage fluxes from a critical mockup of the Hiroshima bomb Little Boy at Los Alamos National Laobratory with detector systems developed by Oak Ridge National Laboratory. Bonner ball detectors were used to map the neutron fluxes in the horizontal midplane at various distances from the mockup and for selected polar angles, keeping the source-detector separation constant. Gamma-ray energy deposition measurements were made with thermoluminescent detectors at several locations on the iron shell of the source mockup. The measurements were performed as part of a larger progam to provide benchmark data formore » testing the methods used to calculate the radiation released from the Little Boy bomb over Hiroshima. 3 references, 10 figures.« less

The design, fabrication and delivery of a spacelab neutral buoyancy Instrument Pointing System (IPS) mockup. [underwater training simulator

NASA Technical Reports Server (NTRS)

Vanvalkenburgh, C. N.

1984-01-01

Underwater simulations of EVA contingency operations such as manual jettison, payload disconnect, and payload clamp actuation were used to define crew aid needs and mockup pecularities and characteristics to verify the validity of simulation using the trainer. A set of mockup instrument pointing system tests was conducted and minor modifications and refinements were made. Flight configuration struts were tested and verified to be operable by the flight crew. Tasks involved in developing the following end items are described: IPS gimbal system, payload, and payload clamp assembly; the igloos (volumetric); spacelab pallets, experiments, and hardware; experiment, and hardware; experiment 7; and EVA hand tools, support hardware (handrails and foot restraints). The test plan preparation and test support are also covered.

Shuttle to Space Station. Heart Assist Implant. Hubble Update. X-30 Mock-Up

NASA Technical Reports Server (NTRS)

1992-01-01

Shuttle to Space Station, Heart Assist Implant, Hubble Update, and X-30 Mockup are the four parts that are discussed in this video. The first part, Shuttle to Space Station, is focussed on the construction and function of the Space Station Freedom. While part two, Heart Assist Implant, discusses a newly developed electromechanical device that helps to reduce heart attack by using electric shocks. Interviews with the co-inventor and patients are also included. Brief introduction to Hubble Telescope, problem behind its poor image quality (mirror aberration), and the plan to correct this problem are the three issues that are discussed in part three, Hubble Update. The last part, part four, reviews the X-30 Mockup designed by the staff and students of Mississippi State University.

Installation of X-15 full-scale mock-up at Dryden

NASA Technical Reports Server (NTRS)

1995-01-01

This photo shows workers installing the full-scale mock-up of X-15 #3 at the NASA Dryden Flight Research Center, Edwards, California, in September 1995. The mock-up is now on a pedestal outside the main gate at the center. The original X-15 #3, serial number 56-6672, was destroyed 15 November 1967, in a crash that also fatally injured pilot Maj. Michael J. Adams. The X-15 was a rocket-powered aircraft 50 ft long with a wingspan of 22 ft. It was a missile-shaped vehicle with an unusual wedge-shaped vertical tail, thin stubby wings, and unique side fairings that extended along the side of the fuselage. The X-15 weighed about 14,000 lb empty and approximately 34,000 lb at launch. The XLR-99 rocket engine, manufactured by Thiokol Chemical Corp., was pilot controlled and was capable of developing 57,000 lb of thrust. North American Aviation built three X-15 aircraft for the program. The X-15 research aircraft was developed to provide in-flight information and data on aerodynamics, structures, flight controls, and the physiological aspects of high-speed, high-altitude flight. A follow-on program used the aircraft as a testbed to carry various scientific experiments beyond the Earth's atmosphere on a repeated basis. For flight in the dense air of the usable atmosphere, the X-15 used conventional aerodynamic controls such as rudder surfaces on the vertical stabilizers to control yaw and movable horizontal stabilizers to control pitch when moving in synchronization or roll when moved differentially. 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. Because of the large fuel consumption, the X-15 was air launched from a B-52 aircraft at 45,000 ft and a speed of about 500 mph. Depending on the mission, the rocket engine provided thrust for the first 80 to 120 sec of flight. The remainder of the normal 10 to 11 min. flight was powerless and ended with a 200-mph glide landing. Generally, one of two types of X-15 flight profiles was used; a high-altitude flight plan that called for the pilot to maintain a steep rate of climb, or a speed profile that called for the pilot to push over and maintain a level altitude. The X-15 was flown over a period of nearly 10 years -- June 1959 to Oct. 1968 -- and set the world's unofficial speed and altitude records of 4,520 mph (Mach 6.7) and 354,200 ft in a program to investigate all aspects of manned hypersonic flight. 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. The X-15s made a total of 199 flights, and were manufactured by North American Aviation. X-15-1, serial number 56-6670, is now located at the National Air and Space Museum, Washington DC. North American X-15A-2, serial number 56-6671, is at the United States Air Force Museum, Wright-Patterson AFB, Ohio. Parts of the crashed X-15-3, recovered by Peter Merlin and Tony Moore (The X-Hunters) in 1992, are on display at the Air Force Flight Test Center Museum at Edwards. The canopy from the X-15-3, recovered during the original search in 1967, is displayed at the San Diego Aerospace Museum, San Diego, California.

STS-135 crew during Ingress/Egress Timeline training in building 9NW space station mockups

NASA Image and Video Library

2011-04-29

JSC2011-E-043876 (29 April 2011) --- NASA astronauts Sandy Magnus and Rex Walheim (mostly out of frame at right), both STS-135 mission specialists, participate in an EVA Thermal Protection System (TPS) overview training session in the TPS/Precision Air Bearing Facility in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center. Photo credit: NASA

STS-135 crew during Ingress/Egress Timeline training in building 9NW space station mockups

NASA Image and Video Library

2011-04-29

JSC2011-E-043872 (29 April 2011) --- NASA astronauts Sandy Magnus and Rex Walheim, both STS-135 mission specialists, participate in an EVA Thermal Protection System (TPS) overview training session in the TPS/Precision Air Bearing Facility in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center. A crew instructor (right) assisted Magnus and Walheim. Photo credit: NASA

STS-117 Crew Training during suited PI/DO Prep in CCT-II mockup

NASA Image and Video Library

2006-08-03

JSC2006-E-32666 (3 Aug. 2006) --- Attired in training versions of their shuttle launch and landing suits, astronauts James F. Reilly II (left) and John D. (Danny) Olivas, both STS-117 mission specialists, participate in a training session on the middeck of the crew compartment trainer (CCT-2) in the Space Vehicle Mockup Facility at Johnson Space Center.

Seeing is Believing: Video Mock-Ups to Evaluate and Demonstrate Multimedia Designs

ERIC Educational Resources Information Center

Fadde, Peter J.

2007-01-01

A video mock-up is a "design story", described by Patrick Parrish in a recent "TechTrends" article as "imagining the journey of a learner's experience in engaging with a finished design". A design story allows designers to show their design vision to others and to observe features and benefits of the program as a learner would experience it. The…

GEMINI-TITAN (GT)-9 - MOCKUP - ADAPTER EQUIPMENT SECTION - FUEL CELL - MSC

NASA Image and Video Library

1966-03-01

S66-22686 (March 1966) --- Mock-up of the adapter equipment section to be used on the Gemini-9 spaceflight. This section provides volume and attach points for several system modules, including Orbit Attitude Maneuver System, Environmental Control System primary oxygen supply, batteries, coolant, and electrical and electric components. This section will also hold the Astronaut Maneuvering Unit (AMU) backpack (center). Photo credit: NASA

STS-125 Crew during Post Insertion/Deorbit Prep training in CCT II mockup.

NASA Image and Video Library

2008-01-29

JSC2008-E-008416 (29 Jan. 2008) --- United Space Alliance (USA) instructor David L. Williams (center) briefs STS-125 crewmembers during a training session in the Space Vehicle Mockup Facility at the Johnson Space Center. Crewmembers pictured are K. Megan McArthur (left), Michael T. Good, John M. Grunsfeld (second right), all mission specialists; and Gregory C. Johnson (right), pilot.

Fabrication of divertor mock-up with ODS-Cu and W by the improved brazing technique

NASA Astrophysics Data System (ADS)

Tokitani, M.; Hamaji, Y.; Hiraoka, Y.; Masuzaki, S.; Tamura, H.; Noto, H.; Tanaka, T.; Muroga, T.; Sagara, A.; FFHR Design Group

2017-07-01

Copper alloy has been considered as a divertor cooling tube or heat sink not only in the helical reactor FFHR-d1 but also in the tokamak DEMO reactor, because it has a high thermal conductivity. This work focused on applying an oxide dispersion strengthened copper alloy (ODS-Cu), GlidCop® (Cu-0.3 wt%Al2O3) as the divertor heat sink material of FFHR-d1. This alloy has superior high temperature yield strength exceeding 300 MPa at room temperature even after annealing up to ~1000 °C. The change in material properties of Pure-Cu, GlidCop® and CuCrZr by neutron irradiation are summarized in this paper. A primary dose limit is the radiation-induced hardening/softening (~0.2 dpa/1-2 dpa) which has a temperature dependence. According to such an evaluation, the GlidCop® can be selected as the current best candidate material in the commercial base of the divertor heat sink, and its temperature should be maintained as close as possible to 300 °C during operation. Bonding between the W armour and the GlidCop® heat sink was successfully performed by using an improved brazing technique with BNi-6 (Ni-11%P) filler material. The bonding strength was measured by a three-point bending test and reached up to approximately 200 MPa. Surprisingly, several specimens showed an obvious yield point. This means that the BNi-6 brazing (bonding) layer caused relaxation of the applied stress. The small-scale divertor mock-up of the W/BNi-6/GlidCop® was successfully fabricated by using the improved brazing technique. The heat loading test was carried out by the electron beam device ACT2 in NIFS. The mock-up showed an excellent heat removal capability for use in the FFHR-d1 divertor.

Design test request No. 1263 K Reactor graphite key and VSR channel sleeve test

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

Kempf, F.J.

1964-12-10

The objectives of this test were: (1) Determine the coefficient of friction between two adjacent layers of K Reactor graphite at room temperature. (2) Determine the average load required to cause failure of an unirradiated K Reactor side reflector bar, when subjected to tensile loading applied through the reflector keys. (3) Determine the average load at failure and the average deflection at failure of a single VSR channel key when loaded in keyways with clearances equal to those used in original stack construction. (4) Determine the average load and deflection required to break the four K Reactor VSR keys whenmore » loaded simultaneously in both `3-layer` and `7-layer` mockups. Also determine the mode of key failure; i.e., shear, flexure or combined compression and bending. Following these key rupture tests, determine the strength and deflection characteristics of the proposed K Reactor VSR channel sleeve when loaded in a manner identical to that used to fracture the keys. (5) Determine the average load and deflection at failure of both the proposed K Reactor VSR channel sleeves and the proposed C Reactor sleeves when subjected to crushing loads. (6) Determine the extent of damage to the proposed K Reactor VSR channel sleeve when subjected to the following vertical rod loading conditions. (a) Full rod drop in a channel mockup which has been misaligned 2 1/2 inches. (b) Full rod drop in a channel which has been misaligned an amount equal to the maximum flexibility of a `universal` VSR.« less

Thermal Fatigue Study on the Divertor Plate Materials

NASA Astrophysics Data System (ADS)

Wu, Ji-hong; Zhang, Fu; Xu, Zeng-yu; Yan, Jian-cheng

2002-10-01

Thermal fatigue property of the divertor plate is one of the key issues that governs the lifetime of the divertor plate. Taking tungsten as surface material, a small-mock-up divertor plate was made by hot isostatic press welding (HIP). A thermal cycling experiment for divertor mock-up was carried out in the vacuum, where a high-heat-flux electronic gun was used as the thermal source. A cyclic heat flux of 9 MW/m2 was loaded onto the mock-up, a heating duration of 20 s was selected, the cooling water flow rate was 80 ml/s. After 1000 cycles, the surface and the W/Cu joint of the mock-up did not show any damage. The SEM was used to analyze the microstructure of the welding joint, where no cracks were found also.

Behavior of Brazed W/Cu Mockup Under High Heat Flux Loads

NASA Astrophysics Data System (ADS)

Chen, Lei; Lian, Youyun; Liu, Xiang

2014-03-01

In order to transfer the heat from the armor to the coolant, tungsten has to be connected with a copper heat sink. The joint technology is the most critical issue for manufacturing plasma facing components. Consequently, the reliability of the joints should be verified by a great number of high-heat-flux (HHF) tests to simulate the real load conditions. W/Cu brazed joint technology with sliver free filler metal CuMnNi has been developed at Southwestern Institute of Physics (SWIP). Screening and thermal fatigue tests of one small-scale flat tile W/CuCrZr mockup were performed on a 60 kW electron-beam Material testing scenario (EMS-60) constructed recently at SWIP. The module successfully survived screening test with the absorbed power density (Pabs) of 2 MW/m2 to 10 MW/m2 and the following 1000 cycles at Pabs of 7.2 MW/m2 without hot spots and overheating zones during the whole test campaign. Metallurgy and SEM observations did not find any cracks at both sides and the interface, indicating a good bonding of W and CuCrZr alloy. In addition, finite element simulations by ANSYS 12.0 under experimental load conditions were performed and compared with experimental results.

Digital Rebirth of the Greatest Church of Cluny Maior Ecclesia: from Optronic Surveys to Real Time Use of the Digital Model

NASA Astrophysics Data System (ADS)

Landrieu, J.; Père, C.; Rollier, J.; Castandet, S.; Schotte, G.

2011-09-01

Our multidisciplinary team has virtually reconstructed the greatest church of the Romanesque period in Europe. The third church of the Abbey of Cluny (12th c.) has been destroyed after the French Revolution, leaving only 8% of the building standing. Many documents have been studied, to include the latest archaeological knowledge in the virtual model. Most remains have been scanned for CAD restitution. The mock-up of the church needed 1600 different numerical files, including the scanned pieces and the anastylosis of a Romanesque portal, a Gothic façade and a mosaic pavement. We faced various difficulties to assemble the different elements of the huge building, and to include the digitized parts. Our workflow consisted in generating geometrical shapes of the church, enriched with metadata such as texture, material... The whole mock up was finally exported to dedicated software to run the rendering step. Our work consisted in creating a whole database of 3D models as well as 2D sources (plans, engravings, pictures...) accessible by the scientific community. The scientific perspectives focus on a representation in virtual immersion of the grand church at scale 1 and an access to the digital mock-up through Augmented Reality.

Visualization of Flow in Pressurizer Spray Line Piping and Estimation of Thermal Stress Fluctuation Caused by Swaying of Water Surface

NASA Astrophysics Data System (ADS)

Oumaya, Toru; Nakamura, Akira; Onojima, Daisuke; Takenaka, Nobuyuki

The pressurizer spray line of PWR plants cools reactor coolant by injecting water into pressurizer. Since the continuous spray flow rate during commercial operation of the plant is considered insufficient to fill the pipe completely, there is a concern that a water surface exists in the pipe and may periodically sway. In order to identify the flow regimes in spray line piping and assess their impact on pipe structure, a flow visualization experiment was conducted. In the experiment, air was used substituted for steam to simulate the gas phase of the pressurizer, and the flow instability causing swaying without condensation was investigated. With a full-scale mock-up made of acrylic, flow under room temperature and atmospheric pressure conditions was visualized, and possible flow regimes were identified based on the results of the experiment. Three representative patterns of swaying of water surface were assumed, and the range of thermal stress fluctuation, when the surface swayed instantaneously, was calculated. With the three patterns of swaying assumed based on the visualization experiment, it was confirmed that the thermal stress amplitude would not exceed the fatigue endurance limit prescribed in the Japanese Design and Construction Code.

STS-135 crew during Ingress/Egress Timeline training in building 9NW space station mockups

NASA Image and Video Library

2011-04-29

JSC2011-E-043869 (29 April 2011) --- NASA astronauts Sandy Magnus and Rex Walheim, both STS-135 mission specialists, participate in an EVA Thermal Protection System (TPS) overview training session in the TPS/Precision Air Bearing Facility in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center. A model of a space shuttle is in the foreground. Photo credit: NASA

STS-40 Payload Specialist Millie Hughes-Fulford trains in JSC's SLS mockup

NASA Image and Video Library

1987-03-10

STS-40 Payload Specialist Millie Hughes-Fulford conducts Spacelab Life Sciences 1 (SLS-1) Experiment No. 198, Pulmonary Function During Weightlessness, in JSC's Life Sciences Project Division (LSPD) SLS mockup located in the Bioengineering and Test Support Facility Bldg 36. Hughes-Fulford sets switches on Rack 8. Behind her in the center aisle are the stowed bicycle ergometer (foreground) and the body restraint system.

STS_135_ SVMF

NASA Image and Video Library

2011-06-29

JSC2011-E-060135 (29 June 2011) --- The crew of STS-135, from left, Chris Ferguson, Rex Walheim, Doug Hurley and Sandy Magnus, review procedures on the middeck of the Crew Compartment Trainer (CCT) mock-up as they train at NASA?s Johnson Space Center in Houston on June 29, 2011. The training marked the crew's final scheduled session in the Space Vehicle Mock-up Facility. Photo credit: NASA photo/Houston Chronicle, Smiley N. Pool

High power millimeter wave experiment of ITER relevant electron cyclotron heating and current drive system.

PubMed

Takahashi, K; Kajiwara, K; Oda, Y; Kasugai, A; Kobayashi, N; Sakamoto, K; Doane, J; Olstad, R; Henderson, M

2011-06-01

High power, long pulse millimeter (mm) wave experiments of the RF test stand (RFTS) of Japan Atomic Energy Agency (JAEA) were performed. The system consists of a 1 MW/170 GHz gyrotron, a long and short distance transmission line (TL), and an equatorial launcher (EL) mock-up. The RFTS has an ITER-relevant configuration, i.e., consisted by a 1 MW-170 GHz gyrotron, a mm wave TL, and an EL mock-up. The TL is composed of a matching optics unit, evacuated circular corrugated waveguides, 6-miter bends, an in-line waveguide switch, and an isolation valve. The EL-mock-up is fabricated according to the current design of the ITER launcher. The Gaussian-like beam radiation with the steering capability of 20°-40° from the EL mock-up was also successfully proved. The high power, long pulse power transmission test was conducted with the metallic load replaced by the EL mock-up, and the transmission of 1 MW/800 s and 0.5 MW/1000 s was successfully demonstrated with no arcing and no damages. The transmission efficiency of the TL was 96%. The results prove the feasibility of the ITER electron cyclotron heating and current drive system. © 2011 American Institute of Physics

Fabrication and integrity test preparation of HIP-joined W and ferritic-martensitic steel mockups for fusion reactor development

NASA Astrophysics Data System (ADS)

Lee, Dong Won; Shin, Kyu In; Kim, Suk Kwon; Jin, Hyung Gon; Lee, Eo Hwak; Yoon, Jae Sung; Choi, Bo Guen; Moon, Se Youn; Hong, Bong Guen

2014-10-01

Tungsten (W) and ferritic-martensitic steel (FMS) as armor and structural materials, respectively, are the major candidates for plasma-facing components (PFCs) such as the blanket first wall (BFW) and the divertor, in a fusion reactor. In the present study, three W/FMS mockups were successfully fabricated using a hot isostatic pressing (HIP, 900 °C, 100 MPa, 1.5 hrs) with a following post-HIP heat treatment (PHHT, tempering, 750 °C, 70 MPa, 2 hrs), and the W/FMS joining method was developed based on the ITER BFW and the test blanket module (TBM) development project from 2004 to the present. Using a 10-MHz-frequency flat-type probe to ultrasonically test of the joint, we found no defects in the fabricated mockups. For confirmation of the joint integrity, a high heat flux test will be performed up to the thermal lifetime of the mockup under the proper test conditions. These conditions were determined through a preliminary analysis with conventional codes such as ANSYS-CFX for thermal-hydraulic conditions considering the test facility, the Korea heat load test facility with an electron beam (KoHLT-EB), and its water coolant system at the Korea Atomic Energy Research Institute (KAERI).

Conceptual design of divertor and first wall for DEMO-FNS

NASA Astrophysics Data System (ADS)

Sergeev, V. Yu.; Kuteev, B. V.; Bykov, A. S.; Gervash, A. A.; Glazunov, D. A.; Goncharov, P. R.; Dnestrovskij, A. Yu.; Khayrutdinov, R. R.; Klishchenko, A. V.; Lukash, V. E.; Mazul, I. V.; Molchanov, P. A.; Petrov, V. S.; Rozhansky, V. A.; Shpanskiy, Yu. S.; Sivak, A. B.; Skokov, V. G.; Spitsyn, A. V.

2015-11-01

Key issues of design of the divertor and the first wall of DEMO-FNS are presented. A double null closed magnetic configuration was chosen with long external legs and V-shaped corners. The divertor employs a cassette design similar to that of ITER. Water-cooled first wall of the tokamak is made of Be tiles and CuCrZr-stainless steel shells. Lithium injection and circulation technologies are foreseen for protection of plasma facing components. Simulations of thermal loads onto the first wall and divertor plates suggest a possibility to distribute heat loads making them less than 10 MW m-2. Evaluations of sputtering and evaporation of plasma-facing materials suggest that lithium may protect the first wall. To prevent Be erosion at the outer divertor plates either the full detached divertor operation or arrangement of the renewal lithium flow on targets should be implemented. Test bed experiments on the Tsefey-M facility with the first wall mockup coated by Ве tiles and cooled by water are presented. The temperature of the surface of tiles reached 280-300 °С at 5 MW m-2 and 600-650 °С at 10.5 MW m-2. The mockup successfully withstood 1000 cycles with the lower thermal loading and 100 cycles with higher thermal loading.

Astronaut Gene Cernan poses in front of Gemini Mission Simulator

NASA Image and Video Library

1966-08-09

S66-32698 (17 June 1966) --- Astronaut Eugene A. Cernan discusses his Gemini-9A extravehicular activity before a gathering of news media representatives in the MSC auditorium. In the background is an Astronaut Maneuvering Unit (AMU) mock-up mounted in a mock-up of a Gemini spacecraft adapter equipment section. Astronauts Cernan and Thomas P. Stafford completed their three-day mission in space on June 6, 1966. Photo credit: NASA

ASTP crewmen in Soyuz orbital module mock-up during training session at JSC

NASA Technical Reports Server (NTRS)

1975-01-01

An interior view of the Soyuz orbital module mock-up in bldg 35 during Apollo Soyuz Test Project (ASTP) joint crew training at JSC. The ASTP crewmen are Astronaut Vance D. Brand (on left), command module pilot of the American ASTP prime crew; and Cosmonaut Valeriy N. Kubasov, engineer on the Soviet ASTP first (prime) crew. The training session simulated activities on the second day in Earth orbit.

Astronauts McMonagle and Brown on flight deck mockup during training

NASA Technical Reports Server (NTRS)

1994-01-01

Astronauts Donald R. McMonagle, STS-66 mission commander, left, and Curtis L. Brown, STS-66 pilot, man the commander's and pilot's stations, respectively, during a rehearsal of procedures to be followed during the launch and entry phases of their scheduled November 1994 flight. This rehearsal, held in the crew compartment trainer (CCT) of JSC's Shuttle mockup and integration laboratory, was followed by a training session on emergency egress procedures.

Development of robotics facility docking test hardware

NASA Technical Reports Server (NTRS)

Loughead, T. E.; Winkler, R. V.

1984-01-01

Design and fabricate test hardware for NASA's George C. Marshall Space Flight Center (MSFC) are reported. A docking device conceptually developed was fabricated, and two docking targets which provide high and low mass docking loads were required and were represented by an aft 61.0 cm section of a Hubble space telescope (ST) mockup and an upgrading of an existing multimission modular spacecraft (MSS) mockup respectively. A test plan is developed for testing the hardware.

Space telescope neutral buoyancy simulations: The first two years

NASA Technical Reports Server (NTRS)

Sanders, F. G.

1982-01-01

Neutral Buoyancy simulations which were conducted to validate the crew systems interface as it relates to space telescope on-orbit maintenance and contingency operations is discussed. The initial concept validation tests using low fidelity mockups is described. The entire spectrum of proposed space telescope refurbishment and selected contingencies using upgraded mockups which reflect flight hardware are reported. Findings which may be applicable to future efforts of a similar nature are presented.

Payload Specialist Scully-Power in full flight suit with helmet

NASA Image and Video Library

1984-09-04

41D-3183 (2 Sept. 1984) --- Paul D. Scully-Power, 41-G payload specialist, appears ready to participate in the eight-day space shuttle mission in this photograph taken during a pause in training in the Johnson Space Center's mockup and integration laboratory. The U.S. Navy oceanographer and a Canadian will join five NASA astronauts for a busy stay in space aboard the Challenger next month. The team was practicing for emergency egress. Photo credit: NASA (Editor's note: Please ignore the odd photo identification number for this image. This is a 41-G training image.)

John Glenn during preflight training for STS-95

NASA Image and Video Library

1998-04-14

S98-06946 (28 April 1998) --- U.S. Sen. John H. Glenn Jr. (D.-Ohio), uses a device called a Sky genie to simulate rappelling from a troubled Space Shuttle during training at the Johnson Space Center (JSC). This training mockup is called The full fuselage trainer (FFT). Glenn has been named as a payload specialist for STS-95, scheduled for launch later this year. This exercise, in the systems integration facility at JSC, trains the crew members for procedures to follow in egressing a troubled shuttle on the ground. Photo Credit: Joe McNally, National Geographic, for NASA

KSC-2015-1214

NASA Image and Video Library

2015-01-28

CAPE CANAVERAL, Fla. – NASA’s Kennedy Space Center in Florida paid tribute to the crews of Apollo 1 and space shuttles Challenger and Columbia, as well as other NASA astronauts who lost their lives while furthering the cause of exploration and discovery, during the agency's Day of Remembrance, Jan. 28. A wreath-laying ceremony was held at the Space Mirror Memorial located in the Kennedy Space Center Visitor Complex. Behind the memorial, the full-size mock-up of the external fuel tank and solid rocket boosters mark the entrance to the Space Shuttle Atlantis exhibit. Photo credit: NASA/Jim Grossmann

KSC-2012-4319

NASA Image and Video Library

2012-08-06

CAPE CANAVERAL, Fla. – The Orion mockup spacecraft sits atop its service module simulator in the transfer aisle of the Vehicle Assembly Building, or VAB, at NASA's Kennedy Space Center in Florida. 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. The first uncrewed test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on a Space Launch System rocket. The Orion mockup is exact in details on the outside, but mostly empty on the inside except for four mockup astronaut seats and hatch. The work in the VAB is crucial to making sure the designs are accurate. For more information, visit http://www.nasa.gov/orion Photo credit: NASA/ Dmitri Gerondidakis

KSC-2012-4320

NASA Image and Video Library

2012-08-06

CAPE CANAVERAL, Fla. – The Orion mockup spacecraft sits atop its service module simulator in the transfer aisle of the Vehicle Assembly Building, or VAB, at NASA's Kennedy Space Center in Florida. To the left is the aerodynamic shell that will cover the capsule during launch. 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. The first uncrewed test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on a Space Launch System rocket. The Orion mockup is exact in details on the outside, but mostly empty on the inside except for four mockup astronaut seats and hatch. The work in the VAB is crucial to making sure the designs are accurate. For more information, visit http://www.nasa.gov/orion Photo credit: NASA/ Dmitri Gerondidakis

KSC-2012-4316

NASA Image and Video Library

2012-08-06

CAPE CANAVERAL, Fla. – The Orion mockup spacecraft sits atop its service module simulator in the transfer aisle of the Vehicle Assembly Building, or VAB, at NASA's Kennedy Space Center in Florida. 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. The first uncrewed test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on a Space Launch System rocket. The Orion mockup is exact in details on the outside, but mostly empty on the inside except for four mockup astronaut seats and hatch. The work in the VAB is crucial to making sure the designs are accurate. For more information, visit http://www.nasa.gov/orion Photo credit: NASA/ Dmitri Gerondidakis

Preparation of W/CuCrZr mono-block test mock-up using vacuum brazing technique

NASA Astrophysics Data System (ADS)

Premjit Singh, K.; Khirwadkar, S.; Bhope, Kedar; Patel, Nikunj; Mokaria, Prakash

2017-04-01

Development of the joining for W/CuCrZr mono-block PFC test mock-up is an interesting area in Fusion R&D. W/Cu bimetallic material has been prepared using OFHC Copper casting approach on the radial surface of W mono-block tile surface. The W/Cu bimetallic material has been joined with CuCrZr tube (heat sink) material with the vacuum brazing route. Vacuum brazing of W/Cu-CuCrZr has been performed @ 970°C for 10 min using NiCuMn-37 filler material under deep vacuum environment (10-6 mbar). Graphite fixture was used for OFHC Copper casting and vacuum brazing experiments. The joint integrity of W/Cu-CuCrZr mono-block mock-up of W/Cu and Cu-CuCrZr interface has been checked using ultrasonic immersion technique. The result of the experimental work is presented in the paper.

Model of Mars-Bound MarCO CubeSat

NASA Image and Video Library

2015-06-12

Engineers for NASA's MarCO technology demonstration display a full-scale mechanical mock-up of the small craft in development as part of NASA's next mission to Mars. Mechanical engineer Joel Steinkraus and systems engineer Farah Alibay are on the team at NASA's Jet Propulsion Laboratory, Pasadena, California, preparing twin MarCO (Mars Cube One) CubeSats for a March 2016 launch. MarCO is the first interplanetary mission using CubeSat technologies for small spacecraft. The briefcase-size MarCO twins will ride along on an Atlas V launch vehicle lifting off from Vandenberg Air Force Base, California, with NASA's next Mars lander, InSight. The mock-up in the photo is in a configuration to show the deployed position of components that correspond to MarCO's two solar panels and two antennas. During launch, those components will be stowed for a total vehicle size of about 14.4 inches (36.6 centimeters) by 9.5 inches (24.3 centimeters) by 4.6 inches (11.8 centimeters). After launch, the two MarCO CubeSats and InSight will be navigated separately to Mars. The MarCO twins will fly past the planet in September 2016 just as InSight is descending through the atmosphere and landing on the surface. MarCO is a technology demonstration mission to relay communications from InSight to Earth during InSight's descent and landing. InSight communications during that critical period will also be recorded by NASA's Mars Reconnaissance Orbiter for delayed transmission to Earth. InSight -- an acronym for Interior Exploration using Seismic Investigations, Geodesy and Heat Transport -- will study the interior of Mars to improve understanding of the processes that formed and shaped rocky planets, including Earth. After launch, the MarCO twins and InSight will be navigated separately to Mars. Note: After thorough examination, NASA managers have decided to suspend the planned March 2016 launch of the Interior Exploration using Seismic Investigations Geodesy and Heat Transport (InSight) mission. The decision follows unsuccessful attempts to repair a leak in a section of the prime instrument in the science payload. http://photojournal.jpl.nasa.gov/catalog/PIA19389

Scale-up of the electrokinetic fence technology for the removal of pesticides. Part II: Does size matter for removal of herbicides?

PubMed

López-Vizcaíno, R; Risco, C; Isidro, J; Rodrigo, S; Saez, C; Cañizares, P; Navarro, V; Rodrigo, M A

2017-01-01

This work reports results of the application of electrokinetic fence technology in a 32 m 3 -prototype which contains soil polluted with 2,4-D and oxyfluorfen, focusing on the evaluation of the mechanisms that describe the removal of these two herbicides and comparing results to those obtained in smaller plants: a pilot-scale mockup (175 L) and a lab-scale soil column (1 L). Results show that electric heating of soil (coupled with the increase in the volatility) is the key to explain the removal of pollutants in the largest scale facility while electrokinetic transport processes are the primary mechanisms that explain the removal of herbicides in the lab-scale plant. 2-D and 3-D maps of the temperature and pollutant concentrations are used in the discussion of results trying to give light about the mechanisms and about how the size of the setup can lead to different conclusions, despite the same processes are occurring in the soil. Copyright © 2016 Elsevier Ltd. All rights reserved.

Rapid growing clay coatings to reduce the fire threat of furniture.

PubMed

Kim, Yeon Seok; Li, Yu-Chin; Pitts, William M; Werrel, Martin; Davis, Rick D

2014-02-12

Layer-by-layer (LbL) assembly coatings reduce the flammability of textiles and polyurethane foam but require extensive repetitive processing steps to produce the desired coating thickness and nanoparticle fire retardant content that translates into a fire retardant coating. Reported here is a new hybrid bi-layer (BL) approach to fabricate fire retardant coatings on polyurethane foam. Utilizing hydrogen bonding and electrostatic attraction along with the pH adjustment, a fast growing coating with significant fire retardant clay content was achieved. This hybrid BL coating exhibits significant fire performance improvement in both bench scale and real scale tests. Cone calorimetry bench scale tests show a 42% and 71% reduction in peak and average heat release rates, respectively. Real scale furniture mockups constructed using the hybrid LbL coating reduced the peak and average heat release rates by 53% and 63%, respectively. This is the first time that the fire safety in a real scale test has been reported for any LbL technology. This hybrid LbL coating is the fastest approach to develop an effective fire retardant coating for polyurethane foam.

Determination of extra trajectory parameters of projectile layout motion

NASA Astrophysics Data System (ADS)

Ishchenko, A.; Burkin, V.; Faraponov, V.; Korolkov, L.; Maslov, E.; Diachkovskiy, A.; Chupashev, A.; Zykova, A.

2017-11-01

The paper presents a brief description of the experimental track developed and implemented on the base of the RIAMM TSU for external trajectory investigations on determining the main aeroballistic parameters of various shapes projectiles, in the wide velocity range. There is comparison between the experimentally obtained dependence of the fin-stabilized projectile mock-up aerodynamic drag coefficient on the Mach number with the 1958 aerodynamic drag law and aerodynamic tests of the same mock-up

KENNEDY SPACE CENTER, FLA. - At the Rotation, Processing and Surge Facility stand a mockup of two segments of a solid rocket booster (SRB) being used to test the feasibility of a vertical SRB propellant grain inspection, required as part of safety analysis.

NASA Image and Video Library

2003-09-11

KENNEDY SPACE CENTER, FLA. - At the Rotation, Processing and Surge Facility stand a mockup of two segments of a solid rocket booster (SRB) being used to test the feasibility of a vertical SRB propellant grain inspection, required as part of safety analysis.

Overview of decade-long development of plasma-facing components at ASIPP

NASA Astrophysics Data System (ADS)

Luo, G.-N.; Liu, G. H.; Li, Q.; Qin, S. G.; Wang, W. J.; Shi, Y. L.; Xie, C. Y.; Chen, Z. M.; Missirlian, M.; Guilhem, D.; Richou, M.; Hirai, T.; Escourbiac, F.; Yao, D. M.; Chen, J. L.; Wang, T. J.; Bucalossi, J.; Merola, M.; Li, J. G.; EAST Team

2017-06-01

The first EAST (Experimental Advanced Superconducting Tokamak) plasma ignited in 2006 with non-actively cooled steel plates as the plasma-facing materials and components (PFMCs) which were then upgraded into full graphite tiles bolted onto water-cooled copper heat sinks in 2008. The first wall was changed further into molybdenum alloy in 2012, while keeping the graphite for both the upper and lower divertors. With the rapid increase in heating and current driving power in EAST, the W/Cu divertor project was launched around the end of 2012, aiming at achieving actively cooled full W/Cu-PFCs for the upper divertor, with heat removal capability up to 10 MW m-2. The W/Cu upper divertor was finished in the spring of 2014, consisting of 80 cassette bodies toroidally assembled. Commissioning of the EAST upper W/Cu divertor in 2014 was unsatisfactory and then several practical measures were implemented to improve the design, welding quality and reliability, which helped us achieve successful commissioning in the 2015 Spring Campaign. In collaboration with the IO and CEA teams, we have demonstrated our technological capability to remove heat loads of 5000 cycles at 10 MW m-2 and 1000 cycles at 20 MW m-2 for the small scale monoblock mockups, and surprisingly over 300 cycles at 20 MW m-2 for the flat-tile ones. The experience and lessons we learned from batch production and commissioning are undoubtedly valuable for ITER (International Thermonuclear Experimental Reactor) engineering validation and tungsten-related plasma physics.

Supplementary Investigation to Determine the Effects of Center-of-Gravity Position on the Spin, Longitudinal-Trim, and Tumbling Characteristics of a 1/20-Scale Model of the Consolidated Vultee 7002 Airplane (Flying Mock-up of XF-92)

NASA Technical Reports Server (NTRS)

Klinar, Walter J.; Jones, Ira P., Jr.

1948-01-01

A supplementary wind-tunnel investigation has been conducted to determine the effect of rearward positions of the center of gravity on the spin, longitudinal-trim, and tumbling characteristics of the 1/20-scale model of the Consolidated Vultee 7002 airplane equipped with the single vertical tail. A few tests were also made with dual vertical tails added to the model. The model was ballasted to represent, the airplane in its approximate design gross weight for two center-of-gravity positions, 3O and 35 percent of the mean aerodynamic chord. The original tests previously reported were for a center-of-gravity position of 24 percent of the mean aerodynamic chord.

First steps in designing an all-in-one ICT-based device for persons with cognitive impairment: evaluation of the first mock-up.

PubMed

Boman, Inga-Lill; Persson, Ann-Christine; Bartfai, Aniko

2016-03-07

This project Smart Assisted Living involving Informal careGivers++ (SALIG) intends to develop an ICT-based device for persons with cognitive impairment combined with remote support possibilities for significant others and formal caregivers. This paper presents the identification of the target groups' needs and requirements of such device and the evaluation of the first mock-up, demonstrated in a tablet. The inclusive design method that includes end-users in the design process was chosen. First, a scoping review was conducted in order to examine the target group's need of an ICT-based device, and to gather recommendations regarding its design and functionalities. In order to capture the users' requirements of the design and functionalities of the device three targeted focus groups were conducted. Based on the findings from the publications and the focus groups a user requirement specification was developed. After that a design concept and a first mock-up was developed in an iterative process. The mock-up was evaluated through interviews with persons with cognitive impairment, health care professionals and significant others. Data were analysed using content analysis. Several useful recommendations of the design and functionalities of the SALIG device for persons with cognitive impairment were identified. The main benefit of the mock-up was that it was a single device with a set of functionalities installed on a tablet and designed for persons with cognitive impairment. An additional benefit was that it could be used remotely by significant others and formal caregivers. The SALIG device has the potentials to facilitate everyday life for persons with cognitive impairment, their significant others and the work situation for formal caregivers. The results may provide guidance in the development of different types of technologies for the target population and for people with diverse disabilities. Further work will focus on developing a prototype to be empirically tested by persons with cognitive impairment, their significant others and formal caregivers.

STS-47 Commander Gibson and Pilot Brown at CCT side hatch during JSC training

NASA Technical Reports Server (NTRS)

1992-01-01

STS-47 Endeavour, Orbiter Vehicle (OV) 105, Spacelab Japan (SLJ) Commander Robert L. Gibson (right) and Pilot Curtis L. Brown, Jr, wearing launch and entry suits (LESs), pose in front of the Crew Compartment Trainer (CCT) mockup side hatch during post landing emergency egress procedures held at JSC's Mockup and Integration Laboratory (MAIL) Bldg 9NE. Note that the crew escape system (CES) pole is in position at side hatch but is not extended.

Investigation of the Flying Mock-Up of the Consolidated Vultee XP-92 Airplane in the Ames 40- by 80-Foot Wind Tunnel. Force and Moment Characteristics

NASA Technical Reports Server (NTRS)

Wick, Bradford, H.; Graham, David

1948-01-01

This report contains the results of the investigation of the aerodynamic characteristics of the flying mock-up of the Consolidated Vultee XP-92 airplane as conducted in the Ames 40- by 80-foot wind tunnel, Data are presented for test conditions which would give information as to the limits of stability and controllability, and also, the effect of Reynolds number. No analysis of the data has been made.

PHOTO DATE: 04-23-15.LOCATION: Bldg. 9NW - ISS Airlock Mockup .SUBJECT: Expedition 48/49 (Soyuz 47) crew members Kate Rubins and Takuya Onishi with Soyuz 49 crew member Peggy Whitson during ISS EVA P/P 1 training with instructor Grant Slusser.PHOTOGRAPHER: BILL STAFFORD

NASA Image and Video Library

2015-04-23

PHOTO DATE: 04-23-15 LOCATION: Bldg. 9NW - ISS Airlock Mockup SUBJECT: Expedition 48/49 (Soyuz 47) crew members Kate Rubins and Takuya Onishi with Soyuz 49 crew member Peggy Whitson during ISS EVA P/P 1 training with instructor Grant Slusser PHOTOGRAPHER: BILL STAFFORD

Non destructive testing of concrete nuclear containment plants with surface waves: Lab experiment on decimeter slabs and on the VeRCoRs mock-up

NASA Astrophysics Data System (ADS)

Abraham, Odile; Legland, Jean-Baptiste; Durand, Olivier; Hénault, Jean-Marie; Garnier, Vincent

2018-04-01

The maintenance and evaluation of concrete nuclear containment walls is a major concern as they must, in case of an accident, ensure the confinement of the nuclear radiations and resist to the loads. A homemade multi-receiver multi-source dry contact linear probe to record ultrasonic surface waves on concrete in the frequency range [60 kHz - 200 kHz] has been used in this context. The measurement protocol includes the summation of up to 50 spatially distributed seismograms and the determination of the surface waves phase velocity dispersion curve. The probe has been tested against several concrete states under no loading (water saturation level, temperature damage). Then, the same measurements have been performed on sound and fire damaged slabs submitted to uniaxial loading (stress up to 30 % of the concrete compression resistance). It is shown that the robustness and precision of the surface waves measurement protocol make it possible to follow the stress level. In March 2017 a first experiment with this surface wave probe has been conducted on a reduced 1:3 scale nuclear containment plant (EDF VeRCoRs mock-up) under loading conditions that replicates that of decennial inspection. The surface wave phase velocity dispersion curves of each state are compared and cross-validated with other NDT results.

Enabling Large Focal Plane Arrays through Mosaic Hybridization

NASA Technical Reports Server (NTRS)

Miller, Timothy M.; Jhabvala, Christine A.; Costen, Nick; Benford, Dominic J.

2012-01-01

We have demonstrated the hybridization of large mosaics of far-infrared detectors, joining separately fabricated sub-units into a single unit on a single, large substrate. We produced a single detector mockup on a 100mm diameter wafer and four mockup readout quadrant chips from a separate 100mm wafer. The individually fabricated parts were hybridized using a Suss FC150 flip chip bonder to assemble the detector-readout stack. Once all of the hybridized readouts were in place, a single, large and thick silicon substrate was placed on the stack and attached with permanent epoxy to provide strength and a Coefficient of Thermal Expansion (CTE) match to the silicon components underneath. Wirebond pads on the readout chips connect circuits to warm readout electronics; and were used to validate the successful superconducting electrical interconnection of the mockup mosaic-hybridized detector. This demonstration is directly scalable to 150 mm diameter wafers, enabling pixel areas over ten times the area currently demonstrated.

KSC-2012-4317

NASA Image and Video Library

2012-08-06

CAPE CANAVERAL, Fla. – Mockup components of an Orion spacecraft are laid out in the transfer aisle of the Vehicle Assembly Building, or VAB, at NASA's Kennedy Space Center in Florida. In the foreground is the Launch Abort System. In the background is the Orion capsule model on top of a service module simulator. 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. The first uncrewed test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on a Space Launch System rocket. The Orion mockup is exact in details on the outside, but mostly empty on the inside except for four mockup astronaut seats and hatch. The work in the VAB is crucial to making sure the designs are accurate. For more information, visit http://www.nasa.gov/orion Photo credit: NASA/ Dmitri Gerondidakis

SOFIA pointing and chopping: performance and prospect

NASA Astrophysics Data System (ADS)

Reinacher, Andreas; Lammen, Yannick; Graf, Friederike; Jakob, Holger

2016-09-01

The Stratospheric Observatory for Infrared Astronomy (SOFIA) is a 2.5m infrared telescope built into a Boeing 747 SP. In 2014 SOFIA reached its Full Operational Capability milestone and nowadays takes off about three times a week to observe the infrared sky from altitudes above most of the atmosphere's water vapor content. Despite reaching this major milestone the work to improve the observatory's performance is continuing in many areas. This paper focuses on the telescope's current pointing and chopping performance and gives an overview over the ongoing and foreseen work to further improve in those two areas. Pointing performance as measured with the fast focal plane camera in flight is presented and based on that data it is elaborated how and in which frequency bands a further reduction of image jitter might be achieved. One contributor to the remaining jitter as well as the major actuator to reduce jitter with frequencies greater than 5 Hz is SOFIA's Secondary Mirror Assembly (SMA) or Chopper. As-is SMA jitter and chopping performance data as measured in flight is presented as well as recent improvements to the position sensor cabling and calibration and their effect on the SMA's pointing accuracy. Furthermore a brief description of a laboratory mockup of the SMA is given and the intended use of this mockup to test major hardware changes for further performance improvement is explained.

Highly light-weighted ZERODUR mirror and fixation for cryogenic applications

NASA Astrophysics Data System (ADS)

Behar-Lafenetre, Stephanie; Lasic, Thierry; Viale, Roger; Ruch, Eric

2017-11-01

Space telescopes require large primary mirrors within a demanding thermal environment: observatories at L2 orbit provide a stable environment with a drawback of very low temperature. Besides, it is necessary to limit as far as possible the mirrors mass while withstanding launch loads and keeping image quality within a cryogenic environment. ZERODUR is a well-known material extensively used for large telescope. Alcatel Alenia Space and Sagem/REOSC have combined their respective skills to go further in the lightweighting ratio of large mirror (36 kg/m2 on 1.5 m2) through a detailed design, performance assessment and technology demonstration with breadboards. Beyond on a large mirror detailed design supported by analysis, a ZERODUR mock-up has been manufacturing by Sagem/REOSC to demonstrate the achievability of the demanding parameters offering this high lightweighting ratio. Through the ISO experience on mirror attachments, a detailed design of the mirror fixation has been done as well. A full size mock-up has been manufactured and successfully tested under thermal cycling and static loading. Eventually, the ZERODUR stability behavior within this large temperature range has been verified through thermal cycling and image quality cryotest on a flat mirror breadboard. These developments demonstrate that ZERODUR is a good candidate for large space cryogenic mirrors offering outstanding optical performances associated to matured and proven technology and manufacturing process.

Spacesuit and Space Vehicle Comparative Ergonomic Evaluation

NASA Technical Reports Server (NTRS)

England, Scott; Benson, Elizabeth; Cowley, Matthew; Harvill, Lauren; Blackledge, Christopher; Perez, Esau; Rajulu, Sudhakar

2011-01-01

With the advent of the latest manned spaceflight objectives, a series of prototype launch and reentry spacesuit architectures were evaluated for eventual down selection by NASA based on the performance of a set of designated tasks. A consolidated approach was taken to testing, concurrently collecting suit mobility data, seat-suit-vehicle interface clearances and movement strategies within the volume of a Multi-Purpose Crew Vehicle mockup. To achieve the objectives of the test, a requirement was set forth to maintain high mockup fidelity while using advanced motion capture technologies. These seemingly mutually exclusive goals were accommodated with the construction of an optically transparent and fully adjustable frame mockup. The mockup was constructed such that it could be dimensionally validated rapidly with the motion capture system. This paper will describe the method used to create a motion capture compatible space vehicle mockup, the consolidated approach for evaluating spacesuits in action, as well as the various methods for generating hardware requirements for an entire population from the resulting complex data set using a limited number of test subjects. Kinematics, hardware clearance, suited anthropometry, and subjective feedback data were recorded on fifteen unsuited and five suited subjects. Unsuited subjects were selected chiefly by anthropometry, in an attempt to find subjects who fell within predefined criteria for medium male, large male and small female subjects. The suited subjects were selected as a subset of the unsuited subjects and tested in both unpressurized and pressurized conditions. Since the prototype spacesuits were fabricated in a single size to accommodate an approximately average sized male, the findings from the suit testing were systematically extrapolated to the extremes of the population to anticipate likely problem areas. This extrapolation was achieved by first performing population analysis through a comparison of suited subjects performance to their unsuited performance and then applying the results to the entire range of population. The use of a transparent space vehicle mockup enabled the collection of large amounts of data during human-in-the-loop testing. Mobility data revealed that most of the tested spacesuits had sufficient ranges of motion for tasks to be performed successfully. A failed tasked by a suited subject most often stemmed from a combination of poor field of view while seated and poor dexterity of the gloves when pressurized or from suit/vehicle interface issues. Seat ingress/egress testing showed that problems with anthropometric accommodation does not exclusively occur with the largest or smallest subjects, but rather specific combinations of measurements that lead to narrower seat ingress/egress clearance.

Analysis of Photogrammetry Data from ISIM Mockup, June 1, 2007

NASA Technical Reports Server (NTRS)

Nowak, Maria; Hill, Mike

2007-01-01

During ground testing of the Integrated Science Instrument Module (ISIM) for the James Webb Space Telescope (JWST), the ISIM Optics group plans to use a Photogrammetry Measurement System for cryogenic calibration of specific target points on the ISIM composite structure and Science Instrument optical benches and other GSE equipment. This testing will occur in the Space Environmental Systems (SES) chamber at Goddard Space Flight Center. Close range photogrammetry is a 3 dimensional metrology system using triangulation to locate custom targets in 3 coordinates via a collection of digital photographs taken from various locations and orientations. These photos are connected using coded targets, special targets that are recognized by the software and can thus correlate the images to provide a 3 dimensional map of the targets, and scaled via well calibrated scale bars. Photogrammetry solves for the camera location and coordinates of the targets simultaneously through the bundling procedure contained in the V-STARS software.

Investigation of the Flying Mock-Up of Consolidated Vultee XP-92 Airplane in the Ames 40- by 80-Foot Wind Tunnel: Pressure Distributions

NASA Technical Reports Server (NTRS)

Graham, David

1948-01-01

This report contains the results of the wind tunnel investigation of the pressure distribution on the flying mock-up of the Consolidated Vultee XP-92 airplane. Data are presented for the pressure distribution over the wing, vertical tail and the fuselage, and for the pressure loss and rate of flow through the ducted fuselage. Data are also presented for the calibration of two airspeed indicators, and for the calibration of angle-of-attack and sideslip-angle indicator vanes.

Astronaut Bruce McCandless shows mockup of occulting disc for Skylab exp.

NASA Image and Video Library

1973-11-23

S73-37251 (23 November 1973) --- Astronaut Bruce McCandless II, left, shows off a mock-up of the occulting disc for the T025 Coronagraph Contamination Measurement Engineering and Technology Experiment to be used by the crewmen of the third manned Skylab mission (Skylab 4), now into their eighth day in Earth orbit. On the right is flight director Neil B. Hutchinson. The men are in the Mission Operations Control Room (MOCR) of the Mission Control Center (MCC) at Johnson Space Center. Photo credit: NASA

KENNEDY SPACE CENTER, FLA. - Seen from below and through a solid rocket booster segment mockup, Jeff Thon, an SRB mechanic with United Space Alliance, tests the feasibility of a vertical solid rocket booster propellant grain inspection technique. The inspection of segments is required as part of safety analysis.

NASA Image and Video Library

2003-09-11

KENNEDY SPACE CENTER, FLA. - Seen from below and through a solid rocket booster segment mockup, Jeff Thon, an SRB mechanic with United Space Alliance, tests the feasibility of a vertical solid rocket booster propellant grain inspection technique. The inspection of segments is required as part of safety analysis.

STS-55 German payload specialists (and backups) in LESs during JSC training

NASA Technical Reports Server (NTRS)

1992-01-01

STS-55 Columbia, Orbiter Vehicle (OV) 102, German payload specialists and backup (alternate) payload specialists, wearing launch and entry suits (LESs), pose for group portrait outside mockup side hatch in JSC's Mockup and Integration Laboratory (MAIL) Bldg 9NE. These payload specialists will support the STS-55 Spacelab Deutsche 2 (SL-D2) mission. It is the second dedicated German (Deutsche) Spacelab flight. Left to right are backup Payload Specialists Renate Brummer and Dr. P. Gerhard Thiele, Payload Specialist 1 Ulrich Walter, and Payload Specialist 2 Hans Schlegel.

President Bill Clinton visits JSC

NASA Image and Video Library

1998-04-14

S98-05025 (14 April 1998) --- President Bill Clinton tours a laboratory mockup used for training purposes by astronauts assigned to fly aboard the International Space Station (ISS). Astronaut William Shepherd (right), mission commander for the first ISS expedition crew, briefs the Chief Executive. Looking on are astronauts C. Michael Foale and Tamara C. Jernigan. Foale spent four months last year aboard Russia's Mir space station. President Clinton toured several mockups and other training components before speaking to a crowd of JSC employees. Photo Credit: Joe McNally, National Geographic, for NASA

Multigenerational Independent Colony for Extraterrestrial Habitation, Autonomy, and Behavior Health (MICEHAB): An Investigation of a Long Duration, Partial Gravity, Autonomous Rodent Colony

NASA Technical Reports Server (NTRS)

Rodgers, Erica M.; Simon, Matthew A.; Antol, Jeffrey; Chai, Patrick R.; Jones, Christopher A.; Klovstad, Jordan J.; Neilan, James H.; Stillwagen, Frederic H.; Williams, Phillip A.; Bednara, Michael;

Self-reported difficulty and preferences of wheeled mobility device users for simulated low-floor bus boarding, interior circulation and disembarking.

PubMed

D'Souza, Clive; Paquet, Victor L; Lenker, James A; Steinfeld, Edward

2017-11-13

Low ridership of public transit buses among wheeled mobility device users suggests the need to identify vehicle design conditions that are either particularly accommodating or challenging. The objective of this study was to determine the effects of low-floor bus interior seating configuration and passenger load on wheeled mobility device user-reported difficulty, overall acceptability and design preference. Forty-eight wheeled mobility users evaluated three interior design layouts at two levels of passenger load (high vs. low) after simulating boarding and disembarking tasks on a static full-scale low-floor bus mockup. User self-reports of task difficulty, acceptability and design preference were analyzed across the different test conditions. Ramp ascent was the most difficult task for manual wheelchair users relative to other tasks. The most difficult tasks for users of power wheelchairs and scooters were related to interior circulation, including moving to the securement area, entry and positioning in the securement area and exiting the securement area. Boarding and disembarking at the rear doorway was significantly more acceptable and preferred compared to the layouts with front doorways. Understanding transit usability barriers, perceptions and preferences among wheeled mobility users is an important consideration for clinicians who recommend mobility-related device interventions to those who use public transportation. Implications for Rehabilitation In order to maximize community participation opportunities for wheeled mobility users, clinicians should consider potential public transit barriers during the processes of wheelchair device selection and skills training. Usability barriers experienced by wheeled mobility device users on transit vehicles differ by mobility device type and vehicle configurations. Full-scale environment simulations are an effective means of identifying usability barriers and design needs in people with mobility impairments and may provide an alternative model for determining readiness for using fixed route buses or eligibility for paratransit.

SiC-CMC-Zircaloy-4 Nuclear Fuel Cladding Performance during 4-Point Tubular Bend Testing

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

IJ van Rooyen; WR Lloyd; TL Trowbridge

2013-09-01

The U.S. Department of Energy Office of Nuclear Energy (DOE NE) established the Light Water Reactor Sustainability (LWRS) program to develop technologies and other solutions to improve the reliability, sustain the safety, and extend the life of current reactors. The Advanced LWR Nuclear Fuel Development Pathway in the LWRS program encompasses strategic research focused on improving reactor core economics and safety margins through the development of an advanced fuel cladding system. Recent investigations of potential options for “accident tolerant” nuclear fuel systems point to the potential benefits of silicon carbide (SiC) cladding. One of the proposed SiC-based fuel cladding designsmore » being investigated incorporates a SiC ceramic matrix composite (CMC) as a structural material supplementing an internal Zircaloy-4 (Zr-4) liner tube, referred to as the hybrid clad design. Characterization of the advanced cladding designs will include a number of out-of-pile (nonnuclear) tests, followed by in-pile irradiation testing of the most promising designs. One of the out-of-pile characterization tests provides measurement of the mechanical properties of the cladding tube using four point bend testing. Although the material properties of the different subsystems (materials) will be determined separately, in this paper we present results of 4-point bending tests performed on fully assembled hybrid cladding tube mock-ups, an assembled Zr-4 cladding tube mock-up as a standard and initial testing results on bare SiC-CMC sleeves to assist in defining design parameters. The hybrid mock-up samples incorporated SiC-CMC sleeves fabricated with 7 polymer impregnation and pyrolysis (PIP) cycles. To provide comparative information; both 1- and 2-ply braided SiC-CMC sleeves were used in this development study. Preliminary stress simulations were performed using the BISON nuclear fuel performance code to show the stress distribution differences for varying lengths between loading points and clad configurations. The 2-ply sleeve samples show a higher bend momentum compared to those of the 1-ply sleeve samples. This is applicable to both the hybrid mock-up and bare SiC-CMC sleeve samples. Comparatively both the 1- and 2-ply hybrid mock-up samples showed a higher bend stiffness and strength compared with the standard Zr-4 mock-up sample. The characterization of the hybrid mock-up samples showed signs of distress and preliminary signs of fraying at the protective Zr-4 sleeve areas for the 1-ply SiC-CMC sleeve. In addition, the microstructure of the SiC matrix near the cracks at the region of highest compressive bending strain shows significant cracking and flaking. The 2-ply SiC-CMC sleeve samples showed a more bonded, cohesive SiC matrix structure. This cracking and fraying causes concern for increased fretting during the actual use of the design. Tomography was proven as a successful tool to identify open porosity during pre-test characterization. Although there is currently insufficient data to make conclusive statements regarding the overall merit of the hybrid cladding design, preliminary characterization of this novel design has been demonstrated.« less

Evaluation of smartphone-based interaction techniques in a CAVE in the context of immersive digital project review

NASA Astrophysics Data System (ADS)

George, Paul; Kemeny, Andras; Colombet, Florent; Merienne, Frédéric; Chardonnet, Jean-Rémy; Thouvenin, Indira Mouttapa

2014-02-01

Immersive digital project reviews consist in using virtual reality (VR) as a tool for discussion between various stakeholders of a project. In the automotive industry, the digital car prototype model is the common thread that binds them. It is used during immersive digital project reviews between designers, engineers, ergonomists, etc. The digital mockup is also used to assess future car architecture, habitability or perceived quality requirements with the aim to reduce using physical mockups for optimized cost, delay and quality efficiency. Among the difficulties identified by the users, handling the mockup is a major one. Inspired by current uses of nomad devices (multi-touch gestures, IPhone UI look'n'feel and AR applications), we designed a navigation technique taking advantage of these popular input devices: Space scrolling allows moving around the mockup. In this paper, we present the results of a study we conducted on the usability and acceptability of the proposed smartphone-based interaction metaphor compared to traditional technique and we provide indications of the most efficient choices for different use-cases accordingly. It was carried out in a traditional 4-sided CAVE and its purpose is to assess a chosen set of interaction techniques to be implemented in Renault's new 5-sides 4K x 4K wall high performance CAVE. The proposed new metaphor using nomad devices is well accepted by novice VR users and future implementation should allow an efficient industrial use. Their use is an easy and user friendly alternative of the existing traditional control devices such as a joystick.

Programmable prostate palpation simulator using property-changing pneumatic bladder.

PubMed

Talhan, Aishwari; Jeon, Seokhee

2018-05-01

The currently available prostate palpation simulators are based on either a physical mock-up or pure virtual simulation. Both cases have their inherent limitations. The former lacks flexibility in presenting abnormalities and scenarios because of the static nature of the mock-up and has usability issues because the prostate model must be replaced in different scenarios. The latter has realism issues, particularly in haptic feedback, because of the very limited performance of haptic hardware and inaccurate haptic simulation. This paper presents a highly flexible and programmable simulator with high haptic fidelity. Our new approach is based on a pneumatic-driven, property-changing, silicone prostate mock-up that can be embedded in a human torso mannequin. The mock-up has seven pneumatically controlled, multi-layered bladder cells to mimic the stiffness, size, and location changes of nodules in the prostate. The size is controlled by inflating the bladder with positive pressure in the chamber, and a hard nodule can be generated using the particle jamming technique; the fine sand in the bladder becomes stiff when it is vacuumed. The programmable valves and system identification process enable us to precisely control the size and stiffness, which results in a simulator that can realistically generate many different diseases without replacing anything. The three most common abnormalities in a prostate are selected for demonstration, and multiple progressive stages of each abnormality are carefully designed based on medical data. A human perception experiment is performed by actual medical professionals and confirms that our simulator exhibits higher realism and usability than do the conventional simulators. Copyright © 2018 Elsevier Ltd. All rights reserved.

Media development effectiveness of geography 3d muckups

NASA Astrophysics Data System (ADS)

Prasetya, S. P.; Daryono; Budiyanto, E.

2018-01-01

Geography examines geosphere phenomena that occurs in a space associated with humans on earth’s surface. Media 3D models are an important visual media in presenting spatial objects on the earth’s surface. This study aims to develop a decent 3D mockups media used for learning materials and test the effectiveness of media geography 3D mockups on learning outcomes. The study involved 90 students of Geography Education, Faculty of Social Sciences and Law, State University of Surabaya. Method development using a model of the Borg and Gall (1989) which has been modified into three stages, namely the introduction, development, and testing. The study produced instructional media 3D Muckups eligible to be used as a learning medium for the material hydrosphere geography, geology, and geomorphology. 3D mockups media use in learning geography materials can increase the activity of students, student interest and a positive response to raise the student learning outcomes as the material can be delivered more concrete geography. Based on observations conducted student activity occurs continuously increase in the use of 3D models for learning geography material.

Flat Tile Armour Cooled by Hypervapotron Tube: a Possible Technology for ITER

NASA Astrophysics Data System (ADS)

Schlosser, J.; Escourbiac, F.; Merola, M.; Schedler, B.; Bayetti, P.; Missirlian, M.; Mitteau, R.; Robin-Vastra, I.

Carbon fibre composite (CFC) flat tile armours for actively cooled plasma facing components (PFC’s) are an important challenge for controlled fusion machines. Flat tile concepts, water cooled by tubes, were studied, developed, tested and finally operated with success in Tore Supra. The components were designed for 10 MW/m2 and mock-ups were successfully fatigue tested at 15 MW/m2, 1000 cycles. For ITER, a tube-in-tile concept was developed and mock-ups sustained up to 25 MW/m2 for 1000 cycles without failure. Recently flat tile armoured mock-ups cooled by a hypervapotron tube successfully sustained a cascade failure test under a mean heat flux of 10 MW/m2 but with a doubling of the heat flux on some tiles to simulate missing tiles (500 cycles). This encouraging results lead to reconsider the limits for flat tile concept when cooled by hypervapotron (HV) tube. New tests are now scheduled to investigate these limits in regard to the ITER requirements. Experimental evidence of the concept could be gained in Tore Supra by installing a new limiter into the machine.

Fundamental research in the area of high temperature fuel cells in Russia

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

Dyomin, A.K.

1996-04-01

Research in the area of molten carbonate and solid oxide fuel cells has been conducted in Russia since the late 60`s. Institute of High Temperature Electrochemistry is the lead organisation in this area. Research in the area of materials used in fuel cells has allowed us to identify compositions of electrolytes, electrodes, current paths and transmitting, sealing and structural materials appropriate for long-term fuel cell applications. Studies of electrode processes resulted in better understanding of basic patterns of electrode reactions and in the development of a foundation for electrode structure optimization. We have developed methods to increase electrode activity levelsmore » that allowed us to reach current density levels of up to 1 amper/cm{sup 2}. Development of mathematical models of processes in high temperature fuel cells has allowed us to optimize their structure. The results of fundamental studies have been tested on laboratory mockups. MCFC mockups with up to 100 W capacity and SOFC mockups with up to 1 kW capacity have been manufactured and tested at IHTE. There are three SOFC structural options: tube, plate and modular.« less

Aerospace industry representatives view actual and mock-up versions of 'X-Planes' intended to enhanc

NASA Technical Reports Server (NTRS)

2000-01-01

Aerospace industry representatives view actual and mock-up versions of 'X-Planes' intended to enhance access to space during a technical exposition on June 22, 2000 at Dryden Flight Research Center, Edwards, California. From left to right: NASA's B-52 launch aircraft, in service with NASA since 1959; a neutral-buoyancy model of the Boeing's X-37; the Boeing X-40A behind the MicroCraft X-43 mock-up; Orbital Science's X-34 and the modified Lockheed L-1011 airliner that was to launch the X-34. These X-vehicles are part of NASA's Access to Space plan intended to bring new technologies to bear in an effort to dramatically lower the cost of putting payloads in space, and near-space environments. The June 22, 2000 NASA Reusable Launch Vehicle (RLV) Technology Exposition included presentations on the history, present, and future of NASA's RLV program. Special Sessions for industry representatives highlighted the X-37 project and its related technologies. The X-37 project is managed by NASA's Marshall Space Flight Center, Huntsville, Alabama.

At NASA Dryden, Aerospace industry representatives view actual and mock-up versions of 'X-Planes' in

NASA Technical Reports Server (NTRS)

2000-01-01

Aerospace industry representatives view actual and mock-up versions of 'X-Planes' intended to enhance access to space during a technical exposition on June 22, 2000 at Dryden Flight Research Center, Edwards, California. From left to right: NASA's B-52 launch aircraft, in service with NASA since 1959; a neutral-buoyancy model of the Boeing's X-37; the Boeing X-40A behind the MicroCraft X-43 mock-up; Orbital Science's X-34 and the modified Lockheed L-1011 airliner that was to launch the X-34. These X-vehicles are part of NASA's Access to Space plan intended to bring new technologies to bear in an effort to dramatically lower the cost of putting payloads in space, and near-space environments. The June 22, 2000 NASA Reusable Launch Vehicle (RLV) Technology Exposition included presentations on the history, present, and future of NASA's RLV program. Special Sessions for industry representatives highlighted the X-37 project and its related technologies. The X-37 project is managed by NASA's Marshall Space Flight Center, Huntsville, Alabama.

KSC-2012-4315

NASA Image and Video Library

2012-08-06

CAPE CANAVERAL, Fla. – Mockup components of an Orion spacecraft are laid out in the transfer aisle of the Vehicle Assembly Building, or VAB, at NASA's Kennedy Space Center in Florida. In the foreground are the Launch Abort System and the aerodynamic shell that will cover the capsule during launch. To the right is the Orion capsule model on top of a service module simulator. 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. The first uncrewed test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on a Space Launch System rocket. The Orion mockup is exact in details on the outside, but mostly empty on the inside except for four mockup astronaut seats and hatch. The work in the VAB is crucial to making sure the designs are accurate. For more information, visit http://www.nasa.gov/orion Photo credit: NASA/ Dmitri Gerondidakis

KSC-2012-4321

NASA Image and Video Library

2012-08-06

CAPE CANAVERAL, Fla. – Seen from overhead, mockup components of an Orion spacecraft are laid out in the transfer aisle of the Vehicle Assembly Building, or VAB, at NASA's Kennedy Space Center in Florida. In the foreground is the Launch Abort System and the aerodynamic shell that will cover the capsule during launch. To the right is the Orion capsule model on top of a service module simulator. 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. The first uncrewed test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on a Space Launch System rocket. The Orion mockup is exact in details on the outside, but mostly empty on the inside except for four mockup astronaut seats and hatch. The work in the VAB is crucial to making sure the designs are accurate. For more information, visit http://www.nasa.gov/orion Photo credit: NASA/ Dmitri Gerondidakis

KSC-2012-4318

NASA Image and Video Library

2012-08-06

CAPE CANAVERAL, Fla. – Seen from overhead, mockup components of an Orion spacecraft are laid out in the transfer aisle of the Vehicle Assembly Building, or VAB, at NASA's Kennedy Space Center in Florida. In the foreground is the Launch Abort System and the aerodynamic shell that will cover the capsule during launch. To the right is the Orion capsule model on top of a service module simulator. 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. The first uncrewed test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on a Space Launch System rocket. The Orion mockup is exact in details on the outside, but mostly empty on the inside except for four mockup astronaut seats and hatch. The work in the VAB is crucial to making sure the designs are accurate. For more information, visit http://www.nasa.gov/orion Photo credit: NASA/ Dmitri Gerondidakis

0g Climbing - The Challenge of Walking in Space

NASA Technical Reports Server (NTRS)

Ambrose, Robert O.; Rehnmark, Frederik; Goza, Michael

2003-01-01

Space walking is poorly named, as it has little in common with how animals walk on Earth. Space walking is more akin to mountain climbing in scuba gear, while parachuting in a freefall -- an odd combination of effects and equipment to help people do a demanding job. Robots are now being studied for service in this same domain, working on large scale space structures like the Space Station, servicing science or military platforms in high orbit, or riding on the outside of a space craft in transit to Mars, the Moon or other destinations. What have we learned about climbing in 0g? How should machines be controlled for serving in this role? What can they do to overcome the problems that humans have faced? In order to move about in this environment, a robot must be able to climb autonomously, using gaits that smoothly manage its momentum and that minimize contact forces (walking lightly) while providing for safety in the event of an emergency requiring the system to stop. All three of these objectives are now being explored at NASA's Johnson Space Center, using the Robonaut system and a set of mockups that emulate the 0g condition. NASA's goal for Robonaut is to develop the control technology that will allow it to climb on the outside of the Space Shuttle, the Space Station, and satellite mockups at JSC, enabling the robot to perform EVA task setups or serve as an Astronaut's assistant.

0g Climbing - The Challenge of Walking in Space

NASA Technical Reports Server (NTRS)

Ambrose, Robert O.; Rehnmark, Frederik; Goza, Michael

2004-01-01

Space walking is poorly named, as it has little in common with how animals walk on Earth. Space walking is more akin to mountain climbing in scuba gear, while parachuting in a freefall-an odd combination of effects and equipment to help people do a demanding job. Robots are now being studied for service in this same domain, working on large scale space structures like the Space Station, servicing science or military platforms in high orbit, or riding on the outside of a space craft in transit to Mars, the Moon or other destinations. What have we learned about climbing in 0g? How should machines be controlled for serving in this role? What can they do to overcome the problems that humans have faced? In order to move about in this environment, a robot must be able to climb autonomously, using gaits that smoothly manage its momentum and that minimize contact forces (walking lightly) while providing for safety in the event of an emergency requiring the system to stop. All three of these objectives are now being explored at NASA's Johnson Space Center, using the Robonaut system and a set of mockups that emulate the 0g condition. NASA's goal for Robonaut is to develop the control technology that will allow it to climb on the outside of the Space Shuttle, the Space Station, and satellite mockups at JSC, enabling the robot to perform EVA task setups or serve as an Astronaut's assistant.

Preflight coverage of STS-114 & Expedition 7 Crews, Emergency Egress Training

NASA Image and Video Library

2002-09-12

JSC2002-01650 (12 September 2002) --- The STS-114 and Expedition Seven crews, attired in training versions of the full-pressure launch and entry suit, pose for a group photo prior to a training session in the Space Vehicle Mockup Facility at the Johnson Space Center (JSC). From the left are astronauts Eileen M. Collins, James M. Kelly, STS-114 mission commander and pilot, respectively; Soichi Noguchi and Stephen K. Robinson, both STS-114 mission specialists; Edward T. Lu, Expedition Seven flight engineer; cosmonauts Sergei I. Moschenko and Yuri I. Malenchenko, Expedition Seven flight engineer and mission commander, respectively. Moschenko and Malenchenko represent Rosaviakosmos and Noguchi represents Japan’s National Space Development Agency (NASDA).

STS-114 with Expedition 7 during ASC/CAP/OES Training.

NASA Image and Video Library

2002-11-12

JSC2002-02020 (12 November 2002) --- The STS-114 and Expedition Seven crews, attired in training versions of the full-pressure launch and entry suit, pose for a group photo prior to a training session in the Space Vehicle Mockup Facility at the Johnson Space Center (JSC). From the left are astronauts Soichi Noguchi, Stephen K. Robinson, both STS-114 mission specialists; James M. Kelly, STS-114 pilot; Eileen M. Collins, STS-114 mission commander; Edward T. Lu, Expedition Seven flight engineer; cosmonauts Yuri I. Malenchenko, Expedition Seven mission commander; and Alexander Y. Kaleri, Expedition Seven flight engineer. Noguchi represents Japan’s National Space Development Agency (NASDA). Malenchenko and Kaleri represent Rosaviakosmos.

Neutron spectrum from the little boy mock-up

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

Robba, A.A.

1986-01-01

Most of the human exposure data used for setting radiation protection guidelines have been obtained by following the survivors of the nuclear explosions at Hiroshima and Nagasaki. Proper evaluation of these data requires estimates of the radiation exposure received by those survivors. Until now neutron dose estimates have relied primarily on calculations as no measurements of the leakage neutron flux or neutron spectrum were available. We have measured the high-energy leakage neutron spectrum from a mock-up of the Little Boy device operating at delayed critical. The measurements are compared with Monte Carlo calculations of the leakage neutron spectrum.

STS-36 Commander Creighton in LES outside CCT side hatch during JSC training

NASA Technical Reports Server (NTRS)

1989-01-01

Standing on an inflated cushion outside the side hatch of the crew compartment trainer (CCT), STS-36 Commander John O. Creighton, wearing launch and entry suit (LES), smiles before climbing into the shuttle mockup. The crew escape system (CES) pole extends beyond the side hatch opening. Mission Specialist (MS) Richard M. Mullane is seen at the lower corner of the frame rolling on the safety cushion. CCT is located in JSC's Mockup and Integration Laboratory (MAIL) Bldg 9A. The crewmembers are practicing egress procedures that might be necessary in the event of an emergency aboard the shuttle.

Modified Convair-240 aircraft at Naval Weapons Center, China Lake, California

NASA Technical Reports Server (NTRS)

1987-01-01

Convair-240 aircraft modified to fill role of a Space Shuttle is parked outside aircraft hangar at Naval Weapons Center, China Lake, California. Space shuttle side hatch mockup is incorporated in fuselage (visible toward the aft section of the aircraft). Convair-240 aircraft is part of November crew escape system (CES) testing of a candidate concept developed to provide crew egress capability during Space Shuttle controlled gliding flight. Tractor rocket testing using the Convair-240 will begin 11-20-87. Life-like dummies will be pulled by the rockets from the modified aircraft's side hatch mockup.

Bilateral Complete and Incomplete Fusion of Incisors and its Management.

PubMed

Da Costa, Godwin Clovis; Chalakkal, Paul; De Souza, Neil; Gavhane, Sanket

2017-01-01

This case report highlights the management of a case of bilateral complete and incomplete fusion of maxillary incisors in a 10-year-old child. A mock-up was done on the diagnostic cast. Pretreatment esthetic evaluation was done using bis-acryl composite temporaries which were transferred intraorally from the diagnostic cast using a putty index. An incisal overlap veneer preparation was done, following which, an IPS e-max veneer was cemented. A digital mock-up was carried out using the Adobe Photoshop and Corel Draw softwares to aid in laboratorial fabrication of the veneer.

KENNEDY SPACE CENTER, FLA. - Jeff Thon, an SRB mechanic with United Space Alliance, is fitted with a harness to test a vertical solid rocket booster propellant grain inspection technique. Thon will be lowered inside a mockup of two segments of the SRBs. The inspection of segments is required as part of safety analysis.

NASA Image and Video Library

2003-09-11

KENNEDY SPACE CENTER, FLA. - Jeff Thon, an SRB mechanic with United Space Alliance, is fitted with a harness to test a vertical solid rocket booster propellant grain inspection technique. Thon will be lowered inside a mockup of two segments of the SRBs. The inspection of segments is required as part of safety analysis.

Astronauts McMonagle and Brown on flight deck mockup during training

NASA Image and Video Library

1994-06-23

S94-40090 (23 June 1994) --- Astronauts Donald R. McMonagle, left, and Curtis L. Brown man the commander's and pilot's stations, respectively, during a rehearsal of ascent and entry phases of their scheduled November 1994 flight aboard Atlantis. Three other NASA astronauts and a European mission specialist joined the two for this training exercise in the Crew Compartment Trainer (CCT) at the Johnson Space Center's (JSC) Shuttle Mockup and Integration Laboratory and will join them aboard the Space Shuttle Atlantis in November. The flight is manifest to support the Atmospheric Laboratory for Applications and Science (ATLAS-3) mission.

Mock-up experiment at Birmingham University for BNCT project of Osaka University--Neutron flux measurement with gold foil.

PubMed

Tamaki, S; Sakai, M; Yoshihashi, S; Manabe, M; Zushi, N; Murata, I; Hoashi, E; Kato, I; Kuri, S; Oshiro, S; Nagasaki, M; Horiike, H

2015-12-01

Mock-up experiment for development of accelerator based neutron source for Osaka University BNCT project was carried out at Birmingham University, UK. In this paper, spatial distribution of neutron flux intensity was evaluated by foil activation method. Validity of the design code system was confirmed by comparing measured gold foil activities with calculations. As a result, it was found that the epi-thermal neutron beam was well collimated by our neutron moderator assembly. Also, the design accuracy was evaluated to have less than 20% error. Copyright © 2015 Elsevier Ltd. All rights reserved.

Comparative Ergonomic Evaluation of Spacesuit and Space Vehicle Design

NASA Technical Reports Server (NTRS)

England, Scott; Cowley, Matthew; Benson, Elizabeth; Harvill, Lauren; Blackledge, Christopher; Perez, Esau; Rajulu, Sudhakar

2012-01-01

With the advent of the latest human spaceflight objectives, a series of prototype architectures for a new launch and reentry spacesuit that would be suited to the new mission goals. Four prototype suits were evaluated to compare their performance and enable the selection of the preferred suit components and designs. A consolidated approach to testing was taken: concurrently collecting suit mobility data, seat-suit-vehicle interface clearances, and qualitative assessments of suit performance within the volume of a Multi-Purpose Crew Vehicle mockup. It was necessary to maintain high fidelity in a mockup and use advanced motion-capture technologies in order to achieve the objectives of the study. These seemingly mutually exclusive goals were accommodated with the construction of an optically transparent and fully adjustable frame mockup. The construction of the mockup was such that it could be dimensionally validated rapidly with the motioncapture system. This paper describes the method used to create a space vehicle mockup compatible with use of an optical motion-capture system, the consolidated approach for evaluating spacesuits in action, and a way to use the complex data set resulting from a limited number of test subjects to generate hardware requirements for an entire population. Kinematics, hardware clearance, anthropometry (suited and unsuited), and subjective feedback data were recorded on 15 unsuited and 5 suited subjects. Unsuited subjects were selected chiefly based on their anthropometry in an attempt to find subjects who fell within predefined criteria for medium male, large male, and small female subjects. The suited subjects were selected as a subset of the unsuited medium male subjects and were tested in both unpressurized and pressurized conditions. The prototype spacesuits were each fabricated in a single size to accommodate an approximately average-sized male, so select findings from the suit testing were systematically extrapolated to the extremes of the population to anticipate likely problem areas. This extrapolation was achieved by first comparing suited subjects performance with their unsuited performance, and then applying the results to the entire range of the population. The use of a transparent space vehicle mockup enabled the collection of large amounts of data during human-in-the-loop testing. Mobility data revealed that most of the tested spacesuits had sufficient ranges of motion for the selected tasks to be performed successfully. A suited subject's inability to perform a task most often stemmed from a combination of poor field of view in a seated position, poor dexterity of the pressurized gloves, or from suit/vehicle interface issues. Seat ingress and egress testing showed that problems with anthropometric accommodation did not exclusively occur with the largest or smallest subjects, but also with specific combinations of measurements that led to narrower seat ingress/egress clearance.

InSight/SEIS@Mars Educational program : Sharing the InSight NASA mission and the Seismic Discovery of Mars with a International Network of classes

NASA Astrophysics Data System (ADS)

Lognonne, P. H.; Berenguer, J. L.; Sauron, A.; Denton, P.; Carrer, D.; Taber, J.; Bravo, T. K.; Gaboriaud, A.; Houston Jones, J.; Banerdt, W. B.; Martinuzzi, J. M.

2015-12-01

The InSIght mission will deploy in September 2016 a Geophysical Station on Mars, equipped with a suite of geophysical instruments, including 3 axis Very Broad Band Seismometer, 3 axis Short Period Seismometer, 3 axis Flux gate Magnetometer, Heat flow probe, geodetic beacon, infrasound/microbarometer, wind sensors and cameras. As for all NASA missions, Children and teenagers will be associated to the mission in the framework of the K12 InSight program, part of it being associated to the SEIS instrument.The two faces of the InSight/SEIS Education program are directed toward the promotion of Space Technologies and of Space Science.For Space technologies, this has already started with the InSight Elysium Educational project. The goal of the project, supported by CNES and performed by Technical High School near Toulouse, was the fabrication of a full scale mockup of the lander (see more at https://jeunes.cnes.fr/fr/elysium-le-jumeau-terrestre-dinsight ). The mockup was exhibited during the June, 2015 Paris air show. More than 300 students participated to the Elysium project.For Space Science, this will be made with the SEIS@Mars Educational project. Its plan is to transmit the SEIS data to a network of several hundred of middle and high schools worldwide, associated to existing "seismo(graph) at school" programs in the United States (https://www.iris.edu/hq/sis), France (www.edusismo.org) Switzerland (www.seismoatschool.ethz.ch) and United Kingdom (http://www.bgs.ac.uk/schoolseismology/). If the transmission of these data to the SEIS@school network will be automatic after their release by the NASA Planetary Data System, an earlier transmission will be made, especially after mid 2017, but also before through the integration of selected Schools to the project activities: the selected classrooms will perform the same activities as the project scientists. They will have to process rapidly the proprietary data in order to identify MarsQuake(s) and will be allowed to perform Event requests to the lander in order to get the associated high frequencies of these events. These school will therefore be fully associated to the InSight/SEIS discoveries. The SEIS@Mars project will therefore allow the students to perform scientific analysis almost at the same time as the International "professional" seismologists.

VVER-440 and VVER-1000 reactor dosimetry benchmark - BUGLE-96 versus ALPAN VII.0

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

Duo, J. I.

2011-07-01

Document available in abstract form only, full text of document follows: Analytical results of the vodo-vodyanoi energetichesky reactor-(VVER-) 440 and VVER-1000 reactor dosimetry benchmarks developed from engineering mockups at the Nuclear Research Inst. Rez LR-0 reactor are discussed. These benchmarks provide accurate determination of radiation field parameters in the vicinity and over the thickness of the reactor pressure vessel. Measurements are compared to calculated results with two sets of tools: TORT discrete ordinates code and BUGLE-96 cross-section library versus the newly Westinghouse-developed RAPTOR-M3G and ALPAN VII.0. The parallel code RAPTOR-M3G enables detailed neutron distributions in energy and space in reducedmore » computational time. ALPAN VII.0 cross-section library is based on ENDF/B-VII.0 and is designed for reactor dosimetry applications. It uses a unique broad group structure to enhance resolution in thermal-neutron-energy range compared to other analogous libraries. The comparison of fast neutron (E > 0.5 MeV) results shows good agreement (within 10%) between BUGLE-96 and ALPAN VII.O libraries. Furthermore, the results compare well with analogous results of participants of the REDOS program (2005). Finally, the analytical results for fast neutrons agree within 15% with the measurements, for most locations in all three mockups. In general, however, the analytical results underestimate the attenuation through the reactor pressure vessel thickness compared to the measurements. (authors)« less

Phased Array Ultrasonic Examination of Reactor Coolant System (Carbon Steel-to-CASS) Dissimilar Metal Weld Mockup Specimen

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

Crawford, S. L.; Cinson, A. D.; Diaz, A. A.

2015-11-23

In the summer of 2009, Pacific Northwest National Laboratory (PNNL) staff traveled to the Electric Power Research Institute (EPRI) NDE Center in Charlotte, North Carolina, to conduct phased-array ultrasonic testing on a large bore, reactor coolant pump nozzle-to-safe-end mockup. This mockup was fabricated by FlawTech, Inc. and the configuration originated from the Port St. Lucie nuclear power plant. These plants are Combustion Engineering-designed reactors. This mockup consists of a carbon steel elbow with stainless steel cladding joined to a cast austenitic stainless steel (CASS) safe-end with a dissimilar metal weld and is owned by Florida Power & Light. The objectivemore » of this study, and the data acquisition exercise held at the EPRI NDE Center, were focused on evaluating the capabilities of advanced, low-frequency phased-array ultrasonic testing (PA-UT) examination techniques for detection and characterization of implanted circumferential flaws and machined reflectors in a thick-section CASS dissimilar metal weld component. This work was limited to PA-UT assessments using 500 kHz and 800 kHz probes on circumferential flaws only, and evaluated detection and characterization of these flaws and machined reflectors from the CASS safe-end side only. All data were obtained using spatially encoded, manual scanning techniques. The effects of such factors as line-scan versus raster-scan examination approaches were evaluated, and PA-UT detection and characterization performance as a function of inspection frequency/wavelength, were also assessed. A comparative assessment of the data is provided, using length-sizing root-mean-square-error and position/localization results (flaw start/stop information) as the key criteria for flaw characterization performance. In addition, flaw signal-to-noise ratio was identified as the key criterion for detection performance.« less

Model Predictions and Observed Performance of JWST's Cryogenic Position Metrology System

NASA Technical Reports Server (NTRS)

Lunt, Sharon R.; Rhodes, David; DiAntonio, Andrew; Boland, John; Wells, Conrad; Gigliotti, Trevis; Johanning, Gary

2016-01-01

The James Webb Space Telescope cryogenic testing requires measurement systems that both obtain a very high degree of accuracy and can function in that environment. Close-range photogrammetry was identified as meeting those criteria. Testing the capability of a close-range photogrammetric system prior to its existence is a challenging problem. Computer simulation was chosen over building a scaled mock-up to allow for increased flexibility in testing various configurations. Extensive validation work was done to ensure that the actual as-built system meet accuracy and repeatability requirements. The simulated image data predicted the uncertainty in measurement to be within specification and this prediction was borne out experimentally. Uncertainty at all levels was verified experimentally to be less than 0.1 millimeters.

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

Microgravity

NASA Image and Video Library

2000-01-31

Arn Harris Hoover of Lockheed Martin Company demonstrates an engineering mockup of the Human Research Facility (HRF) that will be installed in Destiny, the U.S. Laboratory Module on the International Space Station (ISS). Using facilities similar to research hardware available in laboratories on Earth, the HRF will enable systematic study of cardiovascular, musculoskeletal, neurosensory, pulmonary, radiation, and regulatory physiology to determine biomedical changes resulting from space flight. Research results obtained using this facility are relevant to the health and the performance of the astronaut as well as future exploration of space. Because this is a mockup, the actual flight hardware may vary as desings are refined. (Credit: NASA/Marshall Space Flight Center)

KSC-08pd1899

NASA Image and Video Library

2008-07-02

CAPE CANAVERAL, Fla. – NYIT MOCAP (Motion Capture) team Project Manager Jon Squitieri attaches a retro reflective marker to a motion capture suit worn by a technician who will be assembling the Orion Crew Module mockup. The motion tracking aims to improve efficiency of assembly processes and identify potential ergonomic risks for technicians assembling the mockup. The work is being performed in United Space Alliance's Human Engineering Modeling and Performance Lab in the RLV Hangar at NASA's Kennedy Space Center. 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.

Comparative study on neutron data in integral experiments of MYRRHA mockup critical cores in the VENUS-F reactor

NASA Astrophysics Data System (ADS)

Krása, Antonín; Kochetkov, Anatoly; Baeten, Peter; Vittiglio, Guido; Wagemans, Jan; Bécares, Vicente

2017-09-01

VENUS-F is a fast, zero-power reactor with 30% wt. metallic uranium fuel and solid lead as coolant simulator. It serves as a mockup of the MYRRHA reactor core. This paper describes integral experiments performed in two critical VENUS-F core configurations (with and without graphite reflector). Discrepancies between experiments and Monte Carlo calculations (MCNP5) of keff, fission rate spatial distribution and reactivity effects (lead void and fuel Doppler) depending on a nuclear data library used (JENDL-4.0, ENDF-B-VII.1, JEFF-3.1.2, 3.2, 3.3T2) are presented.

Parallel Execution of Functional Mock-up Units in Buildings Modeling

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

Ozmen, Ozgur; Nutaro, James J.; New, Joshua Ryan

2016-06-30

A Functional Mock-up Interface (FMI) defines a standardized interface to be used in computer simulations to develop complex cyber-physical systems. FMI implementation by a software modeling tool enables the creation of a simulation model that can be interconnected, or the creation of a software library called a Functional Mock-up Unit (FMU). This report describes an FMU wrapper implementation that imports FMUs into a C++ environment and uses an Euler solver that executes FMUs in parallel using Open Multi-Processing (OpenMP). The purpose of this report is to elucidate the runtime performance of the solver when a multi-component system is imported asmore » a single FMU (for the whole system) or as multiple FMUs (for different groups of components as sub-systems). This performance comparison is conducted using two test cases: (1) a simple, multi-tank problem; and (2) a more realistic use case based on the Modelica Buildings Library. In both test cases, the performance gains are promising when each FMU consists of a large number of states and state events that are wrapped in a single FMU. Load balancing is demonstrated to be a critical factor in speeding up parallel execution of multiple FMUs.« less

Scanning Laser Doppler Vibrometer Measurements Inside Helicopter Cabins in Running Conditions: Problems and Mock-up Testing

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

Revel, G. M.; Castellini, P.; Chiariotti, P.

2010-05-28

The present work deals with the analysis of problems and potentials of laser vibrometer measurements inside helicopter cabins in running conditions. The paper describes the results of a systematic measurement campaign performed on an Agusta A109MKII mock-up. The aim is to evaluate the applicability of Scanning Laser Doppler Vibrometer (SLDV) for tests in simulated flying conditions and to understand how performances of the technique are affected when the laser head is placed inside the cabin, thus being subjected to interfering inputs. Firstly a brief description of the performed test cases and the used measuring set-ups are given. Comparative tests betweenmore » SLDV and accelerometers are presented, analyzing the achievable performances for the specific application. Results obtained measuring with SLDV placed inside the helicopter cabin during operative excitation conditions are compared with those performed with the laser lying outside the mock-up, these last being considered as 'reference measurements'. Finally, in order to give an estimate of the uncertainty level on measured signals, a study linking the admitted percentage of noise content on vibrometer signals due to laser head vibration levels will be introduced.« less

Exploring the usability of a videophone mock-up for persons with dementia and their significant others.

PubMed

Boman, Inga-Lill; Lundberg, Stefan; Starkhammar, Sofia; Nygård, Louise

2014-04-16

Persons with dementia might have considerable difficulties in using an ordinary telephone. Being able to use the telephone can be very important in order to maintain their social network, getting stimulation and for reaching help when needed. Therefore, persons with dementia might need an easy-to-use videophone to prevent social isolation and to feel safe and independent. This study reports the evaluation of the usability of a touch-screen videophone mock-up for persons with dementia and their significant others. Four persons with dementia and their significant others tested the videophone mock-up at a living laboratory. In order to gain knowledge of the participants' with dementia ability to use their own computers and telephones, interviews and observations were conducted. Overall, the participants had a very positive attitude towards the videophone. The participants with dementia perceived that it was useful, enjoyable and easy to use, although they initially had difficulties in understanding how to handle some functions, thus indicating that the design needs to be further developed to be more intuitive. The findings suggest that the videophone has the potential to enable telephone calls without assistance and add quality in communication.

How Mockups, a Key Engineering Tool, Help to Promote Science, Technology, Engineering, and Mathematics Education

NASA Technical Reports Server (NTRS)

McDonald, Harry E.

2010-01-01

The United States ranking among the world in science, technology, engineering, and mathematics (STEM) education is decreasing. To counteract this problem NASA has made it part of its mission to promote STEM education among the nation s youth. Mockups can serve as a great tool when promoting STEM education in America. The Orion Cockpit Working Group has created a new program called Students Shaping America s Next Space Craft (SSANS) to outfit the Medium Fidelity Orion Mockup. SSANS will challenge the students to come up with unique designs to represent the flight design hardware. There are two main types of project packages created by SSANS, those for high school students and those for university students. The high school projects will challenge wood shop, metal shop and pre-engineering classes. The university projects are created mainly for senior design projects and will require the students to perform finite element analysis. These projects will also challenge the undergraduate students in material selection and safety requirements. The SSANS program will help NASA in its mission to promote STEM education, and will help to shape our nations youth into the next generation of STEM leaders.

Laser Simulations of the Destructive Impact of Nuclear Explosions on Hazardous Asteroids

NASA Astrophysics Data System (ADS)

Aristova, E. Yu.; Aushev, A. A.; Baranov, V. K.; Belov, I. A.; Bel'kov, S. A.; Voronin, A. Yu.; Voronich, I. N.; Garanin, R. V.; Garanin, S. G.; Gainullin, K. G.; Golubinskii, A. G.; Gorodnichev, A. V.; Denisova, V. A.; Derkach, V. N.; Drozhzhin, V. S.; Ericheva, I. A.; Zhidkov, N. V.; Il'kaev, R. I.; Krayukhin, A. A.; Leonov, A. G.; Litvin, D. N.; Makarov, K. N.; Martynenko, A. S.; Malinov, V. I.; Mis'ko, V. V.; Rogachev, V. G.; Rukavishnikov, A. N.; Salatov, E. A.; Skorochkin, Yu. V.; Smorchkov, G. Yu.; Stadnik, A. L.; Starodubtsev, V. A.; Starodubtsev, P. V.; Sungatullin, R. R.; Suslov, N. A.; Sysoeva, T. I.; Khatunkin, V. Yu.; Tsoi, E. S.; Shubin, O. N.; Yufa, V. N.

2018-01-01

We present the results of preliminary experiments at laser facilities in which the processes of the undeniable destruction of stony asteroids (chondrites) in space by nuclear explosions on the asteroid surface are simulated based on the principle of physical similarity. We present the results of comparative gasdynamic computations of a model nuclear explosion on the surface of a large asteroid and computations of the impact of a laser pulse on a miniature asteroid simulator confirming the similarity of the key processes in the fullscale and model cases. The technology of fabricating miniature mockups with mechanical properties close to those of stony asteroids is described. For mini-mockups 4-10 mm in size differing by the shape and impact conditions, we have made an experimental estimate of the energy threshold for the undeniable destruction of a mockup and investigated the parameters of its fragmentation at a laser energy up to 500 J. The results obtained confirm the possibility of an experimental determination of the criteria for the destruction of asteroids of various types by a nuclear explosion in laser experiments. We show that the undeniable destruction of a large asteroid is possible at attainable nuclear explosion energies on its surface.

Intelligent Flexible Materials for Space Structures: Expandable Habitat Engineering Development Unit

NASA Technical Reports Server (NTRS)

Hinkle, Jon; Sharpe, George; Lin, John; Wiley, Cliff; Timmers, Richard

2010-01-01

Expandable habitable elements are an enabling technology for human exploration in space and on planetary surfaces. Large geometries can be deployed from a small launch volume, allowing greater mission capability while reducing mass and improving robustness over traditional rigid shells. This report describes research performed by ILC Dover under the Intelligent Flexible Materials for Space Structures program on the design and manufacture of softgoods for LaRC's Expandable Habitat Engineering Development Unit (EDU). The EDU is a full-scale structural test article of an expandable hybrid habitat, integrating an expandable softgoods center section with two rigid end caps. The design of the bladder, restraint layer and a mock-up Thermal Micrometeoroid Cover is detailed together with the design of the interface hardware used to attach them to the end caps. The integration and design of two windows and a floor are also covered. Analysis was performed to study the effects of the open weave design, and to determine the correct webbing and fabric configuration. Stress analyses were also carried out on the interfaces between the softgoods and the end caps and windows. Testing experimentally determined the strength of the fabric and straps, and component testing was used to proof several critical parts of the design. This program established new manufacturing and design techniques that can be applied to future applications in expandable structures.

Using inertial measurement units originally developed for biomechanics for modal testing of civil engineering structures

NASA Astrophysics Data System (ADS)

Hester, David; Brownjohn, James; Bocian, Mateusz; Xu, Yan; Quattrone, Antonino

2018-05-01

This paper explores the use of wireless Inertial Measurement Units (IMU) originally developed for bio-mechanical research applications for modal testing of civil engineering infrastructure. Due to their biomechanics origin, these devices combine a triaxial accelerometer with gyroscopes and magnetometers for orientation, as well as on board data logging capability and wireless communication for optional data streaming and to coordinate synchronisation with other IMUs in a network. The motivation for application to civil structures is that their capabilities and simple operating procedures make them suitable for modal testing of many types of civil infrastructure of limited dimension including footbridges and floors while also enabling recovering of dynamic forces generated and applied to structures by moving humans. To explore their capabilities in civil applications, the IMUs are evaluated through modal tests on three different structures with increasing challenge of spatial and environmental complexity. These are, a full-scale floor mock-up in a laboratory, a short span road bridge and a seven story office tower. For each case, the results from the IMUs are compared with those from a conventional wired system to identify the limitations. The main conclusion is that the relatively high noise floor and limited communication range will not be a serious limitation in the great majority of typical civil modal test applications where convenient operation is a significant advantage over conventional wired systems.

Investigation of torque generated by Test Blanket Module mock-up in DIII-D

NASA Astrophysics Data System (ADS)

Salmi, A.; Tala, T.; Lanctot, M.; Degrassie, J. S.; Paz-Soldan, C.; Logan, N.; Solomon, W. M.; Grierson, B. A.

2015-11-01

Experiments at DIII-D have investigated the scaling of Test Blanket Module (TBM) torque with plasma pressure and collisionality by performing dimensionless parameter scans. In each configuration, neutral beam torque modulation and TBM torque modulation were sequentially applied to allow experimental characterization of the TBM generated torque and the underlying transport. Calculations of the neoclassical toroidal viscosity (NTV) torque with PENT code of these plasmas find that TBM torque is strongly edge localized while the tentative experimental analysis indicates a more radially broad TBM torque profile. Both the experimental and PENT results will be elaborated and experimental TBM torque scaling with pressure and collisionality presented. Experimental validation of existing plasma response and NTV torque models is an important step toward understanding the impact of magnetic field ripple on plasma rotation, and for predicting the required compensation fields. Work supported by the US Department of Energy under DE-AC52-07NA27344, DE-FC02-04ER54698 and DE-AC02-09CH11466.

SU-F-J-117: Impact of Motion Artifacts On Image Quality and Accuracy of Tumor Motion Reconstruction in 4D CT-On-Rails and MV-CBCT Scans: A Phantom Study

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

Lin, T; Ma, C

Purpose: To compare and quantify respiratory motion artifacts in images from free breathing 4D-CT-on-Rails(CTOR) and those from MV-Cone-beam-CT(MVCB) and facilitate respiratory motion guided radiation therapy. Methods: 4D-CTOR: Siemens Somatom CT-on-Rails system with Anzai belt loaded with pressure sensor load cells. 4D scans were performed in helical mode, pitch 0.1, gantry rotation time 0.5s, 1.5mm slice thickness, 120kVp, 400 mAs. Normal and fast breathing (>12rpm) scanning protocols were investigated. Helical scan, AIP(average intensity projection) and MIP(maximum intensity projection) were generated from 4D-CTOR scans with amplitude sorting into 10 phases.MVCB: Siemens Artiste diamond view(1MV)MVCB was performed with 5MU thorax protocol with 60more » second of full rotation.Phantom: Anzai AZ-733V respiratory phantom. The settings were set to normal and resp. modes with repetition rates at 15 rpm and 10 rpm. Surgical clips, acrylic, wooden, rubber and lung density, total six mock-ups were scanned and compared in this study.Signal-to-noise ratio(SNR), contrast-to-noise ratio(CNR) and reconstructed motion volume were compared to different respiratory setups for the mock-ups. Results: Reconstructed motion volume was compared to the real object volume for the six test mock-ups. It shows that free breathing helical in all instances underestimates the object excursions largest to −67.4% and least −6.3%. Under normal breathing settings, MIP can predict very precise motion volume with minimum 0.4% and largest −13.9%. MVCB shows underestimate of the motion volume with −1.11% minimum and −18.0% maximum. With fast breathing, AIP provides bad representation of the object motion; however, the MIP can predict the motion volume with −2.0% to −11.4% underestimate. Conclusion: Respiratory motion guided radiation therapy requires good motion recording. This study shows that regular CTOR helical scans provides bad guidance, 4D CTOR AIP cannot represent the fast breathing pattern, MIP can represent the best motion volume, MVCBCT can only be used for normal breathing with acceptable uncertainties.« less

Large Eddy Simulation of Air Escape through a Hospital Isolation Room Single Hinged Doorway—Validation by Using Tracer Gases and Simulated Smoke Videos

PubMed Central

Saarinen, Pekka E.; Kalliomäki, Petri; Tang, Julian W.; Koskela, Hannu

2015-01-01

The use of hospital isolation rooms has increased considerably in recent years due to the worldwide outbreaks of various emerging infectious diseases. However, the passage of staff through isolation room doors is suspected to be a cause of containment failure, especially in case of hinged doors. It is therefore important to minimize inadvertent contaminant airflow leakage across the doorway during such movements. To this end, it is essential to investigate the behavior of such airflows, especially the overall volume of air that can potentially leak across the doorway during door-opening and human passage. Experimental measurements using full-scale mock-ups are expensive and labour intensive. A useful alternative approach is the application of Computational Fluid Dynamics (CFD) modelling using a time-resolved Large Eddy Simulation (LES) method. In this study simulated air flow patterns are qualitatively compared with experimental ones, and the simulated total volume of air that escapes is compared with the experimentally measured volume. It is shown that the LES method is able to reproduce, at room scale, the complex transient airflows generated during door-opening/closing motions and the passage of a human figure through the doorway between two rooms. This was a basic test case that was performed in an isothermal environment without ventilation. However, the advantage of the CFD approach is that the addition of ventilation airflows and a temperature difference between the rooms is, in principle, a relatively simple task. A standard method to observe flow structures is dosing smoke into the flow. In this paper we introduce graphical methods to simulate smoke experiments by LES, making it very easy to compare the CFD simulation to the experiments. The results demonstrate that the transient CFD simulation is a promising tool to compare different isolation room scenarios without the need to construct full-scale experimental models. The CFD model is able to reproduce the complex airflows and estimate the volume of air escaping as a function of time. In this test, the calculated migrated air volume in the CFD model differed by 20% from the experimental tracer gas measurements. In the case containing only a hinged door operation, without passage, the difference was only 10%. PMID:26151865

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-2009-2566

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

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

The telerobot testbed: An architecture for remote servicing

NASA Technical Reports Server (NTRS)

Matijevic, J. R.

1990-01-01

The NASA/OAST Telerobot Testbed will reach its next increment in development by the end of FY-89. The testbed will have the capability for: force reflection in teleoperation, shared control, traded control, operator designate and relative update. These five capabilities will be shown in a module release and exchange operation using mockups of Orbital Replacement Units (ORU). This development of the testbed shows examples of the technologies needed for remote servicing, particularly under conditions of delay in transmissions to the servicing site. Here, the following topics are presented: the system architecture of the testbed which incorporates these telerobotic technologies for servicing, the implementation of the five capabilities and the operation of the ORU mockups.

STS-65 PLC Hieb at mockup side hatch prepares to egress via an inflated slide

NASA Technical Reports Server (NTRS)

1994-01-01

STS-65 Mission Specialist and Payload Commander (PLC) Richard J. Hieb, wearing launch and entry suit (LES) and launch and entry helmet (LEH), sits at the top of the inflated slide at the crew compartment trainer (CCT) side hatch and listens to a crew training staffer's instructions. Hieb practiced post landing emergency escape procedures along with his six STS-65 crewmates. The CCT is located in the Johnson Space Center's (JSC's) Mockup and Integration Laboratory (MAIL) Bldg 9NE. Hieb will join five NASA astronauts and a Japanese payload specialist for the International Microgravity Laboratory 2 (IML-2) mission aboard the Space Shuttle Columbia, Orbiter Vehicle (OV) 102, later this year.

STS-40 crew trains in JSC's SLS mockup located in Bldg 36

NASA Image and Video Library

1987-03-10

STS-40 Payload Specialist Millie Hughes-Fulford along with backup payload specialist Robert Ward Phillips familiarize themselves with Spacelab Life Sciences 1 (SLS-1) equipment. The two scientists are in JSC's Life Sciences Project Division (LSPD) SLS mockup located in the Bioengineering and Test Support Facility Bldg 36. Hughes-Fulford, in the center aisle, pulls equipment from an overhead stowage locker while Phillips, in the foreground, experiments with the baroreflex neck pressure chamber at Rack 11. The baroreflex collar will be used in conjuction with Experiment No. 022, Influence of Weightlessness Upon Human Autonomic Cardiovascular Control. Behind Phillips in the center aisle are body mass measurement device (BMMD) (foreground) and the stowed bicycle ergometer.

Astronaut Curtis Brown on flight deck mockup during training

NASA Image and Video Library

1994-06-23

S94-40091 (23 June 1994) --- Astronaut Curtis L. Brown mans the pilot's station of a Shuttle trainer during a rehearsal of procedures to be followed during launch and entry phases of the scheduled November flight of STS-66. This rehearsal, held in the Crew Compartment Trainer (CCT) of the Johnson Space Center's (JSC) Shuttle Mockup and Integration Laboratory, was followed by a training session on emergency egress procedures. Making his second flight in space, Brown will join four other NASA astronauts and a European mission specialist for a week and a half aboard the Space Shuttle Atlantis in Earth-orbit in support of the Atmospheric Laboratory for Applications and Science (ATLAS-3).

STS-26 MS Hilmers during egress training at JSC's MAIL full fuselage trainer

NASA Technical Reports Server (NTRS)

1988-01-01

STS-26 Discovery, Orbiter Vehicle (OV) 103, Mission Specialist (MS) David C. Hilmers, wearing a launch and entry suit (LES) and launch and entry helmet (LEH), tries out the new crew escape system (CES) inflated slide during an emergency egress training exercise in JSC's Shuttle Mockup and Integration Laboratory (MAIL) Bldg 9A. Technicians stand on either side of the slide ready to help Hilmers to his feet once he reaches the bottom. Watching from floor level at the far left is astronaut Steven R. Nagel. A second crewmember stands in the open side hatch of the Full Fuselage Trainer (FFT) awaiting his turn to slide to 'safety'. During Crew Station Review (CSR) #3, the crew donned the new (navy blue) partial pressure suits (LESs) and checked out CES slide and other CES configurations to evaluate crew equipment and procedures related to emergency egress methods and proposed crew escape options. The CES pole extends out the side hatch just above Hilmers' head.

Jet Penetration into a Scaled Microfabricated Stirling Cycle Regenerator

NASA Technical Reports Server (NTRS)

Sun, Liyong; Simon, Terrence W.; Mantell, Susan; Ibrahim, Mournir; Gedeon, David; Tew, Roy

2008-01-01

The cooler and heater adjacent to the regenerator of a Stirling cycle engine have tubes or channels which form jets that pass into the regenerator while diffusing within the matrix. An inactive part of the matrix, beyond the cores of these jets, does not participate fully in the heat transfer between the flow of working fluid and the regenerator matrix material, weakening the regenerator s ability to exchange heat with the working fluid. The objective of the present program is to document this effect on the performance of the regenerator and to develop a model for generalizing the results. However, the small scales of actual Stirling regenerator matrices (on the order of tens of microns) make direct measurements of this effect very difficult. As a result, jet spreading within a regenerator matrix has not been characterized well and is poorly understood. Also, modeling is lacking experimental verification. To address this, a large-scale mockup of thirty times actual scale was constructed and operated under conditions that are dynamically similar to the engine operation. Jet penetration with round jets and slot jets into the microfabricated regenerator geometry are then measured by conventional means. The results are compared with those from a study of spreading of round jets within woven screen regenerator for further documentation of the comparative performance of the microfabricated regenerator geometry.

KSC-2009-2565

NASA Image and Video Library

2009-04-08

CAPE CANAVERAL, Fla. – Members of the 920th Rescue Wing secure 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 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-2009-2563

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 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-2009-2564

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 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-04PD-0224

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. Emergency crew members return to the orbiter crew compartment mock-up that is the scene of a Mode VII emergency landing simulation at Kennedy Space Center. The purpose of the Mode VII is to exercise emergency preparedness personnel, equipment and facilities in rescuing astronauts from a downed orbiter and providing immediate medical attention. This simulation presents an orbiter that has crashed short of the Shuttle Landing Facility in a wooded area 2-1/2 miles south of Runway 33. Emergency crews are responding to the volunteer astronauts simulating various injuries inside the mock-up compartment. Rescuers have had to remove the crew, provide triage and transport to hospitals those who need further treatment. Local hospitals are participating in the exercise.

Thermal modeling of W rod armor.

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

Nygren, Richard Einar

2004-09-01

Sandia has developed and tested mockups armored with W rods over the last decade and pioneered the initial development of W rod armor for International Thermonuclear Experimental Reactor (ITER) in the 1990's. We have also developed 2D and 3D thermal and stress models of W rod-armored plasma facing components (PFCs) and test mockups and are applying the models to both short pulses, i.e. edge localized modes (ELMs), and thermal performance in steady state for applications in C-MOD, DiMES testing and ITER. This paper briefly describes the 2D and 3D models and their applications with emphasis on modeling for an ongoingmore » test program that simulates repeated heat loads from ITER ELMs.« less

Payload specialists in training for STS 51-L in mockup & integration lab

NASA Image and Video Library

1986-01-09

S86-25254 (January 1986) --- Payload specialists in training for STS-51L take a break in shuttle emergency egress training at the Johnson Space Center's (JSC) Shuttle Mock-up and Integration Laboratory. Left to right are Gregory Jarvis of Hughes, Sharon Christa McAuliffe and Barbara Morgan of the Teacher-in-Space Project. McAuliffe was selected as NASA's first citizen observer in the Space Shuttle Program and Morgan was named her backup. The photo was taken by Keith Meyers of the New York Times. EDITOR?S NOTE: The STS-51L crew members lost their lives in the space shuttle Challenger accident moments after launch on Jan. 28, 1986 from the Kennedy Space Center (KSC). Photo credit: NASA

Huygens/HASI 2002 balloon test campaign: Probe trajectory and atmospheric vertical profiles reconstruction

NASA Astrophysics Data System (ADS)

Gaborit, V.; Fulchignoni, M.; Colombatti, G.; Ferri, F.; Bettanini, C.

2004-08-01

In the framework of the activities going on in preparation for the mission of the Huygens probe in Titan's atmosphere (January 2005), the Huygens Atmospheric Structure Instrument (HASI) team scheduled and performed several balloon campaigns to test the HASI sensors' performance in flight conditions in the Earth's atmosphere. In particular, pressure conditions reached during each test are similar to those expected in Titan's lower atmosphere. A 1:1 scaled mock-up of the Huygens probe was launched with a stratospheric balloon in 2001 (Br. Assoc. Adv. Sci. 33 (2001) 1109) and in 2002 (Br. Assoc. Adv. Sci. 34 (2002) 911; Adv. Space. Sci. (2003)) from the G. Broglio base of the Italian Space Agency, located in Trapani Milo (Sicily). In both cases the mock-up was dropped from an altitude higher than 27 and 32 km, respectively, and recovered on the ground after a parachuted descent. In this paper, we describe the results obtained in reconstructing (i) the probe descent trajectory and (ii) the profiles of the physical quantities characterizing the Earth's atmosphere, on the basis of a complete analysis of the data obtained during the HASI 2002 balloon flight experiment. Using temperature and pressure measurements, we are able to reach an accuracy of the order of 0.5% on the altitude reconstruction during the descent. We validate both the models used for trajectory reconstruction and to check the sensors' performance. We describe the problems faced in determining the Huygens probe descent trajectory in Titan's atmosphere focusing our discussion on the critical aspects of the descent reconstruction (such as the uncertainties due to measurement errors, limited knowledge of the atmospheric composition, etc.) and the validity of the adopted assumptions.

Computational fluid dynamics modeling of transport and deposition of pesticides in an aircraft cabin

PubMed Central

Isukapalli, Sastry S.; Mazumdar, Sagnik; George, Pradeep; Wei, Binnian; Jones, Byron; Weisel, Clifford P.

2015-01-01

Spraying of pesticides in aircraft cabins is required by some countries as part of a disinsection process to kill insects that pose a public health threat. However, public health concerns remain regarding exposures of cabin crew and passengers to pesticides in aircraft cabins. While large scale field measurements of pesticide residues and air concentrations in aircraft cabins scenarios are expensive and time consuming, Computational Fluid Dynamics (CFD) models provide an effective alternative for characterizing concentration distributions and exposures. This study involved CFD modeling of a twin-aisle 11 row cabin mockup with heated manikins, mimicking a part of a fully occupied Boeing 767 cabin. The model was applied to study the flow and deposition of pesticides under representative scenarios with different spraying patterns (sideways and overhead) and cabin air exchange rates (low and high). Corresponding spraying experiments were conducted in the cabin mockup, and pesticide deposition samples were collected at the manikin’s lap and seat top for a limited set of five seats. The CFD model performed well for scenarios corresponding to high air exchange rates, captured the concentration profiles for middle seats under low air exchange rates, and underestimated the concentrations at window seats under low air exchange rates. Additionally, both the CFD and experimental measurements showed no major variation in deposition characteristics between sideways and overhead spraying. The CFD model can estimate concentration fields and deposition profiles at very high resolutions, which can be used for characterizing the overall variability in air concentrations and surface loadings. Additionally, these model results can also provide a realistic range of surface and air concentrations of pesticides in the cabin that can be used to estimate potential exposures of cabin crew and passengers to these pesticides. PMID:25642134

Mercury Capsule Construction at the NASA Lewis Research Center

NASA Image and Video Library

1959-08-21

A NASA mechanic secures the afterbody to a Mercury capsule in the hangar at the Lewis Research Center. The capsule was one of two built at Lewis for the “Big Joe” launches scheduled for September 1959. The initial phase of Project Mercury consisted of a series of unmanned launches using the Air Force’s Redstone and Atlas boosters and the Langley-designed Little Joe boosters. The first Atlas launch, referred to as “Big Joe”, was a single attempt early in Project Mercury to use a full-scale Atlas booster to simulate the reentry of a mock-up Mercury capsule without actually placing it in orbit. The overall design of Big Joe had been completed by December 1958, and soon thereafter project manager Aleck Bond assigned NASA Lewis the task of designing the electronic instrumentation and automatic stabilization system. Lewis also constructed the capsule’s lower section, which contained a pressurized area with the electronics and two nitrogen tanks for the retrorockets. Lewis technicians were responsible for assembling the entire capsule: the General Electric heatshield, NASA Langley afterbody and recovery canister, and Lewis electronics and control systems. On June 9, 1959, the capsule was loaded on an air force transport aircraft and flown to Cape Canaveral. A team of 45 test operations personnel from Lewis followed the capsule to Florida and spent the ensuing months preparing it for launch. The launch took place in the early morning hours of September 9, 1959.

Multi-Axis Space Inertia Test Facility inside the Altitude Wind Tunnel

NASA Image and Video Library

1960-04-21

The Multi-Axis Space Test Inertial Facility (MASTIF) in the Altitude Wind Tunnel at the National Aeronautics and Space Administration (NASA) Lewis Research Center. Although the Mercury astronaut training and mission planning were handled by the Space Task Group at Langley Research Center, NASA Lewis played an important role in the program, beginning with the Big Joe launch. Big Joe was a singular attempt early in the program to use a full-scale Atlas booster and simulate the reentry of a mockup Mercury capsule without actually placing it in orbit. A unique three-axis gimbal rig was built inside Lewis’ Altitude Wind Tunnel to test Big Joe’s attitude controls. The control system was vital since the capsule would burn up on reentry if it were not positioned correctly. The mission was intended to assess the performance of the Atlas booster, the reliability of the capsule’s attitude control system and beryllium heat shield, and the capsule recovery process. The September 9, 1959 launch was a success for the control system and heatshield. Only a problem with the Atlas booster kept the mission from being a perfect success. The MASTIF was modified in late 1959 to train Project Mercury pilots to bring a spinning spacecraft under control. An astronaut was secured in a foam couch in the center of the rig. The rig then spun on three axes from 2 to 50 rotations per minute. Small nitrogen gas thrusters were used by the astronauts to bring the MASTIF under control.

A back-projection algorithm in the presence of an extra attenuating medium: towards EPID dosimetry for the MR-Linac

NASA Astrophysics Data System (ADS)

Torres-Xirau, I.; Olaciregui-Ruiz, I.; Rozendaal, R. A.; González, P.; Mijnheer, B. J.; Sonke, J.-J.; van der Heide, U. A.; Mans, A.

2017-08-01

In external beam radiotherapy, electronic portal imaging devices (EPIDs) are frequently used for pre-treatment and for in vivo dose verification. Currently, various MR-guided radiotherapy systems are being developed and clinically implemented. Independent dosimetric verification is highly desirable. For this purpose we adapted our EPID-based dose verification system for use with the MR-Linac combination developed by Elekta in cooperation with UMC Utrecht and Philips. In this study we extended our back-projection method to cope with the presence of an extra attenuating medium between the patient and the EPID. Experiments were performed at a conventional linac, using an aluminum mock-up of the MRI scanner housing between the phantom and the EPID. For a 10 cm square field, the attenuation by the mock-up was 72%, while 16% of the remaining EPID signal resulted from scattered radiation. 58 IMRT fields were delivered to a 20 cm slab phantom with and without the mock-up. EPID reconstructed dose distributions were compared to planned dose distributions using the γ -evaluation method (global, 3%, 3 mm). In our adapted back-projection algorithm the averaged {γmean} was 0.27+/- 0.06 , while in the conventional it was 0.28+/- 0.06 . Dose profiles of several square fields reconstructed with our adapted algorithm showed excellent agreement when compared to TPS.

Experimental studies on tungsten-armour impact on nuclear responses of solid breeding blanket

NASA Astrophysics Data System (ADS)

Sato, Satoshi; Nakao, Makoto; Verzilov, Yury; Ochiai, Kentaro; Wada, Masayuki; Kubota, Naoyoshi; Kondo, Keitaro; Yamauchi, Michinori; Nishitani, Takeo

2005-07-01

In order to experimentally evaluate the tungsten armour impact on tritium production of the solid breeding blanket being developed by JAERI for tokamak-type DEMO reactors, neutronics integral experiments have been performed using DT neutrons at the Fusion Neutron Source facility of JAERI. Solid breeding blanket mockups relevant to the DEMO blanket have been applied in this study. The mockups are made of a set of layers consisting of 0-25.2 mm thick tungsten, 16 mm thick F82H, 12 mm thick Li2TiO3 and 100-200 mm thick beryllium with a cross-section of 660 × 660 mm in maximum. Pellets of Li2CO3 are embedded in the Li2TiO3 layers to measure the tritium production rate. By installing the 5 mm, 12.6 mm and 25.2 mm thick tungsten armours, the sum of the integrated tritium productions at the pellets are reduced by about 2.1%, 2.5% and 6.1% relative to the case without the armour, respectively. Numerical calculations have been conducted using the Monte Carlo code. In the case of the mockups with the tungsten armour, calculation results for the sum of the integrated tritium productions agree well with the experimental data within 4% and 19% in the experiments without and with a neutron reflector, respectively.

STS-103 crewmembers during NBL EVA training

NASA Image and Video Library

1999-06-21

S99-06194 (21 June 1999) --- Astronaut C. Michael Foale, mission specialist, rehearses Extravehicular Activity (EVA) with the Hubble Space Telescope (HST) mockup in the Neutral Buoyancy Laboratory (NBL).

Former President George H.W. Bush paid a visit to NASA's Johnson Space Center to speak with Expedition 46 Commander Scott Kelly and Flight Engineer Tim Kopra and take a tour of the Space Vehicle Mockup Facility. Kelly���s twin brother, Mark Kelly and his wife, former Congresswoman Gabrielle Giffords were also present. Photo Date: February 5, 2016. Location: Building 30 - ISS Flight Control Room. Photographer: Robert Markowitz

NASA Image and Video Library

2016-02-05

Former President George H.W. Bush paid a visit to NASA's Johnson Space Center to speak with Expedition 46 Commander Scott Kelly and Flight Engineer Tim Kopra and take a tour of the Space Vehicle Mockup Facility. Kelly’s twin brother, Mark Kelly and his wife, former Congresswoman Gabrielle Giffords were also present. Photo Date: February 5, 2016. Location: Building 30 - ISS Flight Control Room. Photographer: Robert Markowitz

KSC-08pd1900

NASA Image and Video Library

2008-07-02

CAPE CANAVERAL, Fla. –David Voci, NYIT MOCAP (Motion Capture) team co-director (seated at the workstation in the background) prepares to direct a motion capture session assisted by Kennedy Advanced Visualizations Environment staff led by Brad Lawrence (not pictured) and by Lora Ridgwell from United Space Alliance Human Factors (foreground, left). Ridgwell will help assemble the Orion Crew Module mockup. The motion tracking aims to improve efficiency of assembly processes and identify potential ergonomic risks for technicians assembling the mockup. The work is being performed in United Space Alliance's Human Engineering Modeling and Performance Lab in the RLV Hangar at NASA's Kennedy Space Center. 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.

Boeing Extrication Team training on Boeing Mock-Up Trainer (BMT)

NASA Image and Video Library

2018-05-25

The Boeing extrication team train on the Boeing Mock-up Trainer from May 25 through May 28, 2018, at NASA's Johnson Space Center in Houston. The extrication team is comprised of firefighters from various U.S. Boeing sites. Each member of the team brings an expertise in Aerospace Confined Space Rescue, are Emergency Medical Technicians and have years of rescue experience. The team is highly motivated to getting the crew out quickly, safely and efficiently. The training at Johnson included suit training, side hatch egress, and Intravehicular Activity (IVA) rigging and egress. The week included a run for record on IVA egress for a testing requirement. Participants also included NASA Medical, the 45th Operations Group's Detachment 3, based at Patrick Air Force Base, and U.S. Air Force pararescue representation.

Wernher von Braun

NASA Image and Video Library

1962-09-11

Marshall Space Flight Center Director Dr. Wernher von Braun explains a detail from a Saturn IB mockup and engine to President John F. Kennedy, Vice President Lyndon Johnson and other guests, September 11, 1962.

KSC-2011-8144

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8142

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8140

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8135

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8137

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – A technician works on the removal of a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8141

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8146

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8145

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8134

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8143

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8139

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8136

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8138

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8147

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

Bonded functional esthetic prototype: an alternative pre-treatment mock-up technique and cost-effective medium-term esthetic solution.

PubMed

McLaren, Edward A

2013-09-01

As the economy has receded in recent years, many patients have been inclined to reject dental treatment beyond what they feel is the minimal amount necessary. Increasingly, there has been reluctance to take on the expense of full-mouth restorations and time-consuming procedures. Consequently, clinicians can benefit from innovative, conservative, interim solutions that enable them to provide segment treatment with long-term stability and esthetics, with lower initial cost. The bonded functional esthetic prototype (BFEP) allows fabrication of up to 14 teeth from composite in 1 hour, providing either a pre-treatment restoration or a long-term provisional solution until further treatment can be completed. As demonstrated herein, the BFEP enables superb function, stability, and esthetics in the interim while dispersing the cost of definitive treatment over time.

KENNEDY SPACE CENTER, FLA. - A rescue team carries an “injured” astronaut toward the helicopter for transportation to a local hospital. They are all taking part in a “Mode VII” emergency landing simulation at Kennedy Space Center. The purpose of the Mode VII is to exercise emergency preparedness personnel, equipment and facilities in rescuing astronauts from a downed orbiter and providing immediate medical attention. This simulation presents an orbiter that has crashed short of the Shuttle Landing Facility in a wooded area 2-1/2 miles south of Runway 33. Emergency crews are responding to the volunteer astronauts who are simulating various injuries inside the crew compartment mock-up. Rescuers must remove the crew, provide triage and transport to hospitals those who need further treatment. Local hospitals are participating in the exercise. Emergency crews are responding to the volunteer astronauts who are simulating various injuries inside the crew compartment mock-up. Rescuers must remove the crew, provide triage and transport to hospitals those who need further treatment. Local hospitals are participating in the exercise.

NASA Image and Video Library

2004-02-18

KENNEDY SPACE CENTER, FLA. - A rescue team carries an “injured” astronaut toward the helicopter for transportation to a local hospital. They are all taking part in a “Mode VII” emergency landing simulation at Kennedy Space Center. The purpose of the Mode VII is to exercise emergency preparedness personnel, equipment and facilities in rescuing astronauts from a downed orbiter and providing immediate medical attention. This simulation presents an orbiter that has crashed short of the Shuttle Landing Facility in a wooded area 2-1/2 miles south of Runway 33. Emergency crews are responding to the volunteer astronauts who are simulating various injuries inside the crew compartment mock-up. Rescuers must remove the crew, provide triage and transport to hospitals those who need further treatment. Local hospitals are participating in the exercise. Emergency crews are responding to the volunteer astronauts who are simulating various injuries inside the crew compartment mock-up. Rescuers must remove the crew, provide triage and transport to hospitals those who need further treatment. Local hospitals are participating in the exercise.

Validation results of satellite mock-up capturing experiment using nets

NASA Astrophysics Data System (ADS)

Medina, Alberto; Cercós, Lorenzo; Stefanescu, Raluca M.; Benvenuto, Riccardo; Pesce, Vincenzo; Marcon, Marco; Lavagna, Michèle; González, Iván; Rodríguez López, Nuria; Wormnes, Kjetil

2017-05-01

The PATENDER activity (Net parametric characterization and parabolic flight), funded by the European Space Agency (ESA) via its Clean Space initiative, was aiming to validate a simulation tool for designing nets for capturing space debris. This validation has been performed through a set of different experiments under microgravity conditions where a net was launched capturing and wrapping a satellite mock-up. This paper presents the architecture of the thrown-net dynamics simulator together with the set-up of the deployment experiment and its trajectory reconstruction results on a parabolic flight (Novespace A-310, June 2015). The simulator has been implemented within the Blender framework in order to provide a highly configurable tool, able to reproduce different scenarios for Active Debris Removal missions. The experiment has been performed over thirty parabolas offering around 22 s of zero-g conditions. Flexible meshed fabric structure (the net) ejected from a container and propelled by corner masses (the bullets) arranged around its circumference have been launched at different initial velocities and launching angles using a pneumatic-based dedicated mechanism (representing the chaser satellite) against a target mock-up (the target satellite). High-speed motion cameras were recording the experiment allowing 3D reconstruction of the net motion. The net knots have been coloured to allow the images post-process using colour segmentation, stereo matching and iterative closest point (ICP) for knots tracking. The final objective of the activity was the validation of the net deployment and wrapping simulator using images recorded during the parabolic flight. The high-resolution images acquired have been post-processed to determine accurately the initial conditions and generate the reference data (position and velocity of all knots of the net along its deployment and wrapping of the target mock-up) for the simulator validation. The simulator has been properly configured according to the parabolic flight scenario, and executed in order to generate the validation data. Both datasets have been compared according to different metrics in order to perform the validation of the PATENDER simulator.

CEV Seat Layout Evaluation

NASA Image and Video Library

2007-11-15

Photographic documentation of the CEV Seat Layout Evaluation taken in the Orion mockup located in bldg 9NW, Johnson Space Center (JSC). Test subjects in orange Launch and Entry Suit (LES) is visible in the seat.

STS-335 crew and training team during Bailout training

NASA Image and Video Library

2010-12-03

STS-335 crew and training team during Bailout training with instructors Bob Behrendsen and Patrick Jones. Photo Date: December 3, 2010. Location: Building 9NW - CCT-II Mockup. Photographer: Robert Markowitz.

22 CFR 124.2 - Exemptions for training and military service.

Code of Federal Regulations, 2010 CFR

2010-04-01

... methods and tools include the development and/or use of mockups, computer models and simulations, and test facilities. (iii) Manufacturing know-how, such as: Information that provides detailed manufacturing processes...

KSC-2012-5891

NASA Image and Video Library

2012-10-19

CAPE CANAVERAL, Fla. – An Orion mockup spacecraft atop its service module simulator is lifted in the transfer aisle of the Vehicle Assembly Building, or VAB, at NASA's Kennedy Space Center in Florida. The Orion mockup is exact in details on the outside, but mostly empty on the inside. The work in the VAB is crucial to making sure the designs are accurate. 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. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on a Space Launch System rocket. For more information, visit http://www.nasa.gov/orion Photo credit: NASA/ Dmitri Gerondidakis

KSC-2012-5893

NASA Image and Video Library

2012-10-19

CAPE CANAVERAL, Fla. – An Orion mockup spacecraft atop its service module simulator is lowered onto a transporter in the transfer aisle of the Vehicle Assembly Building, or VAB, at NASA's Kennedy Space Center in Florida. The Orion mockup is exact in details on the outside, but mostly empty on the inside. The work in the VAB is crucial to making sure the designs are accurate. 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. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on a Space Launch System rocket. For more information, visit http://www.nasa.gov/orion Photo credit: NASA/ Dmitri Gerondidakis

STS-31 MS McCandless and MS Sullivan during JSC WETF underwater simulation

NASA Image and Video Library

1990-03-05

This overall view shows STS-31 Mission Specialist (MS) Bruce McCandless II (left) and MS Kathryn D. Sullivan making a practice space walk in JSC's Weightless Environment Training Facility (WETF) Bldg 29 pool. McCandless works with a mockup of the remote manipulator system (RMS) end effector which is attached to a grapple fixture on the Hubble Space Telescope (HST) mockup. Sullivan manipulates HST hardware on the Support System Module (SSM) forward shell. SCUBA-equipped divers monitor the extravehicular mobility unit (EMU) suited crewmembers during this simulated extravehicular activity (EVA). No EVA is planned for the Hubble Space Telescope (HST) deployment, but the duo has trained for contingencies which might arise during the STS-31 mission aboard Discovery, Orbiter Vehicle (OV) 103. Photo taken by NASA JSC photographer Sheri Dunnette.

An Experimental Examination of the Loss-of-Flow Accident Phenomenon for Prototypical ITER Divertor Channels of Y = 0 and Y = 2

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

Marshall, Theron D.; McDonald, Jimmie M.; Cadwallader, Lee C.

2000-01-15

This paper discusses the thermal response of two prototypical International Thermonuclear Experimental Reactor (ITER) divertor channels during simulated loss-of-flow-accident (LOFA) experiments. The thermal response was characterized by the time-to-burnout (TBO), which is a figure of merit on the mockups' survivability. Data from the LOFA experiments illustrate that (a) the pre-LOFA inlet velocity does not significantly influence the TBO, (b) the incident heat flux (IHF) does influence the TBO, and (c) a swirl tape insert significantly improves the TBO and promotes the initiation of natural circulation. This natural circulation enabled the mockup to absorb steady-state IHFs after the coolant circulation pumpmore » was disabled. Several methodologies for thermal-hydraulic modeling of the LOFA were attempted.« less

An experimental examination of the loss-of-flow accident phenomenon for prototypical ITER divertor channels of Y=0 and Y=2

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

Marshall, T.D.; McDonald, J.M.; Cadwallader, L.C.

2000-01-01

This paper discusses the thermal response of two prototypical International Thermonuclear Experimental Reactor (ITER) divertor channels during simulated loss-of-flow-accident (LOFA) experiments. The thermal response was characterized by the time-to-burnout (TBO), which is a figure of merit on the mockups' survivability. Data from the LOFA experiments illustrate that (a) the pre-LOFA inlet velocity does not significantly influence the TBO, (b) the incident heat flux (IHF) does influence the TBO, and (c) a swirl tape insert significantly improves the TBO and promotes the initiation of natural circulation. This natural circulation enabled the mockup to absorb steady-state IHFs after the coolant circulation pumpmore » was disabled. Several methodologies for thermal-hydraulic modeling of the LOFA were attempted.« less

STS-31 MS McCandless and MS Sullivan during JSC WETF underwater simulation

NASA Technical Reports Server (NTRS)

1990-01-01

This overall view shows STS-31 Mission Specialist (MS) Bruce McCandless II (left) and MS Kathryn D. Sullivan making a practice space walk in JSC's Weightless Environment Training Facility (WETF) Bldg 29 pool. McCandless works with a mockup of the remote manipulator system (RMS) end effector which is attached to a grapple fixture on the Hubble Space Telescope (HST) mockup. Sullivan manipulates HST hardware on the Support System Module (SSM) forward shell. SCUBA-equipped divers monitor the extravehicular mobility unit (EMU) suited crewmembers during this simulated extravehicular activity (EVA). No EVA is planned for the Hubble Space Telescope (HST) deployment, but the duo has trained for contingencies which might arise during the STS-31 mission aboard Discovery, Orbiter Vehicle (OV) 103. Photo taken by NASA JSC photographer Sheri Dunnette.

Skylab

NASA Image and Video Library

1968-01-01

This photograph was taken at the Redstone airfield, Huntsville, Alabama, during the unloading of the Saturn V S-IVB stage that housed the Orbital Workshop (OWS) from the Super Guppy, the NASA plane that was specially built to carry oversized cargo. The OWS measured 22 feet (6.7 m) in diameter, and 48 feet (14.6 m) in length. The Saturn V S-IVB stage was modified at the McDornell Douglas facility at Huntington Beach, California, for a new role, which was to house the OWS. In addition to the test articles, engineering mockups, and flight equipment, both McDonnell Douglas and Martin Marietta built 0-G trainers, neutral buoyancy trainers, and high-fidelity mockups for the 1-G trainer to be used in the KC-135 aircraft. The Marshall Space Flight Center had program management responsibility for the development of Skylab hardware and experiments.

Production of footbridge with double curvature made of UHPC

NASA Astrophysics Data System (ADS)

Kolísko, J.; Čítek, D.; Tej, P.; Rydval, M.

2017-09-01

This article present a mix design, preparation and production of thin-walled footbridge made from UHPFRC. In this case an experimental pedestrian bridge was design and prepared. Bridge with span of 10 m and the clear width of 1.50 m designed as single-span bridge. Optimization of UHPFRC matrix and parameters of this material leads to the design of very thin structures. Total thickness of shell structure 30 - 45 mm. Bridge was cast as a prefabricated element in one piece. Self-compacting character of UHPFRC with high flowability allows the production of the final structure. Extensive research was done before production of footbridge. Experimental reached data were compared with extensive numerical analysis and the final design of structure and UHPFRC matrix were optimized in many details. Two versions of large scale mock-ups were casted and tested. According to the complexity of whole experiment a casting technology and production of formwork were tested and optimized many times.

Human-Robot Control Strategies for the NASA/DARPA Robonaut

NASA Technical Reports Server (NTRS)

Diftler, M. A.; Culbert, Chris J.; Ambrose, Robert O.; Huber, E.; Bluethmann, W. J.

2003-01-01

The Robotic Systems Technology Branch at the NASA Johnson Space Center (JSC) is currently developing robot systems to reduce the Extra-Vehicular Activity (EVA) and planetary exploration burden on astronauts. One such system, Robonaut, is capable of interfacing with external Space Station systems that currently have only human interfaces. Robonaut is human scale, anthropomorphic, and designed to approach the dexterity of a space-suited astronaut. Robonaut can perform numerous human rated tasks, including actuating tether hooks, manipulating flexible materials, soldering wires, grasping handrails to move along space station mockups, and mating connectors. More recently, developments in autonomous control and perception for Robonaut have enabled dexterous, real-time man-machine interaction. Robonaut is now capable of acting as a practical autonomous assistant to the human, providing and accepting tools by reacting to body language. A versatile, vision-based algorithm for matching range silhouettes is used for monitoring human activity as well as estimating tool pose.

Space Station UCS antenna pattern computation and measurement. [UHF Communication Subsystem

NASA Technical Reports Server (NTRS)

Hwu, Shian U.; Lu, Ba P.; Johnson, Larry A.; Fournet, Jon S.; Panneton, Robert J.; Ngo, John D.; Eggers, Donald S.; Arndt, G. D.

1993-01-01

The purpose of this paper is to analyze the interference to the Space Station Ultrahigh Frequency (UHF) Communication Subsystem (UCS) antenna radiation pattern due to its environment - Space Station. A hybrid Computational Electromagnetics (CEM) technique was applied in this study. The antenna was modeled using the Method of Moments (MOM) and the radiation patterns were computed using the Uniform Geometrical Theory of Diffraction (GTD) in which the effects of the reflected and diffracted fields from surfaces, edges, and vertices of the Space Station structures were included. In order to validate the CEM techniques, and to provide confidence in the computer-generated results, a comparison with experimental measurements was made for a 1/15 scale Space Station mockup. Based on the results accomplished, good agreement on experimental and computed results was obtained. The computed results using the CEM techniques for the Space Station UCS antenna pattern predictions have been validated.

Experiments and simulation of a net closing mechanism for tether-net capture of space debris

NASA Astrophysics Data System (ADS)

Sharf, Inna; Thomsen, Benjamin; Botta, Eleonora M.; Misra, Arun K.

2017-10-01

This research addresses the design and testing of a debris containment system for use in a tether-net approach to space debris removal. The tether-net active debris removal involves the ejection of a net from a spacecraft by applying impulses to masses on the net, subsequent expansion of the net, the envelopment and capture of the debris target, and the de-orbiting of the debris via a tether to the chaser spacecraft. To ensure a debris removal mission's success, it is important that the debris be successfully captured and then, secured within the net. To this end, we present a concept for a net closing mechanism, which we believe will permit consistently successful debris capture via a simple and unobtrusive design. This net closing system functions by extending the main tether connecting the chaser spacecraft and the net vertex to the perimeter and around the perimeter of the net, allowing the tether to actuate closure of the net in a manner similar to a cinch cord. A particular embodiment of the design in a laboratory test-bed is described: the test-bed itself is comprised of a scaled-down tether-net, a supporting frame and a mock-up debris. Experiments conducted with the facility demonstrate the practicality of the net closing system. A model of the net closure concept has been integrated into the previously developed dynamics simulator of the chaser/tether-net/debris system. Simulations under tether tensioning conditions demonstrate the effectiveness of the closure concept for debris containment, in the gravity-free environment of space, for a realistic debris target. The on-ground experimental test-bed is also used to showcase its utility for validating the dynamics simulation of the net deployment, and a full-scale automated setup would make possible a range of validation studies of other aspects of a tether-net debris capture mission.

Terrestrial Planet Finder Interferometer Science Working Group Report

NASA Technical Reports Server (NTRS)

Lawson, Peter R. (Editor); Lay, Oliver P. (Editor); Johnston, Kenneth J. (Editor); Beichman, Charles A. (Editor)

2007-01-01

Over the past two years, the focus of the project for the interferometric version of the Terrestrial Planet Finder(TPF-I) has been on the development of the scientific rational for the mission, the assessment of TPF-I architectures, the laboratory demonstration of key technologies, and the development of a detailed technology roadmap. The Science Working Group (SWG), in conjunction with European colleagues working on the European Space Agency's (ESA's) Darwin project, has reaffirmed the goals of TPF-I as part of a broad vision for the detection and characterization of Earth-like planets orbiting nearby stars and for the search for life on those planets. The SWG also helped to assess the performance of different interferometric configurations for TPF-I/Darwin. Building on earlier SWG reports, this document restates the scientific case for TPF-I, assesses suitable target stars and relevant wavelengths for observation, discusses dramatic new capabilities for general astrophysical observations, and summarizes how Spitzer has improved our knowledge of the incidence of zodiacal emission on the search for planets. This document discusses in some detail on laboratory advances in interferometric nulling and formation flying. Laboratory experiments have now achieved stable narrow- and broad-band nulling the levels of 10-6 and 2.0x10-5, respectively. A testbed has demonstrated formation flying using two realistic spacecraft mockups. With a suitably funded program of technology development, as summarized herein and described in more detail in the Technology Plan for the Terrestrial Planet Finder Interferometer (2005), the National Aeronautics and Space Administration (NASA) and ESA would be able to start within the coming decade a full-scale TPF-I/Darwin mission capable of finding Earths orbiting more than 150 nearby stars, or a scaled back interferometer capable of studying more than 30 stars. Finding evidence for life on just one of those planets would revolutionize our understanding of our place in the cosmos.

Juno Taking Shape

NASA Image and Video Library

2010-05-03

Assembly began April 1, 2010, for NASA Juno spacecraft in the high-bay cleanroom at Lockheed Martin in Denver, Colo. Workers are moving the radiation vault above a mock-up of the upper part of the spacecraft main body.

Portrait of Astronaut Alan L. Bean

NASA Technical Reports Server (NTRS)

1969-01-01

Portrait of Astronaut Alan L. Bean, Prime Crew Lunar Module Pilot of the Apollo 12 Lunar Landing Mission, in his space suit minus the helmet. He is standing outside beside a mock-up of the Lunar Lander.

Habitability study shuttle orbiter

NASA Technical Reports Server (NTRS)

1973-01-01

Habitability design concepts for the Shuttle Orbiter Program are provided for MSC. A variety of creative solutions for the stated tasks are presented. Sketches, mock-ups, mechanicals and models are included for establishing a foundation for future development.

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

Halliwell, Stephen

Radioactive waste materials, including Transuranic (TRU) wastes from laboratories have been stored below ground in large containments at a number of sites in the US DOE Complex, and at nuclear sites in Europe. These containments are generally referred to as caissons or shafts. The containments are in a range of sizes and depths below grade. The caissons at the DOE's Hanford site are cylindrical, of the order of 2,500 mm in diameter, 3,050 mm in height and are buried about 6,000 mm below grade. One type of caisson is made out of corrugated pipe, whereas others are made of concretemore » with standard re-bar. However, the larger shafts in the UK are of the order of 4,600 mm in diameter, 53,500 mm deep, and 12,000 below grade. This paper describes the R and D work and testing activities performed to date to evaluate the concept of in-ground size reduction and stabilization of the contents of large containments similar to those at Hanford. In practice, the height of the Test Facility provided for a test cell that was approximately 22' deep. That prevented a 'full scale mockup' test in the sense that the Hanford Caisson configuration would be an identical replication. Therefore, the project was conducted in two phases. The first phase tested a simulated Caisson with surrogate contents, and part of a Chute section, and the second phase tested a full chute section. These tests were performed at VJ Technologies Test Facility located in East Haven, CT, as part of the Proof of Design Concept program for studying the feasibility of an in-situ grout/grind/mix/stabilize technology for the remediation of four caissons at the 618-11 Burial Ground at US Department of Energy Hanford Site. The test site was constructed such that multiple testing areas were provided for the evaluation of various tools, equipment and procedures under conditions that simulated the Hanford site, with representative soils and layout dimensions. (authors)« less

Optimizing lighting, thermal performance, and energy production of building facades by using automated blinds and PV cells

NASA Astrophysics Data System (ADS)

Alzoubi, Hussain Hendi

Energy consumption in buildings has recently become a major concern for environmental designers. Within this field, daylighting and solar energy design are attractive strategies for saving energy. This study seeks the integrity and the optimality of building envelopes' performance. It focuses on the transparent parts of building facades, specifically, the windows and their shading devices. It suggests a new automated method of utilizing solar energy while keeping optimal solutions for indoor daylighting. The method utilizes a statistical approach to produce mathematical equations based on physical experimentation. A full-scale mock-up representing an actual office was built. Heat gain and lighting levels were measured empirically and correlated with blind angles. Computational methods were used to estimate the power production from photovoltaic cells. Mathematical formulas were derived from the results of the experiments; these formulas were utilized to construct curves as well as mathematical equations for the purpose of optimization. The mathematical equations resulting from the optimization process were coded using Java programming language to enable future users to deal with generic locations of buildings with a broader context of various climatic conditions. For the purpose of optimization by automation under different climatic conditions, a blind control system was developed based on the findings of this study. This system calibrates the blind angles instantaneously based upon the sun position, the indoor daylight, and the power production from the photovoltaic cells. The functions of this system guarantee full control of the projected solar energy on buildings' facades for indoor lighting and heat gain. In winter, the system automatically blows heat into the space, whereas it expels heat from the space during the summer season. The study showed that the optimality of building facades' performance is achievable for integrated thermal, energy, and lighting models in buildings. There are blind angles that produce maximum energy from the photovoltaic cells while keeping indoor light within the acceptable limits that prevent undesired heat gain in summer.

Integrating Human Factors into Crew Exploration Vehicle Design

NASA Technical Reports Server (NTRS)

Whitmore, Mihriban; Baggerman, Susan; Campbell, paul

2007-01-01

With NASA's new Vision for Exploration to send humans beyond Earth orbit, it is critical to consider the human as a system that demands early and continuous user involvement, and an iterative prototype/test/redesign process. Addressing human-system interface issues early on can be very cost effective even cost reducing when performed early in the design and development cycle. To achieve this goal within Crew Exploration Vehicle (CEV) Project Office, human engineering (HE) team is formed. Key tasks are to apply HE requirements and guidelines to hardware/software, and provide HE design, analysis and evaluation of crew interfaces. Initial activities included many practice-orientated evaluations using low-fidelity CEV mock-ups. What follows is a description of such evaluations that focused on a HE requirement regarding Net Habitable Volume (NHV). NHV is defined as the total remaining pressurized volume available to on-orbit crew after accounting for the loss of volume due to deployed hardware and structural inefficiencies which decrease functional volume. The goal of the NHV evaluations was to develop requirements providing sufficient CEV NHV for crewmembers to live and perform tasks in support of mission goals. Efforts included development of a standard NHV calculation method using computer models and physical mockups, and crew/ stakeholder evaluations. Nine stakeholders and ten crewmembers participated in the unsuited evaluations. Six crewmembers also participated in a suited evaluation. The mock-up was outfitted with volumetric representation of sub-systems such as seats, and stowage bags. Thirteen scenarios were developed to represent mission/crew tasks and considered to be primary volume drivers (e.g., suit donning) for the CEV. Unsuited evaluations included a structured walkthrough of these tasks. Suited evaluations included timed donning of the existing launch and entry suit to simulate a contingency scenario followed by doffing/ stowing of the suits. All mockup evaluations were videotaped. Structured questionnaires were used to document user interface issues and volume impacts of layout configuration. Computer model and physical measures of the NHV agreed within 1 percent. This included measurement of the gross habitable volume, subtraction of intrusive volumes, and other non-habitable spaces. Calculation method developed was validated as a standard means of measuring NHV, and was recommended as a verification method for the NHV requirements. Evaluations confirmed that there was adequate volume for unsuited scenarios and suit donning/ doffing activity. Seats, suit design stowage and waste hygiene system noted to be critical volume drivers. The low-fidelity mock-up evaluations along with human modeling analysis generated discussions that will lead to high-level systems requirements and human-centered design decisions. This approach allowed HE requirements and operational concepts to evolve in parallel with engineering system concepts and design requirements. As the CEV design matures, these evaluations will continue and help with design decisions, and assessment, verification and validation of HE requirements.

Fire tests to evaluate the potential fire threat and its effects on HEPA filter integrity in cell ventilation at the Oak Ridge National Laboratory, Building 7920

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

Hasegawa, H.K.; Staggs, K.J.; Doughty, S.M.

1992-12-01

As a result of a DOE (Tiger Team) Technical Safety Appraisal (November 1990) of the Radiochemical Engineering Development Center (REDC), ORNL Building 7920, a number of fire protection concerns were identified. The primary concern was the perceived loss of ventilation system containment due to the thermal destruction and/or breaching of the prefilters and/or high-efficiency particulate air filters (HEPA `s) and the resultant radioactive release to the external environment. The following report describes the results of an extensive fire test program performed by the Fire Research Discipline (FRD) of the Special Projects Division of Lawrence Livermore National Lab (LLNL) and fundedmore » by ORNL to address these concerns. Full scale mock-ups of a REDC hot cell tank pit, adjacent cubicle pit, and associated ventilation system were constructed at LLNL and 13 fire experiments were conducted to specifically answer the questions raised by the Tiger Team. Our primary test plan was to characterize the burning of a catastrophic solvent spill (kerosene) of 40 liters and its effect on the containment ventilation system prefilters and HEPA filters. In conjunction with ORNL and Lockwood Greene we developed a test matrix that assessed the fire performance of the prefilters and HEPA filters; evaluated the fire response of the fiber reinforced plastic (FRP) epoxy ventilation duct work; the response and effectiveness of the fire protection system, the effect of fire in a cubicle on the vessel off-gas (VOG) elbow, and other fire safety questions.« less

A Human Factors Evaluation of a Methodology for Pressurized Crew Module Acceptability for Zero-Gravity Ingress of Spacecraft

NASA Technical Reports Server (NTRS)

Sanchez, Merri J.

2000-01-01

This project aimed to develop a methodology for evaluating performance and acceptability characteristics of the pressurized crew module volume suitability for zero-gravity (g) ingress of a spacecraft and to evaluate the operational acceptability of the NASA crew return vehicle (CRV) for zero-g ingress of astronaut crew, volume for crew tasks, and general crew module and seat layout. No standard or methodology has been established for evaluating volume acceptability in human spaceflight vehicles. Volume affects astronauts'ability to ingress and egress the vehicle, and to maneuver in and perform critical operational tasks inside the vehicle. Much research has been conducted on aircraft ingress, egress, and rescue in order to establish military and civil aircraft standards. However, due to the extremely limited number of human-rated spacecraft, this topic has been un-addressed. The NASA CRV was used for this study. The prototype vehicle can return a 7-member crew from the International Space Station in an emergency. The vehicle's internal arrangement must be designed to facilitate rapid zero-g ingress, zero-g maneuverability, ease of one-g egress and rescue, and ease of operational tasks in multiple acceleration environments. A full-scale crew module mockup was built and outfitted with representative adjustable seats, crew equipment, and a volumetrically equivalent hatch. Human factors testing was conducted in three acceleration environments using ground-based facilities and the KC-135 aircraft. Performance and acceptability measurements were collected. Data analysis was conducted using analysis of variance and nonparametric techniques.

Crew Configuration, Ingress/Egress Procedures, and In-Flight Caregiving Capacity in a Space Ambulance Based on the Boeing X-37B

NASA Astrophysics Data System (ADS)

Halberg, Ephriam Etan

This study proposes that a Boeing X-37B space plane, its dimensions and performance characteristics estimated from publicly available documents, diagrams, and photographs, could be internally redesigned as a medical evacuation (ambulance) vehicle for the International Space Station. As of 2017, there is currently no spacecraft designed to accommodate a contingency medical evacuation wherein a crew member aboard the ISS is injured or ailing and must be returned to Earth for immediate medical attention. The X-37B is an unmanned vehicle with a history of success in both sub-orbital testing and all four of its long-duration orbital missions to date. Research conducted at UC Davis suggests that it is possible to retain the outer mold line of the X-37B while expanding the internal payload compartment to a volume sufficient for a crew of three--pilot, crew medical officer, and injured crew member--throughout ISS un-dock and atmospheric entry, descent, and landing. In addition to crew life support systems, this re-purposed X-37B, hereafter referred to as the X-37SA (Space Ambulance), includes medical equipment for stabilization of a patient in-transit. This study suggests an optimal, ergonomic crew configuration and berthing port location, procedures for microgravity ingress and 1G egress, a minimum medical equipment list and location within the crew cabin for the medical care and monitoring equipment. Conceptual crew configuration, ingress/egress procedures, and patient/equipment access are validated via physical simulation in a full-scale mockup of the proposed X-37SA crew cabin.

Commerical Crew Astronauts Evaluate Crew Dragon Controls

NASA Image and Video Library

2017-01-10

Astronaut Bob Behnken, work in a mock-up of the SpaceX Crew Dragon flight deck at the company's Hawthorne, California, headquarters as development of the crew systems continues for eventual missions to the International Space Station.

Preparation for Testing of Mars Landing Radar

NASA Image and Video Library

2010-04-13

This image taken March 25, 2010 shows preparations for radar testing for NASA Mars Science Laboratory. This day work evaluated a setup for suspending a rover mock-up beneath a helicopter at Hawthorne Municipal Airport, Hawthorne, Calif.

Astronaut Dale Gardner rehearses control of MMU during EVA practice

NASA Technical Reports Server (NTRS)

1984-01-01

Astronaut Dale A. Gardner, 51-A mission specialist, rehearses control of manned maneuvering unit (MMU) during a practice for an extravehicular activity (EVA). Gardner is in the Shuttle mockup and integration laboratory at JSC.

Lisa Smith in MSFC's Laboratory Training Complex

NASA Image and Video Library

2015-02-11

LISA SMITH, THE TRAINING TEAM LEAD IN MARSHALL'S MISSION OPERATIONS LAB, EXAMINES THE DRAWERS IN THE GLACIER MOCK-UP, A TRAINING VERSION OF A FREEZER ON THE INTERNATIONAL SPACE STATION INSTALLED IN THE MARSHALL CENTER'S LABORATORY TRAINING COMPLEX

77 FR 63897 - Notice of License Terminations for National Aeronautics and Space Administration; Plum Brook...

Federal Register 2010, 2011, 2012, 2013, 2014

2012-10-17

... test reactor, constructed to perform irradiation testing of fueled and unfueled experiments for space... constructed to test ``mock-up'' irradiation components for the Plum Brook Reactor. The reactors operated from...

Commerical Crew Astronaut Suni Williams in SpaceX's Spacesuit

NASA Image and Video Library

2018-05-17

NASA Astronaut Suni Williams, fully suited in SpaceX’s spacesuit, interfaces with the display inside a mock-up of the Crew Dragon spacecraft in Hawthorne, California, during a testing exercise on Tuesday, April 3, 2018.

Engineering and manufacturing of ITER first mirror mock-ups.

PubMed

Joanny, M; Travère, J M; Salasca, S; Corre, Y; Marot, L; Thellier, C; Gallay, G; Cammarata, C; Passier, B; Fermé, J J

2010-10-01

Most of the ITER optical diagnostics aiming at viewing and monitoring plasma facing components will use in-vessel metallic mirrors. These mirrors will be exposed to a severe plasma environment and lead to an important tradeoff on their design and manufacturing. As a consequence, investigations are carried out on diagnostic mirrors toward the development of optimal and reliable solutions. The goals are to assess the manufacturing feasibility of the mirror coatings, evaluate the manufacturing capability and associated performances for the mirrors cooling and polishing, and finally determine the costs and delivery time of the first prototypes with a diameter of 200 and 500 mm. Three kinds of ITER candidate mock-ups are being designed and manufactured: rhodium films on stainless steel substrate, molybdenum on TZM substrate, and silver films on stainless steel substrate. The status of the project is presented in this paper.

An Ultrasonic Scanning Technique for In-Situ `Bowing' Measurement of Prototype Fast Breeder Reactor Fuel Sub-Assembly

NASA Astrophysics Data System (ADS)

Swaminathan, K.; Asokane, C.; Sylvia, J. I.; Kalyanasundaram, P.; Swaminathan, P.

2012-02-01

An ultrasonic under-sodium scanner has been developed for deployment in Prototype Fast Breeder Reactor (PFBR) which is in advanced stage of construction at Kalpakkam, India. Its purpose is to scan the above-core plenum for detection, if any, of displacement of sub-assemblies. During its burn-up in the reactor, the head of a Fuel Sub-Assembly (FSA) may undergo a lateral shift from its original position (called `bowing') due to the fast neutron induced damage on its structural material. A simple scanning technique has been developed for measuring the extent of bowing in-situ. This paper describes a PC-controlled mock-up of the scanner used to implement the scanning technique and the results obtained of scanning a mock-up FSA head under water. The details of the liquid-sodium proof transducer developed for use in the PFBR scanner and its performance are also discussed.

Reprint of: environmental information for military planning.

PubMed

Doherty, Victoria; Croft, Darryl; Knight, Ashley

2013-11-01

A study was conducted to consider the implications of presenting Environmental Information (EI; information on current environmental features including weather, topography and visibility maps) for military planning to the growing audience of non-technical users; to provide guidance for ensuring usability and for development of a suitable EI interface, and to produce an EI concept interface mock-up to demonstrate initial design ideas. Knowledge was elicited from current EI users and providers regarding anticipated use of EI by non-specialists. This was combined with human factors and cognition expertise to produce guidance for data usability and development of an EI interface. A simple mock-up of an EI concept interface was developed. Recommendations for further development were made including application of the guidance derived, identification of a user test-bed and development of business processes. Copyright © 2012 Elsevier Ltd and The Ergonomics Society. All rights reserved.

Environmental information for military planning.

PubMed

Doherty, Victoria; Croft, Darryl; Knight, Ashley

2013-07-01

A study was conducted to consider the implications of presenting Environmental Information (EI; information on current environmental features including weather, topography and visibility maps) for military planning to the growing audience of non-technical users; to provide guidance for ensuring usability and for development of a suitable EI interface, and to produce an EI concept interface mock-up to demonstrate initial design ideas. Knowledge was elicited from current EI users and providers regarding anticipated use of EI by non-specialists. This was combined with human factors and cognition expertise to produce guidance for data usability and development of an EI interface. A simple mock-up of an EI concept interface was developed. Recommendations for further development were made including application of the guidance derived, identification of a user test-bed and development of business processes. Copyright © 2012 Elsevier Ltd and The Ergonomics Society. All rights reserved.

Neutron Characterization of Encapsulated ATF-1/LANL-1 Mockup Fuel Capsules

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

Vogel, Sven C.; Borges, Nicholas Paul; Losko, Adrian Simon

Twenty pellets of mock-up accident tolerant fuels UN-U3Si5 were produced at LANL and loaded in two rodlet/capsule assemblies. Tomographic imaging and diffraction measurements were performed to characterize these samples at the Flight-Path 5 and HIPPO beam lines at LANSCE/LANL between November 2016 and January 2017 as well as in August 2017. The entire ~10 cm long, ~1 cm diameter fuel volume could be characterized, however due to time constraints only 2 mm slices in 4mm increments were characterized with neutron diffraction and a 28mm subset of the entire sample was characterized with energy-resolved neutron imaging. The double encapsulation of themore » fuel into two steel containers does not pose a problem for the neutron analysis and the methods could be applied to enriched as well irradiated fuels.« less

ARCADE-R2 experiment on board BEXUS 17 stratospheric balloon

NASA Astrophysics Data System (ADS)

Barbetta, Marco; Boesso, Alessandro; Branz, Francesco; Carron, Andrea; Olivieri, Lorenzo; Prendin, Jacopo; Rodeghiero, Gabriele; Sansone, Francesco; Savioli, Livia; Spinello, Fabio; Francesconi, Alessandro

2015-09-01

This paper provides an overview of the ARCADE-R2 experiment, a technology demonstrator that aimed to prove the feasibility of small-scale satellite and/or aircraft systems with automatic (a) attitude determination, (b) control and (c) docking capabilities. The experiment embodies a simplified scenario in which an unmanned vehicle mock-up performs rendezvous and docking operations with a fixed complementary unit. The experiment is composed by a supporting structure, which holds a small vehicle with one translational and one rotational degree of freedom, and its fixed target. The dual system features three main custom subsystems: a relative infrared navigation sensor, an attitude control system based on a reaction wheel and a small-scale docking mechanism. The experiment bus is equipped with pressure and temperature sensors, and wind probes to monitor the external environmental conditions. The experiment flew on board the BEXUS 17 stratospheric balloon on October 10, 2013, where several navigation-control-docking sequences were executed and data on the external pressure, temperature, wind speed and direction were collected, characterizing the atmospheric loads applied to the vehicle. This paper describes the critical components of ARCADE-R2 as well as the main results obtained from the balloon flight.

A Large-Scale Design Integration Approach Developed in Conjunction with the Ares Launch Vehicle Program

NASA Technical Reports Server (NTRS)

Redmon, John W.; Shirley, Michael C.; Kinard, Paul S.

2012-01-01

This paper presents a method for performing large-scale design integration, taking a classical 2D drawing envelope and interface approach and applying it to modern three dimensional computer aided design (3D CAD) systems. Today, the paradigm often used when performing design integration with 3D models involves a digital mockup of an overall vehicle, in the form of a massive, fully detailed, CAD assembly; therefore, adding unnecessary burden and overhead to design and product data management processes. While fully detailed data may yield a broad depth of design detail, pertinent integration features are often obscured under the excessive amounts of information, making them difficult to discern. In contrast, the envelope and interface method results in a reduction in both the amount and complexity of information necessary for design integration while yielding significant savings in time and effort when applied to today's complex design integration projects. This approach, combining classical and modern methods, proved advantageous during the complex design integration activities of the Ares I vehicle. Downstream processes, benefiting from this approach by reducing development and design cycle time, include: Creation of analysis models for the Aerodynamic discipline; Vehicle to ground interface development; Documentation development for the vehicle assembly.

Human factors engineering verification and validation for APR1400 computerized control room

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

Shin, Y. C.; Moon, H. K.; Kim, J. H.

2006-07-01

This paper introduces the Advanced Power Reactor 1400 (APR1400) HFE V and V activities the Korea Hydro Nuclear Plant Co. LTD. (KHNP) has performed for the last 10 years and some of the lessons learned through these activities. The features of APR1400 main control room include large display panel, redundant compact workstations, computer-based procedure, and safety console. Several iterations of human factors evaluations have been performed from small scale proof of concept tests to large scale integrated system tests for identifying human engineering deficiencies in the human system interface design. Evaluations in the proof of concept test were focused onmore » checking the presence of any show stopper problems in the design concept. Later evaluations were mostly for finding design problems and for assuring the resolution of human factors issues of advanced control room. The results of design evaluations were useful not only for refining the control room design, but also for licensing the standard design. Several versions of APR1400 mock-ups with dynamic simulation models of currently operating Korea Standard Nuclear Plant (KSNP) have been used for the evaluations with the participation of operators from KSNP plants. (authors)« less

Autonomous sensor-based dual-arm satellite grappling

NASA Technical Reports Server (NTRS)

Wilcox, Brian; Tso, Kam; Litwin, Todd; Hayati, Samad; Bon, Bruce

1989-01-01

Dual-arm satellite grappling involves the integration of technologies developed in the Sensing and Perception (S&P) Subsystem for object acquisition and tracking, and the Manipulator Control and Mechanization (MCM) Subsystem for dual-arm control. S&P acquires and tracks the position, orientation, velocity, and angular velocity of a slowly spinning satellite, and sends tracking data to the MCM subsystem. MCM grapples the satellite and brings it to rest, controlling the arms so that no excessive forces or torques are exerted on the satellite or arms. A 350-pound satellite mockup which can spin freely on a gimbal for several minutes, closely simulating the dynamics of a real satellite is demonstrated. The satellite mockup is fitted with a panel under which may be mounted various elements such as line replacement modules and electrical connectors that will be used to demonstrate servicing tasks once the satellite is docked. The subsystems are housed in three MicroVAX II microcomputers. The hardware of the S&P Subsystem includes CCD cameras, video digitizers, frame buffers, IMFEX (a custom pipelined video processor), a time-code generator with millisecond precision, and a MicroVAX II computer. Its software is written in Pascal and is based on a locally written vision software library. The hardware of the MCM Subsystem includes PUMA 560 robot arms, Lord force/torque sensors, two MicroVAX II computers, and unimation pneumatic parallel grippers. Its software is written in C, and is based on a robot language called RCCL. The two subsystems are described and test results on the grappling of the satellite mockup with rotational rates of up to 2 rpm are provided.

4. TOPSIDE VIEW FROM UPPER DECK LOOKING DOWN INTO TANK ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

4. TOPSIDE VIEW FROM UPPER DECK LOOKING DOWN INTO TANK WITH SHUTTLE CARGO BAY MOCK-UP AT BOTTOM OF 40 FOOT TANK. - Marshall Space Flight Center, Neutral Buoyancy Simulator Facility, Rideout Road, Huntsville, Madison County, AL

5. TOPSIDE VIEW FROM UPPER DECK LOOKING DOWN INTO TANK ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

5. TOPSIDE VIEW FROM UPPER DECK LOOKING DOWN INTO TANK WITH SHUTTLE CARGO BAY MOCK-UP AT BOTTOM OF 40 FOOT TANK. - Marshall Space Flight Center, Neutral Buoyancy Simulator Facility, Rideout Road, Huntsville, Madison County, AL

SRB Safety Analysis

NASA Image and Video Library

2003-09-11

Jeff Thon, an SRB mechanic with United Space Alliance, is lowered into a mockup of a segment of a solid rocket booster. He is testing a technique for vertical SRB propellant grain inspection. The inspection of segments is required as part of safety analysis.

Automated Non-Destructive Testing Array Evaluation System

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

Wei, T; Zavaljevski, N; Bakhtiari, S

2004-12-24

Automated Non-Destructive Testing Array Evaluation System (ANTARES) sofeware alogrithms were developed for use on X-probe(tm) data. Data used for algorithm development and preliminary perfomance determination was obtained for USNRC mock-up at Argone and data from EPRI.

Microgravity

NASA Image and Video Library

1998-01-01

Engineering mockup shows the general arrangement of the plarned Biotechnology Facility inside an EXPRESS rack aboard the International Space Station. This layout includes a gas supply module (bottom left), control computer and laptop interface (bottom right), two rotating wall vessels (top right), and support systems.

STS-133 crew members Drew, Kopra and Stott during EVA Tile Repair.

NASA Image and Video Library

2010-03-30

JSC2010-E-044337 (30 March 2010) --- NASA astronaut Tim Kopra, STS-133 mission specialist, participates in an EVA tile repair training session in the Space Vehicle Mockup Facility at NASA's Johnson Space Center.

Astronauts Allen and Gemar during Extravehicular activity training in CCT

NASA Image and Video Library

1993-10-13

Astronauts Charles D. (Sam) Gemar, and Andrew M. Allen participate in a training exercise at JSC's Crew Compartment Trainer (CCT), located in the Shuttle mockup and integration laboratory. Gemar sits inside the airlock as Allen reviews procedures for EVA.

Commerical Crew Astronauts Evaluate Crew Dragon Controls

NASA Image and Video Library

2017-01-10

Astronauts Eric Boe, right, and Bob Behnken work in a mock-up of the SpaceX Crew Dragon flight deck at the company's Hawthorne, California, headquarters as development of the crew systems continues for eventual missions to the International Space Station.

Commerical Crew Astronauts Evaluate Crew Dragon Controls

NASA Image and Video Library

2017-01-10

Astronauts Bob Behnken, left, and Eric Boe work in a mock-up of the SpaceX Crew Dragon flight deck at the company's Hawthorne, California, headquarters as development of the crew systems continues for eventual missions to the International Space Station.

User documentation for the MSK and OMS intelligent tutoring systems

NASA Technical Reports Server (NTRS)

Fink, Pamela K.; Herren, L. Tandy; Lincoln, David T.

1991-01-01

This user's guide describes how to use the Intelligent Tutoring Systems for the Manual Select Keyboard (MSK) and the Orbital Maneuvering System (OMS) and how to use the C code that runs the mockup version of the MSK.

Astronauts Allen and Gemar during extravehicular activity (EVA) training in CCT

NASA Technical Reports Server (NTRS)

1994-01-01

Astronauts Charles D. (Sam) Gemar, and Andrew M. Allen participate in a training exercise at JSC's Crew Compartment Trainer (CCT), located in the Space Vehicle Mockup Facility. Gemar sits inside the airlock as Allen reviews procedures for EVA.

Crossing Signals

ERIC Educational Resources Information Center

Goldberger, Paul

1976-01-01

The Firemen's Training Center, New York City, consists of an administrative and teaching building built of corrugated metal and glass, with brightly colored interior spaces, and the actual training buildings, mock-ups of real buildings designed to "burn down" again and again in training sessions. (Author/MLF)

Astronaut Kenneth Reightler, STS-60 pilot, during egress training

NASA Image and Video Library

1993-12-10

Astronaut Kenneth S. Reightler, pilot for the STS-60 mission, prepares to simulate egress from a troubled Space Shuttle using Crew Escape System (CES) pole. The action came during emergency egress training in JSC's Shuttle mockup and integration laboratory.

Expedition One crew in Russian with Service Module

NASA Image and Video Library

2000-07-14

JSC2000-E-18632 (June 2000) --- An interior shot of the Zarya Functional Cargo Bay (FGB) trainer/mockup at the Gagarin Cosmonaut Training Center in Russia. This photo was taken prior to a training session by the Expedition One crew.

JAXA astronaut and Expedition 28 crew member Satoshi Furukawa

NASA Image and Video Library

2010-09-17

PHOTO DATE: 09-17-10 LOCATION: Bldg. 9NW - ISS Mockups SUBJECT: JAXA astronaut and Expedition 28 crew member Satoshi Furukawa during P HRF Integ Cardio Integration Ops training WORK ORDER: 02810-BS__HRFSATOSHI_09-17-10 PHOTOGRAPHER: BILL STAFFORD

Asteroid Redirect Crewed Mission Space Suit and EVA System Maturation

NASA Technical Reports Server (NTRS)

Bowie, Jonathan T.; Kelly, Cody; Buffington, Jesse; Watson, Richard D.

2015-01-01

The Asteroid Redirect Crewed Mission (ARCM) requires a Launch/Entry/Abort (LEA) suit capability and short duration Extra Vehicular Activity (EVA) capability from the Orion spacecraft. For this mission, the pressure garment that was selected, for both functions, is the Modified Advanced Crew Escape Suit (MACES) with EVA enhancements and the life support option that was selected is the Exploration Portable Life Support System (PLSS). The proposed architecture was found to meet the mission constraints, but much more work is required to determine the details of the required suit upgrades, the integration with the PLSS, and the rest of the tools and equipment required to accomplish the mission. This work has continued over the last year to better define the operations and hardware maturation of these systems. EVA simulations have been completed in the NBL and interfacing options have been prototyped and analyzed with testing planned for late 2014. For NBL EVA simulations, in 2013, components were procured to allow in-house build up for four new suits with mobility enhancements built into the arms. Boots outfitted with clips that fit into foot restraints have also been added to the suit and analyzed for possible loads. Major suit objectives accomplished this year in testing include: evaluation of mobility enhancements, ingress/egress of foot restraint, use of foot restraint for worksite stability, ingress/egress of Orion hatch with PLSS mockup, and testing with two crew members in the water at one time to evaluate the crew's ability to help one another. Major tool objectives accomplished this year include using various other methods for worksite stability, testing new methods for asteroid geologic sampling and improving the fidelity of the mockups and crew equipment. These tests were completed on a medium fidelity capsule mockup, asteroid vehicle mockup, and asteroid mockups that were more accurate for an asteroid type EVA than previous tests. Another focus was the design and fabrication of the interface between the MACES and the PLSS. The MACES was not designed to interface with a PLSS, hence an interface kit must accommodate the unique design qualities of the MACES and provide the necessary life support function connections to the PLSS. A prototype interface kit for MACES to PLSS has been designed and fabricated. Unmanned and manned testing of the interface will show the usability of the kit while wearing a MACES. The testing shows viability of the kit approach as well as the operations concept. The design will be vetted through suit and PLSS experts and, with the findings from the testing, the best path forward will be determined. As the Asteroid Redirect Mission matures, the suit/life support portion of the mission will mature along with it and EVA Tools & Equipment can be iterated to accommodate the overall mission objectives and compromises inherent in EVA Suit optimization. The goal of the EVA architecture for ARCM is to continue to build on the previously developed technologies and lessons learned, and accomplish the ARCM EVAs while providing a stepping stone to future missions and destinations.

National Boy Scout Jamboree

NASA Technical Reports Server (NTRS)

1989-01-01

This video looks at a NASA sponsored exhibit at the National Boy Scout Jamboree in Fredricksburg, VA. Boy Scouts are shown interacting with NASA researchers and astronauts and touring mockups of Space Station Freedom and Apollo 11. NASA's program to encourage the researchers of tomorrow is detailed.

Expedition One crew in Russian with Service Module

NASA Image and Video Library

2000-07-14

JSC2000-E-18630 (June 2000) --- A wide shot of the Zvezda Service Module trainer/mockup, with the transfer compartment in the foreground, displays the site of a great deal of training activity by astronauts and cosmonauts in training for ISS expeditions.

Air Tight: Building Inflatables/Inflatable Construction: Planning and Details

NASA Technical Reports Server (NTRS)

Kennedy, Kriss J.

2016-01-01

A design-build seminar consisting of students from Physics, Mechanical and Civil Engineering, Robotic, Material Science, Art, and Architecture who will work together on a deployable "closed-loop" inflatable greenhouse for Mars in theory, and an Earth analogue physical mockup on campus.

Astronaut Anna Fisher practices control of the RMS in a trainer

NASA Technical Reports Server (NTRS)

1984-01-01

Astronaut Anna Lee Fisher, mission specialist for 51-A, practices control of the remote manipulator system (RMS) at a special trainer at JSC. Dr. Fisher is pictured in the manipulator development facility (MDF) of JSC's Shuttle mockup and integration laboratory.

STS-122 Preflight Egress Training

NASA Image and Video Library

2007-05-01

JSC2007-E-21208 (1 May 2007) --- Attired in a training version of his shuttle launch and entry suit, astronaut Stanley G. Love, STS-122 mission specialist, awaits the start of an emergency egress training session in the Space Vehicle Mockup Facility at Johnson Space Center.

Dr. Wernher Von Braun

NASA Technical Reports Server (NTRS)

1999-01-01

Shown viewing the Apollo telescope mockup are, from left to right, Charles Donlan, deputy associate administrator for manned space flight; Dr. Wernher Von Braun, Marshall Space Flight Center director; William Horton, astrionics lab; Dr. Thomas Paine, NASA deputy administrator; Warner Kuers, director of the ME lab.

STS-133 crew during SSMTF ISS EVA P/P training

NASA Image and Video Library

2010-03-29

JSC2010-E-044343 (29 March 2010) --- NASA astronaut Alvin Drew, STS-133 mission specialist, participates in a training session in an International Space Station mock-up/trainer in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center.

Biotechnology Facility (BTF) for ISS

NASA Technical Reports Server (NTRS)

1998-01-01

Engineering mockup shows the general arrangement of the plarned Biotechnology Facility inside an EXPRESS rack aboard the International Space Station. This layout includes a gas supply module (bottom left), control computer and laptop interface (bottom right), two rotating wall vessels (top right), and support systems.

Technicians assist STS-41 Pilot Cabana his parachute prior to egress training

NASA Technical Reports Server (NTRS)

1990-01-01

Technicians (training personnel) assist STS-41 Discovery, Orbiter Vehicle (OV) 103, Pilot Robert D. Cabana with his launch and entry suit (LES) parachute prior to emergency egress training exercises in JSC's Mockup and Integration Laboratory (MAIL) Bldg 9A.

STS-134 crew members Mike Fincke, Drew Feustel and Greg Chamitoff performing EVA Tile Repair Training.

NASA Image and Video Library

2010-01-28

JSC2010-E-014767 (28 Jan. 2010) --- NASA astronaut Michael Fincke, STS-134 mission specialist, participates in an EVA tile repair training session in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center.

Development and application of W/Cu flat-type plasma facing components at ASIPP

NASA Astrophysics Data System (ADS)

Li, Q.; Zhao, S. X.; Sun, Z. X.; Xu, Y.; Li, B.; Wei, R.; Wang, W. J.; Qin, S. G.; Shi, Y. L.; Xie, C. Y.; Wang, J. C.; Wang, X. L.; Missirlian, M.; Guilhem, D.; Liu, G. H.; Yang, Z. S.; Luo, G.-N.

2017-12-01

W/Cu flat-type plasma facing components (PFCs) were widely used in divertor of fusion device because of its advantages, such as low cost, light in weight and good machinability. However, it is very difficult to manufacture them due to the large mismatch between the thermo-mechanical properties of W and Cu. Institute of Plasma Physics, Chinese Academy of Sciences (ASIPP) has successfully developed W/Cu flat-type PFCs for EAST W/Cu divertor project by hot isostatic pressing (HIP) technology. This paper presents the development and application of W/Cu flat-type PFCs at ASIPP. The optimized manufacturing process is to cast pure copper onto the rear side of W tiles at temperature of 1200 °C firstly, and then to HIP the W/Cu tiles onto CuCrZr heat sink at temperature of 600 °C, pressure of 150 MPa and duration of 3 h. W/Cu flat-type testing mock-up for EAST survived 1000 cycles at heat load of 5 MW m-2 in high heat flux tests. And then ASIPP prepared two mock-ups for CEA’s tungsten environment in steady-state tokamak (WEST) project. One mock-up withstood successfully 302 cycles of 20 MW m-2, which are far beyond the design requirement. Since 2014, W/Cu flat-type PFCs were wildly used in EAST upper divertor as baffle and dome components which showed excellent performance in 2015 and 2016 campaigns. Given the success in EAST upper divertor, W/Cu flat-type concept is as well applied in the design of actively cooled Langmuir probes which will be mounted onto EAST divertor targets soon.

Key achievements in elementary R&D on water-cooled solid breeder blanket for ITER test blanket module in JAERI

NASA Astrophysics Data System (ADS)

Suzuki, S.; Enoeda, M.; Hatano, T.; Hirose, T.; Hayashi, K.; Tanigawa, H.; Ochiai, K.; Nishitani, T.; Tobita, K.; Akiba, M.

2006-02-01

This paper presents the significant progress made in the research and development (R&D) of key technologies on the water-cooled solid breeder blanket for the ITER test blanket modules in JAERI. Development of module fabrication technology, bonding technology of armours, measurement of thermo-mechanical properties of pebble beds, neutronics studies on a blanket module mockup and tritium release behaviour from a Li2TiO3 pebble bed under neutron-pulsed operation conditions are summarized. With the improvement of the heat treatment process for blanket module fabrication, a fine-grained microstructure of F82H can be obtained by homogenizing it at 1150 °C followed by normalizing it at 930 °C after the hot isostatic pressing process. Moreover, a promising bonding process for a tungsten armour and an F82H structural material was developed using a solid-state bonding method based on uniaxial hot compression without any artificial compliant layer. As a result of high heat flux tests of F82H first wall mockups, it has been confirmed that a fatigue lifetime correlation, which was developed for the ITER divertor, can be made applicable for the F82H first wall mockup. As for R&D on the breeder material, Li2TiO3, the effect of compression loads on effective thermal conductivity of pebble beds has been clarified for the Li2TiO3 pebble bed. The tritium breeding ratio of a simulated multi-layer blanket structure has successfully been measured using 14 MeV neutrons with an accuracy of 10%. The tritium release rate from the Li2TiO3 pebble has also been successfully measured with pulsed neutron irradiation, which simulates ITER operation.

Method Development for Binding Media Analysis in Painting Cross-Sections by Desorption Electrospray Ionization-Mass Spectrometry (DESI-MS).

PubMed

Watts, Kristen; Lagalante, Anthony

2018-06-06

Art conservation science is in need of a relatively nondestructive way of rapidly identifying the binding media within a painting cross-section and isolating binding media to specific layers within the cross-section. Knowledge of the stratigraphy of cross-sections can be helpful for removing possible unoriginal paint layers on the artistic work. Desorption electrospray ionization-mass spectrometry (DESI-MS) was used in ambient mode to study cross-sections from mock-up layered paint samples and samples from a 17th century baroque painting. The DESI spray was raster scanned perpendicular to the cross-section layers to maximize lateral resolution then analyzed with a triple quadrupole mass analyzer in linear ion trap mode. From these scans, isobaric mass maps were created to map the locations of masses indicative of particular binding media onto the cross-sections. Line paint-outs of pigments in different binding media showed specific and unique ions to distinguish between the modern acrylic media and the lipid containing binding media. This included: OP (EO) 9 surfactant in positive ESI for acrylic (m/z 621), and oleic (m/z 281), stearic (m/z 283), and azelaic (m/z 187) acids in negative ESI for oil and egg tempera. DESI-MS maps of mock-up cross-sections of layered pigmented binding media showed correlation between these ions and the layers with a spatial resolution of 100 μm. DESI-MS is effective in monitoring binding media within an intact painting cross-section via mass spectrometric methods. This includes distinguishing between lipid-containing and modern binding materials present in a known mockup cross section matrix as well as identifying lipid binding media in a 17th century baroque era painting. This article is protected by copyright. All rights reserved.

Initial results from a multiple monoenergetic gamma radiography system for nuclear security

NASA Astrophysics Data System (ADS)

O'Day, Buckley E.; Hartwig, Zachary S.; Lanza, Richard C.; Danagoulian, Areg

2016-10-01

The detection of assembled nuclear devices and concealed special nuclear materials (SNM) such as plutonium or uranium in commercial cargo traffic is a major challenge in mitigating the threat of nuclear terrorism. Currently available radiographic and active interrogation systems use ∼1-10 MeV bremsstrahlung photon beams. Although simple to build and operate, bremsstrahlung-based systems deliver high radiation doses to the cargo and to potential stowaways. To eliminate problematic issues of high dose, we are developing a novel technique known as multiple monoenergetic gamma radiography (MMGR). MMGR uses ion-induced nuclear reactions to produce two monoenergetic gammas for dual-energy radiography. This allows us to image the areal density and effective atomic number (Zeff) of scanned cargo. We present initial results from the proof-of-concept experiment, which was conducted at the MIT Bates Research and Engineering Center. The purpose of the experiment was to assess the capabilities of MMGR to measure areal density and Zeff of container cargo mockups. The experiment used a 3.0 MeV radiofrequency quadrupole accelerator to create sources of 4.44 MeV and 15.11 MeV gammas from the 11B(d,nγ)12C reaction in a thick natural boron target; the gammas are detected by an array of NaI(Tl) detectors after transmission through cargo mockups . The measured fluxes of transmitted 4.44 MeV and 15.11 MeV gammas were used to assess the areal density and Zeff. Initial results show that MMGR is capable of discriminating the presence of high-Z materials concealed in up to 30 cm of iron shielding from low- and mid-Z materials present in the cargo mockup.

Astronaut Tamara Jernigan in the CCT during a training session

NASA Technical Reports Server (NTRS)

1994-01-01

Astronaut Tamara E. Jernigan, STS-67 payload commander, is shown here in the Shuttle Training Facility at JSC participating in a training session. Jernigan is training with the RMS controls in the Crew Compartment Trainer (CCT) of JSC's Shuttle mockup and integration laboratory.

Astronaut Wendy Lawrence participates in training session in the CCT

NASA Technical Reports Server (NTRS)

1994-01-01

Seated in the pilot's seat of a JSC Shuttle trainer, astronaut Wendy B. Lawrence, STS-67 flight engineer, participates in a training session. The 1992 astronaut class graduate is in the crew compartment trainer (CCT) of JSC's Shuttle mockup and integration laboratory.

Expedition 29/30 crew training during Electrical Power System Major Case training

NASA Image and Video Library

2011-06-22

PHOTO DATE: 22 June 2011 LOCATION: Bldg. 5, Space Station Training Facility. SUBJECT: Expedition 29/30 crew training during Electrical Power System Major Case training event. Astronauts Dan Burbank, Don Pettit and Andre Kuipers working together in mockup. PHOTOGRAPHER: Mark Sowa

Expedition 15 Crew Members training in the Virtual Reality (VR) Laboratory

NASA Image and Video Library

2006-09-25

JSC2006-E-41640 (25 Sept. 2006) --- Cosmonaut Fyodor N. Yurchikhin, Expedition 15 commander representing Russia's Federal Space Agency, participates in a camera review training session in the virtual reality lab in the Space Vehicle Mockup Facility at Johnson Space Center.

Expedition 15 Crew Members training in the Virtual Reality (VR) Laboratory

NASA Image and Video Library

2006-09-25

JSC2006-E-41641 (25 Sept. 2006) --- Cosmonaut Oleg V. Kotov, Expedition 15 flight engineer representing Russia's Federal Space Agency, participates in a camera review training session in the virtual reality lab in the Space Vehicle Mockup Facility at Johnson Space Center.

A Study of Authoring Alternatives for Training-Oriented Videodiscs.

ERIC Educational Resources Information Center

Bunderson, C. Victor; And Others

This study examined eight areas that are related to the problems of authoring and producing training-oriented videodiscs: the delivery system itself; media selection during instructional systems development; instructional strategies; author mock-up and simulation prior to premastering; premastering; mastering and replication; composition of…

Tour by Saudi prince Salman Abdelazize Al-Saud prior to mission

NASA Image and Video Library

1985-04-04

S85-29788 (May 1985) --- Sultan Salman Abdelazize Al-Saud and Abdulmohsen Hamad Al-Bassam man the controls on the flight deck of the crew compartment trainer (CCT) in the Shuttle mockup and integration laboratory at the Johnson Space Center (JSC).

NASA and Me

NASA Technical Reports Server (NTRS)

Wong, Douglas T.

2010-01-01

Topics in this student project report include: biography, NASA history and structure, overview of Johnson Space Center facilities and major projects, and an overview of the Usability Testing and Analysis Facility (UTAF). The UTAF section slides include space habitat evaluations with mockups, crew space vehicle evaluations, and human factors research.

Astronaut Story Musgrave in launch/landing suit during STS-33 training

NASA Image and Video Library

1989-10-20

S89-48009 (29 Oct. 1996) --- About to embark on his sixth shuttle flight, astronaut Story Musgrave receives assistance with his launch and entry suit during a training session in the Johnson Space Center's (JSC) Shuttle Mockup and Integration Laboratory (SMIL).

KSC-2012-5894

NASA Image and Video Library

2012-10-19

CAPE CANAVERAL, Fla. – An Orion mockup spacecraft atop its service module simulator is lowered onto a transporter in the transfer aisle of the Vehicle Assembly Building, or VAB, at NASA's Kennedy Space Center in Florida. The Orion mockup is exact in details on the outside, but mostly empty on the inside. The work in the VAB is crucial to making sure the designs are accurate. Visible in the background on the left is the space shuttle Atlantis being readied for its move to the Kennedy Space Center Visitor Complex. 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. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on a Space Launch System rocket. For more information, visit http://www.nasa.gov/orion Photo credit: NASA/ Dmitri Gerondidakis

KSC-2012-5892

NASA Image and Video Library

2012-10-19

CAPE CANAVERAL, Fla. – An Orion mockup spacecraft atop its service module simulator is lifted in the transfer aisle of the Vehicle Assembly Building, or VAB, at NASA's Kennedy Space Center in Florida. The Orion mockup is exact in details on the outside, but mostly empty on the inside. The work in the VAB is crucial to making sure the designs are accurate. Visible in the background on the left is the space shuttle Atlantis being readied for its move to the Kennedy Space Center Visitor Complex. 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. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on a Space Launch System rocket. For more information, visit http://www.nasa.gov/orion Photo credit: NASA/ Dmitri Gerondidakis

KSC-2012-5895

NASA Image and Video Library

2012-10-19

CAPE CANAVERAL, Fla. – An Orion mockup spacecraft atop its service module simulator is lowered onto a transporter in the transfer aisle of the Vehicle Assembly Building, or VAB, at NASA's Kennedy Space Center in Florida. The Orion mockup is exact in details on the outside, but mostly empty on the inside. The work in the VAB is crucial to making sure the designs are accurate. Visible in the background on the left is the space shuttle Atlantis being readied for its move to the Kennedy Space Center Visitor Complex. 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. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on a Space Launch System rocket. For more information, visit http://www.nasa.gov/orion Photo credit: NASA/ Dmitri Gerondidakis

The physics of sub-critical lattices in accelerator driven hybrid systems: The MUSE experiments in the MASURCA facility

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

Chauvin, J. P.; Lebrat, J. F.; Soule, R.

Since 1991, the CEA has studied the physics of hybrid systems, involving a sub-critical reactor coupled with an accelerator. These studies have provided information on the potential of hybrid systems to transmute actinides and, long lived fission products. The potential of such a system remains to be proven, specifically in terms of the physical understanding of the different phenomena involved and their modelling, as well as in terms of experimental validation of coupled systems, sub-critical environment/accelerator. This validation must be achieved through mock-up studies of the sub-critical environments coupled to a source of external neutrons. The MUSE-4 mock-up experiment ismore » planed at the MASURCA facility and will use an accelerator coupled to a tritium target. The great step between the generator used in the past and the accelerator will allow to increase the knowledge in hybrid physic and to decrease the experimental biases and the measurement uncertainties.« less

KENNEDY SPACE CENTER, FLA. - During a media tour of the Columbia Debris Hangar, photographers pause at the mockup of the leading edge of Columbia’s left wing. About 83,000 pieces of debris from Columbia were shipped to KSC from search and recovery efforts in East Texas. About 83,000 pieces of debris were shipped to KSC, which represents about 38 percent of the dry weight of Columbia, equaling almost 85,000 pounds. The debris is being packaged for storage in an area of the Vehicle Assembly Building.

NASA Image and Video Library

2003-09-11

KENNEDY SPACE CENTER, FLA. - During a media tour of the Columbia Debris Hangar, photographers pause at the mockup of the leading edge of Columbia’s left wing. About 83,000 pieces of debris from Columbia were shipped to KSC from search and recovery efforts in East Texas. About 83,000 pieces of debris were shipped to KSC, which represents about 38 percent of the dry weight of Columbia, equaling almost 85,000 pounds. The debris is being packaged for storage in an area of the Vehicle Assembly Building.

Unsteady heat dissipation in accelerator superconducting coils insulated with porous ceramic insulation in normal and supercritical helium conditions

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

Pietrowicz, S.; Four, A.; Baudouy, B.

To investigate the unsteady heat dissipation in accelerator superconducting coils insulated with porous ceramic insulation, two experimental mock-ups reproducing the thermal and the mechanical conditions of a superconducting coils were produced. The mock-ups with compressive load of 10 MPa and 20 MPa were tested at normal (T = 4.23 K and p = 1 bar) and supercritical helium conditions (T = 4.23 K and p = 2.0 to 3.75 bar) during unsteady heat dissipation. The paper presents the experimental results of temperature rise in both superconducting coils as a function of time for a wide range of a localized heatmore » load varying from 0.1 kJ/m{sup 3} up to 12.8 MJ m{sup −3} per pulse. A numerical model of the transient process in these coils has been developed and the computations are compared with the experimental results.« less

EC00-0198-2

NASA Image and Video Library

2000-06-22

Aerospace industry representatives view actual and mock-up versions of 'X-Planes' intended to enhance access to space during a technical exposition on June 22, 2000 at Dryden Flight Research Center, Edwards, California. From left to right: NASA's B-52 launch aircraft, in service with NASA from 1959 to 2004; a neutral-buoyancy model of the Boeing's X-37; the Boeing X-40A behind the MicroCraft X-43 mock-up; Orbital Science's X-34 and the modified Lockheed L-1011 airliner that was intended to launch the X-34. These X-vehicles are part of NASA's Access to Space plan intended to bring new technologies to bear in an effort to dramatically lower the cost of putting payloads in space, and near-space environments. The June 22, 2000 NASA Reusable Launch Vehicle (RLV) Technology Exposition included presentations on the history, present, and future of NASA's RLV program. Special Sessions for industry representatives highlighted the X-37 project and its related technologies. The X-37 project is managed by NASA's Marshall Space Flight Center, Huntsville, Alabama.

EC00-0198-102

NASA Image and Video Library

2000-06-22

Aerospace industry representatives view actual and mock-up versions of 'X-Planes' intended to enhance access to space during a technical exposition on June 22, 2000 at Dryden Flight Research Center, Edwards, California. From left to right: NASA's B-52 launch aircraft, in service with NASA since 1959; a neutral-buoyancy model of the Boeing's X-37; the Boeing X-40A behind the MicroCraft X-43 mock-up; Orbital Science's X-34 and the modified Lockheed L-1011 airliner that was intended to launch the X-34. These X-vehicles are part of NASA's Access to Space plan intended to bring new technologies to bear in an effort to dramatically lower the cost of putting payloads in space, and near-space environments. The June 22, 2000 NASA Reusable Launch Vehicle (RLV) Technology Exposition included presentations on the history, present, and future of NASA's RLV program. Special Sessions for industry representatives highlighted the X-37 project and its related technologies. The X-37 project is managed by NASA's Marshall Space Flight Center, Huntsville, Alabama.

EC00-0198-1

NASA Image and Video Library

2000-06-22

Aerospace industry representatives view actual and mock-up versions of 'X-Planes' intended to enhance access to space during a technical exposition on June 22, 2000 at Dryden Flight Research Center, Edwards, California. From left to right: NASA's B-52 launch aircraft, in service with NASA from 1959 to 2004; a neutral-buoyancy model of the Boeing's X-37; the Boeing X-40A behind the MicroCraft X-43 mock-up; Orbital Science's X-34 and the modified Lockheed L-1011 airliner that was intended to launch the X-34. These X-vehicles are part of NASA's Access to Space plan intended to bring new technologies to bear in an effort to dramatically lower the cost of putting payloads in space, and near-space environments. The June 22, 2000 NASA Reusable Launch Vehicle (RLV) Technology Exposition included presentations on the history, present, and future of NASA's RLV program. Special Sessions for industry representatives highlighted the X-37 project and its related technologies. The X-37 project is managed by NASA's Marshall Space Flight Center, Huntsville, Alabama.

EC00-0198-85

NASA Image and Video Library

2000-06-22

Aerospace industry representatives view actual and mock-up versions of 'X-Planes' intended to enhance access to space during a technical exposition on June 22, 2000 at Dryden Flight Research Center, Edwards, California. From left to right: NASA's B-52 launch aircraft, in service with NASA since 1959; a neutral-buoyancy model of the Boeing's X-37; the Boeing X-40A behind the MicroCraft X-43 mock-up; Orbital Science's X-34 and the modified Lockheed L-1011 airliner that was intended to launch the X-34. These X-vehicles are part of NASA's Access to Space plan intended to bring new technologies to bear in an effort to dramatically lower the cost of putting payloads in space, and near-space environments. The June 22, 2000 NASA Reusable Launch Vehicle (RLV) Technology Exposition included presentations on the history, present, and future of NASA's RLV program. Special Sessions for industry representatives highlighted the X-37 project and its related technologies. The X-37 project is managed by NASA's Marshall Space Flight Center, Huntsville, Alabama.

Space station ventilation study

NASA Technical Reports Server (NTRS)

Colombo, G. V.; Allen, G. E.

1972-01-01

A ventilation system design and selection method which is applicable to any manned vehicle were developed. The method was used to generate design options for the NASA 33-foot diameter space station, all of which meet the ventilation system design requirements. System characteristics such as weight, volume, and power were normalized to dollar costs for each option. Total system costs for the various options ranged from a worst case $8 million to a group of four which were all approximately $2 million. A system design was then chosen from the $2 million group and is presented in detail. A ventilation system layout was designed for the MSFC space station mockup which provided comfortable, efficient ventilation of the mockup. A conditioned air distribution system design for the 14-foot diameter modular space station, using the same techniques, is also presented. The tradeoff study resulted in the selection of a system which costs $1.9 million, as compared to the alternate configuration which would have cost $2.6 million.

Space shuttle/food system study. Volume 2, Appendix G: Ground support system analysis. Appendix H: Galley functional details analysis

NASA Technical Reports Server (NTRS)

1974-01-01

The capabilities for preflight feeding of flight personnel and the supply and control of the space shuttle flight food system were investigated to determine ground support requirements; and the functional details of an onboard food system galley are shown in photographic mockups. The elements which were identified as necessary to the efficient accomplishment of ground support functions include the following: (1) administration; (2) dietetics; (3) analytical laboratories; (4) flight food warehouse; (5) stowage module assembly area; (6) launch site module storage area; (7) alert crew restaurant and disperse crew galleys; (8) ground food warehouse; (9) manufacturing facilities; (10) transport; and (11) computer support. Each element is discussed according to the design criteria of minimum cost, maximum flexibility, reliability, and efficiency consistent with space shuttle requirements. The galley mockup overview illustrates the initial operation configuration, food stowage locations, meal assembly and serving trays, meal preparation configuration, serving, trash management, and the logistics of handling and cleanup equipment.

Vector intensity reconstruction using the data completion method.

PubMed

Langrenne, Christophe; Garcia, Alexandre

2013-04-01

This paper presents an application of the data completion method (DCM) for vector intensity reconstructions. A mobile array of 36 pressure-pressure probes (72 microphones) is used to perform measurements near a planar surface. Nevertheless, since the proposed method is based on integral formulations, DCM can be applied with any kind of geometry. This method requires the knowledge of Cauchy data (pressure and velocity) on a part of the boundary of an empty domain in order to evaluate pressure and velocity on the remaining part of the boundary. Intensity vectors are calculated in the interior domain surrounded by the measurement array. This inverse acoustic problem requires the use of a regularization method to obtain a realistic solution. An experiment in a closed wooden car trunk mock-up excited by a shaker and two loudspeakers is presented. In this case, where the volume of the mock-up is small (0.61 m(3)), standing-waves and fluid structure interactions appear and show that DCM is a powerful tool to identify sources in a confined space.

Sub-domain methods for collaborative electromagnetic computations

NASA Astrophysics Data System (ADS)

Soudais, Paul; Barka, André

2006-06-01

In this article, we describe a sub-domain method for electromagnetic computations based on boundary element method. The benefits of the sub-domain method are that the computation can be split between several companies for collaborative studies; also the computation time can be reduced by one or more orders of magnitude especially in the context of parametric studies. The accuracy and efficiency of this technique is assessed by RCS computations on an aircraft air intake with duct and rotating engine mock-up called CHANNEL. Collaborative results, obtained by combining two sets of sub-domains computed by two companies, are compared with measurements on the CHANNEL mock-up. The comparisons are made for several angular positions of the engine to show the benefits of the method for parametric studies. We also discuss the accuracy of two formulations of the sub-domain connecting scheme using edge based or modal field expansion. To cite this article: P. Soudais, A. Barka, C. R. Physique 7 (2006).

Resent Status of ITER Equatorial Launcher Development

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

Takahashi, K.; Kajiwara, K.; Kasugai, A.

2009-11-26

The ITER equatorial launcher is divided into a front shield and a port plug. The front shield is composed of fourteen blanket shield modules so as to form three openings for the injection of mm-wave beams into plasma. Twenty-four waveguide transmission lines, internal shields, cooling pipes and so on are installed in the port plug. The transmission lines consist of the corrugated waveguides, miter bends and the free space propagation region utilizing two mirrors in front of the waveguide outlet. The analysis of mm-wave beam propagation in the region shows that the transmission efficiency more than 99.5% is attained. Themore » high power experiments of the launcher mock-up have been carried out and the measured field patterns at each mirror and the outlet of the launcher are agreed with the calculations. It is concluded that the transmission line components in the launcher mock-up are fabricated as designed and the present mm-wave design in the launcher is feasible.« less

Eleventh interim status report: Model 9975 O-Ring fixture long-term leak performance

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

Daugherty, W.

2016-08-01

A series of experiments to monitor the aging performance of Viton® GLT O-rings used in the Model 9975 package has been ongoing since 2004 at the Savannah River National Laboratory. One approach has been to periodically evaluate the leak performance of O-rings being aged in mock-up 9975 Primary Containment Vessels (PCVs) at elevated temperature. Other methods such as compression-stress relaxation (CSR) tests and field surveillance are also on-going to evaluate O-ring behavior. Seventy tests using PCV mock-ups were assembled and heated to temperatures ranging from 200 to 450 ºF. They were leak-tested initially and have been tested periodically to determinemore » if they continue to meet the leak-tightness criterion defined in ANSI standard N14.5-97. Due to material substitution, fourteen additional tests were initiated in 2008 with GLT-S O-rings heated to temperatures ranging from 200 to 400 ºF.« less

Tenth interim status report: Model 9975 O-ring fixture long-term leak performance

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

Daugherty, W. L.

2015-08-26

A series of experiments to monitor the aging performance of Viton ® GLT O-rings used in the Model 9975 package has been ongoing since 2004 at the Savannah River National Laboratory. One approach has been to periodically evaluate the leak performance of O-rings being aged in mock-up 9975 Primary Containment Vessels (PCVs) at elevated temperatures. Other methods such as compression-stress relaxation (CSR) tests and field surveillance are also on-going to evaluate O-ring behavior. Seventy tests using PCV mock-ups were assembled and heated to temperatures ranging from 200 to 450 °F. They were leak-tested initially and have been tested periodically tomore » determine if they continue to meet the leak-tightness criterion defined in ANSI standard N14.5-97. Due to material substitution, fourteen additional tests were initiated in 2008 with GLT-S O-rings heated to temperatures ranging from 200 to 400 °F.« less

Development of the low-field side reflectometer for ITER

NASA Astrophysics Data System (ADS)

Muscatello, Christopher; Anderson, James; Gattuso, Anthony; Doyle, Edward; Peebles, William; Seraydarian, Raymond; Wang, Guiding; Kramer, Gerrit; Zolfaghari, Ali; Atomics Team, General; University of California Los Angeles Team; Princeton Plasma Physics Laboratory Team

2017-10-01

The Low-Field Side Reflectometer (LFSR) for ITER will provide real-time edge density profiles every 10 ms for feedback control and every 24 μs for physics evaluation. The spatial resolution will be better than 5 mm over 30 - 165 GHz, probing the scrape-off layer to the top of the pedestal in H-mode plasmas. An antenna configuration has been selected for measurements covering anticipated plasma elevations. Laboratory validation of diagnostic performance is underway using a LFSR transmission line (TL) mockup. The 40-meter TL includes circular corrugated waveguide, length calibration feature, Gaussian telescope, vacuum windows, containment membranes, and expansion joint. Transceiver modules coupled to the input of the TL provide frequency-modulated (FM) data for evaluation of performance as a monostatic reflectometer. Results from the mockup tests are presented and show that, with some further optimization, the LFSR will meet or exceed the measurement requirements for ITER. An update of the LFSR instrumentation design status is also presented with preliminary test results. Work supported by PPPL under subcontract S013252-A.

Scale-up of the electrokinetic fence technology for the removal of pesticides. Part I: Some notes about the transport of inorganic species.

PubMed

López-Vizcaíno, R; Risco, C; Isidro, J; Rodrigo, S; Saez, C; Cañizares, P; Navarro, V; Rodrigo, M A

2017-01-01

This work describes the application electrokinetic fence technology to a soil polluted with herbicides in a large prototype containing 32 m 3 of soil. It compares performance in this large facility with results previously obtained in a pilot-scale mockup (175 L) and with results obtained in a lab-scale soil column (1 L), all of them operated under the same driving force: an electric field of 1.0 V cm -1 . Within this wide context, this work focuses on the effect on inorganic species contained in soil and describes the main processes occurring in the prototype facility, as well as the differences observed respect to the lower scale plants. Thus, despite the same processes can be described in the three plants, important differences are observed in the evolution of the current intensity, moisture and conductivity. They can be related to the less important electroosmotic fluxes in the larger facilities and to the very different distances between electrodes, which lead to very different distribution of species and even to a very different evolution of the resulting current intensity. 2-D maps of the main species at different relevant moments of the test are discussed and important information is drawn from them. Ions depletion from soil appears as a very important problem which should be prevented if the effect of natural bioremediation and/or phytoremediation on the removal or organics aims to be accounted. Copyright © 2016 Elsevier Ltd. All rights reserved.

Flexible thermochromic window based on hybridized VO2/graphene.

PubMed

Kim, Hyeongkeun; Kim, Yena; Kim, Keun Soo; Jeong, Hu Young; Jang, A-Rang; Han, Seung Ho; Yoon, Dae Ho; Suh, Kwang S; Shin, Hyeon Suk; Kim, TaeYoung; Yang, Woo Seok

2013-07-23

Large-scale integration of vanadium dioxide (VO2) on mechanically flexible substrates is critical to the realization of flexible smart window films that can respond to environmental temperatures to modulate light transmittance. Until now, the formation of highly crystalline and stoichiometric VO2 on flexible substrate has not been demonstrated due to the high-temperature condition for VO2 growth. Here, we demonstrate a VO2-based thermochromic film with unprecedented mechanical flexibility by employing graphene as a versatile platform for VO2. The graphene effectively functions as an atomically thin, flexible, yet robust support which enables the formation of stoichiometric VO2 crystals with temperature-driven phase transition characteristics. The graphene-supported VO2 was capable of being transferred to a plastic substrate, forming a new type of flexible thermochromic film. The flexible VO2 films were then integrated into the mock-up house, exhibiting its efficient operation to reduce the in-house temperature under infrared irradiation. These results provide important progress for the fabrication of flexible thermochromic films for energy-saving windows.

Examination of How and Why Over-the-Bed Tables Are Used: Use Cases and Needs from Healthcare Providers.

PubMed

Manganelli, Joe; Threatt, Anthony; Brooks, Johnell O; Healy, Stan; Merino, Jessica; Yanik, Paul; Walker, Ian; Green, Keith

2014-01-01

This article presents the results of an exploratory study in which 14 clinical and staff subject matter experts (SMEs) at a regional rehabilitation hospital were interviewed in order to understand how and why over-the-bed tables are used. It is important to understand how and why a device or environment is used when designing it, and not just what features and functions are preferred. This knowledge is valuable both for contextualizing user feature and function preferences and for characterizing and prioritizing design challenges and opportunities. Fourteen hospital clinical and support staff subject-matter experts participated in semi-structured interviews with scenario enactments in a medium-fidelity, full-scale mock-up of a typical patient room. During these interviews, they interacted with two personas played by actors and were asked to enact an example of a normal visit, from entering the room through treatment/service and then exiting. Data were analyzed via methodological triangulation including frequency analysis, content analysis, and affinity diagramming. The results include a use-case analysis with illustrative sketches, a list of needs statements, and final observations. Successfully using the over-the-bed table is dependent upon proper positioning, especially in bed during meals. There are fewer problems associated with over-the-bed table use while seated in a chair than when in the bed. The over-the-bed table is a key component in acute care, inpatient therapies. Clinicians are generally open to "smart" furniture in the patient room but question its cost-effectiveness, robustness, and flexibility. Evidence-based design, human factors, patient-centered care, quality care, technology.

MODULAR MANIPULATOR FOR ROBOTICS APPLICATIONS

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

Joseph W. Geisinger, Ph.D.

ARM Automation, Inc. is developing a framework of modular actuators that can address the DOE's wide range of robotics needs. The objective of this effort is to demonstrate the effectiveness of this technology by constructing a manipulator from these actuators within a glovebox for Automated Plutonium Processing (APP). At the end of the project, the system of actuators was used to construct several different manipulator configurations, which accommodate common glovebox tasks such as repackaging. The modular nature and quickconnects of this system simplify installation into ''hot'' boxes and any potential modifications or repair therein. This work focused on the developmentmore » of self-contained robotic actuator modules including the embedded electronic controls for the purpose of building a manipulator system. Both of the actuators developed under this project contain the control electronics, sensors, motor, gear train, wiring, system communications and mechanical interfaces of a complete robotics servo device. Test actuators and accompanying DISC{trademark}s underwent validation testing at The University of Texas at Austin and ARM Automation, Inc. following final design and fabrication. The system also included custom links, an umbilical cord, an open architecture PC-based system controller, and operational software that permitted integration into a completely functional robotic manipulator system. The open architecture on which this system is based avoids proprietary interfaces and communication protocols which only serve to limit the capabilities and flexibility of automation equipment. The system was integrated and tested in the contractor's facility for intended performance and operations. The manipulator was tested using the full-scale equipment and process mock-ups. The project produced a practical and operational system including a quantitative evaluation of its performance and cost.« less

Effects of transit bus interior configuration on performance of wheeled mobility users during simulated boarding and disembarking.

PubMed

D'Souza, Clive; Paquet, Victor; Lenker, James A; Steinfeld, Edward

2017-07-01

The emergence of low-floor bus designs and related regulatory standards in the U.S. have resulted in substantial improvements in public transit accessibility. However, passengers using wheeled mobility devices still experience safety concerns and inefficiencies in boarding, disembarking, and interior circulation on low-floor buses. This study investigates effects of low-floor bus interior configuration and passenger crowding on boarding and disembarking efficiency and safety. Users of manual wheelchairs (n = 18), powered wheelchairs (n = 21) and electric scooters (n = 9) simulated boarding and disembarking in three interior layout configurations at low and high passenger crowding conditions on a full-scale laboratory mock-up of a low-floor bus. Dependent measures comprised task times and critical incidents during access ramp use, fare payment, and movement to and from the doorway and wheeled mobility securement area. Individual times for unassisted boarding ranged from 15.2 to 245.3 s and for disembarking ranged from 9.1 to 164.6 s across layout and passenger crowding conditions. Nonparametric analysis of variance showed significant differences and interactions across vehicle design conditions, passenger load and mobility device type on user performance. The configuration having electronic on-board fare payment, rear-bus entrance doorways and adjacent device securement areas demonstrated greatest efficiency and safety. High passenger load adversely impacted efficiency and frequency of critical incidents during on-board circulation across all three layouts. Findings have broader implications for improving transit system efficiency and quality of service across the spectrum of transit users. Copyright © 2017 Elsevier Ltd. All rights reserved.

FLOW TESTING AND ANALYSIS OF THE FSP-1 EXPERIMENT

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

Hawkes, Grant L.; Jones, Warren F.; Marcum, Wade

The U.S. High Performance Research Reactor Conversions fuel development team is focused on developing and qualifying the uranium-molybdenum (U-Mo) alloy monolithic fuel to support conversion of domestic research reactors to low enriched uranium. Several previous irradiations have demonstrated the favorable behavior of the monolithic fuel. The Full Scale Plate 1 (FSP-1) fuel plate experiment will be irradiated in the northeast (NE) flux trap of the Advanced Test Reactor (ATR). This fueled experiment contains six aluminum-clad fuel plates consisting of monolithic U-Mo fuel meat. Flow testing experimentation and hydraulic analysis have been performed on the FSP-1 experiment to be irradiated inmore » the ATR at the Idaho National Laboratory (INL). A flow test experiment mockup of the FSP-1 experiment was completed at Oregon State University. Results of several flow test experiments are compared with analyses. This paper reports and shows hydraulic analyses are nearly identical to the flow test results. A water velocity of 14.0 meters per second is targeted between the fuel plates. Comparisons between FSP-1 measurements and this target will be discussed. This flow rate dominates the flow characteristics of the experiment and model. Separate branch flows have minimal effect on the overall experiment. A square flow orifice was placed to control the flowrate through the experiment. Four different orifices were tested. A flow versus delta P curve for each orifice is reported herein. Fuel plates with depleted uranium in the fuel meat zone were used in one of the flow tests. This test was performed to evaluate flow test vibration with actual fuel meat densities and reported herein. Fuel plate deformation tests were also performed and reported.« less

Ferrite Loaded Coils for Improved Wireless Power Transfer Efficiency

DTIC Science & Technology

2015-09-01

visible in yellow, from [4]. ..........................................................................................4  Figure 4.  The Odyssey AUV ...47  Figure 35.  System mockup of AUV in docking/charging station...42  xii THIS PAGE INTENTIONALLY LEFT BLANK xiii LIST OF ACRONYMS AND ABBREVIATIONS AUV Autonomous Underwater Vehicle CST

Destination Entry And Retrieval With The Ali-Scout Navigation System Fast-Trac Phase Iib Deliverable

DOT National Transportation Integrated Search

1996-12-01

AFTER TRAINING, 36 DRIVERS RETRIEVED AND ENTERED A TOTAL OF 20 DESTINATIONS USING AN ALI-SCOUT NAVIGATION COMPUTER AND 10 DESTINATIONS USING A TOUCHSCREEN SIMULATION WHILE SITTING IN A VEHICLE MOCKUP. RETRIEVAL INVOLVED KEYING IN PART OF THE DESTINAT...

Spend a Day in Outer Space

ERIC Educational Resources Information Center

Journal of Aerospace Education, 1975

1975-01-01

Describes the Alabama Space and Rocket Center in Huntsville, Alabama as stimulating experience for students in aerospace education. The center has the largest collection of space-age hardware assembled under one roof, a Space Flight simulator, a Skylab space station mock-up and many more interesting exhibits. (BR)

STS-9 payload specialist Merbold and backup Ockels in training session

NASA Technical Reports Server (NTRS)

1983-01-01

STS-9 payload specialist Ulf Merbold, right, a West German physicist and backup Wubbo Ockels, a Dutch scientist, are pictured in a training session in JSC's Shuttle mockup and integration laboratory. In this view Ockels appears to be showing Merbold how to operate a camera.

STS 41-D mission crew training in Shuttle Mission simulator

NASA Image and Video Library

1983-07-01

View of STS 41-D mission crew training in Shuttle Mission simulator. From left to right are Henry Hartsfield, Jr., commander; mission specialists Judith Resnik, Richard Mullane, and Steven Hawley; and Michael Coats, pilot. They appear to be standing in the middeck mockup, preparing for training.

jsc2013e073504

NASA Image and Video Library

2013-07-29

PHOTO DATE: 29 July 2013 LOCATION: Bldg. 9NW, Space Vehicle Mockup Training Facility - POGO SUBJECT: Expedition 42 crew member and astronaut Barry "Butch" Wilmore during ISS EVA POGO 1 training. Instructors Faruq Sabur (black shirt), Allissa Battocletti (red shirt), Sandy Fletcher (light blue shirt with glasses) and astronaut Shane Kimbrough assist. PHOTOGRAPHER: Mark Sowa

jsc2013e073507

NASA Image and Video Library

2013-07-29

PHOTO DATE: 29 July 2013 LOCATION: Bldg. 9NW, Space Vehicle Mockup Training Facility - POGO SUBJECT: Expedition 42 crew member and astronaut Barry "Butch" Wilmore during ISS EVA POGO 1 training. Instructors Faruq Sabur (black shirt), Allissa Battocletti (red shirt), Sandy Fletcher (light blue shirt with glasses) and astronaut Shane Kimbrough assist. PHOTOGRAPHER: Mark Sowa

jsc2013e073509

NASA Image and Video Library

2013-07-29

PHOTO DATE: 29 July 2013 LOCATION: Bldg. 9NW, Space Vehicle Mockup Training Facility - POGO SUBJECT: Expedition 42 crew member and astronaut Barry "Butch" Wilmore during ISS EVA POGO 1 training. Instructors Faruq Sabur (black shirt), Allissa Battocletti (red shirt), Sandy Fletcher (light blue shirt with glasses) and astronaut Shane Kimbrough assist. PHOTOGRAPHER: Mark Sowa

jsc2013e073510

NASA Image and Video Library

2013-07-29

PHOTO DATE: 29 July 2013 LOCATION: Bldg. 9NW, Space Vehicle Mockup Training Facility - POGO SUBJECT: Expedition 42 crew member and astronaut Barry "Butch" Wilmore during ISS EVA POGO 1 training. Instructors Faruq Sabur (black shirt), Allissa Battocletti (red shirt), Sandy Fletcher (light blue shirt with glasses) and astronaut Shane Kimbrough assist. PHOTOGRAPHER: Mark Sowa

jsc2013e073506

NASA Image and Video Library

2013-07-29

PHOTO DATE: 29 July 2013 LOCATION: Bldg. 9NW, Space Vehicle Mockup Training Facility - POGO SUBJECT: Expedition 42 crew member and astronaut Barry "Butch" Wilmore during ISS EVA POGO 1 training. Instructors Faruq Sabur (black shirt), Allissa Battocletti (red shirt), Sandy Fletcher (light blue shirt with glasses) and astronaut Shane Kimbrough assist. PHOTOGRAPHER: Mark Sowa

jsc2013e073495

NASA Image and Video Library

2013-07-29

PHOTO DATE: 29 July 2013 LOCATION: Bldg. 9NW, Space Vehicle Mockup Training Facility - POGO SUBJECT: Expedition 42 crew member and astronaut Barry "Butch" Wilmore during ISS EVA POGO 1 training. Instructors Faruq Sabur (black shirt), Allissa Battocletti (red shirt), Sandy Fletcher (light blue shirt with glasses) and astronaut Shane Kimbrough assist. PHOTOGRAPHER: Mark Sowa

jsc2013e073498

NASA Image and Video Library

2013-07-29

PHOTO DATE: 29 July 2013 LOCATION: Bldg. 9NW, Space Vehicle Mockup Training Facility - POGO SUBJECT: Expedition 42 crew member and astronaut Barry "Butch" Wilmore during ISS EVA POGO 1 training. Instructors Faruq Sabur (black shirt), Allissa Battocletti (red shirt), Sandy Fletcher (light blue shirt with glasses) and astronaut Shane Kimbrough assist. PHOTOGRAPHER: Mark Sowa

STS-133 crew members Lindsey, Boe and Drew during Tool/Repair Kits training with instructor

NASA Image and Video Library

2010-01-26

JSC2010-E-014264 (26 Jan. 2010) --- NASA astronaut Eric Boe, STS-133 pilot, participates in an ISS tools and repair kits training session in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center. Instructor Ivy Apostolakopoulos assisted Boe.

STS-133 crew members Lindsey, Boe and Drew during Tool/Repair Kits training with instructor

NASA Image and Video Library

2010-01-26

JSC2010-E-014266 (26 Jan. 2010) --- NASA astronauts Steve Lindsey (right), STS-133 commander; and Eric Boe, pilot, participate in an ISS tools and repair kits training session in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center.

Astronaut Donald H. Peterson talks with others during training session STS-6

NASA Technical Reports Server (NTRS)

1982-01-01

Astronaut Donald H. Peterson talks with Astronaut James P. Bagian (almost out of frame at right edge) during a training session for STS-6 crew members in the Shuttle mockup and integration laboratory. Petterson is wearing the shuttle flight suit and holding his helmet.

Demonstration PreFab Solar Heated Vacation Home

ERIC Educational Resources Information Center

Ariola, Frank; Walencik, Vincent J.

1978-01-01

To update a traditional construction shop program, students at Passaic Valley High School, New Jersey, developed a mock-up model of a solar-heated A-frame vacation house using prefab construction. The article describes the project and illustrates it with photographs of the model and a drawing of the solar collector. (MF)

Astronaut John Glenn - Egress Training Activity - Langley AFB, VA

NASA Image and Video Library

1960-12-12

B60-00285 (1960) --- Astronaut John H. Glenn Jr., pilot of the Mercury Atlas 6 spaceflight, emerges from an egress trainer during training activity at the Langley Research Center. He is attempting to transfer onto a life raft from the mock-up of the Mercury capsule. Photo credit: NASA

STS-99 crewmembers train in orbiter mock-up

NASA Image and Video Library

1999-08-24

S99-10568 (24 August 1999) --- Astronaut Janet L. Kavandi, mission specialist, participates in a training exercise in preparation for her upcoming flight aboard the Space Shuttle Endeavour. She is on the mid deck of one of the shuttle trainers in the Johnson Space Center's Systems Integration Facility.

STS-134 crew members Mike Fincke, Drew Feustel and Greg Chamitoff performing EVA Tile Repair Training.

NASA Image and Video Library

2010-01-28

JSC2010-E-014761 (28 Jan. 2010) --- NASA astronauts Greg Chamitoff (left), Andrew Feustel and Michael Fincke, all STS-134 mission specialists, participate in an EVA tile repair training session in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center.

STS-134 crew members Mike Fincke, Drew Feustel and Greg Chamitoff performing EVA Tile Repair Training.

NASA Image and Video Library

2010-01-28

JSC2010-E-014766 (28 Jan. 2010) --- NASA astronaut Michael Fincke (left), STS-134 mission specialist, participates in an EVA tile repair training session in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center. Instructor John Ray assisted Fincke.

STS-134 crew members Mike Fincke, Drew Feustel and Greg Chamitoff performing EVA Tile Repair Training.

NASA Image and Video Library

2010-01-28

JSC2010-E-014762 (28 Jan. 2010) --- NASA astronauts Greg Chamitoff (left), Andrew Feustel and Michael Fincke, all STS-134 mission specialists, participate in an EVA tile repair training session in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center.

ISS Phase One Activities and Manufacturing in Russia, France and Italy

NASA Image and Video Library

1996-10-07

Photographs documenting International Space Station (ISS) Phase One activities at the Russian Space Agency's (RSA) Gagarin Cosmonaut Training Center, Korolov Mission Control Center and Zvezda; and ISS and Soyuz manufacturing at RSA's Khrunichev Design Center and RSC Energiya in Moscow, Russia, the French Space Agency's (CNES) INTESPACE facility in Toulouse, France, and the Italian Space Agency's (ASI) Alenia Spazio facility in Torino, Italy. Photographs were taken by Johnson Space Center Imagery and Publications Office contractors travelling from October 7 to November 4, 1996. Includes: VIEWS FROM RSC ENERGIYA'S SPACE MUSEUM: Room with a Buran model and photographic displays (17372-374). Salyut Space Station mock-up (17376). Russian propulsion engines on display (17377-378). Russian spacecraft on display (17375, 17387-398). Graphic displays (17399-405). VIEWS FROM RSC ENERGIYA MANUFACTURING FACILITIES: Unidentified facility (17379). Mir 24 crew member Michael C. Foale, suited in a Soyuz pressure suit, ingresses the Soyuz TM-26 flight article at RSC Energiya for a fit check (17380-381). Closeups of Foale inside the Soyuz during the fit check (17382-383, 17466-467). Overhead views of RSC Energiya's Building 444 manufacturing floor where docking modules and Soyuz TM spacecraft are built (17495-498). Technicians on the Building 444 manufacturing floor assembling probe and drogue docking modules (17499-500, 17504). Technicians assembling Soyuz spacecraft (17437-439). Views of other Soyuz spacecraft (17440-441). Androgynous Peripheral Docking System (APDS) mock-up (17501-503). Closeups of a control panel, possibly for the APDS mock-up (17519-528). VIEWS FROM ZVEZDA, RSA CONTRACTOR FOR SUIT DESIGN AND SOYUZ SEAT LINERS: Mir 24 crew member Foale dons a "penguin" flight suit for a fit check (17454-456). Zvezda personnel adjust Foale's Soyuz seat and seat liner (17442). Closeup of Foale, suited in a Soyuz pressure suit, sitting on a chair (17444). Zvezda personnel strap pressure-suited Foale into his Soyuz seat (17443, 17445, 17450). Views of Foale in his Soyuz seat during a pressurized pressure suit fit check (17451-453). Views looking into a vacuum chamber where Foale, wearing pressure suit, is strapped into his Soyuz seat (17466-467). Views of Zvezda personnel working at the vacuum chamber control station during the vacuum chamber suit test (17468-471). VIEWS FROM KHRUNICHEV DESIGN CENTER: Views of a green ISS Functional Cargo Block (FGB) test article on the manufacturing floor (17529, 17532-536, 17540-544). Views of an ISS Service Module (SM) test article on the manufacturing floor (17530-531, 17537, 17539). Closeup of the SM test article docking sphere (17538). Views of the FGB flight article on the manufacturing floor during systems tests (17545-548, 17550-567). Views of technicians conducting the FGB systems tests (17549, 17557). VIEWS FROM GAGARIN COSMONAUT TRAINING CENTER: NASA astronauts work out in the cosmonaut gym at Gagarin: Closeup of ISS 2R Expedition Commander William Shepherd on a weight machine (17384). Shepherd and an unidentified man with back to camera work out with dumbbells (17386). Shepherd does pull-ups (17447). Closeup of Foale on an exercise machine (17385). Closeups of Foale exercising arms on a cycle ergometer and a weight machine (17415, 17448-449). Foale exercises on a Nordic Track (17416). Closeup of Mir 23 crew member Jerry Linenger exercising arms (17417). Wendy Lawrence exercises with dumbbells (17418). Closeup of Lawrence in a handstand position (17419). David Wolf works out on a leg press machine (17446). Views of the Mir Space Station mock-up at Gagarin: Interior views of the Mir Base Module mock-up looking toward the transfer compartment (17421-425). Mir Base Module living area mock-up (17420). Overall views of the Base Module mock-up central control station (17426-427, 17505). Closeups of switch panels on the central control station (17428-436, 17506-518). Other views from Gagarin: Personnel work at an unidentified test/trainer control station (17472-473). Linenger sits at a table next to an RSA trainer during a Mir 23 meeting (17475-476). Out-of-focus view of two subjects in the Soyuz trainer (17474). Foale examines a Mir Complex EVA Suit (Orlan) with RSA trainers during an EVA suit training class (17492-494). VIEWS FROM KOROLOV MISSION CONTROL CENTER: Various views of personnel working in the NASA Consulting Room and/or PAO Consulting Room at Korolov Mission Control Center (17457-463). VIEWS FROM INTESPACE: Exterior views of an ISS Mini Pressurized Logistics Module (MPLM) structural test article (STA) during testing at INTESPACE (17406-409, 17477, 17482-484). Technicians install hatch on the MPLM STA (17410-414). Interior views of the MPLM STA (17478-481). VIEWS FROM ALENIA SPAZIO: Closeups of MPLM flight article #1 side panels during milling and refining at Alenia Spazio (17485-488). Workers process MPLM parts at milling machines (17489-491).

STS-9 crewmembers in training session in bldg 9A

NASA Technical Reports Server (NTRS)

1983-01-01

Members of the STS-9 crew discuss flight procedures with a trainer in bldg 9A before the STS-9 mission. From left to right are Brewster Shaw, pilot; John Young, crew commander; Robert Parker, mission specialist; and unidentified trainer. They are reviewing procedures manuals on the shuttle mock-up hatch.

STS-32 Commander Brandenstein adjusts IMAX camera during training session

NASA Technical Reports Server (NTRS)

1989-01-01

STS-32 Commander Daniel C. Brandenstein adjusts IMAX camera setting during briefing and training session as technician looks on. The session was conducted in the JSC Mockup and Integration Laboratory (MAIL) Bldg 9B. The IMAX camera will be used onboard Columbia, Orbiter Vehicle (OV) 102, during the STS-32 mission.

Fiber optic sensing for telecommunication satellites

NASA Astrophysics Data System (ADS)

Reutlinger, Arnd; Glier, Markus; Zuknik, Karl-Heinz; Hoffmann, Lars; Müller, Mathias; Rapp, Stephan; Kurvin, Charles; Ernst, Thomas; McKenzie, Iain; Karafolas, Nikos

2017-11-01

Modern telecommunication satellites can benefit from the features of fiber optic sensing wrt to mass savings, improved performance and lower costs. Within the course of a technology study, launched by the European Space Agency, a fiber optic sensing system has been designed and is to be tested on representative mockups of satellite sectors and environment.

STS-133 crew during MSS/EVAA TEAM training in Virtual Reality Lab

NASA Image and Video Library

2010-10-01

JSC2010-E-170877 (1 Oct. 2010) --- A large monitor is featured in this image during STS-133 crew members? training activities in the virtual reality laboratory in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center. Photo credit: NASA or National Aeronautics and Space Administration

STS-116 payload egress training

NASA Image and Video Library

2005-08-01

JSC2005-E-32739 (1 Aug. 2005) --- Astronaut Mark L. Polansky, STS-116 commander, uses a special pulley device to lower himself from a simulated trouble-plagued shuttle during a training session in the Space Vehicle Mockup Facility at the Johnson Space Center. Polansky is wearing a training version of the shuttle launch and entry suit.

STS-118 Astronaut Tracy Caldwell During Training

NASA Technical Reports Server (NTRS)

2006-01-01

Tracy E. Caldwell, STS-118 astronaut and mission specialist, participates in a training session on the usage of a special device, used to lower oneself from a troubled shuttle, in the Space Vehicle Mockup Facility at the Johnson Space Center. Caldwell is wearing a training version of her shuttle launch and entry suit.

The Constructed Relief: Put the Carving Tools Away and Build a Sculpture.

ERIC Educational Resources Information Center

Kostyniuk, Ron

1990-01-01

Describes origins of the constructed relief and shows some examples of contemporary artists' work. Suggests using this history to motivate students to construct their own reliefs. Outlines a four-step lesson: preliminary drawing, finished drawing, mock-up relief, and finished construction using durable materials, such as wood, acrylic sheet, or…

KSC-00padig124

NASA Image and Video Library

2000-12-08

KENNEDY SPACE CENTER, FLA. -- A film crew gather around Steve Thomas (kneeling) as they shoot inside a mockup of the U.S. Lab, located in the International Space Station Center, a tour facility. Thomas and Norm Abram, host and master carpenter, respectively, of television’s "This Old House," are at KSC to film an episode of the series

STS-61 air-bearing floor training in bldg 9N with Astronaut Jeff Hoffman

NASA Image and Video Library

1993-06-07

Making use of the air-bearing floor in JSC's Shuttle mockup and integration laboratory, Astronaut Jeffrey A. Hoffman practices working with the Hubble Space Telescope's Wide Field/Planetary Camera (WF/PC). Changing out the large camera is one of several jobs to be performed by STS-61.

Astronaut Joseph Tanner checks gloves during during launch/entry training

NASA Technical Reports Server (NTRS)

1994-01-01

Astronaut Joseph R. Tanner, mission specialist, checks his gloves during a rehearsal for the launch and entry phases of the scheduled November 1994 flight of STS-66. This rehearsal, held in the crew compartment trainer (CCT) of JSC's Shuttle mockup and integration laboratory, was followed by a training session on emergency egress procedures.

NASA STEM Event

NASA Image and Video Library

2013-01-19

School children react to food shrinking in a vacuum chamber during an Science, Technology, Engineering, and Math (STEM) education event held at the Ritz-Carlton Hotel in Arlington, VA on Saturday, Jan. 19, 2013. Students were able to meet with Astronaut Melvin, conduct experiments, build their own space jab, and touch a mockup space suit. Photo Credit: (NASA/Bill Ingalls)

STS-133 crew members Lindsey, Boe and Drew during Tool/Repair Kits training with instructor

NASA Image and Video Library

2010-01-26

JSC2010-E-014267 (26 Jan. 2010) --- NASA astronauts Steve Lindsey (center), STS-133 commander; Eric Boe (left), pilot; and Alvin Drew, mission specialist, participate in an ISS tools and repair kits training session in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center.

STS-335 crew during Soyuz Flight Plan training

NASA Image and Video Library

2010-11-30

JSC2010-E-193582 (30 Nov. 2010) --- NASA astronaut Chris Ferguson, STS-135 commander, participates in a training session in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center. STS-135 is planned to be the final mission of the space shuttle program. Photo credit: NASA or National Aeronautics and Space Administration

STS-335 crew during Soyuz Flight Plan training

NASA Image and Video Library

2010-11-30

JSC2010-E-193583 (30 Nov. 2010) --- NASA astronaut Doug Hurley, STS-135 pilot, participates in a training session in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center. STS-135 is planned to be the final mission of the space shuttle program. Photo credit: NASA or National Aeronautics and Space Administration

STS-135 Escape System Refresher training and Stowage Review Training

NASA Image and Video Library

2011-06-29

JSC2011-E-060759 (29 June 2011) --- NASA astronaut Sandy Magnus, STS-135 mission specialist, participates in a training session in the crew compartment trainer (CCT-2) in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center. Here, she is being briefed on the escape pole. Photo credit: NASA

Astronaut Dale Gardner rehearses during EVA practice

NASA Technical Reports Server (NTRS)

1984-01-01

Astronaut Dale A. Gardner, 51-A mission specialist, rehearses control of manned maneuvering unit (MMU) during a practice for an extravehicular activity (EVA). Gardner is in the Shuttle mockup and integration laboratory at JSC. Gardner handles a stinger device to make initial contact with one of the two satellites they will be working with.

Astronaut Dale Gardner rehearses during EVA practice

NASA Technical Reports Server (NTRS)

1984-01-01

Astronaut Dale A. Gardner, 51-A mission specialist, rehearses control of manned maneuvering unit (MMU) during a practice for an extravehicular activity (EVA). Gardner is in the Shuttle mockup and integration laboratory at JSC. Gardner works to deploy a large stinger device designed for locking onto the orbiting satellites via entering a spent engine's nozzle.

Saturn Apollo Program

NASA Image and Video Library

1967-08-01

The Apollo Telescope Mount (ATM), designed and developed by the Marshall Space Flight Center, served as the primary scientific instrument unit aboard the Skylab. The ATM contained eight complex astronomical instruments designed to observe the Sun over a wide spectrum from visible light to x-rays. This photo depicts a mockup of the ATM contamination monitor camera and photometer.

Saturn Apollo Program

NASA Image and Video Library

1967-08-01

The Apollo Telescope Mount (ATM), designed and developed by the Marshall Space Flight Center, served as the primary scientific instrument unit aboard the Skylab. The ATM contained eight complex astronomical instruments designed to observe the Sun over a wide spectrum from visible light to x-rays. This angle view is of an ATM contamination monitor meter mockup.

Tanker Avionics/Aircrew Complement Evaluation (TAACE). Phase 0. Analysis and Mockup. Volume II. Summary of Data.

DTIC Science & Technology

1980-05-01

However, the TF-33s would greatly enhance the mission capabilities of the aircraft. The addition of winglets will increase range and decrease fuel...a sound and capable system. There are certainly some improvements that can be made. A better boom with better aerodynamic design would help

Polysensory Learning through Multi-Media Instruction in Trade and Technical Education.

ERIC Educational Resources Information Center

Allen, David; And Others

This report explains a teaching system designed to stimulate polysensory learning by use of multi-media instructional materials, which use as many of the physical senses as practical to augment traditional instruction. They include motion pictures, filmstrips, audio tapes, models, mock-ups, etc., according to school facilities and course needs.…

Technicians assist STS-47 MS Jemison prior to JSC bailout training

NASA Technical Reports Server (NTRS)

1992-01-01

STS-47 Endeavour, Orbiter Vehicle (OV) 105, Mission Specialist (MS) Mae C. Jemison, assisted by technicians, adjusts a strap on her launch and entry suit (LES) prior to launch emergency egress (bailout) exercises in JSC's Mockup and Integration Laboratory Bldg 9A. Jemison is making her first flight in space.

Astronauts Gibson and Pogue at Apollo Telescope Mount display/control panel

NASA Image and Video Library

1973-09-10

S73-32837 (10 Sept. 1973) --- Scientist-astronaut Edward G. Gibson, seated, and astronaut William R. Pogue discuss a mission procedure at the Apollo Telescope Mount (ATM) display and control panel mock-up in the one-G trainer for the Multiple Docking Adapter (MDA) at Johnson Space Center. Photo credit: NASA

Design, development and evaluation of Stanford/Ames Extra-Vehicular Activity (EVA) prehensors

NASA Technical Reports Server (NTRS)

Leifer, Larry J.; Jameson, J.; Leblanc, M.; Wilson, D.; Sabelman, E.; Schwandt, D.

1987-01-01

A summary is given of progress to date on work proposed in 1983 and continued in 1985, including design iterations on three different types of manually powered prehensors, construction of functional mockups of each and culminating in detailed drawings and specifications for suit-compatible sealed units for testing under realistic conditions.

Dan Poskevich demonstrates experiment for STS student involvement project

NASA Technical Reports Server (NTRS)

1984-01-01

Dan Poskevich, a college student, demonstrates an experiment he developed for the Space Transportation System (STS) student involvement project. In the aluminum box are thousands of honeybees constructing a honeycomb. Poskevich gave a brief demonstration for news media representatives in the Space Shuttle one-G trainer in JSC's mockup and integration lab.

STS_135_ SVMF

NASA Image and Video Library

2011-06-29

JSC2011-E-060138 (29 June 2011) --- NASA astronaut Chris Ferguson crawls out of the Crew Compartment Trainer (CCT-2) as the crew of STS-135 trains at NASA?s Johnson Space Center June 29, 2011. The training marked the crew's final scheduled session in the Space Vehicle Mock-up Facility. Photo credit: NASA Photo/Houston Chronicle, Smiley N. Pool

Underwater views of STS-11 crewman Robert L. Stewart during EVA training

NASA Technical Reports Server (NTRS)

1983-01-01

Underwater views of STS-11 crewman Robert L. Stewart during extravehicular activity (EVA) training in the cargo bay in the weightless environment training facility (WETF) in bldg 27. Stewart busies himself with donning and doffing of the manned maneuvering unit (MMU) in a mockup of the Shuttle's cargo bay.

Mockup design of personal health diary app for patients with chronic kidney disease.

PubMed

Lin, Hsiu-Wen; Wang, Yu-Jen; Jing, Ling-Fang; Chang, Polun

2014-01-01

Health self-management is important in the care of patients with chronic kidney disease. It is possible to improve the efficiency of patient self-management through the use of mobile technology and related software. This study is divided into three stages: 1. analysis of need: through observation, interview and content analysis of the chronic kidney disease health management manual; 2. design of system prototype: establish interface and system function; 3. prototype evaluation: evaluate whether the prototype designed by this study meets user needs. The system prototype includes: daily record, laboratory examination results, trend graphs, information search, sharing, communications and settings. Prototyping is done with Pencil Project for interface design and linking. The prototype is then exported in PDF format for mock-up simulation. Evaluation results: overall score was 4.01±0.60 leaning towards "agree", the highest score was ease of use (4.25±0.6), followed by easy to learn (4.15±0.68), acceptance (4.01±0.61), reliability (3.87±0.6) and functionality (3.83±0.49). The results show positive attitude towards the system.

On display during a technical exposition at Dryden are NASA's B-52 launch aircraft, Boeing's X-37, B

NASA Technical Reports Server (NTRS)

2000-01-01

Aerospace industry representatives view actual and mock-up versions of 'X-Planes' intended to enhance access to space during a technical exposition on June 22, 2000 at Dryden Flight Research Center, Edwards, California. From left to right: NASA's B-52 launch aircraft, in service with NASA since 1959; a neutral-buoyancy model of the Boeing's X-37; the Boeing X-40A behind the MicroCraft X-43 mock-up; Orbital Science's X-34 and the modified Lockheed L-1011 airliner that was to launch the X-34. These X-vehicles are part of NASA's Access to Space plan intended to bring new technologies to bear in an effort to dramatically lower the cost of putting payloads in space, and near-space environments. The June 22, 2000 NASA Reusable Launch Vehicle (RLV) Technology Exposition included presentations on the history, present, and future of NASA's RLV program. Special Sessions for industry representatives highlighted the X-37 project and its related technologies. The X-37 project is managed by NASA's Marshall Space Flight Center, Huntsville, Alabama.

KENNEDY SPACE CENTER, FLA. - During a media tour of the Columbia Debris Hangar, a photographer gets a close-up of the mockup of the leading edge of Columbia’s left wing. About 83,000 pieces of debris were shipped to KSC from search and recovery efforts in East Texas. About 83,000 pieces of debris from Columbia were shipped to KSC, which represents about 38 percent of the dry weight of Columbia, equaling almost 85,000 pounds. The debris is being packaged for storage in an area of the Vehicle Assembly Building.

NASA Image and Video Library

2003-09-11

KENNEDY SPACE CENTER, FLA. - During a media tour of the Columbia Debris Hangar, a photographer gets a close-up of the mockup of the leading edge of Columbia’s left wing. About 83,000 pieces of debris were shipped to KSC from search and recovery efforts in East Texas. About 83,000 pieces of debris from Columbia were shipped to KSC, which represents about 38 percent of the dry weight of Columbia, equaling almost 85,000 pounds. The debris is being packaged for storage in an area of the Vehicle Assembly Building.

A fast and sensitive method for evaluating nuclides migration characteristics in rock medium by using micro-channel reactor concept

NASA Astrophysics Data System (ADS)

Okuyama, Keita; Sasahira, Akira; Noshita, Kenji; Yoshida, Takuma; Kato, Kazuyuki; Nagasaki, Shinya; Ohe, Toshiaki

Experimental effort to evaluate the barrier performance of geologic disposal requires relatively long testing periods and chemically stable conditions. We have developed a new technique, the micro mock-up method, to present a fast and sensitive method to measure both nuclide diffusivity and sorption coefficient within a day to overcome such disadvantage of the conventional method. In this method, a Teflon plate having a micro channel (10-200 μm depth, 2, 4 mm width) is placed just beneath the rock sample plate, radionuclide solution is injected into the channel with constant rate. The breakthrough curve is being measured until a steady state. The outlet flux in the steady state however does not meet the inlet flux because of the matrix diffusion into the rock body. This inlet-outlet difference is simply related to the effective diffusion coefficient ( De) and the distribution coefficient ( Kd) of rock sample. Then, we adopt a fitting procedure to speculate Kd and De values by comparing the observation to the theoretical curve of the two-dimensional diffusion-advection equation. In the present study, we measured De of 3H by using both the micro mock-up method and the conventional through-diffusion method for comparison. The obtained values of De by two different ways for granite sample (Inada area of Japan) were identical: 1.0 × 10 -11 and 9.0 × 10 -12 m 2/s but the testing period was much different: 10 h and 3 days, respectively. We also measured the breakthrough curve of 85Sr and the resulting Kd and De agreed well to the previous study obtained by the batch sorption experiments with crushed samples. The experimental evidence and the above advantages reveal that the micro mock-up method based on the microreactor concept is powerful and much advantageous when compared to the conventional method.

Involvement of the end user: exploration of older people’s needs and preferences for a wearable fall detection device – a qualitative descriptive study

PubMed Central

Thilo, Friederike JS; Bilger, Selina; Halfens, Ruud JG; Schols, Jos MGA; Hahn, Sabine

2017-01-01

Purpose To explore the needs and preferences of community-dwelling older people, by involving them in the device design and mock-up development stage of a fall detection device, consisting of a body-worn sensor linked to a smartphone application. Patients and methods A total of 22 community-dwelling persons 75 years of age and older were involved in the development of a fall detection device. Three semistructured focus group interviews were conducted. The interview data were analyzed using qualitative descriptive analysis with deductive coding. Results The mock-up of a waterproof, body-worn, automatic and manual alerting device, which served both as a day-time wearable sensor and a night-time wearable sensor, was welcomed. Changes should be considered regarding shape, color and size along with alternate ways of integrating the sensor with items already in use in daily life, such as jewelry and personal watches. The reliability of the sensor is key for the participants. Issues important to the alerting process were discussed, for instance, who should be contacted and why. Several participants were concerned with the mandatory use of the smartphone and assumed that it would be difficult to use. They criticized the limited distance between the sensor and the smartphone for reliable fall detection, as it might restrict activity and negatively influence their degree of independence in daily life. Conclusion This study supports that involving end users in the design and mock-up development stage is welcomed by older people and allows their needs and preferences concerning the fall detection device to be explored. Based on these findings, the development of a “need-driven” prototype is possible. As participants are doubtful regarding smartphone usage, careful training and support of community-dwelling older people during real field testing will be crucial. PMID:28053509

Adjusted Framework of M-Learning in Blended Learning System for Mathematics Study Field of Junior High School Level VII

NASA Astrophysics Data System (ADS)

Sugiyanta, Lipur; Sukardjo, Moch.

2018-04-01

The 2013 curriculum requires teachers to be more productive, creative, and innovative in encouraging students to be more independent by strengthening attitudes, skills and knowledge. Teachers are given the options to create lesson plan according to the environment and conditions of their students. At the junior level, Core Competence (KI) and Basic Competence (KD) have been completely designed. In addition, there had already guidebooks, both for teacher manuals (Master’s Books) and for learners (Student Books). The lesson plan and guidebooks which already exist are intended only for learning in the classroom/in-school. Many alternative classrooms and alternatives learning models opened up using educational technology. The advance of educational technology opened opportunity for combination of class interaction using mobile learning applications. Mobile learning has rapidly evolved in education for the last ten years and many initiatives have been conducted worldwide. However, few of these efforts have produced any lasting outcomes. It is evident that mobile education applications are complex and hence, will not become sustainable. Long-term sustainability remains a risk. Long-term sustainability usually was resulted from continuous adaptation to changing conditions [4]. Frameworks are therefore required to avoid sustainability pitfalls. The implementation should start from simple environment then gradually become complex through adaptation steps. Therefore, our paper developed the framework of mobile learning (m-learning) adaptation for grade 7th (junior high school). The environment setup was blended mobile learning (not full mobile learning) and emphasize on Algebra. The research is done by R&D method (research and development). Results of the framework includes requirements and adaptation steps. The adjusted m-learning framework is designed to be a guidance for teachers to adopt m-learning to support blended learning environments. During mock-up prototype, the adjusted framework demonstrates how to make successful implementation of early blended mobile learning through framework. The Social area is in focus of adaptation because participation is important to improve the sustainability. From the short practice of mock-up prototype, blended mobile learning can be an effective pedagogical model in supporting students in inquiry-based learning.