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1

J-2X Upper Stage Engine: Hardware and Testing 2009  

NASA Technical Reports Server (NTRS)

Mission: Common upper stage engine for Ares I and Ares V. Challenge: Use proven technology from Saturn X-33, RS-68 to develop the highest Isp GG cycle engine in history for 2 missions in record time . Key Features: LOX/LH2 GG cycle, series turbines (2), HIP-bonded MCC, pneumatic ball-sector valves, on-board engine controller, tube-wall regen nozzle/large passively-cooled nozzle extension, TEG boost/cooling . Development Philosophy: proven hardware, aggressive schedule, early risk reduction, requirements-driven.

Buzzell, James C.

2009-01-01

2

Testing for the J-2X Upper Stage Engine  

NASA Technical Reports Server (NTRS)

NASA selected the J-2X Upper Stage Engine in 2006 to power the upper stages of the Ares I crew launch vehicle and the Ares V cargo launch vehicle. Based on the proven Saturn J-2 engine, this new engine will provide 294,000 pounds of thrust and a specific impulse of 448 seconds, making it the most efficient gas generator cycle engine in history. The engine's guiding philosophy emerged from the Exploration Systems Architecture Study (ESAS) in 2005. Goals established then called for vehicles and components based, where feasible, on proven hardware from the Space Shuttle, commercial, and other programs, to perform the mission and provide an order of magnitude greater safety. Since that time, the team has made unprecedented progress. Ahead of the other elements of the Constellation Program architecture, the team has progressed through System Requirements Review (SRR), System Design Review (SDR), Preliminary Design Review (PDR), and Critical Design Review (CDR). As of February 2010, more than 100,000 development engine parts have been ordered and more than 18,000 delivered. Approximately 1,300 of more than 1,600 engine drawings were released for manufacturing. A major factor in the J-2X development approach to this point is testing operations of heritage J-2 engine hardware and new J-2X components to understand heritage performance, validate computer modeling of development components, mitigate risk early in development, and inform design trades. This testing has been performed both by NASA and its J-2X prime contractor, Pratt & Whitney Rocketdyne (PWR). This body of work increases the likelihood of success as the team prepares for testing the J-2X powerpack and first development engine in calendar 2011. This paper will provide highlights of J-2X testing operations, engine test facilities, development hardware, and plans.

Buzzell, James C.

2010-01-01

3

Solar Thermal Upper Stage Cryogen System Engineering Checkout Test  

NASA Technical Reports Server (NTRS)

The Solar Thermal Upper Stage technology (STUSTD) program is a solar thermal propulsion technology program cooperatively sponsored by a Boeing led team and by NASA MSFC. A key element of its technology program is development of a liquid hydrogen (LH2) storage and supply system which employs multi-layer insulation, liquid acquisition devices, active and passive thermodynamic vent systems, and variable 40W tank heaters to reliably provide near constant pressure H2 to a solar thermal engine in the low-gravity of space operation. The LH2 storage and supply system is designed to operate as a passive, pressure fed supply system at a constant pressure of about 45 psia. During operation of the solar thermal engine over a small portion of the orbit the LH2 storage and supply system propulsively vents through the enjoy at a controlled flowrate. During the long coast portion of the orbit, the LH2 tank is locked up (unvented). Thus, all of the vented H2 flow is used in the engine for thrust and none is wastefully vented overboard. The key to managing the tank pressure and therefore the H2 flow to the engine is to manage and balance the energy flow into the LH2 tank with the MLI and tank heaters with the energy flow out of the LH2 tank through the vented H2 flow. A moderate scale (71 cu ft) LH2 storage and supply system was installed and insulated at the NASA MSFC Test Area 300. The operation of the system is described in this paper. The test program for the LH2 system consisted of two parts: 1) a series of engineering tests to characterize the performance of the various components in the system: and 2) a 30-day simulation of a complete LEO and GEO transfer mission. This paper describes the results of the engineering tests, and correlates these results with analytical models used to design future advanced Solar Orbit Transfer Vehicles.

Olsen, A. D; Cady, E. C.; Jenkins, D. S.

1999-01-01

4

Integrated Solar Upper Stage (ISUS) engine ground demonstration (EGD)  

NASA Astrophysics Data System (ADS)

The Integrated Solar Upper Stage (ISUS) Engine Ground Demonstration (EGD) Program sponsored by the Air Force Phillips Laboratory (PL) conducted a full-up ground demonstration of a solar thermal power and propulsion system at NASA Lewis Research Center in mid-1997. This test validated system capability in a relevant environment, bringing ISUS to a Technology Readiness Level (TRL) of 6, and paving the way for a flight demonstration by the turn of the century. The ISUS technology offers high specific impulse propulsion at moderate thrust levels and high power, radiation-tolerant electrical power generation. This bimodal system capability offers savings in launch vehicle costs and/or substantial increases in payload power and mass over present day satellite systems. The ISUS EGD consisted of the solar receiver/absorber/converter (RAC), power generation, management, and distribution subsystems, solar concentrator, and cryogen storage/feed subsystems. Simulation of a low Earth orbit (LEO)-to-Molniya orbit transfer (30-day trip time) as well as characterization of on-orbit power production was planned for this ground test. This paper describes the EGD test integration, setup and checkout, system acceptance tests, performance mapping, and exercise of the system through a mission-like series of operations. Key test data collected during the test series is reported along with a summary of technical insights achieved as a result of the experiment. Test data includes propulsion performance as derived from flowrate, temperature, and pressure measurements and the total number of thermal cycles.

Kudija, Charles T.; Frye, Patrick E.

1998-01-01

5

The Malemute development program. [rocket upper stage engine design  

NASA Technical Reports Server (NTRS)

The Malemute vehicle systems are two-stage systems based on utilizing a new high performance upper stage motor with two existing military boosters. The Malmute development program is described relative to program structure, preliminary design, vehicle subsystems, and the Malemute motor. Two vehicle systems, the Nike-Malemute and Terrier-Malemute, were developed which are capable of transporting comparatively large diameter (16 in.) 200-lb payloads to altitudes of 500 and 700 km, respectively. These vehicles provide relatively low-cost transportation with two-stage reliability and launch simplicity. Flight tests of both vehicle systems revealed their performance capabilities, with the Terrier-Malemute system involving a unique Malemute motor spin sensitivity problem. It is suggested that the vehicles can be successfully flown by lowering the burnout spin rate.

Bolster, W. J.; Hoekstra, P. W.

1976-01-01

6

Centaur upper stage  

NASA Astrophysics Data System (ADS)

An account is given of the design features of the LOX/LH2-fueled Centaur upper stage engine and fuel cryotankage, in order to serve as a basis for understanding the Main Engine Cut Off (MECO) system instituted. MECO follows the instant of spacecraft separation from the upper stage. The planetary launch program during 1966-1978 involved 23 Centaur launches and led to no upper stage reentry; LEO missions for HEAO and OAO satellite lofting in 1963-1979 involved nine Centaur launches and led to five reentries. GEO satellite launches in 1969-1986 saw 32 launches and three known reentries.

Groesbeck, W.

7

Low-speed inducers for cryogenic upper-stage engines  

NASA Technical Reports Server (NTRS)

Two-phase, low-speed hydrogen and oxygen inducers driven by electric motors and applicable to the tug engine were designed and constructed. The oxygen inducer was tested in liquid and two-phase oxygen. Its head and flow performance were approximately as designed, and it was able to accelerate to full speed in 3 seconds and produce its design flow and head. The analysis of the two-phase data indicated that the inducer was able to pump with vapor volume fractions in excess of 60 percent. The pump met all of its requirements (duration of runs and number of starts) to demonstrate its mechanical integrity.

Bissell, W. R.; Jenkins, D. S.; King, J. A.; Jackson, E. D.

1975-01-01

8

From Paper to Production: An Update on NASA's Upper Stage Engine for Exploration  

NASA Technical Reports Server (NTRS)

In 2006, NASA selected an evolved variant of the proven Saturn/Apollo J-2 upper stage engine to power the Ares I crew launch vehicle upper stage and the Ares V cargo launch vehicle Earth departure stage (EDS) for the Constellation Program. Any design changes needed by the new engine would be based where possible on proven hardware from the Space Shuttle, commercial launchers, and other programs. In addition to the thrust and efficiency requirements needed for the Constellation reference missions, it would be an order of magnitude safer than past engines. It required the J-2X government/industry team to develop the highest performance engine of its type in history and develop it for use in two vehicles for two different missions. In the attempt to achieve these goals in the past five years, the Upper Stage Engine team has made significant progress, successfully passing System Requirements Review (SRR), System Design Review (SDR), Preliminary Design Review (PDR), and Critical Design Review (CDR). As of spring 2010, more than 100,000 experimental and development engine parts have been completed or are in various stages of manufacture. Approximately 1,300 of more than 1,600 engine drawings have been released for manufacturing. This progress has been due to a combination of factors: the heritage hardware starting point, advanced computer analysis, and early heritage and development component testing to understand performance, validate computer modeling, and inform design trades. This work will increase the odds of success as engine team prepares for powerpack and development engine hot fire testing in calendar 2011. This paper will provide an overview of the engine development program and progress to date.

Kynard, Mike

2010-01-01

9

Upper Stage Flight Experiment 10K Engine Design and Test Results  

NASA Technical Reports Server (NTRS)

A 10,000 lbf thrust chamber was developed for the Upper Stage Flight Experiment (USFE). This thrust chamber uses hydrogen peroxide/JP-8 oxidizer/fuel combination. The thrust chamber comprises an oxidizer dome and manifold, catalyst bed assembly, fuel injector, and chamber/nozzle assembly. Testing of the engine was done at NASA's Stennis Space Center (SSC) to verify its performance and life for future upper stage or Reusable Launch Vehicle applications. Various combinations of silver screen catalyst beds, fuel injectors, and combustion chambers were tested. Results of the tests showed high C* efficiencies (97% - 100%) and vacuum specific impulses of 275 - 298 seconds. With fuel film cooling, heating rates were low enough that the silica/quartz phenolic throat experienced minimal erosion. Mission derived requirements were met, along with a perfect safety record.

Ross, R.; Morgan, D.; Crockett, D.; Martinez, L.; Anderson, W.; McNeal, C.

2000-01-01

10

The J-2X Upper Stage Engine: From Heritage to Hardware  

NASA Technical Reports Server (NTRS)

NASA's Global Exploration Strategy requires safe, reliable, robust, efficient transportation to support sustainable operations from Earth to orbit and into the far reaches of the solar system. NASA selected the Ares I crew launch vehicle and the Ares V cargo launch vehicle to provide that transportation. Guiding principles in creating the architecture represented by the Ares vehicles were the maximum use of heritage hardware and legacy knowledge, particularly Space Shuttle assets, and commonality between the Ares vehicles where possible to streamline the hardware development approach and reduce programmatic, technical, and budget risks. The J-2X exemplifies those goals. It was selected by the Exploration Systems Architecture Study (ESAS) as the upper stage propulsion for the Ares I Upper Stage and the Ares V Earth Departure Stage (EDS). The J-2X is an evolved version ofthe historic J-2 engine that successfully powered the second stage of the Saturn I launch vehicle and the second and third stages of the Saturn V launch vehicle. The Constellation architecture, however, requires performance greater than its predecessor. The new architecture calls for larger payloads delivered to the Moon and demands greater loss of mission reliability and numerous other requirements associated with human rating that were not applied to the original J-2. As a result, the J-2X must operate at much higher temperatures, pressures, and flow rates than the heritage J-2, making it one of the highest performing gas generator cycle engines ever built, approaching the efficiency of more complex stage combustion engines. Development is focused on early risk mitigation, component and subassembly test, and engine system test. The development plans include testing engine components, including the subscale injector, main igniter, powerpack assembly (turbopumps, gas generator and associated ducting and structural mounts), full-scale gas generator, valves, and control software with hardware-in-the-loop. Testing expanded in 2007, accompanied by the refinement of the design through several key milestones. This paper discusses those 2007 tests and milestones, as well as updates key developments in 2008.

Byrd, THomas

2008-01-01

11

From Paper to Production: An Update on NASA's Upper Stage Engine for Exploration  

NASA Technical Reports Server (NTRS)

The NASA/industry team responsible for developing the J-2X Upper Stage Engine for the Constellation Program's Ares I and Ares V launch vehicles has made significant progress toward moving the design from paper to production during the past year. The J-2X exemplifies the Constellation goal of using proven technology and experience from more than 50 years of United States spaceflight experience and seeking where possible to employ common hardware in the Ares I crew launch vehicle and the Ares V cargo launch vehicle. The J-2X will power the Ares I upper stage to place the Orion crew vehicle in orbit. For the Ares V, the J-2X will place the Earth departure stage (EDS) and lunar lander in orbit and later re-start to send the Orion and lander to the Moon. Pratt & Whitney Rocketdyne (PWR) is under contract to develop and produce the engine, leveraging its flight-proven LH2/LOX, gas generator cycle J-2 and RS-68 engine capabilities, recent experience with the X-33 aerospike XRS-2200 engine, and development knowledge of the J-2S tap-off cycle engine. The J-2X employs a gas generator operating cycle designed to produce 294,000 pounds of thrust in primary operating mode for the Ares I and Ares V ascent phases. It also has a secondary mode, during which it operates at 80 percent thrust by altering its mixture ratio to perform the TLI burn for the Ares V lunar sortie and lunar cargo missions. The J-2X development philosophy is based on proven hardware, an aggressive development schedule, and early risk reduction. NASA Marshall Space Flight Center (MSFC) and PWR began development of the J-2X in June 2006. The government/industry team of more than 600 people within NASA and PWR successfully completed the Critical Design Review (CDR) in November 2008, following extensive risk mitigation testing. The team is working toward a first flight of the J-2X on the Orion 1 mission in 2014. This paper will discuss the J-2X development background and provide top-level information on design and testing to date. Details will be provided on overcoming challenges such as gas generator instability, turbine blade life, and nozzle extension selection and materials.

Kynard, Mike

2010-01-01

12

Advanced space engine preliminary design. [liquid hydrogen/liquid oxygen upper stage engine for space tug application  

NASA Technical Reports Server (NTRS)

Analysis and design of an optimum LO2/LH2, combustion topping cycle, 88,964 Newtons (20,000-pound) thrust, liquid rocket engine was conducted. The design selected is well suited to high-energy, upper-stage engine applications such as the Space Tug and embodies features directed toward optimization of vehicle performance. A configuration selection was conducted based on prior Air Force Contracts, and additional criteria for optimum stage performance. Following configuration selection, analyses and design of the major components and engine systems were conducted to sufficient depth to provide layout drawings suitable for subsequent detailing. In addition, engine packaging to a common interface and a retractable nozzle concept were defined. Alternative development plans and related costs were also established. The design embodies high-performance, low-weight, low NPSH requirements (saturated propellant inlet conditions at start), idle-mode operation, and autogenous pressurization. The design is the result of the significant past and current LO2/LH2 technology efforts of the NASA centers and the Air Force, as well as company-funded programs.

Zachary, A. T.

1973-01-01

13

A 20k payload launch vehicle fast track development concept using an RD-180 engine and a Centaur upper stage  

NASA Technical Reports Server (NTRS)

A launch vehicle concept to deliver 20,000 lb of payload to a 100-nmi orbit has been defined. A new liquid oxygen/kerosene booster powered by an RD-180 engine was designed while using a slightly modified Centaur upper stage. The design, development, and test program met the imposed 40-mo schedule by elimination of major structural testing by increased factors of safety and concurrent engineering concepts. A growth path to attain 65,000 lb of payload is developed.

Toelle, Ronald (compiler)

1995-01-01

14

CRYOGENIC UPPER STAGE SYSTEM SAFETY  

NASA Technical Reports Server (NTRS)

NASA s Exploration Initiative will require development of many new systems or systems of systems. One specific example is that safe, affordable, and reliable upper stage systems to place cargo and crew in stable low earth orbit are urgently required. In this paper, we examine the failure history of previous upper stages with liquid oxygen (LOX)/liquid hydrogen (LH2) propulsion systems. Launch data from 1964 until midyear 2005 are analyzed and presented. This data analysis covers upper stage systems from the Ariane, Centaur, H-IIA, Saturn, and Atlas in addition to other vehicles. Upper stage propulsion system elements have the highest impact on reliability. This paper discusses failure occurrence in all aspects of the operational phases (Le., initial burn, coast, restarts, and trends in failure rates over time). In an effort to understand the likelihood of future failures in flight, we present timelines of engine system failures relevant to initial flight histories. Some evidence suggests that propulsion system failures as a result of design problems occur shortly after initial development of the propulsion system; whereas failures because of manufacturing or assembly processing errors may occur during any phase of the system builds process, This paper also explores the detectability of historical failures. Observations from this review are used to ascertain the potential for increased upper stage reliability given investments in integrated system health management. Based on a clear understanding of the failure and success history of previous efforts by multiple space hardware development groups, the paper will investigate potential improvements that can be realized through application of system safety principles.

Smith, R. Kenneth; French, James V.; LaRue, Peter F.; Taylor, James L.; Pollard, Kathy (Technical Monitor)

2005-01-01

15

Upper-Stage Flight Experiment  

NASA Technical Reports Server (NTRS)

For propulsion applications that require that the propellants are storable for long periods, have a high density impulse, and are environmentally clean and non-toxic, the best choice is a combination of high-concentration hydrogen peroxide (High Test Peroxide, or HTP) and a liquid hydrocarbon (LHC) fuel. The HTP/LHC combination is suitable for low-cost launch vehicles, space taxi and space maneuvering vehicles, and kick stages. Orbital Sciences Corporation is under contract with the NASA Marshall Space Flight Center in cooperation with the Air Force Research Lab to design, develop and demonstrate a new low-cost liquid upper stage based on HTP and JP-8. The Upper Stage Flight Experiment (USFE) focuses on key technologies necessary to demonstrate the operation of an inherently simple propulsion system with an innovative, state-of-the-art structure. Two key low-cost vehicle elements will be demonstrated - a 10,000 lbf thrust engine and an integrated composite tank structure. The suborbital flight test of the USFE is scheduled for 2001. Preceding the flight tests are two major series of ground tests at NASA Stennis Space Center and a subscale tank development program to identify compatible composite materials and to verify their compatibility over long periods of time. The ground tests include a thrust chamber development test series and an integrated stage test. This paper summarizes the results from the first phase of the thrust chamber development tests and the results to date from the tank material compatibility tests. Engine and tank configurations that meet the goals of the program are described.

Anderson, W. E.; Boxwell, R.; Crockett, D. V.; Ross, R.; Lewis, T.; McNeal, C.; Verdarame, K.

1999-01-01

16

Ares I Upper Stage Fabrication  

NASA Technical Reports Server (NTRS)

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. In this HD video image, processes for upper stage barrel fabrication are talking place. The aluminum panels are manufacturing process demonstration articles that will undergo testing until perfected. The panels are built by AMRO Manufacturing located in El Monte, California. (Highest resolution available)

2007-01-01

17

Ares I Upper Stage Fabrication  

NASA Technical Reports Server (NTRS)

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. This HD video image depicts a manufactured aluminum panel that will be used to fabricate the Ares I upper stage barrel, undergoing a confidence panel test. In this test, the bent aluminum is stressed to breaking point and thoroughly examined. The panels are manufactured by AMRO Manufacturing located in El Monte, California.

2007-01-01

18

Ares I Upper Stage Fabrication  

NASA Technical Reports Server (NTRS)

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. This HD video image depicts a manufactured panel that will be used for the Ares I upper stage barrel fabrication. The aluminum panels are manufacturing process demonstration articles that will undergo testing until perfected. The panels are built by AMRO Manufacturing located in El Monte, California. (Highest resolution available)

2007-01-01

19

Space Launch System Upper Stage Technology Assessment  

NASA Technical Reports Server (NTRS)

The Space Launch System (SLS) is envisioned as a heavy-lift vehicle that will provide the foundation for future beyond low-Earth orbit (LEO) exploration missions. Previous studies have been performed to determine the optimal configuration for the SLS and the applicability of commercial off-the-shelf in-space stages for Earth departure. Currently NASA is analyzing the concept of a Dual Use Upper Stage (DUUS) that will provide LEO insertion and Earth departure burns. This paper will explore candidate in-space stages based on the DUUS design for a wide range of beyond LEO missions. Mission payloads will range from small robotic systems up to human systems with deep space habitats and landers. Mission destinations will include cislunar space, Mars, Jupiter, and Saturn. Given these wide-ranging mission objectives, a vehicle-sizing tool has been developed to determine the size of an Earth departure stage based on the mission objectives. The tool calculates masses for all the major subsystems of the vehicle including propellant loads, avionics, power, engines, main propulsion system components, tanks, pressurization system and gases, primary structural elements, and secondary structural elements. The tool uses an iterative sizing algorithm to determine the resulting mass of the stage. Any input into one of the subsystem sizing routines or the mission parameters can be treated as a parametric sweep or as a distribution for use in Monte Carlo analysis. Taking these factors together allows for multi-variable, coupled analysis runs. To increase confidence in the tool, the results have been verified against two point-of-departure designs of the DUUS. The tool has also been verified against Apollo moon mission elements and other manned space systems. This paper will focus on trading key propulsion technologies including chemical, Nuclear Thermal Propulsion (NTP), and Solar Electric Propulsion (SEP). All of the key performance inputs and relationships will be presented and discussed in light of the various missions. For each mission there are several trajectory options and each will be discussed in terms of delta-v required and transit duration. Each propulsion system will be modeled, sized, and judged based on their applicability to the whole range of beyond LEO missions. Criteria for scoring will include the resulting dry mass of the stage, resulting propellant required, time to destination, and an assessment of key enabling technologies. In addition to the larger metrics, this paper will present the results of several coupled sensitivity studies. The ultimate goals of these tools and studies are to provide NASA with the most mass-, technology-, and cost-effective in-space stage for its future exploration missions.

Holladay, Jon; Hampton, Bryan; Monk, Timothy

2014-01-01

20

Upper stage alternatives for the shuttle era  

NASA Technical Reports Server (NTRS)

The status and general characteristics of Space Shuttle upper stages now in use or in development, as well as new vehicle possibilities are examined. Upper stage requirements for both civil and Department of Defense missions, categorized generally into near-term (early and mid-1980's), mid-term (late 1980's to mid-1990's), and far-term (late 1990's and beyond) are discussed. Finally, the technical, schedule and cost impact of alternative ways in which these requirements could be met are examined, and a number of conclusions and recommendations are reached.

1981-01-01

21

Integrated Solar Upper Stage (ISUS) mission trades  

Microsoft Academic Search

Solar thermal propulsion and propulsion\\/power systems were identified as key technologies in the operational effectiveness and cost comparison study (OECS) sponsored by Phillips Laboratory (PL). These technologies were found to be pervasively cost effective with short transfer times and very good performance across a wide range of missions. The on-going Integrated Solar Upper Stage (ISUS) Program sponsored by PL represents

P. Frye

1996-01-01

22

Integrated Solar Upper Stage (ISUS) mission analysis  

Microsoft Academic Search

Solar thermal propulsion and propulsion\\/power systems were identified as key technologies by the Operational Effectiveness and Cost Comparison Study. These technologies were found to be pervasively cost effective with short transfer times and very good performance across a wide range of missions (Feuchter 1996). The on-going Integrated Solar Upper Stage (ISUS) Program sponsored by Phillips Laboratory represents development of one

Patrick Frye

1997-01-01

23

STS spin-stabilized upper stage study (study 2.6). Volume 1: Executive summary  

NASA Technical Reports Server (NTRS)

Spinning solid propellant upper stage rocket engines designed for geosynchronous satellite payloads are investigated. Factors considered include: impact of the spinning stages on the payloads; applicability to 1981-1991 NASA mission model; and cost effectiveness.

1975-01-01

24

Inertial Upper Stage booster in VPF  

NASA Technical Reports Server (NTRS)

Workers in the Vertical Processing Facility oversee and control the lowering of the Inertial Upper Stage (IUS) booster into a workstand for preflight processing. The IUS will be attached to the Tracking and Data Relay Satellite (TDRS-G), which will be deployed by the Space Shuttle Discovery on Mission STS-70. The IUS is scheduled to be mated to the TDRS satellite later in April. Liftoff of STS-70 is slated for no earlier than June 8.

1995-01-01

25

Inertial Upper Stage (IUS) software analysis  

NASA Technical Reports Server (NTRS)

The Inertial Upper Stage (IUS) System, an extension of the Space Transportation System (STS) operating regime to include higher orbits, orbital plane changes, geosynchronous orbits, and interplanetary trajectories is presented. The IUS software design, the IUS software interfaces with other systems, and the cost effectiveness in software verification are described. Tasks of the IUS discussed include: (1) design analysis; (2) validation requirements analysis; (3) interface analysis; and (4) requirements analysis.

Grayson, W. L.; Nickel, C. E.; Rose, P. L.; Singh, R. P.

1979-01-01

26

Staging or upper stage reignition for GEO missions  

NASA Astrophysics Data System (ADS)

Geostationary orbit will remain in the near and far future one of the most frequently used for several applications including, mainly, telecommunications. For the time being the GEO satcoms are injected by intermediate, heavy or super heavy class launch vehicles, LV, using quasi standard procedures: low altitude injection on a geostationary transfer orbit, ballistic phase of at least five and a half hour, followed by an apogee manoeuvre (or boost) to reach GEO. Apogee boost is most of the time provided by the propulsive system of the satellite, if this one uses liquid propellant in an integrated system performing final injection and house-keeping for the whole life (up to 15 years) of the satellite. The current launch vehicle features generally a cryogenic (LOX/LH2) or semi-cryogenic (LOX/Kerosene) upper stage having a better Isp than the Isp of the satellite propulsive system: The possibility to provide the apogee boost by the LV upper stage seems attractive. Another possibility is to put on the top of the upper stage an other small stage, or module having the function of kick-stage, as it was done earlier when solid propellant stages were used for this apogee manoeuvre. This presentation will describe the pros and cons of this various choices for single but also dual launches in GTO/GEO, and also will address future new injection scheme, providing new transportation services to satellites featuring advanced propulsive systems such as electric, plasmic or thermo-solar thrusters, requiring other transfer orbits like MEO, GTO+ and super GTO+.

Duret, François

2002-07-01

27

Integrated Solar Upper Stage (ISUS) mission analysis  

NASA Astrophysics Data System (ADS)

Solar thermal propulsion and propulsion/power systems were identified as key technologies by the Operational Effectiveness and Cost Comparison Study. These technologies were found to be pervasively cost effective with short transfer times and very good performance across a wide range of missions (Feuchter 1996). The on-going Integrated Solar Upper Stage (ISUS) Program sponsored by Phillips Laboratory represents development of one such solar thermal propulsion/power system. This paper presents conceptual designs, mission analysis results, and trade study results for a system evaluation of ISUS for future military payloads. These payloads primarily include high power communication satellites for geo-synchronous equatorial orbit (GEO) applications.

Frye, Patrick

1997-01-01

28

Delta interim upper stage system study. Volume 2: Technical report  

Microsoft Academic Search

The Space Shuttle System will require an upper stage (Space Tug, or OOS - Orbit-to-Orbit Shuttle) to achieve maximum effectiveness. A reusable upper stage, although highly desirable, requires a greater initial cash outlay, which would compete for early Shuttle development program funds. Hence, an expendable upper stage, to be used in the interim, has been the subject of various government

R. P. Dawson; J. F. Meyers; R. C. Doiron; R. G. Monger

1975-01-01

29

Commercial launch vehicles and upper stages  

NASA Technical Reports Server (NTRS)

Since the beginning of the space age in October 1957, a family of expendable launch vehicles, capable of launching a wide range of payloads, was developed along with the Space Shuttle and a number of upper stages. A brief description is presented of selected orbits which have proved to be most useful for initial or conceptual understanding of space operations, taking into account direct injection and Hohman transfers, and synchronous and sun-synchronous orbits. Early American boosters are discussed along with current expendable launch vehicles, giving attention to the Vanguard, Redstone and Juno, Saturn 1B and Saturn V, Scout, the Atlas booster, Atlas Centaur, Delta, Titan IIIC, and Ariane. Details regarding the Space Shuttle are considered along with PAM-D, PAM-A, PAM-DII, TOS, IUS, Centaur-G, and Syncom-IV and Intelsat-VI.

Mahon, J.; Wild, J.

1984-01-01

30

Integrated Solar Upper Stage Technical Support  

NASA Technical Reports Server (NTRS)

NASA Lewis Research Center is participating in the Integrated Solar Upper Stage (ISUS) program. This program is a ground-based demonstration of an upper stage concept that will be used to generate both solar propulsion and solar power. Solar energy collected by a primary concentrator is directed into the aperture of a secondary concentrator and further concentrated into the aperture of a heat receiver. The energy stored in the receiver-absorber-converter is used to heat hydrogen gas to provide propulsion during the orbital transfer portion of the mission. During the balance of the mission, electric power is generated by thermionic diodes. Several materials issues were addressed as part of the technical support portion of the ISUS program, including: 1) Evaluation of primary concentrator coupons; 2) Evaluation of secondary concentrator coupons; 3) Evaluation of receiver-absorber-converter coupons; 4) Evaluation of in-test witness coupons. Two different types of primary concentrator coupons were evaluated from two different contractors-replicated coupons made from graphite-epoxy composite and coupons made from microsheet glass. Specular reflectivity measurements identified the replicated graphite-epoxy composite coupons as the primary concentrator material of choice. Several different secondary concentrator materials were evaluated, including a variety of silver and rhodium reflectors. The specular reflectivity of these materials was evaluated under vacuum at temperatures up to 800 C. The optical properties of several coupons of rhenium on graphite were evaluated to predict the thermal performance of the receiver-absorber-converter. Finally, during the ground test demonstration, witness coupons placed in strategic locations throughout the thermal vacuum facility were evaluated for contaminants. All testing for the ISUS program was completed successfully in 1997. Investigations related to materials issues have proven helpful in understanding the operation of the test article, leading to a potential ISUS flight test in 2002.

Jaworske, Donald A.

1998-01-01

31

Dynamic Mechanical Analysis (DMA) to Help Characterize Vespel SP-211 Polyimide Material for Use as a 750 F Valve Seal on the Ares I Upper Stage J-2X Engine  

NASA Technical Reports Server (NTRS)

DuPont(tm) Vespel(R) SP-211 polyimide was selected as the top candidate seal material for use in the Oxidizer Turbine Bypass Valve (OTBV) on NASA's Ares I Upper Stage J-2X engine. In the OTBV, the seal material would get exposed to temperatures up to 750degF for approx 10 minutes at a time. Although the J-2X engine is not reusable, the valve material could be exposed to multiple temperature cycles up to 750degF during engine operation. The Constellation Program that included the Ares I rocket was eventually cancelled, but the J-2X engine was chosen for continued use for development of NASA's Space Launch System (SLS). The SLS is a heavy-lift launch vehicle that will have capability of taking astronauts and hardware to the Moon, Mars and asteroids. Dynamic mechanical analysis (DMA) was one of several test techniques used to characterize Vespel SP-211 to help prove its worthiness for use on the OTBV of the J-2X engine.

Wingard, Doug

2013-01-01

32

Dynamic Mechanical Analysis (DMA) to Help Characterize Vespel SP-211 Polyimide Material for Use as a 750 F Valve Seal on the Ares I Upper Stage J-2X Engine  

NASA Technical Reports Server (NTRS)

DuPont (TM) Vespel (R) SP-211 polyimide was selected as the top candidate seal material for use in the Oxidizer Turbine Bypass Valve (OTBV) on NASA's Ares I Upper Stage J-2X engine. In the OTBV, the seal material would get exposed to temperatures up to 750degF for approx 10 minutes at a time. Although the J-2X engine is not reusable, the valve material could be exposed to multiple temperature cycles up to 750 F during engine operation. The Constellation Program that included the Ares I rocket was eventually cancelled, but the J-2X engine was chosen for continued use for development of NASA's Space Launch System (SLS). The SLS is a heavy-lift launch vehicle that will have capability of taking astronauts and hardware to the Moon, Mars and asteroids. Dynamic mechanical analysis (DMA) was one of several test techniques used to characterize Vespel SP-211 to help prove its worthiness for use on the OTBV of the J-2X engine.

Wingard, Doug

2013-01-01

33

Staged combustion with piston engine and turbine engine supercharger  

DOEpatents

A combustion engine method and system provides increased fuel efficiency and reduces polluting exhaust emissions by burning fuel in a two-stage combustion system. Fuel is combusted in a piston engine in a first stage producing piston engine exhaust gases. Fuel contained in the piston engine exhaust gases is combusted in a second stage turbine engine. Turbine engine exhaust gases are used to supercharge the piston engine.

Fischer, Larry E. (Los Gatos, CA); Anderson, Brian L. (Lodi, CA); O'Brien, Kevin C. (San Ramon, CA)

2011-11-01

34

Upper Stage Tank Thermodynamic Modeling Using SINDA/FLUINT  

NASA Technical Reports Server (NTRS)

Modeling to predict the condition of cryogenic propellants in an upper stage of a launch vehicle is necessary for mission planning and successful execution. Traditionally, this effort was performed using custom, in-house proprietary codes, limiting accessibility and application. Phenomena responsible for influencing the thermodynamic state of the propellant have been characterized as distinct events whose sequence defines a mission. These events include thermal stratification, passive thermal control roll (rotation), slosh, and engine firing. This paper demonstrates the use of an off the shelf, commercially available, thermal/fluid-network code to predict the thermodynamic state of propellant during the coast phase between engine firings, i.e. the first three of the above identified events. Results of this effort will also be presented.

Schallhorn, Paul; Campbell, D. Michael; Chase, Sukhdeep; Piquero, Jorge; Fortenberry, Cindy; Li, Xiaoyi; Grob, Lisa

2006-01-01

35

Camera Layout Design for the Upper Stage Thrust Cone  

NASA Technical Reports Server (NTRS)

Engineers in the Integrated Design and Analysis Division (EV30) use a variety of different tools to aid in the design and analysis of the Ares I vehicle. One primary tool in use is Pro-Engineer. Pro-Engineer is a computer-aided design (CAD) software that allows designers to create computer generated structural models of vehicle structures. For the Upper State thrust cone, Pro-Engineer was used to assist in the design of a layout for two camera housings. These cameras observe the separation between the first and second stage of the Ares I vehicle. For the Ares I-X, one standard speed camera was used. The Ares I design calls for two separate housings, three cameras, and a lighting system. With previous design concepts and verification strategies in mind, a new layout for the two camera design concept was developed with members of the EV32 team. With the new design, Pro-Engineer was used to draw the layout to observe how the two camera housings fit with the thrust cone assembly. Future analysis of the camera housing design will verify the stability and clearance of the camera with other hardware present on the thrust cone.

Wooten, Tevin; Fowler, Bart

2010-01-01

36

New upper stage propulsion concept for future launchers  

NASA Astrophysics Data System (ADS)

A pressure-fed system is leading to a stage easy to operate, reliable, needing no costly solutions (expander engine, boost pumps). On the other hand, many R&D programs are going on all ceramic liquid engines, engines cooled by "effusion" (DLR), Transpiration (PTAH-SOCAR from MBDA), Film or Trim (Astrium, Snecma), so very light engine may be offered on the market in the close future. Operating to relatively low pressure the specific impulse is slightly lower than a conventional one with a turbomachine (expander type or other) and the structural index lightly less interesting: a concept with the LOX tank nested inside the fuel tank with a scrolling common bulkhead appears easily usable for LOX/methane stage due to the fact that the two propellants are liquids in the same range of temperature and may lead to an interesting mass saving. Even if such an upper stage may lead to a dramatic increase of the performance of a small launch vehicle such as Vega (replacement of Z9 and AVUM), the aim of this presentation is mainly to show the interest of special tools to make the very first evaluation of the interest of a new solution. The Inner Arch developed for the CNES DLA two softwares: One dedicated to solid propulsion projects: APSOL. One dedicated to liquid propulsion projects: ELIS. A third one, PERFOL, is used to optimize the trajectory and the propulsion parameters. The paper will describe the main software used for this study and illustrate the interest of the approach.

Calabro, Max; Talbot, Christophe

2008-07-01

37

NASA Ares I Crew Launch Vehicle Upper Stage Overview  

NASA Technical Reports Server (NTRS)

By incorporating rigorous engineering practices, innovative manufacturing processes and test techniques, a unique multi-center government/contractor partnership, and a clean-sheet design developed around the primary requirements for the International Space Station (ISS) and Lunar missions, the Upper Stage Element of NASA's Crew Launch Vehicle (CLV), the "Ares I," is a vital part of the Constellation Program's transportation system. Constellation's exploration missions will include Ares I and Ares V launch vehicles required to place crew and cargo in low-Earth orbit (LEO), crew and cargo transportation systems required for human space travel, and transportation systems and scientific equipment required for human exploration of the Moon and Mars. Early Ares I configurations will support ISS re-supply missions. A self-supporting cylindrical structure, the Ares I Upper Stage will be approximately 84' long and 18' in diameter. The Upper Stage Element is being designed for increased supportability and increased reliability to meet human-rating requirements imposed by NASA standards. The design also incorporates state-of-the-art materials, hardware, design, and integrated logistics planning, thus facilitating a supportable, reliable, and operable system. With NASA retiring the Space Shuttle fleet in 2010, the success of the Ares I Project is essential to America's continued leadership in space. The first Ares I test flight, called Ares I-X, is scheduled for 2009. Subsequent test flights will continue thereafter, with the first crewed flight of the Crew Exploration Vehicle (CEV), "Orion," planned for no later than 2015. Crew transportation to the ISS will follow within the same decade, and the first Lunar excursion is scheduled for the 2020 timeframe.

McArthur, J. Craig

2008-01-01

38

Guidance and controls for an interim upper stage \\/IUS  

Microsoft Academic Search

The adaptability of the Titan Transtage (the upper stage of the Titan IIIC launch vehicle) as a low risk interim upper stage (IUS) in the Space Transportation System is examined. The object of the study is to determine whether the Titan Transtage is compatible with the Shuttle and to provide operational data for the design of a new Space Tug.

R. B. Schroer

1975-01-01

39

The IRIS-GUS Shuttle Borne Upper Stage System  

NASA Technical Reports Server (NTRS)

This paper describes the Italian Research Interim Stage - Gyroscopic Upper Stage (IRIS-GUS) upper stage system that will be used to launch NASA's Triana Observatory from the Space Shuttle. Triana is a pathfinder earth science mission being executed on rapid schedule and small budget, therefore the mission's upper stage solution had to be a system that could be fielded quickly at relatively low cost and risk. The building of the IRIS-GUS system wa necessary because NASA lost the capability to launch moderately sized upper stage missions fro the Space Shuttle when the PAM-D system was retired. The IRIS-GUS system restores this capability. The resulting system is a hybrid which mates the existing, flight proven IRIS (Italian Research Interim Stage) airborne support equipment to a new upper stage, the Gyroscopic Upper Stage (GUS) built by the GSFC for Triana. Although a new system, the GUS exploits flight proven hardware and design approaches in most subsystems, in some cases implementing proven design approaches with state-of-the-art electronics. This paper describes the IRIS-GUS upper stage system elements, performance capabilities, and payload interfaces.

Tooley, Craig; Houghton, Martin; Bussolino, Luigi; Connors, Paul; Broudeur, Steve (Technical Monitor)

2002-01-01

40

Ares I-X Upper Stage Simulator Residual Stress Analysis  

NASA Technical Reports Server (NTRS)

The structural analyses described in the present report were performed in support of the NASA Engineering and Safety Center (NESC) Critical Initial Flaw Size (CIFS) assessment for the Ares I-X Upper Stage Simulator (USS) common shell segment. An independent assessment was conducted to determine the critical initial flaw size (CIFS) for the flange-to-skin weld in the Ares I-X Upper Stage Simulator (USS). The Ares system of space launch vehicles is the US National Aeronautics and Space Administration s plan for replacement of the aging space shuttle. The new Ares space launch system is somewhat of a combination of the space shuttle system and the Saturn launch vehicles used prior to the shuttle. Here, a series of weld analyses are performed to determine the residual stresses in a critical region of the USS. Weld residual stresses both increase constraint and mean stress thereby having an important effect on fatigue and fracture life. The results of this effort served as one of the critical load inputs required to perform a CIFS assessment of the same segment.

Raju, Ivatury S.; Brust, Frederick W.; Phillips, Dawn R.; Cheston, Derrick

2008-01-01

41

Staged direct injection diesel engine  

DOEpatents

A diesel engine having staged injection for using lower cetane number fuels than No. 2 diesel fuel. The engine includes a main fuel injector and a pilot fuel injector. Pilot and main fuel may be the same fuel. The pilot injector injects from five to fifteen percent of the total fuel at timings from 20.degree. to 180.degree. BTDC depending upon the quantity of pilot fuel injected, the fuel cetane number and speed and load. The pilot fuel injector is directed toward the centerline of the diesel cylinder and at an angle toward the top of the piston, avoiding the walls of the cylinder. Stratification of the early injected pilot fuel is needed to reduce the fuel-air mixing rate, prevent loss of pilot fuel to quench zones, and keep the fuel-air mixture from becoming too fuel lean to become effective. In one embodiment, the pilot fuel injector includes a single hole for injection of the fuel and is directed at approximately 48.degree. below the head of the cylinder.

Baker, Quentin A. (San Antonio, TX)

1985-01-01

42

Upper stages using liquid propulsion and metallized propellants  

NASA Technical Reports Server (NTRS)

Metallized propellants are liquid propellants with a metal additive suspended in a gelled fuel. Typically, aluminum particles are the metal additive. These propellants increase the density and/or the specific impulse of the propulsion system. Using metallized propellants for volume- and mass-constrained upper stages can deliver modest increases in performance for low Earth orbit to geosynchronous Earth orbit (LEO-GEO) and other Earth-orbital transfer missions. However, using metallized propellants for planetary missions can deliver great reductions in flight time with a single-stage, upper-stage system. Tradeoff studies comparing metallized propellant stage performance with nonmetallized upper stages and the Inertial Upper Stage (IUS) are presented. These upper stages, launched from the STS and STS-C, are both one- and two-stage vehicles that provide the added energy to send payloads to high altitude orbits and onto interplanetary trajectories that are unattainable with only the Space Transportation System (STS) and the Space Transportation System-Cargo (STS-C). The stage designs are controlled by the volume and the mass constraints of the STS and STS-C launch vehicles. The influences of the density and specific impulse increases enabled by metallized propellants are examined for a variety of different stage and propellant combinations.

Palaszewski, Bryan A.

1992-01-01

43

Which way to Shuttle upper stages  

Microsoft Academic Search

Suitable approaches for obtaining a cost-efficient space transportation system which in supplementing the Space Shuttle will permit payload insertion into high-altitude orbits are discussed. Attention is given to a low-cost geosynchronous payload deployment\\/retrieval propulsion system. The system comprises two expendable solid-rocket stages, one for the perigee and one for the apogee kick. It is pointed out that the perigee and

A. O. Tischler

1975-01-01

44

IUS (Inertial Upper Stage)/SRM-2 Nozzle Thermal Assessment.  

National Technical Information Service (NTIS)

During the space shuttle mission (STS-6) on April 5, 1983, the inertial upper stage/tracking data relay satellite-A payload experienced a loss of control at approximately 85 seconds into the planned 105 second burn of the second stage. The anomaly was rev...

K. E. McCoy J. L. Vaniman

1984-01-01

45

Overview of the Crew Launch Vehicle Upper Stage  

NASA Technical Reports Server (NTRS)

The overview begins with the bold vision for space exploration set out by President Bush in 2004. A brief description of the proposed systems architecture is presented along with an animation showing the various stages and phases of a mission. The overview concludes with latest roadmaps for the Upper Stage.

Funk, Joan G.

2006-01-01

46

Lessons Learned from Ares I Upper Stage Structures and Thermal Design  

NASA Technical Reports Server (NTRS)

The Ares 1 Upper Stage was part of the vehicle intended to succeed the Space Shuttle as the United States manned spaceflight vehicle. Although the Upper Stage project was cancelled, there were many lessons learned that are applicable to future vehicle design. Lessons learned that are briefly detailed in this Technical Memorandum are for specific technical areas such as tank design, common bulkhead design, thrust oscillation, control of flight and slosh loads, purge and hazardous gas system. In addition, lessons learned from a systems engineering and vehicle integration perspective are also included, such as computer aided design and engineering, scheduling, and data management. The need for detailed systems engineering in the early stages of a project is emphasized throughout this report. The intent is that future projects will be able to apply these lessons learned to keep costs down, schedules brief, and deliver products that perform to the expectations of their customers.

Ahmed, Rafiq

2012-01-01

47

Reusable Agena study. Volume 1: Executive summary. [space shuttle Agena upper stage tug concept  

NASA Technical Reports Server (NTRS)

The shuttle Agena upper stage interim tug concept is based on a building block approach. These building block concepts are extensions of existing ascent Agena configurations. Several current improvements, have been used in developing the shuttle/Agena upper stage concepts. High-density acid is used as the Agena upper stage oxidizer. The baffled injector is used in the main engine. The DF-224 is a fourth generation computer currently in development and will be flight proven in the near future. The Agena upper stage building block concept uses the current Agena as a baseline, adds an 8.5-inch (21.6 cm) extension to the fuel tank for optimum mixture ratio, uses monomethyl hydrazine as fuel, exchanges a 150:1 nozzle extension for the existing 45:1, exchanges an Autonetics DF-224 for the existing Honeywell computer, and adds a star sensor for guidance update. These modifications to the current Agena provide a 5-foot (1.52m) diameter shuttle/Agena upper stage that will fly all Vandenberg Air Force Base missions in the reusable mode without resorting to a kick motor. The delta V velocity of the Agena is increased by use of a strap-on propellant tank option. This option provides a shuttle/Agena upper stage with the capability to place almost 3900 pounds (1769 kg) into geosynchronous orbit (24 hour period) without the aid of kick motors.

1974-01-01

48

Optimization, an Important Stage of Engineering Design  

ERIC Educational Resources Information Center

A number of leaders in technology education have indicated that a major difference between the technological design process and the engineering design process is analysis and optimization. The analysis stage of the engineering design process is when mathematical models and scientific principles are employed to help the designer predict design…

Kelley, Todd R.

2010-01-01

49

Ares I Crew Launch Vehicle Upper Stage Element Overview.  

National Technical Information Service (NTIS)

This viewgraph presentation gives an overview of NASA's Ares I Crew Launch Vehicle Upper Stage Element. The topics incluse: 1) What is NASA s Mission.; 2) NASA s Exploration Roadmap What is our time line.; 3) Building on a Foundation of Proven Technologie...

J. C. McArthur

2008-01-01

50

Comparative evaluation of existing expendable upper stages for space shuttle  

NASA Technical Reports Server (NTRS)

The use of existing expendable upper stages in the space shuttle during its early years of operation is evaluated. The Burner 2, Scout, Delta, Agena, Transtage, and Centaur were each studied under contract by their respective manufacturers to determine the extent and cost of the minimum modifications necessary to integrate the stage with the shuttle orbiter. A comparative economic analysis of thirty-five different families of these stages is discussed. Results show that the overall transportation system cost differences between many of the families are quite small. However, by considering several factors in addition to cost, it is possible to select one family as being representative of the capability of the minimum modification existing stage approach. The selected family meets all of the specified mission requirements during the early years of shuttle operation.

Weyers, V. J.; Sagerman, G. D.; Borsody, J.; Lubick, R. J.

1974-01-01

51

Reusable launch vehicles, enabling technology for the development of advanced upper stages and payloads  

NASA Astrophysics Data System (ADS)

In the near future there will be classes of upper stages and payloads that will require initial operation at a high-earth orbit to reduce the probability of an inadvertent reentry that could result in a detrimental impact on humans and the biosphere. A nuclear propulsion system, such as was being developed under the Space Nuclear Thermal Propulsion (SNTP) Program, is an example of such a potential payload. This paper uses the results of a reusable launch vehicle (RLV) study to demonstrate the potential importance of a Reusable Launch Vehicle (RLV) to test and implement an advanced upper stage (AUS) or payload in a safe orbit and in a cost effective and reliable manner. The RLV is a horizontal takeoff and horizontal landing (HTHL), two-stage-to-orbit (TSTO) vehicle. The results of the study shows that an HTHL is cost effective because it implements airplane-like operation, infrastructure, and flight operations. The first stage of the TSTO is powered by Rocket-Based-Combined-Cycle (RBCC) engines, the second stage is powered by a LOX/LH rocket engine. The TSTO is used since it most effectively utilizes the capability of the RBCC engine. The analysis uses the NASA code POST (Program to Optimize Simulated Trajectories) to determine trajectories and weight in high-earth orbit for AUS/advanced payloads. Cost and reliability of an RLV versus current generation expandable launch vehicles are presented.

Metzger, John D.

1998-01-01

52

Propellant Management in Booster and Upper Stage Propulsion Systems  

NASA Technical Reports Server (NTRS)

A summary review of some of the technical issues which surround the design of the propulsion systems for Booster and Upper Stage systems are presented. The work focuses on Propellant Geyser, Slosh, and Orientation. A brief description of the concern is given with graphics which help the reader to understand the physics of the situation. The most common solutions to these problems are given with there respective advantages and disadvantages.

Fisher, Mark F.

1997-01-01

53

Overview of the Main Propulsion System for the NASA Ares I Upper Stage  

NASA Technical Reports Server (NTRS)

A functional overview of the Main Propulsion System (MPS) of the NASA Ares I Upper Stage is provided. In addition to a simple overview of the key MPS functions and design philosophies, major lessons learned are discussed. The intent is to provide a technical overview with enough detail to allow engineers outside of the MPS Integrated Product Team (IPT) to develop a rough understanding of MPS operations, components, design philosophy, and lessons learned.

Quinn, Jason E.; Swanson, Luke A.

2009-01-01

54

Maturation of enabling technologies for the next generation reignitable cryogenic upper stage  

NASA Astrophysics Data System (ADS)

Following the ESA decision in November 2008, a pre-development phase (Phase 1) of a future evolution of the Ariane 5 launcher (named Ariane 5 Midlife Evolution, A5ME) was started under Astrium Prime leadership. This upgraded version of the Ariane 5 launcher is based on an enhanced performance Upper Stage including the cryogenic re-ignitable VINCI engine. Thanks to this reignition capability, this new Upper Stage shall be "versatile" in the sense that it shall fulfil customer needs on a broader spectrum of orbits than the "standard" orbits (i.e. Geosynchronous Transfer Orbits, GTO) typically used for commercial telecommunications satellites. In order to meet the challenges of versatility, new technologies are currently being investigated. These technologies are mainly related -but not limited-to propellant management during the extended coasting phases with the related heat transfer into the tanks and the required multiple engine re-ignitions. Within the frame of the ESA Future Launchers Preparatory Programme (Period 2 Slice 1), the Cryogenic Upper Stage Technology project (CUST) aims to mature critical technologies to such a Technology Readiness Level (TRL) that they can be integrated into the baseline A5ME Upper Stage development schedule. In addition to A5ME application, these technologies can also be used on the future next generation European launcher. This paper shows the down-selection process implemented to identify the most crucial enabling technologies for a future versatile Upper Stage and gives a description of each technology finally selected for maturation in the frame of CUST. These include -amongst others-a Sandwich Common Bulkhead for the propellant tank, an external thermal insulation kit and various propellant management devices for the coasting phase. The paper also gives an overview on the related development and maturation plan including the tests to be conducted, as well as first results of the maturation activities themselves.

Mueller, Mark

55

Materials, Processes and Manufacturing in Ares 1 Upper Stage: Integration with Systems Design and Development  

NASA Technical Reports Server (NTRS)

Ares I Crew Launch Vehicle Upper Stage is designed and developed based on sound systems engineering principles. Systems Engineering starts with Concept of Operations and Mission requirements, which in turn determine the launch system architecture and its performance requirements. The Ares I-Upper Stage is designed and developed to meet these requirements. Designers depend on the support from materials, processes and manufacturing during the design, development and verification of subsystems and components. The requirements relative to reliability, safety, operability and availability are also dependent on materials availability, characterization, process maturation and vendor support. This paper discusses the roles and responsibilities of materials and manufacturing engineering during the various phases of Ares IUS development, including design and analysis, hardware development, test and verification. Emphasis is placed how materials, processes and manufacturing support is integrated over the Upper Stage Project, both horizontally and vertically. In addition, the paper describes the approach used to ensure compliance with materials, processes, and manufacturing requirements during the project cycle, with focus on hardware systems design and development.

Bhat, Biliyar N.

2008-01-01

56

Analytical Approach for Estimating Preliminary Mass of ARES I Crew Launch Vehicle Upper Stage Structural Components  

NASA Technical Reports Server (NTRS)

In January 2004, President Bush gave the National Aeronautics and Space Administration (NASA) a vision for Space Exploration by setting our sight on a bold new path to go back to the Moon, then to Mars and beyond. In response to this vision, NASA started the Constellation Program, which is a new exploration launch vehicle program. The primary mission for the Constellation Program is to carry out a series of human expeditions ranging from Low Earth Orbit to the surface of Mars and beyond for the purposes of conducting human exploration of space, as specified by the Vision for Space Exploration (VSE). The intent is that the information and technology developed by this program will provide the foundation for broader exploration activities as our operational experience grows. The ARES I Crew Launch Vehicle (CLV) has been designated as the launch vehicle that will be developed as a "first step" to facilitate the aforementioned human expeditions. The CLV Project is broken into four major elements: First Stage, Upper Stage Engine, Upper Stage (US), and the Crew Exploration Vehicle (CEV). NASA's Marshall Space Flight Center (MSFC) is responsible for the design of the CLV and has the prime responsibility to design the upper stage of the vehicle. The US is the second propulsive stage of the CLV and provides CEV insertion into low Earth orbit (LEO) after separation from the First Stage of the Crew Launch Vehicle. The fully integrated Upper Stage is a mix of modified existing heritage hardware (J-2X Engine) and new development (primary structure, subsystems, and avionics). The Upper Stage assembly is a structurally stabilized cylindrical structure, which is powered by a single J-2X engine which is developed as a separate Element of the CLV. The primary structure includes the load bearing liquid hydrogen (LH2) and liquid oxygen (LOX) propellant tanks, a Forward Skirt, the Intertank structure, the Aft Skirt and the Thrust Structure. A Systems Tunnel, which carries fluid and electrical power functions to other Elements of the CLV, is included as secondary structure. The MSFC has an overall responsibility for the integrated US element as well as structural design an thermal control of the fuel tanks, intertank, interstage, avionics, main propulsion system, Reaction Control System (RCS) for both the Upper Stage and the First Stage. MSFC's Spacecraft and Vehicle Department, Structural and Analysis Design Division is developing a set of predicted mass of these elements. This paper details the methodology, criterion and tools used for the preliminary mass predictions of the upper stage structural assembly components. In general, weight of the cylindrical barrel sections are estimated using the commercial code Hypersizer, whereas, weight of the domes are developed using classical solutions. HyperSizer is software that performs automated structural analysis and sizing optimization based on aerospace methods for strength, stability, and stiffness. Analysis methods range from closed form, traditional hand calculations repeated every day in industry to more advanced panel buckling algorithms. Margin-of-safety reporting for every potential failure provides the engineer with a powerful insight into the structural problem. Optimization capabilities include finding minimum weight panel or beam concepts, material selections, cross sectional dimensions, thicknesses, and lay-ups from a library of 40 different stiffened and sandwich designs and a database of composite, metallic, honeycomb, and foam materials. Multiple different concepts (orthogrid, isogrid, and skin stiffener) were run for multiple loading combinations of ascent design load with and with out tank pressure as well as proof pressure condition. Subsequently, selected optimized concept obtained from Hypersizer runs was translated into a computer aid design (CAD) model to account for the wall thickness tolerance, weld land etc for developing the most probable weight of the components. The flow diram summarizes the analysis steps used in developing these predicted mass.

Aggarwal, Pravin

2007-01-01

57

NDE for the ARES I Upper Stage Common Bulkhead  

NASA Technical Reports Server (NTRS)

The current design of the ARES 1 Upper Stage uses a common bulkhead to separate the liquid hydrogen and liquid oxygen tanks. The bulkhead consists of aluminum face sheets bonded to a Phenolic honeycomb core. The face sheets, or domes, are friction stir welded to Y-rings that connect the bulkhead to the barrel sections of the liquid hydrogen and liquid oxygen tanks. Load between the Y-rings is carried by an externally attached bolting ring. The development of nondestructive evaluation methods for the ARES I Upper Stage Common Bulkhead are outlined in this presentation. Methods for inspecting the various components of the bulkhead are covered focusing in on the dome skins, core-to-dome bond lines and friction stir welds as well as structural details like the fastener holes. Thermography, shearography and ultrasonic methods are discussed for the bond lines. Eddy current methods are discussed for the fastener holes and dome skins. A combination of phased array ultrasound, liquid penetrant and radiography are to being investigated for use on the friction stir welds. Keywords: Composite materials, NDE, Cryogenic structures

Walker, James

2008-01-01

58

DETAIL VIEW OF WINCHING ENGINE LOCATED AT THE UPPER TRAM ...  

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

DETAIL VIEW OF WINCHING ENGINE LOCATED AT THE UPPER TRAM TERMINAL, LOOKING NORTHEAST. THE CABLE FROM THIS ENGINE LEADS DOWN INTO THE DEEP RAVINE IN FRONT OF THE UPPER TRAM TERMINAL. IT WAS PROBABLY USED TO DRAG MATERIALS UP TOWARD THE TERMINAL WHEN THE TERMINAL WAS BEING CONSTRUCTED, OR IN TIMES OF TRAMWAY BREAKDOWN. THE DRIVE ENGINE IS IN THE BACKGROUND. TWO LONG OPERATING LEVERS FOR THE ENGINE ARE IN THE CENTER FOREGROUND. AN EXTRA SPOOL OF CABLE IS ON THE GROUND TO THE RIGHT OF THE ENGINE. A WATER PIPELINE STRETCHES ACROSS THE SLOPE IN THE BACKGROUND, CARRYING WATER TO THE UPPER MINES. SEE CA-291-37 FOR IDENTICAL B&W NEGATIVE. - Keane Wonder Mine, Park Route 4 (Daylight Pass Cutoff), Death Valley Junction, Inyo County, CA

59

DETAIL VIEW OF WINCHING ENGINE LOCATED AT THE UPPER TRAM ...  

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

DETAIL VIEW OF WINCHING ENGINE LOCATED AT THE UPPER TRAM TERMINAL LOOKING NORTHEAST. THE CABLE FROM THIS ENGINE LEADS DOWN INTO THE DEEP RAVINE IN FRONT OF THE UPPER TRAM TERMINAL. IT WAS PROBABLY USED TO DRAG MATERIALS UP TOWARD THE TERMINAL WHEN THE TERMINAL WAS BEING CONSTRUCTED, OR IN TIMES OF TRAMWAY BREAK DOWN. THE DRIVE ENGINE IS IN THE BACKGROUND. TWO LONG OPERATING LEVERS FOR THE ENGINE ARE IN THE CENTER FOREGROUND. AN EXTRA SPOOL OF CABLE IS ON THE GROUND TO THE RIGHT OF THE ENGINE. A WATER PIPELINE STRETCHES ACROSS THE SLOPE IN THE BACKGROUND, CARRYING WATER TO THE UPPER MINES. SEE CA-291-52 (CT) FOR IDENTICAL COLOR TRANSPARENCY. - Keane Wonder Mine, Park Route 4 (Daylight Pass Cutoff), Death Valley Junction, Inyo County, CA

60

Safety and Mission Assurance for In-House Design Lessons Learned from Ares I Upper Stage  

NASA Technical Reports Server (NTRS)

This viewgraph presentation identifies lessons learned in the course of the Ares I Upper Stage design and in-house development effort. The contents include: 1) Constellation Organization; 2) Upper Stage Organization; 3) Presentation Structure; 4) Lesson-Importance of Systems Engineering/Integration; 5) Lesson-Importance of Early S&MA Involvement; 6) Lesson-Importance of Appropriate Staffing Levels; 7) Lesson-Importance S&MA Team Deployment; 8) Lesson-Understanding of S&MA In-Line Engineering versus Assurance; 9) Lesson-Importance of Close Coordination between Supportability and Reliability/Maintainability; 10) Lesson-Importance of Engineering Data Systems; 11) Lesson-Importance of Early Development of Supporting Databases; 12) Lesson-Importance of Coordination with Safety Assessment/Review Panels; 13) Lesson-Implementation of Software Reliability; 14) Lesson-Implementation of S&MA Technical Authority/Chief S&MA Officer; 15) Lesson-Importance of S&MA Evaluation of Project Risks; 16) Lesson-Implementation of Critical Items List and Government Mandatory Inspections; 17) Lesson-Implementation of Critical Items List Mandatory Inspections; 18) Lesson-Implementation of Test Article Safety Analysis; and 19) Lesson-Importance of Procurement Quality.

Anderson, Joel M.

2011-01-01

61

Robotic planetary science missions enabled with small NTR engine\\/stage technologies  

Microsoft Academic Search

The high specific impulse (Isp) and engine thrust-to-weight ratio of liquid hydrogen (LH2)-cooled nuclear thermal rocket (NTR) engines makes them ideal for upper stage applications to difficult robotic planetary science missions. A small 15 thousand pound force (klbf) NTR engine using a uranium-zirconium-niobium 'ternary carbide' fuel (Isp approximately 960 seconds at approximately 3025K) developed in the Commonwealth of Independent States

Stanley K. Borowski

1995-01-01

62

Upper stage options for reusable launch vehicle {open_quotes}pop-up{close_quotes} missions  

SciTech Connect

Suborbital separation of an expendable upper stage from a small, single-stage Reusable Launch Vehicle (RLV) to transfer spacecraft into Geosynchronous Equatorial Orbit (GEO) was investigated and found to significantly increase spacecraft mass into GEO (over 400{percent}) although operational issues exist. An assessment of propulsion system options for this {open_quotes}Pop-Up{close_quotes} Mission was performed to determine the propellant combinations, stage configurations, and propulsion technologies that maximize spacecraft mass and minimize size. Propellants included earth and space storable combinations, cryogenic LH{sub 2}/LO{sub 2}, and Class 1.3 solids. Stage configurations employing cylindrical metal and overwrapped tanks, isogrid tanks, and toroidal tanks were considered. Non-toxic earth storable propellants provided comparable performance (5{endash}10{percent}) to existing storables while the use of pressure-fed engines gave about 15{percent} lower performance than pump-fed. Solid stage performance was within 5{percent} of existing storable propellants. Stages employing toroidal tanks packaged more efficiently in length constrained RLV payload bays than 4-cylindrical tank configurations, giving up to 30{percent} greater mass into GEO. The use of Extendable Exit Cones (EEC) for length constrained cases resulted in about 5{endash}10{percent} higher stage performance. {copyright} {ital 1997 American Institute of Physics.}

Eckmann, J.B.; Cotta, R.B. [Sparta Inc. Edwards AFB, California 93524 (United States); Matuszak, L.W.; Perkins, D.R. [Phillips Laboratory Edwards AFB, California 93524 (United States)

1997-01-01

63

Stir Friction Welding Used in Ares I Upper Stage Fabrication  

NASA Technical Reports Server (NTRS)

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. This HD video image depicts friction stir welding used in manufacturing aluminum panels that will fabricate the Ares I upper stage barrel. The panels are subjected to confidence tests in which the bent aluminum is stressed to breaking point and thoroughly examined. The panels are manufactured by AMRO Manufacturing located in El Monte, California. (Highest resolution available)

2007-01-01

64

Stir Friction Welding Used in Ares I Upper Stage Fabrication  

NASA Technical Reports Server (NTRS)

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. This HD video image depicts the preparation and placement of a confidence ring for friction stir welding used in manufacturing aluminum panels that will fabricate the Ares I upper stage barrel. The aluminum panels are manufactured and subjected to confidence tests during which the bent aluminum is stressed to breaking point and thoroughly examined. The panels are manufactured by AMRO Manufacturing located in El Monte, California. (Highest resolution available)

2007-01-01

65

Stir Friction Welding Used in Ares I Upper Stage Fabrication  

NASA Technical Reports Server (NTRS)

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. This HD video image depicts friction stir welding used in manufacturing aluminum panels that will fabricate the Ares I upper stage barrel. The aluminum panels are subjected to confidence panel tests during which the bent aluminum is stressed to breaking point and thoroughly examined. The panels are manufactured by AMRO Manufacturing located in El Monte, California. (Highest resolution available)

2007-01-01

66

Waterhammer Testing and Modeling of the Ares I Upper Stage Reaction Control System  

NASA Technical Reports Server (NTRS)

NASA's Ares I rocket is the agency's first step in completing the goals of the Constellation Program, which plans to deliver a new generation of space explorers into low earth orbit for future missions to the International Space Station, the moon, and other destinations within the solar system. Ares I is a two-stage rocket topped by the Orion crew capsule and its service module. The launch vehicle's First Stage is a single, five-segment reusable solid rocket booster (RSRB), derived from the Space Shuttle Program's four segment RSRB. The vehicle's Upper Stage, being designed at Marshall Space Flight Center (MSFC), is propelled by a single J-2X Main Engine fueled with liquid oxygen and liquid hydrogen. During active Upper Stage flight of the Ares I launch vehicle, the Upper Stage Reaction Control System (US ReCS) will perform attitude control operations for the vehicle. The US ReCS will provide three-axis attitude control capability (roll, pitch, and yaw) for the Upper Stage while the J-2X is not firing and roll control capability while the engine is firing. Because of the requirements imposed upon the system, the design must accommodate rapid pulsing of multiple thrusters simultaneously to maintain attitude control. In support of these design activities and in preparation for Critical Design Review, analytical models of the US ReCS propellant feed system have been developed using the Thermal Hydraulic Library of MSC.EASY5 v.2008, herein referred to as EASY5. EASY5 is a commercially available fluid system modeling package with significant history of modeling space propulsion systems. In Fall 2009, a series of development tests were conducted at MSFC on a cold-flow test article for the US ReCS, herein referred to as System Development Test Article (SDTA). A subset of those tests performed were aimed at examining the effects of waterhammer on a flight-representative system and to ensure that those effects could be quantified with analytical models and incorporated into the design of the flight system. This paper presents an overview of the test article and the test approach, along with a discussion of the analytical modeling methodology. In addition, the results of that subset of development tests, along with analytical model pre-test predictions and post-test model correlations, will also be discussed in detail.

Williams, J. Hunter; Holt, Kimberly A.

2010-01-01

67

Shuttle program standard maneuver sequences for orbiter/upper-stage separation SSUS-A, SSUS-D, and IUS  

NASA Technical Reports Server (NTRS)

Descriptions of standard post-ejection maneuver sequences for the deployment of IUS, SSUS-A, and SSUS-D upper stages from the space shuttle orbiter are presented. The sequences were designed to satisfy requirements for limiting the damage inflicted on the orbiter by upper-stage exhaust particles, subject to a further requirement for minimizing the impingement of orbiter thruster plumes on the deployed payload. In all cases it was assumed that the orbital maneuvering system engines would be used to apply the orbiter's major separation velocity increment.

Wilson, S. W.

1980-01-01

68

Solar Thermal Upper Stage Liquid Hydrogen Pressure Control Testing and Analytical Modeling  

NASA Technical Reports Server (NTRS)

The demonstration of a unique liquid hydrogen (LH2) storage and feed system concept for solar thermal upper stage was cooperatively accomplished by a Boeing/NASA Marshall Space Flight Center team. The strategy was to balance thermodynamic venting with the engine thrusting timeline during a representative 30-day mission, thereby, assuring no vent losses. Using a 2 cubic m (71 cubic ft) LH2 tank, proof-of-concept testing consisted of an engineering checkout followed by a 30-day mission simulation. The data were used to anchor a combination of standard analyses and computational fluid dynamics (CFD) modeling. Dependence on orbital testing has been incrementally reduced as CFD codes, combined with standard modeling, continue to be challenged with test data such as this.

Olsen, A. D.; Cady, E. C.; Jenkins, D. S.; Chandler, F. O.; Grayson, G. D.; Lopez, A.; Hastings, L. J.; Flachbart, R. H.; Pedersen, K. W.

2012-01-01

69

Preventing Accidental Ignition of Upper-Stage Rocket Motors  

NASA Technical Reports Server (NTRS)

A report presents a proposal to reduce the risk of accidental ignition of certain upper-stage rocket motors or other high energy hazardous systems. At present, mechanically in-line initiators are used for initiation of many rocket motors and/or other high-energy hazardous systems. Electrical shorts and/or mechanical barriers, which are the basic safety devices in such systems, are typically removed as part of final arming or pad preparations while personnel are present. At this time, static discharge, test equipment malfunction, or incorrect arming techniques can cause premature firing. The proposal calls for a modular out-of-line ignition system incorporating detonating-cord elements, identified as the donor and the acceptor, separated by an air gap. In the safe configuration, the gap would be sealed with two shields, which would prevent an accidental firing of the donor from igniting the system. The shields would be removed to enable normal firing, in which shrapnel generated by the donor would reliably ignite the acceptor to continue the ordnance train. The acceptor would then ignite a through bulkhead initiator (or other similar device), which would ignite the motor or high-energy system. One shield would be remotely operated and would be moved to the armed position when a launch was imminent or conversely returned to the safe position if the launch were postponed. In the event of failure of the remotely operated shield, the other shield could be inserted manually to safe the system.

Hickman, John; Morgan, Herbert; Cooper, Michael; Murbach, Marcus

2005-01-01

70

Hosted non-deployed payloads on upper stages for enhanced space missions  

NASA Astrophysics Data System (ADS)

With the growing market of “ hosted payloads” on Low Earth Orbit (LEO) and Geosynchronous (GEO) satellites, the capability exists to leverage the excess performance on existing upper stages to provide similar or enhanced opportunities for science experiments or low TRL instruments. Leveraging the capabilities of the Atlas V Centaur and Delta IV upper stages, Special Aerospace Services (SAS) and United Launch Alliance (ULA) are investigating hosting non-deployed systems on these existing upper stages.

Bulk, T. A.; Lindas, K.; Pitchford, B.; Szatkowski, J.

71

Solid rocket technology advancement for Space Tug and IUS applications. [Interim Upper Stage  

NASA Technical Reports Server (NTRS)

Two-burn restartable solid propellant rocket motors for the kick stage (auxiliary stage) of the Shuttle Tug, or Interim Upper Stage, are described, with details on features and test results of the ignition and quench (thrust termination) systems and procedures, fabrication of propellant and insulation, explosion hazards of propellants, and comparative data on present and future motor design. These rocket motor systems are designed for upper stage augmentation of launch vehicles and possible service in Shuttle-launched outer planet spacecraft.

Ascher, W.; Bailey, R. L.; Behm, J. W.; Gin, W.

1975-01-01

72

IUS/SPINSIM - INERTIAL UPPER STAGE SPIN STAGE SIX DEGREE OF FREEDOM SIMULATION  

NASA Technical Reports Server (NTRS)

IUS/SPINSIM was written to evaluate a proposed spinning third stage for the Inertial Upper Stage (IUS) Jupiter Mission. The third stage of the IUS was not to have altitude control during the solid motor burn for this mission. IUS was to be spun up about its principle thrust axis in the desired attitude prior to ignition of its solid motor. IUS/SPINSIM can also be used to evaluate the performance of other spinning stages that utilize a fixed burn motor. IUS/SPINSIM is a Six-Degree-of-Freedom simulation for exo-atmospheric flight of an IUS. It assumes the stage is released in orbit at or near its desired inertial attitude, and is spinning slowly. The code models three phases: a coast phase in which further spin-up may occur, a burn stage during which a solid rocket motor (SRM) burn injects the space craft into a transfer trajectory, and a final coast phase. IUS/SPINSIM takes into account the effects of the following: a reaction control system (RCS) spinning the vehicle; SRM thrust buildup, decay, and misalignment; changing mass, center of gravity, principle moments of inertia, cross products of inertia, time derivatives of inertia; jet damping moments; and an oblate gravity model. Numerical integration of the equations of motion using a Runge-Kutta fourth order integrator and small step sizes is used to track the vehicle's position, velocity, attitude and spin rates. Instead of using Euler angles or the Direction Cosine Matrix, Quarternions are used to model the attitude and spinning of the vehicle. This eliminates the renormalization difficulties associated with either of the other methods. Program input is taken from a file, and output is to a print file and a data file suitable for use in plotting. The IUS/SPINSIM is written in FORTRAN 77 for DEC VAX series computers running VMS. The standard distribution medium for this program is a 9track 1600 BPI magnetic tape in DEC VAX BACKUP format. It is also available on a TK50 tape cartridge in DEC VAX BACKUP format. This program was developed in 1992.

Dauro, V. A.

1994-01-01

73

Physics Identity Development: A Snapshot of the Stages of Development of Upper-Level Physics Students  

ERIC Educational Resources Information Center

As part of a longitudinal study into identity development in upper-level physics students a phenomenographic research method is employed to assess the stages of identity development of a group of upper-level students. Three categories of description were discovered which indicate the three different stages of identity development for this group…

Irving, Paul W.; Sayre, Eleanor C.

2013-01-01

74

Control of a two stage turbocharger on a Diesel engine  

Microsoft Academic Search

Two stage turbochargers have been developed recently for Diesel engines in order to improve their performances in terms of power, consumption, emissions and dynamic behavior. For this kind of system, the operating conditions are very different than for one stage turbochargers and specific control issues must be considered. In this paper an analysis of single stage turbochargers control issues is

Philippe Moulin; Olivier Grondin; Laurent Fontvieille

2009-01-01

75

Advanced transportation system studies technical area 3: Alternate propulsion system concepts. SSME upper stage use  

NASA Technical Reports Server (NTRS)

The main objective was to determine viable methods for starting the Space Shuttle Main Engine (SSME) in an altitude environment and restarting it in an orbit environment with minimum changes in utilization of the engine system or hardware. The study concluded that the use of the SSME in an upper stage is feasible with minimal changes to the engine systems. The altitude start case requires only a change in the valve sequencing during start and reorificing of the ASI lines. Inlet pressures can be moderately low at 40 psia for the LOX and 32 psia for the H2. The orbital restart case adds the need to recirculate propellant and thermal control paint (to keep the turbomachinery inlets cold to minimize the tank pressures needed), and the need to heat two small components (to maintain acceptable mixture ratios during the early part of the start). These actions allow start anytime after approximately 120 minutes. Earlier starts (approximately one hour) are also possible but would require additional component heating for mixture ratio control during the early portion of the start sequence.

Strangeland, Eric; Levak, Daniel

1993-01-01

76

Advanced transportation system studies technical area 3: Alternate propulsion system concepts. SSME upper stage use  

NASA Astrophysics Data System (ADS)

The main objective was to determine viable methods for starting the Space Shuttle Main Engine (SSME) in an altitude environment and restarting it in an orbit environment with minimum changes in utilization of the engine system or hardware. The study concluded that the use of the SSME in an upper stage is feasible with minimal changes to the engine systems. The altitude start case requires only a change in the valve sequencing during start and reorificing of the ASI lines. Inlet pressures can be moderately low at 40 psia for the LOX and 32 psia for the H2. The orbital restart case adds the need to recirculate propellant and thermal control paint (to keep the turbomachinery inlets cold to minimize the tank pressures needed), and the need to heat two small components (to maintain acceptable mixture ratios during the early part of the start). These actions allow start anytime after approximately 120 minutes. Earlier starts (approximately one hour) are also possible but would require additional component heating for mixture ratio control during the early portion of the start sequence.

Strangeland, Eric; Levak, Daniel

1993-04-01

77

Advanced launch vehicle upper stages using liquid propulsion and metallized propellants  

NASA Technical Reports Server (NTRS)

Metallized propellants are liquid propellants with a metal additive suspended in a gelled fuel or oxidizer. Typically, aluminum particles are the metal additives. These propellants provide increase in the density and/or the specific impulse of the propulsion system. Using metallized propellants for volume- and mass-constrained upper stages can deliver modest increases in performance for Low Earth Orbit to Geosynchronous Earth Orbit and other Earth orbital transfer missions. Metallized propellants, however, can enable very fast planetary missions with a single-stage upper stage system. Trade studies comparing metallized propellant stage performance with non-metallized upper stages and the Inertial Upper Stage are presented. These upper stages are both one- and two-stage vehicles that provide the added energy to send payloads to altitudes and onto trajectories that are unattainable with only the launch vehicle. The stage designs are controlled by the volume and the mass constraints of the Space Transportation System and Space Transportation System-Cargo launch vehicles. The influences of the density and specific impulse increases enabled by metallized propellants are examined for a variety of different stage and propellant combinations.

Palaszewski, B. A.

1990-01-01

78

Advanced Launch Vehicle Upper Stages Using Liquid Propulsion and Metallized Propellants  

NASA Technical Reports Server (NTRS)

Metallized propellants are liquid propellants with a metal additive suspended in a gelled fuel or oxidizer. Typically, aluminum (Al) particles are the metal additive. These propellants provide increase in the density and/or the specific impulse of the propulsion system. Using metallized propellant for volume-and mass-constrained upper stages can deliver modest increases in performance for low earth orbit to geosynchronous earth orbit (LEO-GEO) and other earth orbital transfer missions. Metallized propellants, however, can enable very fast planetary missions with a single-stage upper stage system. Trade studies comparing metallized propellant stage performance with non-metallized upper stages and the Inertial Upper Stage (IUS) are presented. These upper stages are both one- and two-stage vehicles that provide the added energy to send payloads to altitudes and onto trajectories that are unattainable with only the launch vehicle. The stage designs are controlled by the volume and the mass constraints of the Space Transportation System (STS) and Space Transportation System-Cargo (STS-C) launch vehicles. The influences of the density and specific impulse increases enabled by metallized propellants are examined for a variety of different stage and propellant combinations.

Palaszewski, Bryan A.

1990-01-01

79

Upper stage options for reusable launch vehicle “pop-up” missions  

Microsoft Academic Search

Suborbital separation of an expendable upper stage from a small, single-stage Reusable Launch Vehicle (RLV) to transfer spacecraft into Geosynchronous Equatorial Orbit (GEO) was investigated and found to significantly increase spacecraft mass into GEO (over 400%) although operational issues exist. An assessment of propulsion system options for this “Pop-Up” Mission was performed to determine the propellant combinations, stage configurations, and

James B. Eckmann; Roy B. Cotta; Leo W. Matuszak; David R. Perkins

1997-01-01

80

Upper stage options for reusable launch vehicle ``pop-up'' missions  

Microsoft Academic Search

Suborbital separation of an expendable upper stage from a small, single-stage Reusable Launch Vehicle (RLV) to transfer spacecraft into Geosynchronous Equatorial Orbit (GEO) was investigated and found to significantly increase spacecraft mass into GEO (over 400%) although operational issues exist. An assessment of propulsion system options for this ``Pop-Up'' Mission was performed to determine the propellant combinations, stage configurations, and

James B. Eckmann; Roy B. Cotta; Leo W. Matuszak; David R. Perkins

1997-01-01

81

NASA Ares I Launch Vehicle Upper Stage Reaction Control System (ReCS) Cold Flow Development Test Overview  

NASA Technical Reports Server (NTRS)

NASA s Ares I launch vehicle, consisting of a five segment solid rocket booster first stage and a liquid bi-propellant J2-X engine Upper Stage, is the vehicle that s been chosen to launch the Orion Crew Module, which will return humans to the Moon, Mars, and beyond. After First Stage booster separation, the Reaction Control System (ReCS), a monopropellant hydrazine system, will provide the Upper Stage element with three degrees of freedom control as needed. This paper provides an overview of the system level development testing that has taken place on the Ares I launch vehicle Upper Stage ReCS. The ReCS System Development Test Article (SDTA) was built as a flight representative water flow test article whose primary test objective was to obtain fluid system performance data to evaluate the integrate system performance characteristics and verify analytical models. Water is the industry standard for cold flow testing of hydrazine systems, because the densities are very close and the speeds of sound are well characterized. The completion of this development level test program was considered necessary to support the ReCS Critical Design Review. This paper will address the design approach taken in building the test article, the objectives of the test program, types of testing completed, general results, the ability of the program to meet the test objectives, and lessons learned

Dervan, Melanie; Williams, Hunter; Holt, Kim; Sivak, Amy; Morris, Jon D.

2010-01-01

82

Detail view of steam chest for low pressure stage engine ...  

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

Detail view of steam chest for low pressure stage engine of unit 43. - Burnsville Natural Gas Pumping Station, Saratoga Avenue between Little Kanawha River & C&O Railroad line, Burnsville, Braxton County, WV

83

DETAIL VIEW OF STEAM CHEST FOR LOW PRESSURE STAGE ENGINE ...  

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

DETAIL VIEW OF STEAM CHEST FOR LOW PRESSURE STAGE ENGINE OF UNIT #3. - Burnsville Natural Gas Pumping Station, Saratoga Avenue between Little Kanawha River & C&O Railroad line, Burnsville, Braxton County, WV

84

Creation of an Upper Stage Trajectory Capability Boundary to Enable Booster System Trade Space Exploration  

NASA Technical Reports Server (NTRS)

The problem of trajectory optimization is important in all space missions. The solution of this problem enables one to specify the optimum thrust steering program which should be followed to achieve a specified mission objective, simultaneously satisfying the constraints.1 It is well known that whether or not the ascent trajectory is optimal can have a significant impact on propellant usage for a given payload, or on payload weight for the same gross vehicle weight.2 Consequently, ascent guidance commands are usually optimized in some fashion. Multi-stage vehicles add complexity to this analysis process as changes in vehicle properties in one stage propagate to the other stages through gear ratios and changes in the optimal trajectory. These effects can cause an increase in analysis time as more variables are added and convergence of the optimizer to system closure requires more analysis iterations. In this paper, an approach to simplifying this multi-stage problem through the creation of an upper stage capability boundary is presented. This work was completed as part of a larger study focused on trade space exploration for the advanced booster system that will eventually form a part of NASA s new Space Launch System.3 The approach developed leverages Design of Experiments and Surrogate Modeling4 techniques to create a predictive model of the SLS upper stage performance. The design of the SLS core stages is considered fixed for the purposes of this study, which results in trajectory parameters such as staging conditions being the only variables relevant to the upper stage. Through the creation of a surrogate model, which takes staging conditions as inputs and predicts the payload mass delivered by the SLS upper stage to a reference orbit as the response, it is possible to identify a "surface" of staging conditions which all satisfy the SLS requirement of placing 130 metric tons into low-Earth orbit (LEO).3 This identified surface represents the 130 metric ton capability boundary for the upper stage, such that if the combined first stage and boosters can achieve any one staging point on that surface, then the design is identified as feasible. With the surrogate model created, design and analysis of advanced booster concepts is streamlined, as optimization of the upper stage trajectory is no longer required in every design loop.

Walsh, Ptrick; Coulon, Adam; Edwards, Stephen; Mavris, Dimitri N.

2012-01-01

85

Study of a High-Energy Upper Stage for Future Shuttle Missions  

NASA Technical Reports Server (NTRS)

Space Shuttle Orbiters are likely to remain in service to 2020 or beyond for servicing the International Space Station and for launching very high value spacecraft. There is a need for a new STS-deployable upper stage that can boost certain Orbiter payloads to higher energy orbits, up to and including Earth-escape trajectories. The inventory of solid rocket motor Inertial Upper Stages has been depleted, and it is unlikely that a LOX/LH2-fueled upper stage can fly on Shuttle due to safety concerns. This paper summarizes the results of a study that investigated a low cost, low risk approach to quickly developing a new large upper stage optimized to fly on the existing Shuttle fleet. Two design reference missions (DRMs) were specified: the James Webb Space Telescope (JWST) and the Space Interferometry Mission (SIM). Two categories of upper stage propellants were examined in detail: a storable liquid propellant and a storable gel propellant. Stage subsystems 'other than propulsion were based largely on heritage hardware to minimize cost, risk and development schedule span. The paper presents the ground rules and guidelines for conducting the study, the preliminary conceptual designs margins, assessments of technology readiness/risk, potential synergy with other programs, and preliminary estimates of development and production costs and schedule spans. Although the Orbiter Columbia was baselined for the study, discussion is provided to show how the results apply to the remaining STS Orbiter fleet.

Dressler, Gordon A.; Matuszak, Leo W.; Stephenson, David D.

2003-01-01

86

Upper stage options for reusable launch vehicle {open_quotes}pop-up{close_quotes} missions  

Microsoft Academic Search

Suborbital separation of an expendable upper stage from a small, single-stage Reusable Launch Vehicle (RLV) to transfer spacecraft into Geosynchronous Equatorial Orbit (GEO) was investigated and found to significantly increase spacecraft mass into GEO (over 400%) although operational issues exist. An assessment of propulsion system options for this {open_quotes}Pop-Up{close_quotes} Mission was performed to determine the propellant combinations, stage configurations, and

J. B. Eckmann; R. B. Cotta; L. W. Matuszak; D. R. Perkins

1997-01-01

87

J-2X Upper Stage Engine: From Design to Hardware.  

National Technical Information Service (NTIS)

NASA is well on its way toward developing a new generation of launch vehicles to support of national space policy to retire the Space Shuttle fleet, complete the International Space Station, and return to the Moon as the first step in resuming this nation...

T. Byrd

2010-01-01

88

Robotic planetary science missions enabled with small NTR engine/stage technologies  

NASA Astrophysics Data System (ADS)

The high specific impulse (Isp) and engine thrust-to-weight ratio of liquid hydrogen (LH2)-cooled nuclear thermal rocket (NTR) engines makes them ideal for upper stage applications to difficult robotic planetary science missions. A small 15 thousand pound force (klbf) NTR engine using a uranium-zirconium-niobium 'ternary carbide' fuel (Isp approximately 960 seconds at approximately 3025K) developed in the Commonwealth of Independent States (CIS) is examined and its use on an expendable injection stage is shown to provide major increases in payload delivered to the outer planets (Saturn, Uranus, Neptune and Pluto). Using a single 'Titan IV-class' launch vehicle, with a lift capability to low Earth orbit (LEO) of approximately 20 metric tons (t), an expendable NTR upper stage can inject two Pluto 'Fast Flyby' spacecraft (PFF/SC) plus support equipment-combined mass of approximately 508 kg--on high energy, '6.5-9.2 year' direct trajectory missions to Pluto. A conventional chemical propulsion mission would use a liquid oxygen (LOX)/LH2 'Centaur' upper stage and two solid rocket 'kick motors' to inject a single PFF/SC on the same Titan IV launch vehicle. For follow on Pluto missions, the NTR injection stage would utilize a Jupiter 'gravity assist' (JGA) maneuver to launch a LOX/liquid methane (CH4) capture stage (Isp approximately 375 seconds) and a Pluto 'orbiter' spacecraft weighing between approximately 167-312 kg. With chemical propulsion, a Pluto orbiter mission is not a viable option because c inadequate delivered mass. Using a 'standardized' NTR injection stage and the same single Titan IV launch scenario, 'direct flight' (no gravity assist) orbiter missions to Saturn, Uranus and Neptune are also enabled with transit times of 2.3, 6.6, and 12.6 years, respectively. Injected mass includes a storable, nitrogen tetroxide/monomethyl hydrazine (N2O4/MMH) capture stage (Isp approximately 330 seconds) and orbiter payloads 340 to 820% larger than that achievable using a LOX/LH2-fueled injection stage. The paper discusses NTR technology and mission characteristics, shows NTR stage and payload accommodations within the 26.2 m long Titan IV payload fairing, and discusses NTR stage performance as a function of assumed cryogenic tank technology.

Borowski, Stanley K.

1995-10-01

89

Robotic Planetary Science Missions Enabled with Small NTR Engine/Stage Technologies  

NASA Technical Reports Server (NTRS)

The high specific impulse (Isp) and engine thrust-to-weight ratio of liquid hydrogen (LH2)-cooled nuclear thermal rocket (NTR) engines makes them ideal for upper stage applications to difficult robotic planetary science missions. A small 15 thousand pound force (klbf) NTR engine using a uranium-zirconium-niobium 'ternary carbide' fuel (Isp approximately 960 seconds at approximately 3025K) developed in the Commonwealth of Independent States (CIS) is examined and its use on an expendable injection stage is shown to provide major increases in payload delivered to the outer planets (Saturn, Uranus, Neptune and Pluto). Using a single 'Titan IV-class' launch vehicle, with a lift capability to low Earth orbit (LEO) of approximately 20 metric tons (t), an expendable NTR upper stage can inject two Pluto 'Fast Flyby' spacecraft (PFF/SC) plus support equipment-combined mass of approximately 508 kg--on high energy, '6.5-9.2 year' direct trajectory missions to Pluto. A conventional chemical propulsion mission would use a liquid oxygen (LOX)/LH2 'Centaur' upper stage and two solid rocket 'kick motors' to inject a single PFF/SC on the same Titan IV launch vehicle. For follow on Pluto missions, the NTR injection stage would utilize a Jupiter 'gravity assist' (JGA) maneuver to launch a LOX/liquid methane (CH4) capture stage (Isp approximately 375 seconds) and a Pluto 'orbiter' spacecraft weighing between approximately 167-312 kg. With chemical propulsion, a Pluto orbiter mission is not a viable option because c inadequate delivered mass. Using a 'standardized' NTR injection stage and the same single Titan IV launch scenario, 'direct flight' (no gravity assist) orbiter missions to Saturn, Uranus and Neptune are also enabled with transit times of 2.3, 6.6, and 12.6 years, respectively. Injected mass includes a storable, nitrogen tetroxide/monomethyl hydrazine (N2O4/MMH) capture stage (Isp approximately 330 seconds) and orbiter payloads 340 to 820% larger than that achievable using a LOX/LH2-fueled injection stage. The paper discusses NTR technology and mission characteristics, shows NTR stage and payload accommodations within the 26.2 m long Titan IV payload fairing, and discusses NTR stage performance as a function of assumed cryogenic tank technology.

Borowski, Stanley K.

1995-01-01

90

NASA Ares 1 Crew Launch Vehicle Upper Stage Configuration Selection Process  

NASA Technical Reports Server (NTRS)

The Upper Stage Element of NASA s Ares I Crew Launch Vehicle (CLV) is a "clean-sheet" approach that is being designed and developed in-house, with Element management at MSFC. The USE concept is a self-supporting cylindrical structure, approximately 115 long and 216" in diameter. While the Reusable Solid Rocket Booster (RSRB) design has changed since the CLV inception, the Upper Stage Element design has remained essentially a clean-sheet approach. Although a clean-sheet upper stage design inherently carries more risk than a modified design, it does offer many advantages: a design for increased reliability; built-in extensibility to allow for commonality/growth without major redesign; and incorporation of state-of-the-art materials, hardware, and design, fabrication, and test techniques and processes to facilitate a potentially better, more reliable system.

Cook, Jerry R.

2006-01-01

91

TROJID: A portable software package for upper-stage trajectory optimization  

NASA Technical Reports Server (NTRS)

Performance optimization for upper-stage exoatmospheric vehicles often is performed within the framework of a full capability trajectory simulation package requiring either a large mainframe computer or powerful work-station. Since these software packages tend to include capabilities providing for high-fidelity boost and reentry simulations, the programs usually are quite large and not very portable. The program TROJID is an attempt to provide an environment for the optimization of upper-stage trajectories within a small package capable of being run on a standard desktop microcomputer. Utilizing a state-of-the-art nonlinear programming algorithm and a trajectory simulator implementing impulsive burns and an analytic coast phase propagator, TROJID is capable of producing trajectories for optimal multi-burn upper-stage orbit transfers. The package has been designed to allow full generality in definition of both the trajectory simulator and the parameter optimization problem.

Hammes, Steven M.

1990-01-01

92

Simulink Model of the Ares I Upper Stage Main Propulsion System  

NASA Technical Reports Server (NTRS)

A numerical model of the Ares I upper stage main propulsion system is formulated based on first principles. Equation's are written as non-linear ordinary differential equations. The GASP fortran code is used to compute thermophysical properties of the working fluids. Complicated algebraic constraints are numerically solved. The model is implemented in Simulink and provides a rudimentary simulation of the time history of important pressures and temperatures during re-pressurization, boost and upper stage firing. The model is validated against an existing reliable code, and typical results are shown.

Burchett, Bradley T.

2008-01-01

93

Subsystem Hazard Analysis Methodology for the Ares I Upper Stage Source Controlled Items  

NASA Technical Reports Server (NTRS)

This article describes processes involved in developing subsystem hazard analyses for Source Controlled Items (SCI), specific components, sub-assemblies, and/or piece parts, of the NASA ARES I Upper Stage (US) project. SCIs will be designed, developed and /or procured by Boeing as an end item or an off-the-shelf item. Objectives include explaining the methodology, tools, stakeholders and products involved in development of these hazard analyses. Progress made and further challenges in identifying potential subsystem hazards are also provided in an effort to assist the System Safety community in understanding one part of the ARES I Upper Stage project.

Mitchell, Michael S.; Winner, David R.

2010-01-01

94

Ares First Stage "Systemology" - Combining Advanced Systems Engineering and Planning Tools to Assure Mission Success  

NASA Technical Reports Server (NTRS)

Ares is an integral part of NASA s Constellation architecture that will provide crew and cargo access to the International Space Station as well as low earth orbit support for lunar missions. Ares replaces the Space Shuttle in the post 2010 time frame. Ares I is an in-line, two-stage rocket topped by the Orion Crew Exploration Vehicle, its service module, and a launch abort system. The Ares I first stage is a single, five-segment reusable solid rocket booster derived from the Space Shuttle Program's reusable solid rocket motor. The Ares second or upper stage is propelled by a J-2X main engine fueled with liquid oxygen and liquid hydrogen. This paper describes the advanced systems engineering and planning tools being utilized for the design, test, and qualification of the Ares I first stage element. Included are descriptions of the current first stage design, the milestone schedule requirements, and the marriage of systems engineering, detailed planning efforts, and roadmapping employed to achieve these goals.

Seiler, James; Brasfield, Fred; Cannon, Scott

2008-01-01

95

Utilization of solid-propellant upper stages in STS payload orbital operations  

NASA Technical Reports Server (NTRS)

The main purpose of this report is to discuss techniques of trajectory design, maneuver execution, and stage loading that are compatible with the use of SRM's (solid rocket motors) which, once ignited, must burn to propellant depletion. It is anticipated that some shuttle payloads will use non-IUS (interim upper stage) solid propellant kick stages; therefore this subject is also pertinent to shuttle flights other than those involving the use of the IUS. The SRM utilization techniques can be divided into two major categories: (1) those in which the stage performance is adjusted to match the velocity increment magnitude requirements of a preselected trajectory, and (2) those in which the trajectory is designed to match the velocity increment magnitude capability of the stage(s).

Wilson, S. W.

1976-01-01

96

Computed tomography-guided tissue engineering of upper airway cartilage.  

PubMed

Normal laryngeal function has a large impact on quality of life, and dysfunction can be life threatening. In general, airway obstructions arise from a reduction in neuromuscular function or a decrease in mechanical stiffness of the structures of the upper airway. These reductions decrease the ability of the airway to resist inspiratory or expiratory pressures, causing laryngeal collapse. We propose to restore airway patency through methods that replace damaged tissue and improve the stiffness of airway structures. A number of recent studies have utilized image-guided approaches to create cell-seeded constructs that reproduce the shape and size of the tissue of interest with high geometric fidelity. The objective of the present study was to establish a tissue engineering approach to the creation of viable constructs that approximate the shape and size of equine airway structures, in particular the epiglottis. Computed tomography images were used to create three-dimensional computer models of the cartilaginous structures of the larynx. Anatomically shaped injection molds were created from the three-dimensional models and were seeded with bovine auricular chondrocytes that were suspended within alginate before static culture. Constructs were then cultured for approximately 4 weeks post-seeding and evaluated for biochemical content, biomechanical properties, and histologic architecture. Results showed that the three-dimensional molded constructs had the approximate size and shape of the equine epiglottis and that it is possible to seed such constructs while maintaining 75%+ cell viability. Extracellular matrix content was observed to increase with time in culture and was accompanied by an increase in the mechanical stiffness of the construct. If successful, such an approach may represent a significant improvement on the currently available treatments for damaged airway cartilage and may provide clinical options for replacement of damaged tissue during treatment of obstructive airway disease. PMID:24164398

Brown, Bryan N; Siebenlist, Nicholas J; Cheetham, Jonathan; Ducharme, Norm G; Rawlinson, Jeremy J; Bonassar, Lawrence J

2014-06-01

97

Lessons Learnt from the Dynamic Identification / Qualification Tests on the ESC-A Upper stage Model  

NASA Astrophysics Data System (ADS)

The dynamic qualification of the new cryogenic upper stage ESC-A of the ARIANE 5 is supported by several tests in order to verify the assumptions and the modelling approach made at the beginning of the development. The upper composite of the ARIANE 5, consisting of upper stage, vehicle equipment bay, payload carrying structures, payload dummies and fairing, was modal tested to validate the mathematical model of the launcher. Additionally, transfer functions were measured for Pogo investigations. Validated mathematical launcher models are the basis to predict the launcher global responses in the low frequency domain with sufficient confidence. The predicted global axial and lateral responses for selected sections at the stage represent the flight loads for these sections. The stage contains a large amount of equipment such as propellant lines, acceleration rockets, batteries, fluid control equipment etc. The verification of the equipment responses in the integrated state was done by a sine vibration test, excited to levels representing the predicted flight loads including a qualification factor. Acoustic tests with the upper stage were performed to verify the random vibration responses in the frequency range up to 2000 Hz. To verify the shock response level induced by stage separation (pyro shock) a stage separation test was performed. All the equipment was qualified separately for its dynamic (sine, random and shock excitation) and thermal environment to proof its structural and functional integrity. The paper concentrates on the experience made with the modal identification and sine-vibration test of the stage. For the sine vibration test an electrodynamic multi-shaker table was used. It was able to produce the required input precisely up to 150 Hz as specified, not an easy task for a test set-up of 20 tons weight. The paper presents the approach how the dynamic qualification was reached successfully and highlights the experiences which were made - the comparison between prediction and test results shows the ability and good quality of analysis but - the advantage of combined analysis of shaker table and stage model for test prediction - local effects observed in test - the dependency of damping on the load level - the efficiency of the so called SARO-Damping Device

Rittweger, A.; Beuchel, W.; Eckhardt, K.

2002-01-01

98

Infusing Training into the Documentation and Culture of Ares I Upper Stage Design and Manufacturing  

NASA Technical Reports Server (NTRS)

In roughly two years time, Marshall Space Flight Center's (MSFC) Mission Operations Laboratory (MOL) has incubated a personnel training and certification program for about 1000 learners and multiple phases of the Ares I Upper Stage (US) project. Previous MOL-developed training programs focused on about 100 learners with a focus on operations, and had enough full-time training staff to develop courseware and provide training administration. This paper discusses 1) how creation of a broad, structured training program unfolded as feedback from more narrowly defined tasks, 2) how training philosophy, development methods, and administration are being simplified and tailored so that many Upper Stage organizations can grow their own training yet maintain consistency, accountability, and traceability across the project, and 3) possibilities for interfacing with the production contractor's training system and staff.

Scott, David W.

2009-01-01

99

Growing a Training System and Culture for the Ares I Upper Stage Project  

NASA Technical Reports Server (NTRS)

In roughly two years time, Marshall Space Flight Center s (MSFC) Mission Operations Laboratory (MOL) has incubated a personnel training and certification program for about 1000 learners and multiple phases of the Ares I Upper Stage (US) project. Previous MOL-developed training programs focused on about 100 learners with a focus on operations, and had enough full-time training staff to develop courseware and provide training administration. This paper discusses 1) the basics of MOL's training philosophy, 2) how creation of a broad, structured training program unfolded as feedback from more narrowly defined tasks, 3) how training philosophy, development methods, and administration are being simplified and tailored so that many Upper Stage organizations can "grow their own" training yet maintain consistency, accountability, and traceability across the project, 4) interfacing with the production contractor's training system and staff, and 5) reaping training value from existing materials and events.

Scott, David W.

2009-01-01

100

Waterhammer Modeling for the Ares I Upper Stage Reaction Control System Cold Flow Development Test Article  

NASA Technical Reports Server (NTRS)

The Upper Stage Reaction Control System provides three-axis attitude control for the Ares I launch vehicle during active Upper Stage flight. The system design must accommodate rapid thruster firing to maintain the proper launch trajectory and thus allow for the possibility to pulse multiple thrusters simultaneously. Rapid thruster valve closure creates an increase in static pressure, known as waterhammer, which propagates throughout the propellant system at pressures exceeding nominal design values. A series of development tests conducted in the fall of 2009 at Marshall Space Flight Center were performed using a water-flow test article to better understand fluid performance characteristics of the Upper Stage Reaction Control System. A subset of the tests examined waterhammer along with the subsequent pressure and frequency response in the flight-representative system and provided data to anchor numerical models. This thesis presents a comparison of waterhammer test results with numerical model and analytical results. An overview of the flight system, test article, modeling and analysis are also provided.

Williams, Jonathan H.

2010-01-01

101

The Inertial Upper Stage - A space transportation system element nearing first flight  

NASA Technical Reports Server (NTRS)

The Inertial Upper Stage (IUS) developed by the USAF and NASA is a highly reliable, cost-effective solid propellant upper stage, with inherent flexibility and adaptability for integration with the Space Shuttle. The propulsion system is simple, utilizing safe, solid rocket motors with extremely light-weight nonmetallic cases and nozzles. The IUS can deliver 2268 kg from the Shuttle to geosynchronous altitude; it consists of a 9700 kg propellant weight first stage, an interstage structure, a 2720 kg propellant weight second stage, and an equipment support section. The avionics system includes the electronic and electrical hardware used to perform all signal conditioning, data processing, and software formatting associated with navigation, guidance, control, data management, and redundancy management. The generic thermal design of the IUS is suited to a wide range of thermal environments; the software design provides for selectable thermal maneuvers (rotisserie, reciprocating, toasting, space facing, sun facing) to satisfy different payload thermal requirements. A 1982 launch with the Titan 34D and a 1983 launch with the Shuttle Orbiter are planned.

Rohrbaugh, D. J.; Redd, F. J.; Van Rensselaer, F.

1981-01-01

102

Status and capability of the TOS and AMS upper stage family  

NASA Astrophysics Data System (ADS)

In May 1986, the development of the Transfer Orbit Stage (TOS) is to be completed. TOS represents a new upper stage for the Space Transportation System (STS). It can place payloads in the weight range from 2,490 to 6,080 kg into Geostationary Transfer Orbit (GTO) and deliver spacecraft to planetary and other high-energy trajectories. Aspects of design approach and reliability are considered along with structures and mechanisms, the main propulsion system with its solid rocket motor, the reaction control system, the avionics system, the airborne support equipment, performance capabilities, qualification testing, production schedule, acceptance testing, the Apogee and Maneuvering Stage (AMS) capabilities, and an AMS system description. Attention is also given to TOS/AMS capabilities, a TOS/AMS system description, and Expendable Launch Vehicle (ELV) application.

White, R. C.

1986-03-01

103

Wind tunnel investigation of a twin engine straight wing upper surface blown jet flap configuration  

NASA Technical Reports Server (NTRS)

An investigation was conducted in a full scale wind tunnel to determine the performance and aerodynamic characteristics of a twin engine, straight wing, upper surface blown jet flap configuration. The model had two simulated high bypass ratio turbofan engines with rectangular nozzles exhausting onto the upper surface of the wing at the 35 percent chord station. The model was tested with an aspect ratio 8.2 wing and with the wingtips removed to give an aspect ratio of 6.0.

Phelps, A. E., III

1975-01-01

104

Initial Assessment of the Ares I-X Launch Vehicle Upper Stage to Vibroacoustic Flight Environments  

NASA Technical Reports Server (NTRS)

The Ares I launch vehicle will be NASA s first new launch vehicle since 1981. Currently in design, it will replace the Space Shuttle in taking astronauts to the International Space Station, and will eventually play a major role in humankind s return to the Moon and eventually to Mars. Prior to any manned flight of this vehicle, unmanned test readiness flights will be flown. The first of these readiness flights, named Ares I-X, is scheduled to be launched in April 2009. The NASA Glenn Research Center is responsible for the design, manufacture, test and analysis of the Ares I-X upper stage simulator (USS) element. As part of the design effort, the structural dynamic response of the Ares I-X launch vehicle to its vibroacoustic flight environments must be analyzed. The launch vehicle will be exposed to extremely high acoustic pressures during its lift-off and aerodynamic stages of flight. This in turn will cause high levels of random vibration on the vehicle's outer surface that will be transmitted to its interior. Critical flight equipment, such as its avionics and flight guidance components are susceptible to damage from this excitation. This study addresses the modelling, analysis and predictions from examining the structural dynamic response of the Ares I-X upper stage to its vibroacoustic excitations. A statistical energy analysis (SEA) model was used to predict the high frequency response of the vehicle at locations of interest. Key to this study was the definition of the excitation fields corresponding to lift off acoustics and the unsteady aerodynamic pressure fluctuations during flight. The predicted results will be used by the Ares I-X Project to verify the flight qualification status of the Ares I-X upper stage components.

Larko, Jeffrey M.; Hughes, William O.

2008-01-01

105

Migration and winter distributions of canvasbacks staging on the Upper Mississippi River  

USGS Publications Warehouse

Fall and winter distribution patterns of canvasbacks (Aythya valisineria) staging on the upper Mississippi River near LaCrosse, Wisconsin (navigational Pools 7 and 8) and Keokuk, Iowa (Pool 19) were studied during 1973-77. Sightings and recoveries obtained from 1,488 color-marked males during 1973-75 and 3,789 banded males and females during 1973-77 suggested 2 principal migration corridors: 1 extending eastward from Pools 7 and 8 to the eastern Great Lakes and southeast to the Mid-Atlantic Region and another southward from Pools 7 and 8 to the lower Mississippi Valley, Gulf Coast, and east Texas regions. These discrete populations stage concurrently on Pools 7 and 8 during the fall, but winter in different areas of the Atlantic, Mississippi, and Central flyways. Populations staging on Pool 19 were not discrete from those staging on Pools 7 and 8. A continual turnover of birds passing through these staging areas was indicated. Canvasbacks wintering in the Mississippi and Central flyways were widely dispersed among a variety of habitats, whereas canvasbacks wintering in the Atlantic Flyway were concentrated in a few traditional habitats. Canvasbacks exhibited strong fidelity to wintering areas. Distribution patterns and population attributes of canvasbacks during fall and winter may be explained by the predictability of natural foods and their ability to exploit these foods.

Serie, J. R.; Trauger, D. L.; Sharp, D. E.

1983-01-01

106

Preliminary Performance of Lithium-ion Cell Designs for Ares I Upper Stage Applications  

NASA Technical Reports Server (NTRS)

NASA's Ares I Crew Launch Vehicle (CLV) baselined lithium-ion technology for the Upper Stage (US). Under this effort, the NASA Glenn Research Center investigated three different aerospace lithium-ion cell suppliers to assess the performance of the various lithium-ion cell designs under acceptance and characterization testing. This paper describes the overall testing approaches associated with lithium-ion cells, their ampere-hour capacity as a function of temperature and discharge rates, as well as their performance limitations for use on the Ares I US vehicle.

Miller, Thomas B.; Reid, Concha M.; Kussmaul, Michael T.

2011-01-01

107

Two BRM promoter insertion polymorphisms increase the risk of early-stage upper aerodigestive tract cancers.  

PubMed

Brahma (BRM) has a key function in chromatin remodeling. Two germline BRM promoter insertion-deletion polymorphisms, BRM-741 and BRM-1321, have been previously associated with an increased risk of lung cancer in smokers and head and neck cancer. To further evaluate their role in cancer susceptibility particularly in early disease, we conducted a preplanned case-control study to investigate the association between the BRM promoter variants and stage I/II upper aerodigestive tract (UADT) cancers (i.e., lung, esophageal, head and neck), a group of early-stage malignancies in which molecular and genetic etiologic factors are poorly understood. The effects of various clinical factors on this association were also studied. We analyzed 562 cases of early-stage UADT cancers and 993 matched healthy controls. The double homozygous BRM promoter variants were associated with a significantly increased risk of early stage UADT cancers (adjusted odds ratio [aOR], 2.46; 95% confidence interval [CI], 1.7-3.8). This association was observed in lung (aOR, 2.61; 95% CI, 1.5-4.9) and head and neck (aOR, 2.75; 95% CI, 1.4-5.6) cancers, but not significantly in esophageal cancer (aOR, 1.66; 95% CI, 0.7-5.8). There was a nonsignificant trend for increased risk in the heterozygotes or single homozygotes. The relationship between the BRM polymorphisms and early-stage UADT cancers was independent of age, sex, smoking status, histology, and clinical stage. These findings suggest that the BRM promoter double insertion homozygotes may be associated with an increased risk of early-stage UADT cancers independent of smoking status and histology, which must be further validated in other populations. PMID:24519853

Wong, Kit Man; Qiu, Xiaoping; Cheng, Dangxiao; Azad, Abul Kalam; Habbous, Steven; Palepu, Prakruthi; Mirshams, Maryam; Patel, Devalben; Chen, Zhuo; Roberts, Heidi; Knox, Jennifer; Marquez, Stephanie; Wong, Rebecca; Darling, Gail; Waldron, John; Goldstein, David; Leighl, Natasha; Shepherd, Frances A; Tsao, Ming; Der, Sandy; Reisman, David; Liu, Geoffrey

2014-04-01

108

Light Curve Observations of Upper Stages in the Low Earth Orbit Environment  

NASA Technical Reports Server (NTRS)

Active debris removal (ADR) is a potential means to remediate the orbital debris environment in low Earth orbit (LEO). Massive intact objects, including spent upper stages and retired payloads, with high collision probabilities have been suggested as potential targets for ADR. The challenges to remove such objects on a routine basis are truly monumental. A key piece of information needed for any ADR operations is the tumble motion of the targets. Rapid tumble motion (in excess of one degree per second) of a multiple-ton intact object could be a major problem for proximity and docking operations. Therefore, there is a need to characterize the general tumble motion of the potential ADR targets for future ADR planning. The NASA Orbital Debris Program Office has initiated an effort to identify the global tumble behavior of potential ADR targets in LEO. The activities include optical light curve observations, imaging radar data collection, and laboratory light curve simulations and modeling. This paper provides a preliminary summary of light curve data of more than 100 upper stages collected by two telescope facilities in Colorado and New Mexico between 2011 and 2012. Analyses of the data and implications for the tumble motions of the objects are also discussed in the paper.

Liou, J.-C.; Lederer, S.; Cowardin, H.; Mulrooney, M.; Read, J.; Chun, F.; Dearborn, M.; Tippets, R.

2012-01-01

109

Axially staged combustion system for a gas turbine engine  

DOEpatents

An axially staged combustion system is provided for a gas turbine engine comprising a main body structure having a plurality of first and second injectors. First structure provides fuel to at least one of the first injectors. The fuel provided to the one first injector is adapted to mix with air and ignite to produce a flame such that the flame associated with the one first injector defines a flame front having an average length when measured from a reference surface of the main body structure. Each of the second injectors comprising a section extending from the reference surface of the main body structure through the flame front and having a length greater than the average length of the flame front. Second structure provides fuel to at least one of the second injectors. The fuel passes through the one second injector and exits the one second injector at a location axially spaced from the flame front.

Bland, Robert J. (Oviedo, FL)

2009-12-15

110

The role of the upper sample size limit in two-stage bioequivalence designs.  

PubMed

Two-stage designs (TSDs) are currently recommended by the regulatory authorities for bioequivalence (BE) assessment. The TSDs presented until now rely on an assumed geometric mean ratio (GMR) value of the BE metric in stage I in order to avoid inflation of type I error. In contrast, this work proposes a more realistic TSD design where sample re-estimation relies not only on the variability of stage I, but also on the observed GMR. In these cases, an upper sample size limit (UL) is introduced in order to prevent inflation of type I error. The aim of this study is to unveil the impact of UL on two TSD bioequivalence approaches which are based entirely on the interim results. Monte Carlo simulations were used to investigate several different scenarios of UL levels, within-subject variability, different starting number of subjects, and GMR. The use of UL leads to no inflation of type I error. As UL values increase, the % probability of declaring BE becomes higher. The starting sample size and the variability of the study affect type I error. Increased UL levels result in higher total sample sizes of the TSD which are more pronounced for highly variable drugs. PMID:23954235

Karalis, Vangelis

2013-11-01

111

Modeling and Simulation of the ARES UPPER STAGE Transportation, Lifting, Stacking and Mating Operations Within the Vehicle Assembly Building at KSC  

NASA Technical Reports Server (NTRS)

This viewgraph presentation describes the modeling and simulation of the Ares Upper Stage Transportation, lifting, stacking, and mating operations within the Vehicle Assembly Building (VAB) at Kennedy Space Center (KSC). An aerial view of KSC Launch Shuttle Complex, two views of the Delmia process control layout, and an upper stage move subroutine and breakdown are shown. An overhead image of the VAB and the turning basin along with the Pegasus barge at the turning basin are also shown. This viewgraph presentation also shows the actual design and the removal of the mid-section spring tensioners, the removal of the AFT rear and forward tensioners tie downs, and removing the AFT hold down post and mount. US leaving the Pegasus Barge, the upper stage arriving at transfer aisle, upper stage receiving/inspection in transfer aisle, and an overhead view of upper stage receiving/inspection in transfer aisle are depicted. Five views of the actual connection of the cabling to the upper stage aft lifting hardware are shown. The upper stage transporter forward connector, two views of the rotation horizontal to vertical, the disconnection of the rear bolt ring cabling, the lowering of the upper stage to the inspection stand, disconnection of the rear bolt ring from the upper stage, the lifting of the upper stage and inspection of AFT fange, and the transfer of upper stage in an integrated stack are shown. Six views of the mating of the upper stage to the first stage are depicted. The preparation, inspection, and removal of the forward dome are shown. The upper stage mated on the integrated stack and crawler is also shown. This presentation concludes with A Rapid Upper Limb Assessment (RULA) utilizing male and female models for assessing risk factors to the upper extremities of human beings in an actual physical environment.

Kromis, Phillip A.

2010-01-01

112

28. ENGINE CLUSTER OF 1ST STAGE OF A SATURN I ...  

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

28. ENGINE CLUSTER OF 1ST STAGE OF A SATURN I ROCKET ENGINE LOCATED ON NORTH SIDE OF STATIC TEST STAND. - Marshall Space Flight Center, Saturn Propulsion & Structural Test Facility, East Test Area, Huntsville, Madison County, AL

113

Experimental approach on the pyrotechnical shock reduction of Ariane-5 upper stage  

NASA Astrophysics Data System (ADS)

The separation of the upper stage of the Ariane 5 launcher is to be achieved by means of a Pyrotechnical Expansive Tube (PET) installed in the Vehicle Equipment Bay (VEB) structure. When the pyrotechnical device is activated, severe shock levels are transmitted to the structural components and electronic equipment located near the separation section. These shock inputs could affect the operational performances of the above mentioned components during and after separation. An experimental research project to verify that VEB equipment will not be damaged, to achieve a deeper knowledge of the nature and consequences of the event, and to improve existing theoretical models, was undertaken. A specification was identified for the equipment platform, and a campaign of technological tests were started in order to select a damping material and its layout to obtain the highest shock reduction without compromising the VEB structural integrity and stiffness.

Uribarri, I.; Tejero, P.; Rivaillon, B.; Laviron, B.

1991-10-01

114

IUS/TUG orbital operations and mission support study. Volume 2: Interim upper stage operations  

NASA Technical Reports Server (NTRS)

Background data and study results are presented for the interim upper stage (IUS) operations phase of the IUS/tug orbital operations study. The study was conducted to develop IUS operational concepts and an IUS baseline operations plan, and to provide cost estimates for IUS operations. The approach used was to compile and evaluate baseline concepts, definitions, and system, and to use that data as a basis for the IUS operations phase definition, analysis, and costing analysis. Both expendable and reusable IUS configurations were analyzed and two autonomy levels were specified for each configuration. Topics discussed include on-orbit operations and interfaces with the orbiter, the tracking and data relay satellites and ground station support capability analysis, and flight control center sizing to support the IUS operations.

1975-01-01

115

Inertial Upper Stage for the Chandra X-ray Observatory arrives in VPF  

NASA Technical Reports Server (NTRS)

The Inertial Upper Stage (IUS) booster is moved toward a workstand in Kennedy Space Center's Vertical Processing Facility. The IUS will be mated with the Chandra X-ray Observatory and then undergo testing to validate the IUS/Chandra connections and check the orbiter avionics interfaces. Following that, an end-to-end test (ETE) will be conducted to verify the communications path to Chandra, commanding it as if it were in space. With the world's most powerful X-ray telescope, Chandra will allow scientists from around the world to see previously invisible black holes and high-temperature gas clouds, giving the observatory the potential to rewrite the books on the structure and evolution of our universe. Chandra is scheduled for launch July 22 aboard Space Shuttle Columbia, on mission STS-93.

1999-01-01

116

STS-93 crew members look over the Inertial Upper Stage booster at CCAS  

NASA Technical Reports Server (NTRS)

In the Solid Motor Assembly Building, Cape Canaveral Air Station, STS-93 Pilot Jeffrey S. Ashby and Mission Specialist Steven A. Hawley look over the Inertial Upper Stage booster being readied for their mission. Other crew members (not shown) are Commander Eileen Collins and Mission Specialists Catherine G. Coleman and Michel Tognini of France, who represents the Centre National d'Etudes Spatiales (CNES). STS-93, scheduled to launch July 9 aboard Space Shuttle Columbia, has the primary mission of the deployment of the Chandra X-ray Observatory. Formerly called the Advanced X-ray Astrophysics Facility, Chandra comprises three major elements: the spacecraft, the science instrument module (SIM), and the world's most powerful X-ray telescope. Chandra will allow scientists from around the world to see previously invisible black holes and high-temperature gas clouds, giving the observatory the potential to rewrite the books on the structure and evolution of our universe.

1999-01-01

117

Inertial Upper Stage for the Chandra X-ray Observatory arrives in VPF  

NASA Technical Reports Server (NTRS)

The Inertial Upper Stage (IUS) booster (right) is lifted out of its container after arriving at Kennedy Space Center's Vertical Processing Facility. The IUS will be mated with the Chandra X-ray Observatory (at left) and then undergo testing to validate the IUS/Chandra connections and check the orbiter avionics interfaces. Following that, an end-to-end test (ETE) will be conducted to verify the communications path to Chandra, commanding it as if it were in space. With the world's most powerful X-ray telescope, Chandra will allow scientists from around the world to see previously invisible black holes and high-temperature gas clouds, giving the observatory the potential to rewrite the books on the structure and evolution of our universe. Chandra is scheduled for launch July 22 aboard Space Shuttle Columbia, on mission STS-93.

1999-01-01

118

Inertial Upper Stage for the Chandra X-ray Observatory arrives in VPF  

NASA Technical Reports Server (NTRS)

In the Vertical Processing Facility, the Chandra X-ray Observatory is lifted from its workstand in order to move it to the Inertial Upper Stage (IUS) nearby. After being mated, the two components will then undergo testing to validate the IUS/Chandra connections and check the orbiter avionics interfaces. Following that, an end-to-end test (ETE) will be conducted to verify the communications path to Chandra, commanding it as if it were in space. With the world's most powerful X-ray telescope, Chandra will allow scientists from around the world to see previously invisible black holes and high-temperature gas clouds, giving the observatory the potential to rewrite the books on the structure and evolution of our universe. Chandra is scheduled for launch July 22 aboard Space Shuttle Columbia, on mission STS-93.

1999-01-01

119

Inertial Upper Stage for the Chandra X-ray Observatory arrives in VPF  

NASA Technical Reports Server (NTRS)

The Inertial Upper Stage (IUS) booster is lowered toward a workstand in Kennedy Space Center's Vertical Processing Facility. The IUS will be mated with the Chandra X-ray Observatory and then undergo testing to validate the IUS/Chandra connections and check the orbiter avionics interfaces. Following that, an end-to-end test (ETE) will be conducted to verify the communications path to Chandra, commanding it as if it were in space. With the world's most powerful X-ray telescope, Chandra will allow scientists from around the world to see previously invisible black holes and high-temperature gas clouds, giving the observatory the potential to rewrite the books on the structure and evolution of our universe. Chandra is scheduled for launch July 22 aboard Space Shuttle Columbia, on mission STS-93.

1999-01-01

120

STS-93 crew members look over the Inertial Upper Stage booster at CCAS  

NASA Technical Reports Server (NTRS)

In the Solid Motor Assembly Building, Cape Canaveral Air Station, STS-93 Mission Specialist Catherine G. Coleman kneels next to the Inertial Upper Stage booster being readied for the mission. Other crew members (not shown) are Commander Eileen Collins, Pilot Jeffrey S. Ashby and Mission Specialists Steven A. Hawley and Michel Tognini of France, who represents the Centre National d'Etudes Spatiales (CNES). STS-93, scheduled to launch July 9 aboard Space Shuttle Columbia, has the primary mission of the deployment of the Chandra X-ray Observatory. Formerly called the Advanced X-ray Astrophysics Facility, Chandra comprises three major elements: the spacecraft, the science instrument module (SIM), and the world's most powerful X-ray telescope. Chandra will allow scientists from around the world to see previously invisible black holes and high-temperature gas clouds, giving the observatory the potential to rewrite the books on the structure and evolution of our universe.

1999-01-01

121

Weld Residual Stress and Distortion Analysis of the ARES I-X Upper Stage Simulator (USS)  

NASA Technical Reports Server (NTRS)

An independent assessment was conducted to determine the critical initial flaw size (CIFS) for the flange-to-skin weld in the Ares I-X Upper Stage Simulator (USS). The Ares system of space launch vehicles is the US National Aeronautics and Space Administration s plan for replacement of the aging space shuttle. The new Ares space launch system is somewhat of a combination of the space shuttle system and the Saturn launch vehicles used prior to the shuttle. Here, a series of weld analyses are performed to determine the residual stresses in a critical region of the USS. Weld residual stresses both increase constraint and mean stress thereby having an important effect on fatigue and fracture life. While the main focus of this paper is a discussion of the weld modeling procedures and results for the USS, a short summary of the CIFS assessment is provided.

Raju, Ivatury; Dawicke, David; Cheston, Derrick; Phillips, Dawn

2008-01-01

122

Ares I-X Upper Stage Simulator Compartment Pressure Comparisons During Ascent  

NASA Technical Reports Server (NTRS)

Predictions of internal compartment pressures are necessary in the design of interstage regions, systems tunnels, and protuberance covers of launch vehicles to assess potential burst and crush loading of the structure. History has proven that unexpected differential pressure loads can lead to catastrophic failure. Pressures measured in the Upper Stage Simulator (USS) compartment of Ares I-X during flight were compared to post-flight analytical predictions using the CHCHVENT chamber-to-chamber venting analysis computer program. The measured pressures were enveloped by the analytical predictions for most of the first minute of flight but were outside of the predictions thereafter. This paper summarizes the venting system for the USS, discusses the probable reasons for the discrepancies between the measured and predicted pressures, and provides recommendations for future flight vehicles.

Downs. William J.; Kirchner, Robert D.; McLachlan, Blair G.; Hand, Lawrence A.; Nelson, Stuart L.

2011-01-01

123

Assembly of 5.5-Meter Diameter Developmental Barrel Segments for the Ares I Upper Stage  

NASA Technical Reports Server (NTRS)

Full scale assembly welding of Ares I Upper Stage 5.5-Meter diameter cryogenic tank barrel segments has been performed at the Marshall Space Flight Center (MSFC). One full-scale developmental article produced under the Ares 1 Upper Stage project is the Manufacturing Demonstration Article (MDA) Barrel. This presentation will focus on the welded assembly of this barrel section, and associated lessons learned. Among the MDA articles planned on the Ares 1 Program, the Barrel was the first to be completed, primarily because the process of manufacture from piece parts (barrel panels) utilized the most mature friction stir process planned for use on the Ares US program: Conventional fixed pin Friction Stir Welding (FSW). This process is in use on other space launch systems, including the Shuttle s External Tank, the Delta IV common booster core, the Delta II, and the Atlas V rockets. The goals for the MDA Barrel development were several fold: 1) to prove out Marshall Space Flight Center s new Vertical Weld Tool for use in manufacture of cylindrical barrel sections, 2) to serve as a first run for weld qualification to a new weld specification, and 3) to provide a full size cylindrical section for downstream use in precision cleaning and Spray-on Foam Insulation development. The progression leading into the welding of the full size barrel included sub scale panel welding, subscale cylinder welding, a full length confidence weld, and finally, the 3 seamed MDA barrel processing. Lessons learned on this MDA program have been carried forward into the production tooling for the Ares 1 US Program, and in the use of the MSFC VWT in processing other large scale hardware, including two 8.4 meter diameter Shuttle External Tank barrel sections that are currently being used in structural analysis to validate shell buckling models.

Carter, Robert W.

2011-01-01

124

Taming Liquid Hydrogen: The Centaur Upper Stage Rocket, 1958-2002  

NASA Technical Reports Server (NTRS)

During its maiden voyage in May 1962, a Centaur upper stage rocket, mated to an Atlas booster, exploded 54 seconds after launch, engulfing the rocket in a huge fireball. Investigation revealed that Centaur's light, stainless-steel tank had split open, spilling its liquid-hydrogen fuel down its sides, where the flame of the rocket exhaust immediately ignited it. Coming less than a year after President Kennedy had made landing human beings on the Moon a national priority, the loss of Centaur was regarded as a serious setback for the National Aeronautics and Space Administration (NASA). During the failure investigation, Homer Newell, Director of Space Sciences, ruefully declared: "Taming liquid hydrogen to the point where expensive operational space missions can be committed to it has turned out to be more difficult than anyone supposed at the outset." After this failure, Centaur critics, led by Wernher von Braun, mounted a campaign to cancel the program. In addition to the unknowns associated with liquid hydrogen, he objected to the unusual design of Centaur. Like the Atlas rocket, Centaur depended on pressure to keep its paper-thin, stainless-steel shell from collapsing. It was literally inflated with its propellants like a football or balloon and needed no internal structure to give it added strength and stability. The so-called "pressure-stabilized structure" of Centaur, coupled with the light weight of its high- energy cryogenic propellants, made Centaur lighter and more powerful than upper stages that used conventional fuel. But, the critics argued, it would never become the reliable rocket that the United States needed.

Dawson, Virginia P.; Bowles, Mark D.

2004-01-01

125

Study of the anabranch dynamics for different sinuosity stages in the Upper Amazon River Basin  

NASA Astrophysics Data System (ADS)

The Upper Peruvian Amazon River is characterized by a sequence of anabranching structures, which are composed by several channels behaving as non-developed and quasy-freely meandering channels. The widest channel in these anabranching structures is considered as the main channel or main anabranch while the other channels are secondary anabranches. Based on satellite imagery, it is observed that the main channels show different sinuosities along the Upper Peruvian Amazon River valley. Little is known about the effects of the planform characteristics of the main channel into the morphodynamics of the secondary anabranches. Thus, two study sites were selected to characterize anabranching structures with low and medium-high sinuosity main channels. For the low sinuosity main channel case, an area at the tri-point boundary between Colombia-Brazil and Peru was selected. For the medium-high sinuosity main channel case, an area upstream of Iquitos City (the largest city in the Peruvian Amazon Rainforest) was selected. A field campaign was carried out on 2010 and 2011 for the medium-high and low sinuosity stages respectively. On this field campaign velocity measurement, bathymetry and water surface elevations were obtained. With the field data it was possible to develop and validate a two dimensional shallow water numerical model to study the hydrodynamics on both sites. This allows us to discuss the effects of the current planform configuration of the anabranching structures into the short-term behavior of individual channels. In past studies, temporal analysis of the Amazon River planform have been carried out using satellite imagery with special focus into the floodplain, main channel, number of islands and valley slope. However, the dynamics in these anabranching structures containing multiple channels have not been studied in detailed. The metrics obtained for this study were sinuosity, channel width and annual migration rates. It was confirmed that in a medium to high sinuosity stage, the secondary anabranches behave as non-developed meanders. Also, it was concluded that the planform for secondary anabranches in all main channel sinuosity stages are controlled by the main anabranch migration.

Frias, C. E.; Mendoza, A.; Dauer, K.; Abad, J. D.; Montoro, H.; Paredes, J.; Vizcarra, J.

2013-12-01

126

Designing the Ares I Crew Launch Vehicle Upper Stage Element and Integrating the Stack at NASA's Marshall Space Flight Center  

NASA Technical Reports Server (NTRS)

Fielding an integrated launch vehicle system entails many challenges, not the least of which is the fact that it has been over 30 years since the United States has developed a human-rated vehicle - the venerable Space Shuttle. Over time, whole generations of rocket scientists have passed through the aerospace community without the opportunity to perform such exacting, demanding, and rewarding work. However, with almost 50 years of experience leading the design, development, and end-to-end systems engineering and integration of complex launch vehicles, NASA's Marshall Space Flight Center offers the in-house talent - both junior- and senior-level personnel - to shape a new national asset to meet the requirements for safe, reliable, and affordable space exploration solutions.' These personnel are housed primarily in Marshall's Engineering Directorate and are matrixed into the programs and projects that reside at the rocket center. Fortunately, many Apollo era and Shuttle engineers, as well as those who gained valuable hands-on experience in the 1990s by conducting technology demonstrator projects such as the Delta-Clipper Experimental Advanced, X-33, X-34, and X-37, as well as the short-lived Orbital Space Plane, work closely with industry partners to advance the nation's strategic capability for human access to space. Currently, only three spacefaring nations have this distinction, including the United States, Russia, and, more recently, China. The U.S. National Space Policy of2006 directs that NASA provide the means to travel to space, and the NASA Appropriations Act of2005 provided the initial funding to begin in earnest to replace the Shuttle after the International Space Station construction is complete in 20 IO? These and other strategic goals and objectives are documented in NASA's 2006 Strategic Plan.3 In 2005, a team of NASA aerospace experts conducted the Exploration Systems Architecture Study, which recommended a two-vehicle approach to America's next space transportation system for missions to the International Space Station in the next decade and to explore the Moon and establish an outpost around the 2020 timeframe.4 Based on this extensive study, NASA selected the Ares I crew launch vehicle configuration and the heavy-lift Ares V cargo launch vehicle (fig 1). This paper will give an overview of NASA's approach to integrating the Ares I vehicle stack using capabilities and assets that are resident in Marshall's Engineering Directorate, working in partnership with other NASA Centers and the U.S. aerospace industry. It also will provide top-level details on the progress of the in-house design of the Ares I vehicle's upper stage element.

Lyles, Garry; Otte, Neil E.

2008-01-01

127

Operations analysis (study 2.1). Contingency analysis. [of failure modes anticipated during space shuttle upper stage planning  

NASA Technical Reports Server (NTRS)

Future operational concepts for the space transportation system were studied in terms of space shuttle upper stage failure contingencies possible during deployment, retrieval, or space servicing of automated satellite programs. Problems anticipated during mission planning were isolated using a modified 'fault tree' technique, normally used in safety analyses. A comprehensive space servicing hazard analysis is presented which classifies possible failure modes under the catagories of catastrophic collision, failure to rendezvous and dock, servicing failure, and failure to undock. The failure contingencies defined are to be taken into account during design of the upper stage.

1974-01-01

128

Utility of palmatolepids and icriodontids in recognizing Upper Devonian Series, Stage, and possible substage boundaries  

USGS Publications Warehouse

Conodonts are accepted internationally to define Devonian Series and Stage boundaries. Hence, the evolution and taxonomy of pelagic palmatolepids, primarily Palmatolepis and its direct ancestor Mesotaxis, and shallow-water icriodontids, Icriodus, Pelekysgnathus, and "Icriodus", are the major tools for recognizing subdivisions of the Upper Devonian. Palmatolepids are the basis for the Late Devonian Standard Conodont Zonation (ZIEGLER & SANDBERG 1990), whereas icriodontids are the basis for the alternative, integrated shallow-water zonation (SANDBERG & DREESEN 1984). However, an alternative palmatolepid taxonomy for some Frasnian species has been employed recently by some conodont workers using the Montagne Noire (M.N.) zonation, shape analyses of Pa elements, and multielement reconstructions of KLAPPER (1989), KLAPPER & FOSTER (1993); and KLAPPER et al. (1996). Herein, the evolution of palmatolepids and icriodontids is summarized in terms of our zonation and some of the taxonomic differences with the alternative M.N. zonation are exemplified. One of the problems in relating the Standard and M.N. zonations arises from previous errors of interpretation and drafting of the Martenberg section in Germany. This section was designated the reference section for the Frasnian transitans through jamieae Zones by ZIEGLER & SANDBERG (1990). Herein, the early and middle Frasnian zonal boundaries at Martenberg are improved by re-study of our old and recent collections from three profiles, spaced only 4 m apart. Serious problems exist with the Global Stratotype Sections and Points (GSSP's), selected by the Subcommission on Devonian Stratigraphy, following the paleontologic definition of the bases of the Frasnian, Famennian, and Tournaisian Stages, because of the difficulty in making global correlations from these GSSP's. Our summary of these problems should be helpful if future workers decide to relocate these GSSP's.

Ziegler, W.; Sandberg, C. A.

2000-01-01

129

Reusable Centaur study. Volume 1: Executive summary. [development costs of Centaur launch vehicle as upper stage for space shuttle orbiter  

NASA Technical Reports Server (NTRS)

A study of the Reusable Centaur for use as an initial upper stage with the space shuttle was conducted. The currently operative Centaur stage, with modifications for space shuttle orbiter compatibility and for improved performance, represents a cost effective development solution. The performance needs and available development funds are discussed. The main features of three Reusable Centaur configurations with increasing capability at increasing development costs are summarized.

Heald, D. A.

1974-01-01

130

Linear aerospike engine. [for reusable single-stage-to-orbit vehicle  

NASA Technical Reports Server (NTRS)

A description is presented of a dual-fuel modular split-combustor linear aerospike engine concept. The considered engine represents an approach to an integrated engine for a reusable single-stage-to-orbit (SSTO) vehicle. The engine burns two fuels (hydrogen and a hydrocarbon) with oxygen in separate combustors. Combustion gases expand on a linear aerospike nozzle. An engine preliminary design is discussed. Attention is given to the evaluation process for selecting the optimum number of modules or divisions of the engine, aspects of cooling and power cycle balance, and details of engine operation.

Kirby, F. M.; Martinez, A.

1977-01-01

131

STS-93 crew members look over the Inertial Upper Stage booster at CCAS  

NASA Technical Reports Server (NTRS)

In the Solid Motor Assembly Building, Cape Canaveral Air Station, STS-93 Mission Specialist Catherine G. Coleman (left) lifts the protective covering to look at the avionics box on the Inertial Upper Stage booster. Next to her are Eric Herrburger (center), with Boeing, and crew member Mission Specialist Michel Tognini (right) of France, who represents the Centre National d'Etudes Spatiales (CNES). STS-93 is scheduled to launch July 9 aboard Space Shuttle Columbia and has the primary mission of the deployment of the Chandra X-ray Observatory. Formerly called the Advanced X-ray Astrophysics Facility, Chandra comprises three major elements: the spacecraft, the science instrument module (SIM), and the world's most powerful X-ray telescope. Chandra will allow scientists from around the world to see previously invisible black holes and high-temperature gas clouds, giving the observatory the potential to rewrite the books on the structure and evolution of our universe. Other STS-93 crew members are Commander Eileen M. Collins, Pilot Jeffrey S. Ashby and Mission Specialist Steven A. Hawley.

1999-01-01

132

Flight Results of the Chandra X-Ray Observatory Inertial Upper Stage Space Mission  

NASA Technical Reports Server (NTRS)

Under contract to NASA, a specially configured version of the Boeing developed Inertial Upper Stage (IUS) booster was provided by Boeing to deliver NASA's 1.5 billion dollar Chandra X-Ray Observatory satellite into a highly elliptical transfer orbit from a Shuttle provided circular park orbit. Subsequently, the final orbit of the Chandra satellite was to be achieved using the Chandra Integral Propulsion System (IPS) through a series of IPS burns. On 23 July 1999 the Shuttle Columbia (STS-93) was launched with the IUS/Chandra stack in the Shuttle payload bay. Unfortunately, the Shuttle Orbiter was unexpectantly inserted into an off-nominal park orbit due to a Shuttle propulsion anomaly occurring during ascent. Following the IUS/Chandra on-orbit deployment from the Shuttle, at seven hours from liftoff, the flight proven IUS GN&C system successfully injected Chandra into the targeted transfer orbit, in spite of the off-nominal park orbit. This paper describes the IUS GN&C system, discusses the specific IUS GN&C mission data load development, analyses and testing for the Chandra mission, and concludes with a summary of flight results for the IUS part of the Chandra mission.

Tillotson, R.; Walter, R.

2000-01-01

133

STS-93 crew members look over the Inertial Upper Stage booster at CCAS  

NASA Technical Reports Server (NTRS)

In the Solid Motor Assembly Building, Cape Canaveral Air Station, looking over the Inertial Upper Stage booster being readied for their mission are (left to right) STS-93 Pilot Jeffrey S. Ashby and Mission Specialists Michel Tognini, who represents the Centre National d'Etudes Spatiales (CNES), and Steven A. Hawley. On the far right is Eric Herrburger, with Boeing. Other crew members (not shown) are Commander Eileen Collins and Mission Specialist Catherine G. Coleman. STS-93, scheduled to launch July 9 aboard Space Shuttle Columbia, has the primary mission of the deployment of the Chandra X-ray Observatory. Formerly called the Advanced X- ray Astrophysics Facility, Chandra comprises three major elements: the spacecraft, the science instrument module (SIM), and the world's most powerful X-ray telescope. Chandra will allow scientists from around the world to see previously invisible black holes and high-temperature gas clouds, giving the observatory the potential to rewrite the books on the structure and evolution of our universe.

1999-01-01

134

Aerodynamic characteristics of a large-scale hybrid upper surface blown flap model having four engines  

NASA Technical Reports Server (NTRS)

Data are presented from an investigation of the aerodynamic characteristics of large-scale wind tunnel aircraft model that utilized a hybrid-upper surface blown flap to augment lift. The hybrid concept of this investigation used a portion of the turbofan exhaust air for blowing over the trailing edge flap to provide boundary layer control. The model, tested in the Ames 40- by 80-foot Wind Tunnel, had a 27.5 deg swept wing of aspect ratio 8 and 4 turbofan engines mounted on the upper surface of the wing. The lift of the model was augmented by turbofan exhaust impingement on the wind upper-surface and flap system. Results were obtained for three flap deflections, for some variation of engine nozzle configuration and for jet thrust coefficients from 0 to 3.0. Six-component longitudinal and lateral data are presented with four engine operation and with the critical engine out. In addition, a limited number of cross-plots of the data are presented. All of the tests were made with a downwash rake installed instead of a horizontal tail. Some of these downwash data are also presented.

Carros, R. J.; Boissevain, A. G.; Aoyagi, K.

1975-01-01

135

Multiple output power supply circuit for an ion engine with shared upper inverter  

NASA Technical Reports Server (NTRS)

A power supply circuit for an ion engine suitable for a spacecraft is coupled to a bus having a bus input and a bus return. The power supply circuit has a first primary winding of a first transformer. An upper inverter circuit is coupled to the bus input and the first primary winding. The power supply circuit further includes a first lower inverter circuit coupled to the bus return and the first primary winding. The second primary winding of a second transformer is coupled to the upper inverter circuit. A second lower inverter circuit is coupled to the bus return and the second primary winding.

Cardwell, Jr., Gilbert I. (Inventor); Phelps, Thomas K. (Inventor)

2001-01-01

136

ARIANE 5 upper-stage ignition conditions improvement, and return to operation with ''Envisat'' payload  

NASA Astrophysics Data System (ADS)

ARIANE 5 experienced a flight anomaly with the 10 th model mission (F 510), having placed its both satellites in a lower orbit than the planned GTO. Only one satellite (Artemis) could be retrieved due to its own propulsion systems. Arianespace, CNES and Astrium-GmbH (former DaimlerChrysler Aerospace Dasa) immediately set up a recovery team, combining forces for carrying deep and schedule-driven investigations, and later qualifying recovery measures. A failure in such an important program: is immediately triggering a large "post-shock" reaction from the ARIANE community implied in the relevant business and technology. The investigation fields are summarised in the following chapters, showing how failure analysis, engineering investigations and basic research have been combined in order to have a schedule and methodic efficient approach. The combination of all available European resources in space vehicle design has been implemented, involving industry, agency technical centers and research laboratories. The investigation methodology applied has been driven by the particular situation of a flight anomaly investigation, which has to take into account the reduced amount of measurement available in flight and the necessary combination with ground test data for building a strategy to reach identification of possible failure scenario. From the investigations and from extensive sensitivity characterisation test of EPS engine (AESTUS) ignition transient, stability margins have been deeply investigated and introduced in the post-anomaly upgraded stage design. The identification and implementation of recovery measures, extended as well to - potential ignition margin reduction factors even beyond the observed flight anomaly allowed to establish a robust complementary qualification status, thus allowing resuming of operational flight, starting with the valuable "Envisat" payload of European Space Agency, dedicated to earth and climate monitoring, on flight 511, the 28/02/2002, from Kourou Spaceport.

Dutheil, J. Ph.; Langel, G.

2003-08-01

137

One-stage reconstruction of the entire upper lip and the columella with a modified bilateral nasolabial flap.  

PubMed

The functional and cosmetic reconstruction of the upper lip after a subtotal defect is a highly demanding challenge, especially when the columella is involved. In the majority of cases, the surgical techniques described in the literature are suitable only for restoring the function and appearance of the upper lip but not for reconstructing adjacent areas. In this article, we present the case of an 85-year-old female patient with an extensive, aggressive and highly invasive basal cell carcinoma of the upper lip and the columella. We describe a modification of the nasolabial flap technique using cheek tissue for the reconstruction of the defect. The modified flap is used for both the full-thickness reconstruction of the subtotal upper-lip defect and the restoration of the function and appearance of the columella. This technique allows excellent cosmetic and functional results to be obtained in a single-stage procedure. PMID:19771441

Lorenz, Kai Johannes; Maier, Heinz

2010-06-01

138

Development of an innovative sandwich common bulkhead for cryogenic upper stage propellant tank  

NASA Astrophysics Data System (ADS)

In the frame of the Future Launcher Preparatory Program (FLPP) investigating advancing technologies for the Next Generation of Launchers (NGL) a number of novel key technologies are presently under development for significantly improving vehicle performance in terms of payload capacity and mission versatility. As a respective ESA guided technology development program, Cryogenic Upper Stage Technologies (CUST) has been launched within FLPP that hosts among others the development of a common bulkhead to separate liquid hydrogen from the liquid oxygen compartment. In this context, MT Aerospace proposed an advanced sandwich design concept which is currently in the development phase reaching for TRL4 under MT Aerospace responsibility. Key components of this sandwich common bulkhead are a specific core material, situated in-between two thin aluminum face sheets, and an innovative thermal decoupling element at the equatorial region. The combination of these elements provides excellent thermal insulation capabilities and mechanical performance at a minimum weight, since mechanical and thermal functions are merged in the same component. This improvement is expressed by substantial performance figures of the proposed concept that include high resistance against reverse pressure, an optimized heat leak and minimized mass, involving the sandwich dome structure and the adjacent interface rings. The development of single sub-technologies, all contributing to maturate the sandwich common bulkhead towards the desired technology readiness level (TRL), is described in the context of the given design constraints as well as technical, functional and programmatic requirements, issued from the stage level. This includes the thermal and mechanical characterization of core materials, manufacturing issues as well as non-destructive testing and the thermal and structural analyses and dimensioning of the complete common bulkhead system. Dedicated TRL assessments in the Ariane 5 Mid-life Evolution (A5-ME) program track the progress of these technology developments and analyze their applicability in time for A5-ME. In order to approximate A5-ME concerned preconditions, activities are initiated aiming at harmonization of the available specifications. Hence, a look-out towards a further technology step approaching TRL6 in a subsequent phase is given, briefly addressing topics of full scale manufacture and appropriate thermo-mechanical testing of an entire sandwich common bulkhead.

Szelinski, B.; Lange, H.; Röttger, C.; Sacher, H.; Weiland, S.; Zell, D.

2012-12-01

139

An Investigation of the Properties of a Repetitively Fired Two-Stage Coaxial Plasma Engine  

Microsoft Academic Search

A repetitively fired two-stsge coaxial plasma engine was successfully ; operated in a 3 x 13 foot test chambet under conditions closely simulating those ; of outer space, that is, with negligible interaction between the plasma exhaust ; and the residual gas in the test chamber. The operating principies of the two-; stage engine are described in detail, along with

Per Gloersen; Bernard Gorowitz; Warren A. Hovis Jr.; Richard B. Thomas Jr.

1962-01-01

140

Piston expansion engines for the final cooling stage of cryogenic helium installations  

Microsoft Academic Search

matic braking stage and with a powdered electromagnetic brake DP~T-I. The expansion engine DPG-33-20\\/2,5 is a single-line vertical inverted-type piston engine. The design is based on a fundamentally new method of braking and a new principle of driving and controlling the inlet and outlet valves. Braking and control of the capacity of the expansion engine by its rotational frequency are

V. V. Krylov; N. A. Purtov; E. A. Dokshitskii; I. K. Butkevich; V. S. Bogdanov; M. A. Kuznetsov; N. V. Barmin

1990-01-01

141

Evolutionary stages of a mid-Proterozoic carbonate basin as inferred from the upper marble, Adirondack Lowlands, New York  

SciTech Connect

Mineral abundances for Upper Marble protoliths, obtained through least-squares multiple regression calculations, and trace element concentrations for 112 samples from two drill cores, exhibit stratigraphic variations that are interpretable in terms of stages in the development of the original carbonate basin. Factor analysis with varimax rotation reveals three dominant factors; dolomite, calcite + Sr, and quartz; and five minor factors: clastics, anhydrite + Sr, magnesite, ore + Sr, and illite. When the factor affiliations of samples are considered with respect to their stratigraphic arrangement, the result can be interpreted in terms of a seven-stage model of basin evolution that possesses elements common to both Proterozoic and Phanerozoic carbonate basins. According to this model, stage 1 was dominated by widespread penecontemporaneous dolomitization punctuated by brief periods of increased basin restriction. Stage 2 involved increasing basin restriction during which dolomitization was progressively inhibited by increasing Ca[sup 2+] and/or sulfate levels. Stage 3 was characterized by further basin restriction and episodes of anhydrite precipitation during which dolomitization resumed briefly because of lowered Ca[sup 2+] and/or sulfate levels. Stage 4 and 5 involved decreasing restriction and brine concentrations which allowed large-scale dolomitization to resume during stage 5, and abundant chert was formed in these sediments subsequent to dolomitization. Stage 6 was characterized by increasing restriction and progressive inhibition of dolomitization. Finally, stage 7 saw rapid increases in aluminosilicate sedimentation that ended further carbonate deposition. Sr abundances throughout the cores reflect control by carbonate mineralogy, which was in turn controlled by the degree of basin restriction.

Hauer, K.L.; Grant, N.K. (Miami Univ., Oxford, OH (United States). Dept. of Geology)

1992-01-01

142

Static tests of a simulated upper surface blown jet-flap configuration utilizing a full-size turbofan engine  

NASA Technical Reports Server (NTRS)

The investigation utilizing a small turbofan engine was conducted to evaluate static turning performance and pressure and temperature environment of an upper surface blown wing and flap segment. The tests involved modifications of the engine primary nozzle to alleviate high-temperature problems on the wing and flaps without adversely affecting static turning performance over the desired range of flap deflection and thrust condition.

Shivers, J. P.; Smith, C. C., Jr.

1975-01-01

143

Bilateral slipping of the upper femoral epiphysis in end-stage renal failure. A report of two cases.  

PubMed

Two cases of bilateral slipping of the upper femoral epiphysis in boys with end-stage renal failure due to megacystis and mega-ureter with severe renal osteodystrophy are reported. In one patient the lesion emerged after a dystonic reaction to drugs and in the other after bilateral nephro-ureterectomy. Neither showed marked elevation of growth hormone levels, but both had evidence of renal rickets with severe secondary hyperparathyroidism. Both had a satisfactory response to bilateral internal fixation. The complication should be borne in mind in all young patients with renal osteodystrophy. PMID:7351429

Nixon, J R; Douglas, J F

1980-02-01

144

Large Scale Testing of a Foam/Multilayer Insulation Thermal Control System (TCS) for Cryogenic Upper Stages  

NASA Technical Reports Server (NTRS)

The development of high energy cryogenic upper stages is essential for the efficient delivery of large payloads to various destinations envisioned in future programs. A key element in such upper stages is cryogenic fluid management (CFM) advanced development/technology. Due to the cost of and limited opportunities for orbital experiments, ground testing must be employed to the fullest extent possible. Therefore, a system level test bed termed the Multipurpose Hydrogen Test Bed (MHTB), which is representative in size and shape (3 meter diameter by 3 meter long with a volume of 18 cubic meters) of a fully integrated space transportation vehicle liquid hydrogen propellant tank has been established. To date, upper stage studies have often baselined the foam/multilayer insulation (FMLI) combination concept; however, hardware experience with the concept is minimal and was therefore selected for the MHTB. The foam element (isofoam SS-1 171 with an average thickness of 3.5 centimeters) is designed to protect against ground hold/ascent flight environments, and allows for the use of a dry nitrogen purge as opposed to the more complex/heavy helium purge subsystem normally required with MLI in cryogenic applications. The MLI (45 layers of Double Aluminized Mylar with Dacron spacers) provides protection in the vacuum environment of space and is designed for an on-orbit storage period of 45 days. Several unique features were incorporated in the MLI concept and included: variable density MLI (reduces weight and radiation losses by changing the layer density), larger but fewer DAM perforations for venting during ascent to orbit (reduces radiation losses), and roll wrap installation of the MLI with a commercially established process to lower assembly man-hours and reduce seam heat leak. Thermal performance testing of the MHTB TCS was conducted during three test series conducted between September 1995 and May 1996. Results for the ground hold portion of the tests were as expected producing an average heat leak of 63 WattS/M2 at an average foam surface temperature of 170 K. The results of the simulated orbit hold test interval produced heat leaks ranging from 0.085 to 0.22 Watts/squareM at warm boundary temperatures of 164K and 305K, respectively. When compared to the performance for a traditional MLI system, a 60% reduction in orbital heat leak or boiloff was measured. Overall, the MHTB TCS demonstrated satisfactory performance for all mission phases required of a cryogenic upper stage.

Hastings, Leon; Martin, James

1998-01-01

145

Engineering Science--Raising Awareness of Engineering through Key Stage 3 (Age 11-14) Science  

ERIC Educational Resources Information Center

During 2011, a team from the Centre for Science Education (CSE) worked with four local schools and five Sheffield city region engineering organisations on a project to identify ways to increase the input into young people's awareness of engineering that comes from activities they do in school science. The project also tested an hypothesis that…

Mannion, Ken

2012-01-01

146

Evaluation of innovative rocket engines for single-stage earth-to-orbit vehicles  

NASA Astrophysics Data System (ADS)

Computer models of rocket engines and single-stage-to-orbit vehicles that were developed by the authors at DFVLR and NASA have been combined. The resulting code consists of engine mass, performance, trajectory and vehicle sizing models. The engine mass model includes equations for each subsystem and describes their dependences on various propulsion parameters. The engine performance model consists of multidimensional sets of theoretical propulsion properties and a complete thermodynamic analysis of the engine cycle. The vehicle analyses include an optimized trajectory analysis, mass estimation, and vehicle sizing. A vertical-takeoff, horizontal-landing, single-stage, winged, manned, fully reusable vehicle with a payload capability of 13.6 Mg (30,000 lb) to low earth orbit was selected. Hydrogen, methane, propane, and dual-fuel engines were studied with staged-combustion, gas-generator, dual bell, and the dual-expander cycles. Mixture ratio, chamber pressure, nozzle exit pressure liftoff acceleration, and dual fuel propulsive parameters were optimized.

Manski, Detlef; Martin, James A.

1988-07-01

147

Evaluation of innovative rocket engines for single-stage earth-to-orbit vehicles  

NASA Technical Reports Server (NTRS)

Computer models of rocket engines and single-stage-to-orbit vehicles that were developed by the authors at DFVLR and NASA have been combined. The resulting code consists of engine mass, performance, trajectory and vehicle sizing models. The engine mass model includes equations for each subsystem and describes their dependences on various propulsion parameters. The engine performance model consists of multidimensional sets of theoretical propulsion properties and a complete thermodynamic analysis of the engine cycle. The vehicle analyses include an optimized trajectory analysis, mass estimation, and vehicle sizing. A vertical-takeoff, horizontal-landing, single-stage, winged, manned, fully reusable vehicle with a payload capability of 13.6 Mg (30,000 lb) to low earth orbit was selected. Hydrogen, methane, propane, and dual-fuel engines were studied with staged-combustion, gas-generator, dual bell, and the dual-expander cycles. Mixture ratio, chamber pressure, nozzle exit pressure liftoff acceleration, and dual fuel propulsive parameters were optimized.

Manski, Detlef; Martin, James A.

1988-01-01

148

Regenerative therapy and tissue engineering for the treatment of end-stage cardiac failure  

PubMed Central

Regeneration of myocardium through regenerative therapy and tissue engineering is appearing as a prospective treatment modality for patients with end-stage heart failure. Focusing on this area, this review highlights the new developments and challenges in the regeneration of myocardial tissue. The role of various cell sources, calcium ion and cytokine on the functional performance of regenerative therapy is discussed. The evolution of tissue engineering and the role of tissue matrix/scaffold, cell adhesion and vascularisation on tissue engineering of cardiac tissue implant are also discussed.

Finosh, G.T.; Jayabalan, Muthu

2012-01-01

149

Engineering upper hinge improves stability and effector function of a human IgG1.  

PubMed

Upper hinge is vulnerable to radical attacks that result in breakage of the heavy-light chain linkage and cleavage of the hinge of an IgG1. To further explore mechanisms responsible for the radical induced hinge degradation, nine mutants were designed to determine the roles that the upper hinge Asp and His play in the radical reactions. The observation that none of these substitutions could inhibit the breakage of the heavy-light chain linkage suggests that the breakage may result from electron transfer from Cys(231) directly to the heavy-light chain linkage upon radical attacks, and implies a pathway separate from His(229)-mediated hinge cleavage. On the other hand, the substitution of His(229) with Tyr showed promising advantages over the native antibody and other substitutions in improving the stability and function of the IgG1. This substitution inhibited the hinge cleavage by 98% and suggests that the redox active nature of Tyr did not enable it to replicate the ability of His to facilitate radical induced degradation. We propose that the lower redox potential of Tyr, a residue that may be the ultimate sink for oxidizing equivalents in proteins, is responsible for the inhibition. More importantly, the substitution increased the antibody's binding to Fc?RIII receptors by 2-3-fold, and improved ADCC activity by 2-fold, while maintaining a similar pharmacokinetic profile with respect to the wild type. Implications of these observations for antibody engineering and development are discussed. PMID:22203673

Yan, Boxu; Boyd, Daniel; Kaschak, Timothy; Tsukuda, Joni; Shen, Amy; Lin, Yuwen; Chung, Shan; Gupta, Priyanka; Kamath, Amrita; Wong, Anne; Vernes, Jean-Michel; Meng, Gloria Y; Totpal, Klara; Schaefer, Gabriele; Jiang, Guoying; Nogal, Bartek; Emery, Craig; Vanderlaan, Martin; Carter, Paul; Harris, Reed; Amanullah, Ashraf

2012-02-17

150

Engineering Upper Hinge Improves Stability and Effector Function of a Human IgG1  

PubMed Central

Upper hinge is vulnerable to radical attacks that result in breakage of the heavy-light chain linkage and cleavage of the hinge of an IgG1. To further explore mechanisms responsible for the radical induced hinge degradation, nine mutants were designed to determine the roles that the upper hinge Asp and His play in the radical reactions. The observation that none of these substitutions could inhibit the breakage of the heavy-light chain linkage suggests that the breakage may result from electron transfer from Cys231 directly to the heavy-light chain linkage upon radical attacks, and implies a pathway separate from His229-mediated hinge cleavage. On the other hand, the substitution of His229 with Tyr showed promising advantages over the native antibody and other substitutions in improving the stability and function of the IgG1. This substitution inhibited the hinge cleavage by 98% and suggests that the redox active nature of Tyr did not enable it to replicate the ability of His to facilitate radical induced degradation. We propose that the lower redox potential of Tyr, a residue that may be the ultimate sink for oxidizing equivalents in proteins, is responsible for the inhibition. More importantly, the substitution increased the antibody's binding to Fc?RIII receptors by 2–3-fold, and improved ADCC activity by 2-fold, while maintaining a similar pharmacokinetic profile with respect to the wild type. Implications of these observations for antibody engineering and development are discussed.

Yan, Boxu; Boyd, Daniel; Kaschak, Timothy; Tsukuda, Joni; Shen, Amy; Lin, Yuwen; Chung, Shan; Gupta, Priyanka; Kamath, Amrita; Wong, Anne; Vernes, Jean-Michel; Meng, Gloria Y.; Totpal, Klara; Schaefer, Gabriele; Jiang, Guoying; Nogal, Bartek; Emery, Craig; Vanderlaan, Martin; Carter, Paul; Harris, Reed; Amanullah, Ashraf

2012-01-01

151

Stress Intensity Factors in the Third-Stage Fan Disk of the TF-30 Turbine Engine.  

National Technical Information Service (NTIS)

A photoelastic determination of the mixed-mode stress-intensity factors in a scale model of the third-stage fan disk of the TF-30 turbine engine has been performed. A series of 23 tests were conducted to obtain isochromatic fringe patterns at the tip of a...

R. J. Sanford, J. W. Dally

1978-01-01

152

Failure Studies of a Third Stage Fan Disk from a TF-30 Turbine Engine.  

National Technical Information Service (NTIS)

A detailed failure analysis was made of a fan disk from the third stage of the Navy's turbo-jet engine in order to gain a better understanding of the origing and growth kinetics of the cracks that had developed in service. The in service stress that had c...

W. H. Vaughan, R. J. Sanford, J. M. Krafft, W. H. Cullen, J. W. Dally

1978-01-01

153

Feeding ecology of canvasbacks staging on Pool 7 of the Upper Mississippi River  

USGS Publications Warehouse

Foods consumed by canvasback ducks (Aythya valisineria), food availability, and energetic relationships were studied on Navigation Pool 7 of the upper Mississippi River in 1978, 1979, and 1980. Canvasbacks fed primarily upon winter buds of American wildcelery (Vallisneria americana) and tubers of stiff arrowhead (Sagittaria rigida). In 1980, waterfowl consumed 40% of 380,160 kg of wildcelery winter buds on a portion of Pool 7 referred to as Lake Onalaska. Daily energy expenditure based on estimates from the literature suggests that individual canvasbacks require a minimum of 125 g (dry wt) of wildcelery winter buds each day. Extrapolation of use-days and the daily energy requirement suggests that 3,470 ha of wildcelery are required to support a canvasback population represented by 5 million use-days.

Korschgen, C. E.; George, L. S.; Green, W. L.

1988-01-01

154

Development of Weld Inspection of the Ares I Crew Launch Vehicle Upper Stage  

NASA Technical Reports Server (NTRS)

NASA is designing a new crewed launch vehicle called Ares I to replace the Space Shuttle after its scheduled retirement in 2010. This new launch vehicle will build on the Shuttle technology in many ways including using a first stage based upon the Space Shuttle Solid Rocket Booster, advanced aluminum alloys for the second stage tanks, and friction stir welding to assemble the second stage. Friction stir welding uses a spinning pin that is inserted in the joint between two panels that are to be welded. The pin mechanically mixes the metal together below the melting temperature to form the weld. Friction stir welding allows high strength joints in metals that would otherwise lose much of their strength as they are melted during the fusion welding process. One significant change from the Space Shuttle that impacts NDE is the implementation of self-reacting friction stir welding for non-linear welds on the primary metallic structure. The self-reacting technique differs from the conventional technique because the load of the pin tool pressing down on the metal being joined is reacted by a nut on the end of the tool rather than an anvil behind the part. No spacecraft has ever flown with a self-reacting friction stir weld, so this is a major advancement in the manufacturing process, bringing with it a whole new set of challenges for NDE to overcome. The metal microstructure and possible defects are different from other weld processes. Friction plug welds will be used to close out the hole remaining in the radial welds when friction stir welded. This plug welding also has unique challenges in inspection. The current state of development of these inspections will be presented, along with other information pertinent to NDE of the Ares I.

Russell, Sam; Ezell, David

2010-01-01

155

Joining of Materials - An Upper Level Undergraduate Course in Materials and Manufacturing Engineering A Progress Report  

NSDL National Science Digital Library

An upper level undergraduate course: Joining of Materials, has been designed to require that students perform at the higher level of Blooms Taxonomy1. Students are required to synthesize the subject matter from several prerequisite core engineering courses (applied materials science, thermal sciences, chemistry, and mathematics) in order to best determine the means to join two materials. To make these engineering decisions the students also must consider non-technical issues such as economics, safety, and human resources. Effective communication is critical. This ten-week course introduces the students to the following joining methods: welding, brazing, soldering, and adhesive bonding. After completing the course the students should be able to differentiate between the methods, and based on this knowledge decide the best method to join two materials. Because most texts focus on only one of the four methods listed above, and then tend to focus on either scientific background or technique (not both), it was necessary to develop a series of learning modules for this course. These modules include classroom presentation, webbased notes and exercises, laboratory experiences (joining, physical testing, and metalography), and assignments. This progress report will focus on all aspects of this newly developed course including pedagogy, course content, and course structure. Results of course assessments and continuous improvement will also be presented.

Palmer, Mark A.

2011-08-25

156

Impact of variable river water stage on the simulation of groundwater-river interactions over the Upper Rhine Graben hydrosystem  

NASA Astrophysics Data System (ADS)

The Upper Rhine alluvial aquifer is an important transboundary water resource which is particularly vulnerable to pollution from the rivers due to anthropogenic activities. A realistic simulation of the groundwater-river exchanges is therefore of crucial importance for effective management of water resources, and hence is the main topic of the NAPROM project financed by the French Ministry of Ecology. Characterization of these fluxes in term of quantity and spatio-temporal variability depends on the choice made to represent the river water stage in the model. Recently, a couple surface-subsurface model has been applied to the whole aquifer basin. The river stage was first chosen to be constant over the major part of the basin for the computation of the groundwater-river interactions. The present study aims to introduce a variable river water stage to better simulate these interactions and to quantify the impact of this process over the simulated hydrological variables. The general modeling strategy is based on the Eau-Dyssée modeling platform which couples existing specialized models to address water resources and quality in regional scale river basins. In this study, Eau-Dyssée includes the RAPID river routing model and the SAM hydrogeological model. The input data consist in runoff and infiltration coming from a simulation of the ISBA land surface scheme covering the 1986-2003 period. The QtoZ module allows to calculate river stage from simulated river discharges, which is then used to calculate the exchanges between aquifer units and river. Two approaches are compared. The first one uses rating curves derived from observed river discharges and river stages. The second one is based on the Manning's formula. Manning's parameters are defined with geomorphological parametrizations and topographic data based on Digital Elevation Model (DEM). First results show a relatively good agreement between observed and simulated river water height. Taking into account a variable river stage seems to increase the amount of water exchanged between groundwater and river. Systematic biases are nevertheless found between simulated and observed mean river stage elevation. They show that the primary source of errors when simulating river stage - and hence groundwater-river interactions - is the uncertainties associated with the topographic data used to define the riverbed elevation. Thus, this study confirms the need to access to more accurate DEM for estimating riverbed elevation and studying groundwater-river interactions, at least at regional scale.

Habets, F.; Vergnes, J.

2013-12-01

157

On prediction of re-entry time of an upper stage from GTO  

NASA Astrophysics Data System (ADS)

The evolution of objects in geostationary transfer orbit (GTO) is determined by a complex interplay of atmospheric drag and luni-solar gravity. These orbits are highly eccentric (eccentricity >0.7) and have large variations in velocity and perturbations during a revolution. The periodic changes in the perigee altitudes of these orbits are mainly due to the gravitational perturbations of the Sun and the Moon. The re-entry time of the objects in such orbits is sensitive to the initial conditions. The aim of this paper is to study the re-entry time of the cryogenic stage of the Indian geo-synchronous launch vehicle, GSLV-F04/CS, which has been decaying since 2 September 2007 from initial orbit with eccentricity equal to 0.706. Two parameters, initial eccentricity and ballistic coefficient, are chosen for optimal estimation. It is known that the errors are more in eccentricity for the observations based on two line elements (TLEs). These two parameters are computed with response surface method using a genetic algorithm for the selected eight different zones, based on rough linear variation of the mean apogee altitude during 200 days orbit evolution. The study shows that the GSLV-F04/CS will re-enter between 5 December 2010 and 7 January 2011. The methodology is also applied to study the re-entry of six decayed objects (cryogenic stages of GSLV and Molniya satellites). Good agreement is noticed between the actual and the predicted re-entry times. The absolute percentage error in re-entry prediction time for all the six objects is found to be less than 7%. The present methodology is being adopted at Vikram Sarabhai Space Centre (VSSC) to predict the re-entry time of GSLV-F04/CS.

Mutyalarao, M.; Sharma, Ram Krishan

2011-06-01

158

Advanced Development Program for a 625 lbf thrust engine for Ares First Stage Roll Control System  

NASA Technical Reports Server (NTRS)

NASA's new Ares Launch Vehicle will require twelve thrusters to provide roll control of the vehicle during the first stage firing. All twelve roll control thrusters will be located at the inter-stage segment that separates the solid rocket booster first stage from the second stage. NASA selected a mono propellant hydrazine solution and as a result awarded Aerojet-General a contract in 2007 for an advanced development program for an MR-80- series 625 Ibf vacuum thrust monopropellant hydrazine thruster. This thruster has heritage dating back to the 1976 Viking Landers and most recently for the 2011 Mars Science Laboratory. Prior to the Ares application, the MR-80-series thrusters had been equipped with throttle valves and not typically operated in pulse mode. The primary objective of the advanced development program was to increase the technology readiness level and retire major technical risks for the future flight qualification test program. Aerojet built on their heritage MR-80 rocket engine designs to achieve the design and performance requirements. Significant improvements to cost and lead-time were achieved by applying Design for Manufacturing and Assembly (DFMA) principles. AerojetGeneral has completed Preliminary and Critical Design Reviews, followed by two successful rocket engine development test programs. The test programs included qualification random vibration and firing lite that significantly exceed the flight qualification requirements. This paper discusses the advanced development program and the demonstrated capability of the MR-80C engine. Y;

Dawson, Matt; Chenevert, Blake; Brewster, Gerry; Frei, Tom; Bullard, Brad; Fuller, Ray

2009-01-01

159

Thrust-vector control of a three-axis stabilized upper-stage rocket with fuel slosh dynamics  

NASA Astrophysics Data System (ADS)

This paper studies the thrust vector control problem for an upper-stage rocket with fuel slosh dynamics. The dynamics of a three-axis stabilized spacecraft with a single partially-filled fuel tank are formulated and the sloshing propellant is modeled as a multi-mass–spring system, where the oscillation frequencies of the mass–spring elements represent the prominent sloshing modes. The equations of motion are expressed in terms of the three-dimensional spacecraft translational velocity vector, the attitude, the angular velocity, and the internal coordinates representing the slosh modes. A Lyapunov-based nonlinear feedback control law is proposed to control the translational velocity vector and the attitude of the spacecraft, while attenuating the sloshing modes characterizing the internal dynamics. A simulation example is included to illustrate the effectiveness of the control law.

Rubio Hervas, Jaime; Reyhanoglu, Mahmut

2014-05-01

160

An Updated Zero Boil-Off Cryogenic Propellant Storage Analysis Applied to Upper Stages or Depots in a LEO Environment  

NASA Technical Reports Server (NTRS)

Previous efforts have shown the analytical benefits of zero boil-off (ZBO) cryogenic propellant storage in launch vehicle upper stages of Mars transfer vehicles for conceptual Mars Missions. However, recent NASA mission investigations have looked at a different and broad array of missions, including a variety of orbit transfer vehicle (OTV) propulsion concepts, some requiring cryogenic storage. For many of the missions, this vehicle will remain for long periods (greater than one week) in low earth orbit (LEO), a relatively warm thermal environment. Under this environment, and with an array of tank sizes and propellants, the performance of a ZBO cryogenic storage system is predicted and compared with a traditional, passive-only storage concept. The results show mass savings over traditional, passive-only cryogenic storage when mission durations are less than one week in LEO for oxygen, two weeks for methane, and roughly 2 months for LH2. Cryogenic xenon saves mass over passive storage almost immediately.

Plachta, David; Kittel, Peter

2003-01-01

161

Design and Analysis of a Turbopump for a Conceptual Expander Cycle Upper-Stage Engine  

NASA Technical Reports Server (NTRS)

This viewgraph presentation reviews the motivation for the study, the numerical method used, the numerical simulations of the vaneless diffuser and vaned diffuser. It also reviews the conclusions from the study

Dorney, D.; Rothermel, J.; Griffin, L.; Thornton, R.; Forbes, J.; Skelley, S.; Huber, F.

2006-01-01

162

Wind tunnel investigation of a large-scale upper surface blown-flap transport model having two engines  

NASA Technical Reports Server (NTRS)

An investigation has been conducted to determine the aerodynamic characteristics of a large-scale subsonic jet transport model with an upper surface blowing flap system that would augment lift. The model had a 25 deg swept wing of aspect ratio 7.89 and two turbofan engines with the engine centerline located at 0.256 of the wing semispan. The lift of the flap system was augmented by turbofan exhaust impingement on the Coanda surface. Results were obtained for several flap deflections and engine nozzle configurations at jet momentum coefficients from 0 to 4.0. Three-component longitudinal data are presented with two engines operating. Limited longitudinal and lateral data are presented with an engine out. In addition, limited exhaust and flap pressure data are presented.

Aoyagi, K.; Falarski, M. D.; Koenig, D. G.

1973-01-01

163

Computer program for post-flight evaluation of a launch vehicle upper-stage on-off reaction control system  

NASA Technical Reports Server (NTRS)

This report describes a FORTRAN IV coded computer program for post-flight evaluation of a launch vehicle upper stage on-off reaction control system. Aerodynamic and thrust misalignment disturbances are computed as well as the total disturbing moments in pitch, yaw, and roll. Effective thrust misalignment angle time histories of the rocket booster motor are calculated. Disturbing moments are integrated and used to estimate the required control system total inpulse. Effective control system specific inpulse is computed for the boost and coast phases using measured control fuel useage. This method has been used for more than fifteen years for analyzing the NASA Scout launch vehicle second and third-stage reaction control system performance. The computer program is set up in FORTRAN IV for a CDC CYBER 175 system. With slight modification it can be used on other machines having a FORTRAN compiler. The program has optional CALCOMP plotting output. With this option the program requires 19K words of memory and has 786 cards. Running time on a CDC CYBER 175 system is less than three (3) seconds for a typical problem.

Knauber, R. N.

1982-01-01

164

Investigation of low NOx staged combustor concept in high-speed civil transport engines  

NASA Technical Reports Server (NTRS)

Levels of exhaust emissions due to high temperatures in the main combustor of high-speed civil transport (HSCT) engines during supersonic cruise are predicted. These predictions are based on a new combustor design approach: a rich burn/quick quench/lean burn combustor. A two-stage stirred reactor model is used to calculate the combustion efficiency and exhaust emissions of this novel combustor. A propane-air chemical kinetics model is used to simulate the fuel-rich combustion of jet fuel. Predicted engine exhaust emissions are compared with available experimental test data. The effect of HSCT engine operating conditions on the levels of exhaust emissions is also presented. The work described in this paper is a part of the NASA Lewis Research Center High-Speed Civil Transport Low NO(x) Combustor program.

Nguyen, Hung Lee; Bittker, David A.; Niedzwiecki, Richard W.

1989-01-01

165

Dinosaur Census Reveals Abundant Tyrannosaurus and Rare Ontogenetic Stages in the Upper Cretaceous Hell Creek Formation (Maastrichtian), Montana, USA  

PubMed Central

Background A dinosaur census recorded during the Hell Creek Project (1999–2009) incorporates multiple lines of evidence from geography, taphohistory, stratigraphy, phylogeny and ontogeny to investigate the relative abundance of large dinosaurs preserved in the Upper Cretaceous Hell Creek Formation of northeastern Montana, USA. Overall, the dinosaur skeletal assemblages in the Hell Creek Formation (excluding lag-influenced records) consist primarily of subadult or small adult size individuals. Small juveniles and large adults are both extremely rare, whereas subadult individuals are relatively common. We propose that mature individuals of at least some dinosaur taxa either lived in a separate geographic locale analogous to younger individuals inhabiting an upland environment where sedimentation rates were relatively less, or these taxa experienced high mortality before reaching terminal size where late stage and often extreme cranial morphology is expressed. Methodology/Principal Findings Tyrannosaurus skeletons are as abundant as Edmontosaurus, an herbivore, in the upper Hell Creek Formation and nearly twice as common in the lower third of the formation. Smaller, predatory dinosaurs (e.g., Troodon and dromaeosaurids) are primarily represented by teeth found in microvertebrate localities and their skeletons or identifiable lag specimens were conspicuously absent. This relative abundance suggests Tyrannosaurus was not a typical predator and likely benefited from much wider food choice opportunities than exclusively live prey and/or specific taxa. Tyrannosaurus adults may not have competed with Tyrannosaurus juveniles if the potential for selecting carrion increased with size during ontogeny. Conclusions/Significance Triceratops is the most common dinosaur and isolated skulls contribute to a significant portion of this census. Associated specimens of Triceratops consisting of both cranial and postcranial elements remain relatively rare. This rarity may be explained by a historical collecting bias influenced by facies and taphonomic factors. The limited discovery of postcranial elements may also depend on how extensive a fossil quarry is expanded after a skull is collected.

Horner, John R.; Goodwin, Mark B.; Myhrvold, Nathan

2011-01-01

166

Upper stage affair  

Microsoft Academic Search

Three fundamental requirements must be satisfied by NASA's next-generation OTV: (1) the delivery of payloads at low acceleration levels; (2) ease of operational interface with the Space Shuttle Orbiter and its support infrastructure; and (3) the achievement of a LEO-to-GEO round-trip range capability. Propulsive efficiency is identified as the key factor in man-rated OTV effectiveness; cryogenic rather than solid, storable

Donald Robertson

1988-01-01

167

United States upper stages for the next decade 1 1 Paper IAF96–V. 2.01 presented at the 47th International Astronautical Congress, Beijing, China, 7–11 October 1996  

Microsoft Academic Search

United States (U.S.) upper stage development is approaching another crossroads. In the 1970s the decision was made to fly all future payloads on the space shuttle. Work on high performance shuttle upper stages was halted after the Challenger accident, because of heightened safety concerns about liquid stages in the payload bay. The centaur G? was ultimately developed as the centaur

A. Goldstein; F. Woods

1997-01-01

168

Brunnstrom recovery stage and motricity index for the evaluation of upper extremity in stroke: analysis for correlation and responsiveness.  

PubMed

The aim of this study was to find out first whether Brunnstrom recovery stage (BRS) and motricity index (MI) were correlated with each other and second to observe whether the two assessment tools were sensitive to changes regarding the rehabilitation outcome. Forty-six stroke patients who were admitted to the Stroke Rehabilitation Unit at our Rehabilitation Centre were recruited. All measurements were made within the first 72 h of admission and on the last day of discharge. A physiotherapist performed all MI evaluations and a physiatrist blind to the results performed all BRS evaluations. Both upper extremity (UE) and hand BRS scores were found to be positively correlated with those of UE-MI; moreover, correlations between the discharge values were stronger than those between the admission values. The responsiveness of both the total scores of the BRS and UE-MI were strong (effect size d = 0.97, Wilcoxon Z=5.33, P<0.001 for the UE-BRS; d=0.81, Z=5.09, P<0.001 for the hand BRS; d=0.91, Z=5.45, P<0.001 for the UE-MI). BRS and MI scores were found to be increased on discharge when compared with those of admission and the differences in between were statistically significant (P<0.001). BRS and MI seem to be well correlated and responsive concerning the evaluation of UEs in early stage stroke patients. Being convenient tests, they may easily be applied repetitively for close follow-up during rehabilitation. PMID:19339892

Safaz, Ismail; Yilmaz, Bilge; Ya?ar, Evren; Alaca, Rdvan

2009-09-01

169

Atlantic overturning circulation and Agulhas leakage influences on southeast Atlantic upper ocean hydrography during marine isotope stage 11  

NASA Astrophysics Data System (ADS)

Climate dynamics during the marine isotope stage (MIS) 11 interglacial may provide information about how the climate system will evolve under the conditions of low-amplitude orbital forcing that are also found during the late Holocene. New stable isotope and alkenone data are presented from southeast Atlantic Ocean Drilling Program Site 1085, providing detailed information on interglacial climate evolution and the impacts of Atlantic meridional overturning circulation (MOC) and Agulhas leakage on the regional upper ocean hydrography. The data suggest that although warm surface ocean conditions were maintained at approximate Holocene levels for 40,000 years during MIS 11, subsurface temperature and salinity recorded by deeper-dwelling planktonic foraminifera species were maintained at their highest values for only 7000-8000 years. Surface water temperature and salinity data suggest that the interocean exchange of warm, salty waters into the southeast Atlantic Ocean was directly related to changes in the activity of the MOC during the study interval. Specifically, transient regional warming events during periods of weakened overturning circulation may have been amplified by the continuous interocean exchange of warm, salty Indian Ocean waters that primed the MOC for abrupt resumptions into a vigorous mode of operation. Conversely, a peak in interocean exchange at the end of the MIS 11 interglacial optimum may reflect enhanced trade wind forcing of surface waters whose export to the North Atlantic Ocean could have contributed to renewed ice sheet buildup during the MIS 11 to 10 glacial inception.

Dickson, Alexander J.; Leng, Melanie J.; Maslin, Mark A.; Sloane, Hilary J.; Green, Joanne; Bendle, James A.; McClymont, Erin L.; Pancost, Richard D.

2010-08-01

170

Controlled Re-Entry of the H-IIB Launch Vehicle Upper Stage with the Use of the Re-Entry Safety System  

NASA Astrophysics Data System (ADS)

On January 22, 2011, during flight No. 2 of the H-IIB launch vehicle, the Japan Aerospace Exploration Agency (JAXA) succeeded in performing a controlled re-entry experiment for the upper stage. This is the first time this has been done for the upper stage of a Japanese launch vehicle. For flight No. 1, the upper stage performed a random re- entry. With a view to avoiding debris generation and debris-related impact accidents, JAXA resolved to develop a more refined re-entry process. Consequently, the "Re-entry Safety System" was developed in order to achieve controlled re-entry with certainty. After one orbit, while executing controlled re-entry, the Re-entry Safety System monitored the upper stage's function and orbit. Subsequently, a command disengaging the lockout of the deorbit manoeuvre was issued from ground and re-entry commenced. The details of the Re-entry Safety System, which facilitated the controlled re-entry, are described herein.

Ida, K.; Mori, S.; Sakamoto, K.; Ikeda, S.; Sato, T.; Kawabata, H.

2012-01-01

171

Modelling the early stage of spark ignition engine combustion using the KIVA3V code incorporating an ignition model  

Microsoft Academic Search

The evolution of early stages of homogeneous mixture combustion in spark ignition (SI) engines represents a critical period that greatly affects the whole combustion process. A proper description of this critical phase represents a major issue, which could strongly influence the overall model predictive capability (i.e. model ability to reproduce the real engine behaviour for a large range of operating

L Andreassi; S Cordiner; V Rocco

2003-01-01

172

Designing and Evaluating a Climate Change Course for Upper-Division Engineers and Scientists  

Microsoft Academic Search

AOSS 300, GLOBAL ENVIRONMENTAL IMPACT OF TECHNOLOGICAL CHANGE, was created to provide a mechanism for scientific exploration of the unexpected global environmental side effects of technological innovation with emphasis on issues of the atmosphere and oceans. The course is specifically designed to contribute to the desired Accreditation Board for Engineering and Technology (ABET) outcomes that engineering and science graduates possess

P. J. Samson

2002-01-01

173

Underrepresentation by Race-Ethnicity across Stages of U.S. Science and Engineering Education  

PubMed Central

Blacks, Hispanics, and American Indians/Alaskan Natives are underrepresented in science and engineering fields. A comparison of race–ethnic differences at key transition points was undertaken to better inform education policy. National data on high school graduation, college enrollment, choice of major, college graduation, graduate school enrollment, and doctoral degrees were used to quantify the degree of underrepresentation at each level of education and the rate of transition to the next stage. Disparities are found at every level, and their impact is cumulative. For the most part, differences in graduation rates, rather than differential matriculation rates, make the largest contribution to the underrepresentation. The size, scope, and persistence of the disparities suggest that small-scale, narrowly targeted remediation will be insufficient.

Garrison, Howard

2013-01-01

174

Fuel/oxidizer-rich high-pressure preburners. [staged-combustion rocket engine  

NASA Technical Reports Server (NTRS)

The analyses, designs, fabrication, and cold-flow acceptance testing of LOX/RP-1 preburner components required for a high-pressure staged-combustion rocket engine are discussed. Separate designs of injectors, combustion chambers, turbine simulators, and hot-gas mixing devices are provided for fuel-rich and oxidizer-rich operation. The fuel-rich design addresses the problem of non-equilibrium LOX/RP-1 combustion. The development and use of a pseudo-kinetic combustion model for predicting operating efficiency, physical properties of the combustion products, and the potential for generating solid carbon is presented. The oxygen-rich design addresses the design criteria for the prevention of metal ignition. This is accomplished by the selection of materials and the generation of well-mixed gases. The combining of unique propellant injector element designs with secondary mixing devices is predicted to be the best approach.

Schoenman, L.

1981-01-01

175

Performance Testing of the Engineering Model Astro-H 3-stage ADR  

NASA Technical Reports Server (NTRS)

The Japanese Astro-H mission will include the Soft X-ray Spectrometer (SXS) instrument provided by NASA/GSFC. The SXS will perform imaging spectroscopy in the soft x-ray band using a 6x6 array of silicon microcalorimeters operated at 50 mK. The detectors are cooled by a 3-stage adiabatic demagnetization refrigerator (ADR), which is configured to use either a 1.3 K superfluid helium tank or a 4.5 K Joule-Thomson cryocooler as a heat sink. At present, the engineering model SXS, including the detectors and ADR, has been performance tested at GSFC and integrated with the EM dewar in Japan. The flight model SXS is currently being fabricated. This paper presents test results of the EM ADR and changes that will be implemented in the flight version.

Shirron, Peter J.; Kimball, Mark O.; DiPirro, Michael J.

2013-01-01

176

Aerodynamic Characteristics of a Large-Scale Hybrid Upper Surface Blown Flap Model Having Four Engines.  

National Technical Information Service (NTIS)

Data are presented from an investigation of the aerodynamic characteristics of large-scale wind tunnel aircraft model that utilized a hybrid-upper surface blown flap to augment lift. The hybrid concept of this investigation used a portion of the turbofan ...

R. J. Carros A. G. Boissevain K. Aoyagi

1975-01-01

177

The Attenuation of a Detonation Wave by an Aircraft Engine Axial Turbine Stage  

NASA Technical Reports Server (NTRS)

A Constant Volume Combustion Cycle Engine concept consisting of a Pulse Detonation Combustor (PDC) followed by a conventional axial turbine was simulated numerically to determine the attenuation and reflection of a notional PDC pulse by the turbine. The multi-stage, time-accurate, turbomachinery solver TURBO was used to perform the calculation. The solution domain consisted of one notional detonation tube coupled to 5 vane passages and 8 rotor passages representing 1/8th of the annulus. The detonation tube was implemented as an initial value problem with the thermodynamic state of the tube contents, when the detonation wave is about to exit, provided by a 1D code. Pressure time history data from the numerical simulation was compared to experimental data from a similar configuration to verify that the simulation is giving reasonable results. Analysis of the pressure data showed a spectrally averaged attenuation of about 15 dB across the turbine stage. An evaluation of turbine performance is also presented.

VanZante, Dale; Envia, Edmane; Turner, Mark G.

2007-01-01

178

Changing the facial features of patients with treacher collins syndrome: protocol for 3-stage treatment of hard and soft tissue hypoplasia in the upper half of the face.  

PubMed

Treacher Collins syndrome is a disorder characterized by various congenital soft tissue anomalies involving hypoplasia of the zygoma, maxilla, and mandible. A variety of treatments have been reported to date. These treatments can be classified into 2 major types. The first type involves osteotomy for hard tissue such as the zygoma and mandible. The second type involves plastic surgery using bone grafting in the malar region and soft tissue repair of eyelid deformities. We devised a new treatment to comprehensively correct hard and soft tissue deformities in the upper half of the face of Treacher Collins patients. The aim was to "change facial features and make it difficult to tell that the patients have this disorder." This innovative treatment strategy consists of 3 stages: (1) placement of dermal fat graft from the lower eyelid to the malar subcutaneous area, (2) custom-made synthetic zygomatic bone grafting, and (3) Z-plasty flap transposition from the upper to the lower eyelid and superior repositioning and fixation of the lateral canthal tendon using a Mitek anchor system. This method was used on 4 patients with Treacher Collins syndrome who had moderate to severe hypoplasia of the zygomas and the lower eyelids. Facial features of these patients were markedly improved and very good results were obtained. There were no major complications intraoperatively or postoperatively in any of the patients during the series of treatments. In synthetic bone grafting in the second stage, the implant in some patients was in the way of the infraorbital nerve. Thus, the nerve was detached and then sutured under the microscope. Postoperatively, patients had almost full restoration of sensory nerve torpor within 5 to 6 months. We devised a 3-stage treatment to "change facial features" of patients with hypoplasia of the upper half of the face due to Treacher Collins syndrome. The treatment protocol provided a very effective way to treat deformities of the upper half of the face in patients with Treacher Collins syndrome. PMID:23511742

Mitsukawa, Nobuyuki; Saiga, Atsuomi; Satoh, Kaneshige

2014-07-01

179

Designing and Evaluating a Climate Change Course for Upper-Division Engineers and Scientists  

NASA Astrophysics Data System (ADS)

AOSS 300, GLOBAL ENVIRONMENTAL IMPACT OF TECHNOLOGICAL CHANGE, was created to provide a mechanism for scientific exploration of the unexpected global environmental side effects of technological innovation with emphasis on issues of the atmosphere and oceans. The course is specifically designed to contribute to the desired Accreditation Board for Engineering and Technology (ABET) outcomes that engineering and science graduates possess "the broad education necessary to understand the impact of solutions in a global and societal context." To facilitate this new course a new suite of coupled Flash/PHP/MySQL tools have been created that allow personalization of the students' learning space and interaction with faculty. Using these tools students are challenged to actively participate in the construction of knowledge through development of on-line portfolios that influence course content. This paper reports on lessons learned in the first semester that will guide further course development.

Samson, P. J.

2002-12-01

180

A Technique of Two-Stage Clustering Applied to Environmental and Civil Engineering and Related Methods of Citation Analysis.  

ERIC Educational Resources Information Center

A method of two-stage clustering of literature based on citation frequency is applied to 5,065 articles from 57 journals in environmental and civil engineering. Results of related methods of citation analysis (hierarchical graph, clustering of journals, multidimensional scaling) applied to same set of articles are compared. Ten references are…

Miyamoto, S.; Nakayama, K.

1983-01-01

181

USB environment measurements based on full-scale static engine ground tests. [Upper Surface Blowing for YC-14  

NASA Technical Reports Server (NTRS)

Flow turning parameters, static pressures, surface temperatures, surface fluctuating pressures and acceleration levels were measured in the environment of a full-scale upper surface blowing (USB) propulsive-lift test configuration. The test components included a flightworthy CF6-50D engine, nacelle and USB flap assembly utilized in conjunction with ground verification testing of the USAF YC-14 Advanced Medium STOL Transport propulsion system. Results, based on a preliminary analysis of the data, generally show reasonable agreement with predicted levels based on model data. However, additional detailed analysis is required to confirm the preliminary evaluation, to help delineate certain discrepancies with model data and to establish a basis for future flight test comparisons.

Sussman, M. B.; Harkonen, D. L.; Reed, J. B.

1976-01-01

182

Computer program for prediction of fuel consumption statistical data for an upper stage three-axes stabilized on-off control system  

NASA Technical Reports Server (NTRS)

A FORTRAN coded computer program and method to predict the reaction control fuel consumption statistics for a three axis stabilized rocket vehicle upper stage is described. A Monte Carlo approach is used which is more efficient by using closed form estimates of impulses. The effects of rocket motor thrust misalignment, static unbalance, aerodynamic disturbances, and deviations in trajectory, mass properties and control system characteristics are included. This routine can be applied to many types of on-off reaction controlled vehicles. The pseudorandom number generation and statistical analyses subroutines including the output histograms can be used for other Monte Carlo analyses problems.

1982-01-01

183

Methane Dual Expander Aerospike Nozzle Rocket Engine.  

National Technical Information Service (NTIS)

The Air Force Institute of Technology (AFIT), working to meet requirements set by the Air Force Research Laboratory's Next Generation Engine (NGE) initiative, is developing upper stage rocket models. The current path of investigation focuses on combining ...

M. D. Moen

2012-01-01

184

Atlantic overturning circulation and Agulhas leakage influences on southeast Atlantic upper ocean hydrography during marine isotope stage 11  

Microsoft Academic Search

Climate dynamics during the marine isotope stage (MIS) 11 interglacial may provide information about how the climate system will evolve under the conditions of low-amplitude orbital forcing that are also found during the late Holocene. New stable isotope and alkenone data are presented from southeast Atlantic Ocean Drilling Program Site 1085, providing detailed information on interglacial climate evolution and the

Alexander J. Dickson; Melanie J. Leng; Mark A. Maslin; Hilary J. Sloane; Joanne Green; James A. Bendle; Erin L. McClymont; Richard D. Pancost

2010-01-01

185

Integrated configuration effects of hypersonic upper body designs on Single Stage To Orbit non-circular bodies  

Microsoft Academic Search

The development of air breathing Single Stage To Orbit vehicles requires investigating configurations that integrate 'Tip to Tail' propulsion flowpaths, active aerodynamic control, and large propellant volumes. The selection of these configurations can vary from arrangements like a Conical Fuselage Wing Body to a Non-Circular Lifting Body. Specifically, the selection criterion relies on satisfying both the aeropropulsion requirements and the

Patrick F. Cassidy

1993-01-01

186

Parallel 3D Multi-Stage Simulation of a Turbofan Engine  

NASA Technical Reports Server (NTRS)

A 3D multistage simulation of each component of a modern GE Turbofan engine has been made. An axisymmetric view of this engine is presented in the document. This includes a fan, booster rig, high pressure compressor rig, high pressure turbine rig and a low pressure turbine rig. In the near future, all components will be run in a single calculation for a solution of 49 blade rows. The simulation exploits the use of parallel computations by using two levels of parallelism. Each blade row is run in parallel and each blade row grid is decomposed into several domains and run in parallel. 20 processors are used for the 4 blade row analysis. The average passage approach developed by John Adamczyk at NASA Lewis Research Center has been further developed and parallelized. This is APNASA Version A. It is a Navier-Stokes solver using a 4-stage explicit Runge-Kutta time marching scheme with variable time steps and residual smoothing for convergence acceleration. It has an implicit K-E turbulence model which uses an ADI solver to factor the matrix. Between 50 and 100 explicit time steps are solved before a blade row body force is calculated and exchanged with the other blade rows. This outer iteration has been coined a "flip." Efforts have been made to make the solver linearly scaleable with the number of blade rows. Enough flips are run (between 50 and 200) so the solution in the entire machine is not changing. The K-E equations are generally solved every other explicit time step. One of the key requirements in the development of the parallel code was to make the parallel solution exactly (bit for bit) match the serial solution. This has helped isolate many small parallel bugs and guarantee the parallelization was done correctly. The domain decomposition is done only in the axial direction since the number of points axially is much larger than the other two directions. This code uses MPI for message passing. The parallel speed up of the solver portion (no 1/0 or body force calculation) for a grid which has 227 points axially.

Turner, Mark G.; Topp, David A.

1998-01-01

187

Geochemical make-up of oceanic peridotites from NW Turkey and the multi-stage melting history of the Tethyan upper mantle  

NASA Astrophysics Data System (ADS)

We present the whole-rock and the mineral chemical data for upper mantle peridotites from the Harmanc?k region in NW Turkey and discuss their petrogenetic-tectonic origin. These peridotites are part of a Tethyan ophiolite belt occurring along the ?zmir-Ankara-Ercincan suture zone in northern Turkey, and include depleted lherzolites and refractory harzburgites. The Al2O3 contents in orthopyroxene and clinopyroxene from the depleted lherzolite are high, and the Cr-number in the coexisting spinel is low falling within the abyssal field. However, the orthopyroxene and clinopyroxene in the harzburgites have lower Al2O3 contents for a given Cr-number of spinel, and plot within the lower end of the abyssal field. The whole-rock geochemical and the mineral chemistry data imply that the Harmanc?k peridotites formed by different degrees of partial melting (~%10-27) of the mantle. The depleted lherzolite samples have higher MREE and HREE abundances than the harzburgitic peridotites, showing convex-downward patterns. These peridotites represent up to ~16 % melting residue that formed during the initial seafloor spreading stage of the Northern Neotethys. On the other hand, the more refractory harzburgites represent residues after ~4-11 % hydrous partial melting of the previously depleted MOR mantle, which was metasomatized by slab-derived fluids during the early stages of subduction. The Harmanc?k peridotites, hence, represent the fragments of upper mantle rocks that formed during different stages of the tectonic evolution of the Tethyan oceanic lithosphere in Northern Neotethys. We infer that the multi-stage melting history of the Harmanc?k peridotites reflect the geochemically heterogeneous character of the Tethyan oceanic lithosphere currently exposed along the ?zmir-Ankara-Erzincan suture zone.

Uysal, ?brahim; ?en, A. Dündar; Ersoy, E. Yalç?n; Dilek, Yildirim; Saka, Samet; Zaccarini, Federica; Escayola, Monica; Karsl?, Orhan

2014-02-01

188

Basic stages in the development of the theory of Ramjet Engines (RJE)  

NASA Technical Reports Server (NTRS)

Basic periods in the history of the development of ramjet engine theory are cited. The periods include the first experimental tests as well as the development of basic ideas and theoretical development of the cosmic ramjet engine.

Merkulov, I. A.

1977-01-01

189

Preliminary static tests of a simulated upper-surface blown jet-flap configuration utilizing a full-size turbofan engine  

NASA Technical Reports Server (NTRS)

The investigation was conducted to evaluate the static turning performance and the pressure and temperature environment of an upper-surface-blown wing and flap utilizing a small turbofan engine. The tests involved modifications of the engine primary nozzle designed to alleviate high temperature problems on the wing and flaps and yet provide acceptable static turning performance over the desired range of flap deflections and thrust conditions.

Shivers, J. P.; Smith, C. C., Jr.

1974-01-01

190

Validation of Supersonic Film Cooling Modeling for Liquid Rocket Engine Applications.  

National Technical Information Service (NTIS)

Topics include: upper stage engine key requirements and design drivers; Calspan 'stage 1' results, He slot injection into hypersonic flow (air); test articles for shock generator diagram, slot injector details, and instrumentation positions; test conditio...

C. I. Morris J. H. Ruf

2010-01-01

191

Liquid Rocket Engine Testing Overview  

NASA Technical Reports Server (NTRS)

Contents include the following: Objectives and motivation for testing. Technology, Research and Development Test and Evaluation (RDT&E), evolutionary. Representative Liquid Rocket Engine (LRE) test compaigns. Apollo, shuttle, Expandable Launch Vehicles (ELV) propulsion. Overview of test facilities for liquid rocket engines. Boost, upper stage (sea-level and altitude). Statistics (historical) of Liquid Rocket Engine Testing. LOX/LH, LOX/RP, other development. Test project enablers: engineering tools, operations, processes, infrastructure.

Rahman, Shamim

2005-01-01

192

Space Shuttle Main Engine structural analysis and data reduction/evaluation. Volume 7: High pressure fuel turbo-pump third stage impeller analysis  

NASA Technical Reports Server (NTRS)

This volume summarizes the analysis used to assess the structural life of the Space Shuttle Main Engine (SSME) High Pressure Fuel Turbo-Pump (HPFTP) Third Stage Impeller. This analysis was performed in three phases, all using the DIAL finite element code. The first phase was a static stress analysis to determine the mean (non-varying) stress and static margin of safety for the part. The loads involved were steady state pressure and centrifugal force due to spinning. The second phase of the analysis was a modal survey to determine the vibrational modes and natural frequencies of the impeller. The third phase was a dynamic response analysis to determine the alternating component of the stress due to time varying pressure impulses at the outlet (diffuser) side of the impeller. The results of the three phases of the analysis show that the Third Stage Impeller operates very near the upper limits of its capability at full power level (FPL) loading. The static loading alone creates stresses in some areas of the shroud which exceed the yield point of the material. Additional cyclic loading due to the dynamic force could lead to a significant reduction in the life of this part. The cyclic stresses determined in the dynamic response phase of this study are based on an assumption regarding the magnitude of the forcing function.

Pool, Kirby V.

1989-01-01

193

Postoperative nomogram for disease recurrence and cancer-specific death for upper tract urothelial carcinoma: comparison to american joint committee on cancer staging classification.  

PubMed

Purpose: We sought to develop prognostic models to predict disease recurrence and cancerspecific mortality in patients with upper tract urothelial carcinoma (UTUC) who underwent radical nephroureterectomy (RNU). Materials and Methods: Data on 253 patients treated with RNU between 1995 and 2008 at a single high-volume tertiary referral center were analyzed. Statistically and clinically significant patient and tumor characteristics were identified in a univariate analysis and incorporated into a multivariable Cox regression model. The model was compared to the 2010 American Joint Committee on Cancer (AJCC) staging classification using the concordance index (c-index), corrected for statistical optimism using bootstrap methods. Results: Five-year recurrence-free survival (RFS) and cancer-specific survival (CSS) rates were 73% [95% confidence interval (CI): 66-79%)] and 78% (95% CI: 71-84%), respectively. On multivariate analysis, higher preoperative glomerular filtration rate (GFR) was associated with better CSS [hazard ratio (HR) per 1 mL/min/m2 increase in GFR for CSS: 0.74; P = .002)], while higher pathologic stage (HR for pT2: 2.99 and for ? pT3: 7.34; P < .001) and lymph node involvement (HR: 3.75; P < .001) were associated with worse CSS; results were similar for RFS. The ability of the final models, which included preoperative GFR, lymph node status, pathologic grade, and stage, to predict RFS and CSS (c-index 0.82 and 0.83, respectively) was similar to that of the 2010 AJCC staging classification (c-index 0.80 and 0.81, respectively). Conclusion: Given the data-dependent selection of variables in this single institution cohort, it is unlikely that the marginal improvement found with these prediction models would importantly impact clinical decision-making or improve patient care. The 2010 AJCC staging classification alone is very accurate and should continue to guide follow-up after RNU.  PMID:24807756

Ehdaie, Behfar; Shariat, Shahrokh F; Savage, Caroline; Coleman, Jonathan; Dalbagni, Guido

2014-01-01

194

The First Stage of an Engineering Educational Program on Yatsushiro National College of Technology  

NASA Astrophysics Data System (ADS)

This paper presents a lecture, “Introduction to Engineering” , as a step for the first year of an engineering education program on Yatsushiro National College of Technology. The purpose of the lecture is to motivate students in terms of the variety of engineering work and how such work is related to humans' lives, and to educate students regarding the history of engineering. In this pursuit, students receive lectures in an omnibus from a plurality of teachers from a plurality of departments. This thesis introduces a characteristic and contents these lectures and their effect as measured by questionnaires filled out by students.

Iwatsubo, Kaname

195

Connection between Mature Stages of Deep Convection and the Vertical Transport of Aerosols in the Upper Troposphere  

NASA Astrophysics Data System (ADS)

Convective transport of aerosol has implications to aerosol-cloud interactions and is an important problem for climate studies. We use along-track Cloud-Aerosol Lidar and Infrared Pathfinder Satellite Observation (Calipso) vertical feature mask data, CloudSat data, and International Satellite Cloud Climatology Project (ISCCP) deep convection tracking data to study the impact of deep convection on the transport of aerosols to the upper troposphere (UT) over the South Asian region (0-40N, 70-100E). To minimize misclassification among aerosols and the clouds at UT, we have only used data having large magnitude of cloud aerosol discrimination (CAD) scores for the period of June 2006 to June 2008 when CloudSat and Calipso overlap with the ISCCP deep convection tracking data. Preliminary results suggest that active clouds most likely transport aerosols to high altitudes, whereas decaying clouds are least likely to transport aerosols to the UT. Mature clouds act in-between the active and decaying clouds. Active clouds that transport aerosols are different than decaying clouds in terms of higher cloud water path, cloud water content at 10 km altitude, number of convective clusters, and convective fraction. The NASA Goddard Global Modeling and Assimilation Office wind data, projected onto the CloudSat tracks, suggests a strong updraft associated with active clouds in favor of aerosol transportation, and a low level or mid-level subsidence associated with decaying clouds.

Chakraborty, S.; Fu, R.; Massie, S. T.; Pan, L.

2011-12-01

196

Turbopumps for cryogenic upper stage engines. [fabrication and evaluation of turbine pumps for liquid hydrogen and liquid oxygen  

NASA Technical Reports Server (NTRS)

Small, high-performance LO2 and LH2 turbopump assembly configurations were selected, detail designs were prepared and two of each unit were fabricated with each unit consisting of pump, turbine gas generator, and appropriate controls. Following fabrication, development testing was conducted on each type to demonstrate performance, durability, transient characteristics, and heat transfer under simulated altitude conditions. Following successful completion of development effort, the two LO2 turbopump units and one LH2 turbopump unit were acceptance tested as specified. Inspection of the units following development testing revealed no deleterious effects of testing. The test results of LO2 turbopump assembly testing correlated well with predicted performance while the LH2 turbopump test results, though generally consistent with predicted values, did show lower than anticipated developed head at the design point and in the high flow range of operation.

Zachary, A. T.; Csomor, A.; Tignac, L. L.

1973-01-01

197

From Concept to Design: Progress on the J-2X Upper Stage Engine for the Ares Launch Vehicles  

NASA Technical Reports Server (NTRS)

In accordance with national policy and NASA's Global Exploration Strategy, the Ares Projects Office is embarking on development of a new launch vehicle fleet to fulfill the national goals of replacing the space shuttle fleet, returning to the moon, and exploring farther destinations like Mars. These goals are shaped by the decision to retire the shuttle fleet by 2010, budgetary constraints, and the requirement to create a new fleet that is safer, more reliable, operationally more efficient than the shuttle fleet, and capable of supporting long-range exploration goals. The present architecture for the Constellation Program is the result of extensive trades during the Exploration Systems Architecture Study and subsequent refinement by the Ares Projects Office at Marshall Space Flight Center.

Byrd, Thomas

2008-01-01

198

Modeling and Test Data Analysis of a Tank Rapid Chill and Fill System for the Advanced Shuttle Upper Stage (ASUS) Concept  

NASA Technical Reports Server (NTRS)

The Advanced Shuttle Upper Stage (ASUS) concept addresses safety concerns associated .with cryogenic stages by launching empty, and filling on ascent. The ASUS employs a rapid chill and fill concept. A spray bar is used to completely chill the tank before fill, allowing the vent valve to be closed during the fill process. The first tests of this concept, using a flight size (not flight weight) tank. were conducted at Marshall Space Flight Center (MSFC) during the summer of 2000. The objectives of the testing were to: 1) demonstrate that a flight size tank could be filled in roughly 5 minutes to accommodate the shuttle ascent window, and 2) demonstrate a no-vent fill of the tank. A total of 12 tests were conducted. Models of the test facility fill and vent systems, as well as the tank, were constructed. The objective of achieving tank fill in 5 minutes was met during the test series. However, liquid began to accumulate in the tank before it was chilled. Since the tank was not chilled until the end of each test, vent valve closure during fill was not possible. Even though the chill and fill process did not occur as expected, reasonable model correlation with the test data was achieved.

Flachbart, Robin; Hedayat, Ali; Holt, Kimberly A.; Cruit, Wendy (Technical Monitor)

2001-01-01

199

Three-stage autoignition of gasoline in an HCCI engine: An experimental and chemical kinetic modeling investigation  

SciTech Connect

The alternative HCCI combustion mode presents a possible means for decreasing the pollution with respect to conventional gasoline or diesel engines, while maintaining the efficiency of a diesel engine or even increasing it. This paper investigates the possibility of using gasoline in an HCCI engine and analyzes the autoignition of gasoline in such an engine. The compression ratio that has been used is 13.5, keeping the inlet temperature at 70 C, varying the equivalence ratio from 0.3 to 0.54, and the EGR (represented by N{sub 2}) ratio from 0 to 37 vol%. For comparison, a PRF95 and a surrogate containing 11 vol% n-heptane, 59 vol% iso-octane, and 30 vol% toluene are used. A previously validated kinetic surrogate mechanism is used to analyze the experiments and to yield possible explanations to kinetic phenomena. From this work, it seems quite possible to use the high octane-rated gasoline for autoignition purposes, even under lean inlet conditions. Furthermore, it appeared that gasoline and its surrogate, unlike PRF95, show a three-stage autoignition. Since the PRF95 does not contain toluene, it is suggested by the kinetic mechanism that the benzyl radical, issued from toluene, causes this so-defined ''obstructed preignition'' and delaying thereby the final ignition for gasoline and its surrogate. The results of the kinetic mechanism supporting this explanation are shown in this paper. (author)

Machrafi, Hatim; Cavadias, Simeon [UPMC Universite Paris 06, LGPPTS, Ecole Nationale Superieure de Chimie de Paris (France); UPMC Universite Paris 06, Institut Jean Le Rond D'Alembert (France)

2008-12-15

200

Pressure distribution of a twin-engine upper-surface blown jet-flap model. [wind tunnel tests to determine chordwise and spanwise pressure distributions  

NASA Technical Reports Server (NTRS)

An investigation has been made to determine the chordwise and spanwise pressure distributions of a small-scale upper-surface blown jet-augmented flap STOL model. The model was powered by two simulated high-bypass-ratio turbofan engines mounted ahead of and above an unswept-untapered wing in a nacelle having a rectangular nozzle. The results of the investigation are presented as tabulated and plotted chordwise pressure distribution coefficients for nine spanwise stations.

Smith, C. C., Jr.; White, L. C.

1974-01-01

201

A review of findings of a study of rocket based combined cycle engines applied to extensively axisymmetric single stage to orbit vehicles  

NASA Technical Reports Server (NTRS)

Extensively axisymmetric and non-axisymmetric Single Stage To Orbit (SSTO) vehicles are considered. The information is presented in viewgraph form and the following topics are presented: payload comparisons; payload as a percent of dry weight - a system hardware cost indicator; life cycle cost estimations; operations and support costs estimation; selected engine type; and rocket engine specific impulse calculation.

Foster, Richard W.

1992-01-01

202

A knowledge-based engineering tool to estimate cost and weight of composite aerospace structures at the conceptual stage of the design process  

Microsoft Academic Search

Purpose – This paper seeks to address issues related to the development of a knowledge-based engineering system for estimating manufacturing cost and weight of a composite structure at the conceptual stage of a design. Design\\/methodology\\/approach – The system has been developed in the CATIA V5 knowledge environment and is applied to structures made of composite materials. At the conceptual stage

Jin-Woo Choi; Don Kelly; John Raju

2007-01-01

203

Multimodel ensemble predictions of river stages computed in real time: application of the HydroProg system in the upper Nysa K?odzka basin (SW Poland)  

NASA Astrophysics Data System (ADS)

A novel system for computing predictions of river stages in real time, based on the concept of multimodelling, has been recently designed and built at the University of Wroc?aw, Poland. The system, known as HydroProg, has been launched in August 2013, and its first experimental basin is the upper Nysa K?odzka basin (SW Poland) above the outlet in the town of Bardo, with the catchment area of 1744 square kilometres. The study area, which includes a large and flood-prone intramontane basin with the surrounding mountains, has been chosen in order to connect the HydroProg system to the existing real-time hydrometeorological observational network, namely the Local System for Flood Monitoring in K?odzko County. This network offers a high temporal resolution of observations, as the length of the sampling interval is equal to 15 minutes. Multiple external hydrologic prediction models - those which enable rapid recalibration every quarter of an hour - can be plugged in to HydroProg, and the latter keeps calculating multimodel ensemble forecasts of river stages with weights updated along with the 15-minute update of the entire system. The initial results - based on a few data-based hydrologic models and the following two types of predictions: (1) 15 minute update and lead time of 3h and (2) 6 hour update and lead time of 2 days - clearly show that both normal and peak flow water levels can be successfully predicted. The paper discusses the maximal prediction horizons, at 11 hydrologic gauges under scrutiny, for which Nash-Sutcliffe efficiency judges the predictions as reasonable. Along with the discussion of scientific results, the dedicated real-time web map service, presenting both the current predictions and their statistics in the online mode, is shown.

Niedzielski, Tomasz; Mizi?ski, Bart?omiej; Kryza, Maciej; Netzel, Pawe?; Wieczorek, Ma?gorzata; Spallek, Waldemar; Szymanowski, Mariusz; Migo?, Piotr; Kasprzak, Marek; Witek, Matylda; Jeziorska, Justyna; Kosek, Wies?aw

2014-05-01

204

Development and Lab-Scale Testing of a Gas Generator Hybrid Fuel in Support of the Hydrogen Peroxide Hybrid Upper Stage Program  

NASA Technical Reports Server (NTRS)

As part of a NASA funded contract to develop and demonstrate a gas generator cycle hybrid rocket motor for upper stage space motor applications, the development and demonstration of a low sensitivity, high performance fuel composition was undertaken. The ultimate goal of the development program was to demonstrate successful hybrid operation (start, stop, throttling) of the fuel with high concentration (90+%) hydrogen peroxide. The formulation development and lab-scale testing of a simple DOT Class 1.4c gas generator propellant is described. Both forward injected center perforated and aft injected end burner hybrid combustion behavior were evaluated with gaseous oxygen and catalytically decomposed 90% hydrogen peroxide. Cross flow and static environments were found to yield profoundly different combustion behaviors, which were further governed by binder type, oxidizer level and, significantly, oxidizer particle size. Primary extinguishment was accomplished via manipulation of PDL behavior and oxidizer turndown, which is enhanced with the hydrogen peroxide system. Laboratory scale combustor results compared very well with 11-inch and 24-inch sub-scale test results with 90% hydrogen peroxide.

Lund, Gary K.; Starrett, William David; Jensen, Kent C.; McNeal, Curtis (Technical Monitor)

2001-01-01

205

Increased Upper and Lower Tract Urothelial Carcinoma in Patients with End-Stage Renal Disease: A Nationwide Cohort Study in Taiwan during 1997-2008  

PubMed Central

Background. Urothelial cancer (UC) is the leading cancer of patients with end-stage renal disease (ESRD) in Taiwan. The aims of this study were to explore the time trends of UC incidences and propose possible etiologic factors. Methods. Abstracting from the National Health Insurance Research Database (NHIRD), there were 90,477 newly diagnosed cases of ESRD between 1997 and 2008 covering the patients aged 40–85. Among them, 2,708 had developed UC after diagnosis of ESRD. The CIR40–85 (cumulative incidence rate) of upper tract UC (UTUC) and lower tract UC (LTUC) were calculated for ESRD patients and general population, as well as SIR40–85 (standardized incidence ratio) for comparison. Results. Female ESRD patients were found to have 9–18 times of elevated risks of UC, while those of males were increased up to 4–14 times. The time trends of CIR40–84 and SIR40–84 of UTUC in females appear to decline after calendar year 2000. These trends may be related to AA associated herbal products after 1998. Conclusions. Patients with ESRD are at increased risks for both LTUC and UTUC in Taiwan. We hypothesize that the time trends associate with the consumption of aristolochic acid in Chinese herbal products (female predominant).

Wang, Shuo-Meng; Lai, Ming-Nan; Chen, Pau-Chung; Pu, Yeong-Shiau; Lai, Ming-Kuen; Hwang, Jing-Shiang; Wang, Jung-Der

2014-01-01

206

Natural growth and diet of known-age pallid sturgeon (Scaphirhynchus albus) early life stages in the upper Missouri River basin, Montana and North Dakota  

USGS Publications Warehouse

Prior to anthropogenic modifications, the historic Missouri River provided ecological conditions suitable for reproduction, growth, and survival of pallid sturgeon Scaphirhynchus albus. However, little information is available to discern whether altered conditions in the contemporary Missouri River are suitable for feeding, growth and survival of endangered pallid sturgeon during the early life stages. In 2004 and 2007, nearly 600 000 pallid sturgeon free embryos and larvae were released in the upper Missouri River and survivors from these releases were collected during 2004–2010 to quantify natural growth rates and diet composition. Based on genetic analysis and known-age at release (1–17 days post-hatch, dph), age at capture (dph, years) could be determined for each survivor. Totals of 23 and 28 survivors from the 2004 and 2007 releases, respectively, were sampled. Growth of pallid sturgeon was rapid (1.91 mm day-1) during the initial 13–48 dph, then slowed as fish approached maximum length (120–140 mm) towards the end of the first growing season. The diet of young-of-year pallid sturgeon was comprised of Diptera larvae, Diptera pupae, and Ephemeroptera nymphs. Growth of pallid sturgeon from ages 1–6 years was about 48.0 mm year-1. This study provides the first assessment of natural growth and diet of young pallid sturgeon in the wild. Results depict pallid sturgeon growth trajectories that may be expected for naturally produced wild stocks under contemporary habitat conditions in the Missouri River and Yellowstone River.

Braaten, P. J.; Fuller, D. B.; Lott, R. D.; Haddix, T. M.; Holte, L. D.; Wilson, R. H.; Bartron, M. L.; Kalie, J. A.; DeHaan, P. W.; Ardren, W. R.; Holm, R. J.; Jaeger, M. E.

2012-01-01

207

Energy efficient engine. Fan and quarter-stage component performance report  

NASA Technical Reports Server (NTRS)

The fan configuration for the general Electric/NASA Energy Efficient Engine was selected following an extensive preliminary design study. The fan has an inlet radius ratio of 0.342 and a specific flowrate of 208.9 Kg/sec/sq. m (42.8 1bm/sec/sq. ft). The design corrected tip speed is 411.5 m/sec (1350 ft/sec) producing a bypass flow total-pressure ratio of 1.65 and a core flow total-pressure ratio of 1.6. The design bypass ratio is 6.8. The aerodynamic design point corresponds to the maximum climb power setting at Mach 0.8 and 10.67 Km (35,000 ft) altitude. The fully-instrumented fan component was tested in the Lynn Large Fan Test Facility in 1981. The overall performance results, reported herein, showed excellent fan performance with the fan meeting all of its component test goals of flow, efficiency and stall margin.

Cline, S. J.; Halter, P. H.; Kutney, J. T., Jr.; Sullivan, T. J.

1983-01-01

208

J-2X, The Engine of the Future  

NASA Technical Reports Server (NTRS)

My project was two-fold, with both parts involving the J-2X Upper Stage engine (which will be used on both the Ares I and V). Mainly, I am responsible for using a program called Iris to create visual represen tations of the rocket engine's telemetry data. Also, my project includes the application of my newly acquired Pro Engineer skills in develo ping a 3D model of the engine's nozzle.

Smith, Gail

2009-01-01

209

INTEGRATED GEOLOGIC-ENGINEERING MODEL FOR REEF AND CARBONATE SHOAL RESERVOIRS ASSOCIATED WITH PALEOHIGHS: UPPER JURASSIC SMACKOVER FORMATION, NORTHEASTERN GULF OF MEXICO  

SciTech Connect

The University of Alabama in cooperation with Texas A&M University, McGill University, Longleaf Energy Group, Strago Petroleum Corporation, and Paramount Petroleum Company are undertaking an integrated, interdisciplinary geoscientific and engineering research project. The project is designed to characterize and model reservoir architecture, pore systems and rock-fluid interactions at the pore to field scale in Upper Jurassic Smackover reef and carbonate shoal reservoirs associated with varying degrees of relief on pre-Mesozoic basement paleohighs in the northeastern Gulf of Mexico. The project effort includes the prediction of fluid flow in carbonate reservoirs through reservoir simulation modeling which utilizes geologic reservoir characterization and modeling and the prediction of carbonate reservoir architecture, heterogeneity and quality through seismic imaging. The primary objective of the project is to increase the profitability, producibility and efficiency of recovery of oil from existing and undiscovered Upper Jurassic fields characterized by reef and carbonate shoals associated with pre-Mesozoic basement paleohighs. The principal research effort for Year 1 of the project has been reservoir description and characterization. This effort has included four tasks: (1) geoscientific reservoir characterization, (2) the study of rock-fluid interactions, (3) petrophysical and engineering characterization and (4) data integration. This work was scheduled for completion in Year 1. Overall, the project work is on schedule. Geoscientific reservoir characterization is essentially completed. The architecture, porosity types and heterogeneity of the reef and shoal reservoirs at Appleton and Vocation Fields have been characterized using geological and geophysical data. The study of rock-fluid interactions has been initiated. Observations regarding the diagenetic processes influencing pore system development and heterogeneity in these reef and shoal reservoirs have been made. Petrophysical and engineering property characterization is progressing. Data on reservoir production rate and pressure history at Appleton and Vocation Fields have been tabulated, and porosity data from core analysis has been correlated with porosity as observed from well log response. Data integration is on schedule, in that, the geological, geophysical, petrophysical and engineering data collected to date for Appleton and Vocation Fields have been compiled into a fieldwide digital database for reservoir characterization, modeling and simulation for the reef and carbonate shoal reservoirs for each of these fields.

Ernest A. Mancini

2001-09-14

210

Wind-tunnel investigation of aerodynamic performance, steady amd vibratory loads, surface temperatures, and acoustic characteristics of a large-scale twin-engine upper-surface blown jet-flap configuration  

NASA Technical Reports Server (NTRS)

Static and wind-on tests were conducted to determine the aerodynamic characteristics of and the effects of jet impingement on the wing of a large scale upper surface blown configuration powered with an actual turbine engine. The wing and flaps were instrumented with experimental dual-sensing transducer units consisting of a fluctuating pressure gage, a vibratory accelerometer, and a surface mounted alumel thermocouple. Noise directivity and spectral content measurements were obtained for various flap configurations and various engine thrust settings to provide baseline noise data for other upper surface blown configurations.

1976-01-01

211

Time scales of change in chemical and biological parameters after engineered levee breaches adjacent to Upper Klamath and Agency Lakes, Oregon  

USGS Publications Warehouse

Eight sampling trips were coordinated after engineered levee breaches hydrologically reconnected both Upper Klamath Lake and Agency Lake, Oregon, to adjacent wetlands. The reconnection, by a series of explosive blasts, was coordinated by The Nature Conservancy to reclaim wetlands that had for approximately seven decades been leveed for crop production. Sets of nonmetallic porewater profilers (U.S. Patent 8,051,727 B1; November 8, 2011; http://www.uspto.gov/web/patents/patog/ week45/OG/html/1372-2/US08051727-20111108.html.) were deployed during these trips in November 2007, June 2008, May 2009, July 2009, May 2010, August 2010, June 2011, and July 2011 (table 1). Deployments temporally spanned the annual cyanophyte bloom of Aphanizomenon flos-aquae and spatially involved three lake and four wetland sites. Spatial and temporal variation in solute benthic flux was determined by the field team, using the profilers, over an approximately 4-year period beginning 3 days after the levee breaches. The highest flux to the water column of dissolved organic carbon (DOC) was detected in the newly flooded wetland, contrasting negative or insignificant DOC fluxes at adjacent lake sites. Over the multiyear study, DOC benthic fluxes dissipated in the reconnected wetlands, converging to values similar to those for established wetlands and to the adjacent lake (table 2). In contrast to DOC, benthic sources of soluble reactive phosphorus, ammonium, dissolved iron and manganese from within the reconnected wetlands were consistently elevated (that is, significant in magnitude relative to riverine and established-wetland sources) indicating a multi-year time scale for certain chemical changes after the levee breaches (table 2). Colonization of the reconnected wetlands by aquatic benthic invertebrates during the study trended toward the assemblages in established wetlands, providing further evidence of a multiyear transition of this area to permanent aquatic habitat (table 3). Both the lake and wetland benthic environments substantively contribute to macro- and micronutrients in the water column. Wetland areas undergoing restoration, and those being used for water storage, function very differently relatively to the established wetland within the Upper Klamath Lake National Wildlife Refuge, adjacent Upper Klamath Lake. Developing long-term management strategies for water quality in the Upper Klamath Basin requires recognition of the multi-year time scales associated with restoring wetlands that provide natural, seasonal ecosystem function and services.

Kuwabara, James S.; Topping, Brent R.; Carter, James L.; Wood, Tamara M.; Parchaso, Francis; Cameron, Jason M.; Asbill, Jessica R.; Carlson, Rick A.; Fend, Steven V.

2012-01-01

212

Icehouse, cool-water carbonate ramps: the case of the Upper Pliocene Capodarso Fm (Sicily): role of trace fossils in the reconstruction of growth stages of prograding wedges  

Microsoft Academic Search

An integrated approach, based on the use of trace fossils combined with analysis of physical and biogenic structures, identification\\u000a of key surfaces, and reconstruction of stratigraphic architecture, proved to be of critical value in defining the depositional\\u000a environments, elucidating the dynamics of progradation, and characterizing the various systems tracts of Upper Pliocene progradational\\u000a wedges (Capodarso area, Sicily) generated by cool-water

Francesco Massari; Assunta D’Alessandro

2010-01-01

213

Comparative study of Botox® injection treatment for upper eyelid retraction with 6-month follow-up in patients with thyroid eye disease in the congestive or fibrotic stage  

Microsoft Academic Search

AimTo compare morphometric data of the eyelid fissure and the levator muscle function (LF) before and up to 6 months after transcutaneous injection with five units of Botox® in patients with upper lid retraction (ULR) from congestive or fibrotic thyroid eye disease (TED).MethodsTwenty-four patients with ULR from TED were submitted to transcutaneous injection of 5 units (0.1 ml) of Botox

P G Costa; F P Saraiva; I C Pereira; M L R Monteiro; S Matayoshi; MLR Monteiro

2009-01-01

214

The Use of the Maurer Factor for Estimating the Cost of a Turbine Engine in the Early Stages of Development.  

National Technical Information Service (NTIS)

Military managers are faced with increasing systems costs. One area where this increasing cost is especially true is in the acquisition of aircraft weapon systems. A driving factor in the aircraft cost is the turbine engine, and therefore acquisition mana...

C. W. Barrett M. J. Koenig

1979-01-01

215

A Collaborative Analysis Tool for Integrating Hypersonic Aerodynamics, Thermal Protection Systems, and RBCC Engine Performance for Single Stage to Orbit Vehicles  

NASA Technical Reports Server (NTRS)

Presented is a computer-based tool that connects several disciplines that are needed in the complex and integrated design of high performance reusable single stage to orbit (SSTO) vehicles. Every system is linked to every other system, as is the case of SSTO vehicles with air breathing propulsion, which is currently being studied by NASA. The deficiencies in the scramjet powered concept led to a revival of interest in Rocket-Based Combined-Cycle (RBCC) propulsion systems. An RBCC propulsion system integrates airbreathing and rocket propulsion into a single engine assembly enclosed within a cowl or duct. A typical RBCC propulsion system operates as a ducted rocket up to approximately Mach 3. At this point the transitions to a ramjet mode for supersonic-to-hypersonic acceleration. Around Mach 8 the engine transitions to a scram4jet mode. During the ramjet and scramjet modes, the integral rockets operate as fuel injectors. Around Mach 10-12 (the actual value depends on vehicle and mission requirements), the inlet is physically closed and the engine transitions to an integral rocket mode for orbit insertion. A common feature of RBCC propelled vehicles is the high degree of integration between the propulsion system and airframe. At high speeds the vehicle forebody is fundamentally part of the engine inlet, providing a compression surface for air flowing into the engine. The compressed air is mixed with fuel and burned. The combusted mixture must be expanded to an area larger than the incoming stream to provide thrust. Since a conventional nozzle would be too large, the entire lower after body of the vehicle is used as an expansion surface. Because of the high external temperatures seen during atmospheric flight, the design of an airbreathing SSTO vehicle requires delicate tradeoffs between engine design, vehicle shape, and thermal protection system (TPS) sizing in order to produce an optimum system in terms of weight (and cost) and maximum performance.

Stanley, Thomas Troy; Alexander, Reginald

1999-01-01

216

NASA/DOD Aerospace Knowledge Diffusion Research Project. Paper 53: From student to entry-level professional: Examining the technical communications practices of early career-stage US aerospace engineers and scientists  

NASA Technical Reports Server (NTRS)

Studies indicate that communications and information-related activities take up a substantial portion of an engineer's work week; therefore, effective communications and information-use skills are one of the key engineering competencies that early career-stage aerospace engineers and scientists must possess to be successful. Feedback from industry rates communications and information-use skills high in terms of their importance to engineering practice; however, this same feedback rates the communications and information-use skills of early career-stage engineers low. To gather adequate and generalizable data about the communications and information-related activities of entry-level aerospace engineers and scientists, we surveyed 264 members of the AIAA who have no more than 1-5 years of aerospace engineering work experience. To learn more about the concomitant communications norms, we compared the results of this study with data (1,673 responses) we collected from student members of the AIAA and with data (341 responses) we collected from a study of aerospace engineering professionals. In this paper, we report selected results from these studies that focused on the communications practices and information-related activities of early career-stage U.S. aerospace engineers and scientists in the workplace.

Pinelli, Thomas E.; Holloway, Karen; Barclay, Rebecca O.; Kennedy, John M.

1995-01-01

217

Stage Separation Performance Analysis Project  

NASA Technical Reports Server (NTRS)

Stage separation process is an important phenomenon in multi-stage launch vehicle operation. The transient flowfield coupled with the multi-body systems is a challenging problem in design analysis. The thermodynamics environment with burning propellants during the upper-stage engine start in the separation processes adds to the complexity of the-entire system. Understanding the underlying flow physics and vehicle dynamics during stage separation is required in designing a multi-stage launch vehicle with good flight performance. A computational fluid dynamics model with the capability to coupling transient multi-body dynamics systems will be a useful tool for simulating the effects of transient flowfield, plume/jet heating and vehicle dynamics. A computational model using generalize mesh system will be used as the basis of this development. The multi-body dynamics system will be solved, by integrating a system of six-degree-of-freedom equations of motion with high accuracy. Multi-body mesh system and their interactions will be modeled using parallel computing algorithms. Adaptive mesh refinement method will also be employed to enhance solution accuracy in the transient process.

Chen, Yen-Sen; Zhang, Sijun; Liu, Jiwen; Wang, Ten-See

2001-01-01

218

Towards a standard upper ontology  

Microsoft Academic Search

The Suggested Upper Merged Ontology (SUMO) is an upper levelontology that has been proposed as a starter document for TheStandard Upper Ontology Working Group, an IEEE-sanctioned workinggroup of collaborators from the fields of engineering, philosophy,and information science. The SUMO provides definitions forgeneral-purpose terms and acts as a foundation for more specificdomain ontologies. In this paper we outline the strategy used

Ian Niles; Adam Pease

2001-01-01

219

Parametric and exergetic analysis of a two-stage transcritical combined organic Rankine cycle used for multiple grades waste heat recovery of diesel engine  

NASA Astrophysics Data System (ADS)

Diesel engine has multiple grades of waste heat with different ratios of combustion heat, exhaust is 400 °C with the ratio of 21% and coolant is 90 °C with 19%. Few previous publications investigate the recovery of multiple grades waste heat together. In this paper, a two-stage transcritical combined organic rankine cycle (CORC) is presented and analyzed. In the combined system, the high and low temperature stages transcritical cycle recover the high grades waste heat, and medium to low grades waste heat respectively, and being combined efficiently. Meanwhile, the suitable working fluids for high stage are chosen and analyzed. The cycle parameters, including thermal efficiency (?th), net power output (Pnet), energy efficiency (?exg) and global thermal efficiency of DE-CORC(?glo) have also been analyzed and optimized. The results indicate that this combined system could recover all the waste heat with a high recovery ratio (above 90%) and obtain a maximum power output of 37kW for a DE of 243kW. The global thermal efficiency of DE-CORC can get a max value of 46.2% compared with 40% for single DE. The results also indicate that all the energy conversion process have a high exergy efficiency.

Tian, H.; Zhang, J.; Xu, X. F.; Shu, G. Q.; Wei, H. Q.

2013-12-01

220

Studies of an extensively axisymmetric rocket based combined cycle (RBCC) engine powered single-stage-to-orbit (SSTO) vehicle  

SciTech Connect

The present comparative performance study has established that rocket-based combined cycle (RBCC) propulsion systems, when incorporated by essentially axisymmetric SSTO launch vehicle configurations whose conical forebody maximizes both capture-area ratio and total capture area, are capable of furnishing payload-delivery capabilities superior to those of most multistage, all-rocket launchers. Airbreathing thrust augmentation in the rocket-ejector mode of an RBCC powerplant is noted to make a major contribution to final payload capability, by comparison to nonair-augmented rocket engine propulsion systems. 16 refs.

Foster, R.W.; Escher, W.J.D.; Robinson, J.W.

1989-01-01

221

A Collaborative Analysis Tool for Integrated Hypersonic Aerodynamics, Thermal Protection Systems, and RBCC Engine Performance for Single Stage to Orbit Vehicles  

NASA Technical Reports Server (NTRS)

Presented is a computer-based tool that connects several disciplines that are needed in the complex and integrated design of high performance reusable single stage to orbit (SSTO) vehicles. Every system is linked to every other system, as is the case of SSTO vehicles with air breathing propulsion, which is currently being studied by NASA. An RBCC propulsion system integrates airbreathing and rocket propulsion into a single engine assembly enclosed within a cowl or duct. A typical RBCC propulsion system operates as a ducted rocket up to approximately Mach 3. Then there is a transition to a ramjet mode for supersonic-to-hypersonic acceleration. Around Mach 8 the engine transitions to a scramjet mode. During the ramjet and scramjet modes, the integral rockets operate as fuel injectors. Around Mach 10-12 (the actual value depends on vehicle and mission requirements), the inlet is physically closed and the engine transitions to an integral rocket mode for orbit insertion. A common feature of RBCC propelled vehicles is the high degree of integration between the propulsion system and airframe. At high speeds the vehicle forebody is fundamentally part of the engine inlet, providing a compression surface for air flowing into the engine. The compressed air is mixed with fuel and burned. The combusted mixture must be expanded to an area larger than the incoming stream to provide thrust. Since a conventional nozzle would be too large, the entire lower after body of the vehicle is used as an expansion surface. Because of the high external temperatures seen during atmospheric flight, the design of an airbreathing SSTO vehicle requires delicate tradeoffs between engine design, vehicle shape, and thermal protection system (TPS) sizing in order to produce an optimum system in terms of weight (and cost) and maximum performance. To adequately determine the performance of the engine/vehicle, the Hypersonic Flight Inlet Model (HYFIM) module was designed to interface with the RBCC engine model. HYFIM performs the aerodynamic analysis of forebodies and inlet characteristics of RBCC powered SSTO launch vehicles. HYFIM is applicable to the analysis of the ramjet/scramjet engine operations modes (Mach 3-12), and provides estimates of parameters such as air capture area, shock-on-lip Mach number, design Mach number, compression ratio, etc., based on a basic geometry routine for modeling axisymmetric cones, 2-D wedge geometries. HYFIM also estimates the variation of shock layer properties normal to the forebody surface. The thermal protection system (TPS) is directly linked to determination of the vehicle moldline and the shaping of the trajectory. Thermal protection systems to maintain the structural integrity of the vehicle must be able to mitigate the heat transfer to the structure and be lightweight. Herein lies the interdependency, in that as the vehicle's speed increases, the TPS requirements are increased. And as TPS masses increase the effect on the propulsion system and all other systems is compounded. The need to analyze vehicle forebody and engine inlet is critical to be able to design the RBCC vehicle. To adequately determine insulation masses for an RBCC vehicle, the hypersonic aerodynamic environment and aeroheating loads must be calculated and the TPS thicknesses must be calculated for the entire vehicle. To accomplish this an ascent or reentry trajectory is obtained using the computer code Program to Optimize Simulated Trajectories (POST). The trajectory is then used to calculate the convective heat rates on several locations on the vehicles using the Miniature Version of the JA70 Aerodynamic Heating Computer Program (MINIVER). Once the heat rates are defined for each body point on the vehicle, then insulation thicknesses that are required to maintain the vehicle within structural limits are calculated using Systems Improved Numerical Differencing Analyzer (SINDA) models. If the TPS masses are too heavy for the performance of the vehicle the process may be repeated altering the trajectory or some other input to reduce the TPS mass.

Stanley, Thomas Troy; Alexander, Reginald; Landrum, Brian

2000-01-01

222

Ares 1 First Stage Design, Development, Test, and Evaluation  

NASA Technical Reports Server (NTRS)

The Ares I Crew Launch Vehicle (CLV) is an integral part of NASA s exploration architecture that will provide crew and cargo access to the International Space Station as well as low earth orbit support for lunar missions. Currently in the system definition phase, the CLV is planned to replace the Space Shuttle for crew transport in the post 2010 time frame. It is comprised of a solid rocket booster (SRB) first stage derived from the current Space Shuttle SRB, a liquid oxygen/hydrogen fueled second stage utilizing a derivative of the Apollo upper stage engine for propulsion, and a Crew Exploration Vehicle (CEV) composed of command and service modules. This paper deals with current design, development, test, and evaluation planning for the CLV first stage SRB. Described are the current overall point-of-departure design and booster subsystems, systems engineering approach, and milestone schedule requirements.

Williams, Tom; Cannon, Scott

2006-01-01

223

Static and wind-on tests of an upper-surface-blown jet-flap nozzle arrangement for use on the Quiet Clean Short-haul Experimental Engine (QCSEE)  

NASA Technical Reports Server (NTRS)

The internal aerodynamic performance, the static turning characteristics, and the forward-speed characteristics of two 1/12-scale upper surface-blown jet-flap exhaust-nozzle arrangements designed for use on the Quiet Clean Short-Haul Experimental Engine (QCSEE) were investigated. The nozzles were equipped with interchangeable area-control side doors in the aft sidewalls of the nozzle so that the effective nozzle area could be varied over a wide range. A simulated wing was used to evaluate installation losses for the nozzles. A smoothly curved flap was attached to the trailing edge of the simulated wing to allow an evaluation of the static turning characteristics of the nozzle arrangement. Forward-speed effects on the jet turning characteristics of the QCSEE nozzles were evaluated by mounting a single engine on a semispan wing designed to be representative of a four-engine STOL transport configuration.

Phelps, A. E., III

1977-01-01

224

Chemically engineered sulfated glucans from rice bran exert strong antiviral activity at the stage of viral entry.  

PubMed

Attachment and entry of many viruses are mediated by their affinity for polysaccharides present on the surface of target cells. In this paper, we demonstrate that sulfated glucans isolated from rice (Oryza sativa) can be utilized as experimental drugs exerting strong antiviral activity. In particular, oleum-DMF-based extraction is described as a procedure for the generation of chemically engineered glucans from commercially available rice bran. The one-step procedure has the potential to provide a spectrum of related glucans with varying molecular masses and modifications, including sulfation. The sulfated glucans P444, P445, and P446 possess increased antiviral activity compared to a previously described glucan (S1G). P444, P445, and P446 were highly active against human cytomegalovirus (HCMV), moderately active against other members of the family Herpesviridae, while not active against unrelated viruses. Specific experimentation with HCMV-infected cells provided evidence that antiviral activity was based on inhibition of viral entry and that inhibition occurred in the absence of drug-induced cytotoxicity. These findings underline the high potential of sulfated glucans for antiviral research and drug development. In addition, the procedure described for the efficient transformation of glucan hydroxy groups to sulfate groups may be similarly beneficial for the chemical alteration of other natural products. PMID:24279818

Ray, Bimalendu; Hutterer, Corina; Bandyopadhyay, Shruti S; Ghosh, Kanika; Chatterjee, Udipta R; Ray, Sayani; Zeitträger, Isabel; Wagner, Sabrina; Marschall, Manfred

2013-12-27

225

Staging or upper stage reignition for GEO missions  

Microsoft Academic Search

Geostationary orbit will remain in the near and far future one of the most frequently used for several applications including, mainly, telecommunications. For the time being the GEO satcoms are injected by intermediate, heavy or super heavy class launch vehicles, LV, using quasi standard procedures: low altitude injection on a geostationary transfer orbit, ballistic phase of at least five and

François Duret

2002-01-01

226

Ares I-X Launch Abort System, Crew Module, and Upper Stage Simulator Vibroacoustic Flight Data Evaluation, Comparison to Predictions, and Recommendations for Adjustments to Prediction Methodology and Assumptions  

NASA Technical Reports Server (NTRS)

The National Aeronautics and Space Administration (NASA) Constellation Program (CxP) has identified a series of tests to provide insight into the design and development of the Crew Launch Vehicle (CLV) and Crew Exploration Vehicle (CEV). Ares I-X was selected as the first suborbital development flight test to help meet CxP objectives. The Ares I-X flight test vehicle (FTV) is an early operational model of CLV, with specific emphasis on CLV and ground operation characteristics necessary to meet Ares I-X flight test objectives. The in-flight part of the test includes a trajectory to simulate maximum dynamic pressure during flight and perform a stage separation of the Upper Stage Simulator (USS) from the First Stage (FS). The in-flight test also includes recovery of the FS. The random vibration response from the ARES 1-X flight will be reconstructed for a few specific locations that were instrumented with accelerometers. This recorded data will be helpful in validating and refining vibration prediction tools and methodology. Measured vibroacoustic environments associated with lift off and ascent phases of the Ares I-X mission will be compared with pre-flight vibration predictions. The measured flight data was given as time histories which will be converted into power spectral density plots for comparison with the maximum predicted environments. The maximum predicted environments are documented in the Vibroacoustics and Shock Environment Data Book, AI1-SYS-ACOv4.10 Vibration predictions made using statistical energy analysis (SEA) VAOne computer program will also be incorporated in the comparisons. Ascent and lift off measured acoustics will also be compared to predictions to assess whether any discrepancies between the predicted vibration levels and measured vibration levels are attributable to inaccurate acoustic predictions. These comparisons will also be helpful in assessing whether adjustments to prediction methodologies are needed to improve agreement between the predicted and measured flight data. Future assessment will incorporate hybrid methods in VAOne analysis (i.e., boundary element methods, BEM and finite element methods, FEM). These hybrid methods will enable the ability to import NASTRAN models providing much more detailed modeling of the underlying beams and support structure of the ARES 1-X test vehicle. Measured acoustic data will be incorporated into these analyses to improve correlation for additional post flight analysis.

Smith, Andrew; Harrison, Phil

2010-01-01

227

Stennis engineer part of LCROSS moon mission  

NASA Technical Reports Server (NTRS)

Karma Snyder, a project manager at NASA's John C. Stennis Space Center, was a senior design engineer on the RL10 liquid rocket engine that powered the Centaur, the upper stage of the rocket used in NASA's Lunar CRater Observation and Sensing Satellite (LCROSS) mission in October 2009. Part of the LCROSS mission was to search for water on the moon by striking the lunar surface with a rocket stage, creating a plume of debris that could be analyzed for water ice and vapor. Snyder's work on the RL10 took place from 1995 to 2001 when she was a senior design engineer with Pratt & Whitney Rocketdyne. Years later, she sees the project as one of her biggest accomplishments in light of the LCROSS mission. 'It's wonderful to see it come into full service,' she said. 'As one of my co-workers said, the original dream was to get that engine to the moon, and we're finally realizing that dream.'

2009-01-01

228

Compositionally heterogeneous podiform chromitite in the Shetland Ophiolite Complex (Scotland): Implications for chromitite petrogenesis and late-stage alteration in the upper mantle portion of a supra-subduction zone ophiolite  

NASA Astrophysics Data System (ADS)

The mantle sequence of the ~ 492 Ma Shetland Ophiolite Complex (SOC; Scotland) contains abundant compositionally heterogeneous podiform chromitite bodies enclosed in elongate dunite lenses in the vicinity of the petrological Moho. Chromitite petrogenesis and late-stage alteration events recorded in these seams are examined here using petrography, mineral chemistry and crystal structural data. The resistant nature of Cr-spinel to serpentinisation and other late-stage alteration means that primary igneous compositions are preserved in unaltered crystal cores. Chromitite mineralogy and texture from five sampled localities at The Viels, Hagdale, Harold's Grave, Nikka Vord and Cliff reveal significant inter-pod chemical heterogeneity. The Cr-spinel mineral chemistry is consistent with supra-subduction zone melt extraction from the SOC peridotites. The occurrence of chromitite seams in the centres of the dunite lenses combined with variable Cr-spinel compositions at different chromitite seam localities supports a model of chromitite formation from spatially (and temporally?) fluctuating amounts of melt-rock interaction through channelised and/or porous melt flow. Pervasive serpentinisation of the SOC has led to the almost complete replacement of the primary (mantle) silicate mineral assemblages with serpentine (lizardite with minor chrysotile and antigorite). Magmatic sulphide (e.g., pentlandite) in dunite and chromitite is locally converted to reduced Ni-sulphide varieties (e.g., heazlewoodite and millerite). A post-serpentinisation (prograde) oxidisation event is recorded in the extensively altered Cliff chromitite seams in the west of the studied area, where chromitite Cr-spinel is extensively altered to ferritchromit. The ferritchromit may comprise > 50% of the volume of the Cliff Cr-spinels and contain appreciable quantities of 1-2 ?m inclusions of sperrylite (PtAs2) and Ni-arsenide, signifying the coeval formation of these minerals with ferritchromit at temperatures of up to ~ 500 °C. The SOC chromitite Cr-spinels thus not only preserve key insights into the complex melting processes occurring in the upper mantle wedge but can also be utilised to construct a comprehensive alteration history of the lower mantle portions of such supra-subduction zone ophiolites.

Derbyshire, E. J.; O'Driscoll, B.; Lenaz, D.; Gertisser, R.; Kronz, A.

2013-03-01

229

Laparoscopic Staging in Gallbladder Cancer  

Microsoft Academic Search

Purpose: Laparoscopy is beneficial in the staging of pancreatic and upper gastrointestinal malignancies but its role in gallbladder cancer has not been investigated. We evaluated the role of laparoscopy in the staging of gallbladder cancer. Methods: From 1989 through 2001, 91 patients with gallbladder cancer, without any evidence of metastatic disease on imaging (ultrasound and\\/or computed tomographic scan), underwent staging

Shaleen Agrawal; Rajendra N. Sonawane; Anu Behari; Ashok Kumar; Sadiq S. Sikora; Rajan Saxena; Vinay K. Kapoor

2005-01-01

230

Two-stage Supercharging  

NASA Technical Reports Server (NTRS)

The arrangement of the parts and the installation and control problems of the two-stage mechanically driven superchargers for aircraft engines are discussed. Unless an entirely new form of supercharging is developed, there will be a definite need for a two-stage centrifugal supercharger. It is shown that the two-stage mechanically driven supercharger itself is a comparatively simple device; the complications arise from the addition of inter-coolers and controls.

Buck, Richard S

1941-01-01

231

Two-stage supercharging  

NASA Technical Reports Server (NTRS)

The arrangement of the parts and the installation and control problems of the two-stage mechanically driven superchargers for aircraft engines are discussed. Unless an entirely new form of supercharging is developed, there will be a definite need for a two-stage centrifugal supercharger. It is shown that the two-stage mechanically driven supercharger itself is a comparatively simple device; the complications arise from the addition of inter-coolers and controls.

Buck, Richard S

1941-01-01

232

Staged cascade fluidized bed combustor  

DOEpatents

A fluid bed combustor comprising a plurality of fluidized bed stages interconnected by downcomers providing controlled solids transfer from stage to stage. Each stage is formed from a number of heat transfer tubes carried by a multiapertured web which passes fluidizing air to upper stages. The combustor cross section is tapered inwardly from the middle towards the top and bottom ends. Sorbent materials, as well as non-volatile solid fuels, are added to the top stages of the combustor, and volatile solid fuels are added at an intermediate stage.

Cannon, Joseph N. (4103 Farragut St., Hyattsville, MD 20781); De Lucia, David E. (58 Beacon St., Apt. No. 2, Boston, MA 02108); Jackson, William M. (5300 McArthur Blvd., NW., Washington, DC 20016); Porter, James H. (P.O. Box 1131, Daggett Ave., Vineyard Haven, MA 02568)

1984-01-01

233

Stage Separation Failure: Model Based Diagnostics and Prognostics  

NASA Technical Reports Server (NTRS)

Safety of the next-generation space flight vehicles requires development of an in-flight Failure Detection and Prognostic (FD&P) system. Development of such system is challenging task that involves analysis of many hard hitting engineering problems across the board. In this paper we report progress in the development of FD&P for the re-contact fault between upper stage nozzle and the inter-stage caused by the first stage and upper stage separation failure. A high-fidelity models and analytical estimations are applied to analyze the following sequence of events: (i) structural dynamics of the nozzle extension during the impact; (ii) structural stability of the deformed nozzle in the presence of the pressure and temperature loads induced by the hot gas flow during engine start up; and (iii) the fault induced thrust changes in the steady burning regime. The diagnostic is based on the measurements of the impact torque. The prognostic is based on the analysis of the correlation between the actuator signal and fault-induced changes in the nozzle structural stability and thrust.

Luchinsky, Dmitry; Hafiychuk, Vasyl; Kulikov, Igor; Smelyanskiy, Vadim; Patterson-Hine, Ann; Hanson, John; Hill, Ashley

2010-01-01

234

The Scribble Stage  

ERIC Educational Resources Information Center

The term "Scribble Stage" highlights how first efforts appear in student independent work. Age does not correlate with "scribble" work as does experience; upper grade students and even adults will often approach new materials and techniques in an experimental manner as a means to become familiar with them. Everyone is a beginner at the things they…

Douglas, Katherine

2012-01-01

235

Surgical management of upper tract urothelial carcinoma  

PubMed Central

Upper tract urothelial cell carcinoma accounts for 5% of all urothelial tumors. Compared to lower urinary tract tumors, upper tract urothelial carcinoma is diagnosed more frequently at advanced stages. Open radical nephroureterectomy remains the gold standard treatment option for upper tract tumors. However, with the advancement of minimally invasive techniques and the benefits of these procedures regarding perioperative morbidity, cosmesis, and earlier convalescence, these options have shown promise in managing the patients with upper tract urothelial carcinoma. Despite the perioperative advantages, concerns exist on the oncological safety after minimally invasive surgery. In this article, we provide a comprehensive overview of the surgical management of upper tract urothelial carcinoma.

Bird, Vincent G.; Kanagarajah, Prashanth

2011-01-01

236

Reliability analysis of forty-five strain-gage systems mounted on the first fan stage of a YF-100 engine  

Microsoft Academic Search

The reliability of 45 state-of-the-art strain gage systems under full scale engine testing was investigated. The flame spray process was used to install 23 systems on the first fan rotor of a YF-100 engine; the others were epoxy cemented. A total of 56 percent of the systems failed in 11 hours of engine operation. Flame spray system failures were primarily

R. Holanda; L. M. Frause

1977-01-01

237

Stages in Teaching Software Design  

Microsoft Academic Search

This paper describes how a staged approach to the development of students' abilities to engineer software systems applies to the specific issue of teaching software design. It evaluates the courses relating to software design in the Software Engineering volume of Computing Curriculum 2001 with a theoretical model that has been developed from a well-establish ed programme in software engineering, from

Anthony J. Cowling; Regent Court

2007-01-01

238

Small, high-performance engine component technology status. [liquid rocket engine for spacecraft  

NASA Technical Reports Server (NTRS)

Rocketdyne, under contract to NASA-Lewis Research Center, is engaged in developing the technology for major subsystems of a small, high-performance, liquid rocket engine with the capabilities required for high-energy, upper-stage applications. Included in these efforts are the high-pressure turbopumps, preburner, igniter components, and high-area-ratio thrust chamber. A brief description of the engine system and its subsystems is given. The status of the programs is reviewed and the results of the testing conducted are presented.

Yost, M. C.; Csomor, A.

1976-01-01

239

Lernpunkt Deutsch--Stage 1.  

ERIC Educational Resources Information Center

Evaluates the first stage of "Lernpunkt Deutsch," a new three-stage German course designed for upper elementary and early secondary school. Describes the publisher's package of materials and the appropriateness of the course, utility of the different package elements, format of the materials, and assesses whether the course provides pedagogically…

Theil, Elvira

1997-01-01

240

Reliability analysis of forty-five strain-gage systems mounted on the first fan stage of a YF-100 engine  

NASA Technical Reports Server (NTRS)

The reliability of 45 state-of-the-art strain gage systems under full scale engine testing was investigated. The flame spray process was used to install 23 systems on the first fan rotor of a YF-100 engine; the others were epoxy cemented. A total of 56 percent of the systems failed in 11 hours of engine operation. Flame spray system failures were primarily due to high gage resistance, probably caused by high stress levels. Epoxy system failures were principally erosion failures, but only on the concave side of the blade. Lead-wire failures between the blade-to-disk jump and the control room could not be analyzed.

Holanda, R.; Frause, L. M.

1977-01-01

241

Cryogenic Propulsion Stage  

NASA Technical Reports Server (NTRS)

The CPS is an in-space cryogenic propulsive stage based largely on state of the practice design for launch vehicle upper stages. However, unlike conventional propulsive stages, it also contains power generation and thermal control systems to limit the loss of liquid hydrogen and oxygen due to boil-off during extended in-space storage. The CPS provides the necessary (Delta)V for rapid transfer of in-space elements to their destinations or staging points (i.e., E-M L1). The CPS is designed around a block upgrade strategy to provide maximum mission/architecture flexibility. Block 1 CPS: Short duration flight times (hours), passive cryo fluid management. Block 2 CPS: Long duration flight times (days/weeks/months), active and passive cryo fluid management.

Jones, David

2011-01-01

242

Overview of the ITER EC upper launcher  

Microsoft Academic Search

The ITER electron cyclotron (EC) upper port antenna (or launcher) is nearing completion of the detailed design stage and the final build-to-print design stage will soon start. The main objective of this launcher is to drive current locally to stabilize the neoclassical tearing modes (NTMs) (depositing ECCD inside of the island that forms on either the q = 3\\/2 or

M. A. Henderson; R. Heidinger; D. Strauss; R. Bertizzolo; A. Bruschi; R. Chavan; E. Ciattaglia; S. Cirant; A. Collazos; I. Danilov; F. Dolizy; J. Duron; D. Farina; U. Fischer; G. Gantenbein; G. Hailfinger; W. Kasparek; K. Kleefeldt; J.-D. Landis; A. Meier; A. Moro; P. Platania; B. Plaum; E. Poli; G. Ramponi; G. Saibene; F. Sanchez; O. Sauter; A. Serikov; H. Shidara; C. Sozzi; P. Spaeh; V. S. Udintsev; H. Zohm; C. Zucca

2008-01-01

243

Non-Toxic Orbital Maneuvering System Engine Development  

NASA Technical Reports Server (NTRS)

Recent results using the Aestus engine operated with LOx/ethanol propellant are presented. An experimental program at Rocketdyne Propulsion and Power is underway to adapt this engine for the Boeing Reusable Space Systems Division non-toxic Orbital Maneuvering System/Reaction control System (OMS/RCS) system. Daimler-Chrysler Aerospace designed the Aestus as an nitrogen tetroxide/monomethyl hydrazine (NTO/MMH) upper-stage engine for the Ariane 5. The non-toxic OMS/RCS system's preliminary design requires a LOx/ethanol (O2/C2H5OH) engine that operates with a mixture ratio of 1.8, a specific impulse of 323 seconds, and fits within the original OMS design envelope. This paper describes current efforts to meet these requirements including, investigating engine performance using LOx/ethanol, developing the en-ine system sizing package, and meeting the vehicle operation parameters. Data from hot-fire testing are also presented and discussed.

Green, Christopher; Claflin, Scott; Maeding, Chris; Butas, John

1999-01-01

244

Laser velocimeter measurements of the flow downstream of the Space Shuttle Main Engine high pressure oxidizer turbopump first-stage turbine nozzle  

NASA Technical Reports Server (NTRS)

A laser two-focus velocimeter was used in an open-loop water test facility in order to map the flowfield downstream of the SSME's high-pressure oxidizer turbopump first-stage turbine nozzle; attention was given to the effects of the upstream strut-downstream nozzle configuration on the flow at the rotor inlet, in order to estimate dynamic loads on the first-stage rotor blades. Velocity and flow angles were plotted as a function of circumferential position, and were found to clearly display the periodic behavior of the wake flow field. The influence of the upstream centerbody-supporting struts on the vane nozzle wake pattern was evident.

Ferguson, T. V.; Havskjold, G. L.; Rojas, L.

1988-01-01

245

Cardiovascular risk and mortality in end-stage renal disease patients undergoing dialysis: sleep study, pulmonary function, respiratory mechanics, upper airway collapsibility, autonomic nervous activity, depression, anxiety, stress and quality of life: a prospective, double blind, randomized controlled clinical trial  

PubMed Central

Background Chronic kidney disease (CKD) is one of the most serious public health problems. The increasing prevalence of CKD in developed and developing countries has led to a global epidemic. The hypothesis proposed is that patients undergoing dialysis would experience a marked negative influence on physiological variables of sleep and autonomic nervous system activity, compromising quality of life. Methods/Design A prospective, consecutive, double blind, randomized controlled clinical trial is proposed to address the effect of dialysis on sleep, pulmonary function, respiratory mechanics, upper airway collapsibility, autonomic nervous activity, depression, anxiety, stress and quality of life in patients with CKD. The measurement protocol will include body weight (kg); height (cm); body mass index calculated as weight/height2; circumferences (cm) of the neck, waist, and hip; heart and respiratory rates; blood pressures; Mallampati index; tonsil index; heart rate variability; maximum ventilatory pressures; negative expiratory pressure test, and polysomnography (sleep study), as well as the administration of specific questionnaires addressing sleep apnea, excessive daytime sleepiness, depression, anxiety, stress, and quality of life. Discussion CKD is a major public health problem worldwide, and its incidence has increased in part by the increased life expectancy and increasing number of cases of diabetes mellitus and hypertension. Sleep disorders are common in patients with renal insufficiency. Our hypothesis is that the weather weight gain due to volume overload observed during interdialytic period will influence the degree of collapsibility of the upper airway due to narrowing and predispose to upper airway occlusion during sleep, and to investigate the negative influences of haemodialysis in the physiological variables of sleep, and autonomic nervous system, and respiratory mechanics and thereby compromise the quality of life of patients. Trial registration The protocol for this study is registered with the Brazilian Registry of Clinical Trials (ReBEC RBR-7yhr4w and World Health Organization under Universal Trial Number UTN: U1111-1127-9390 [http://www.ensaiosclinicos.gov.br/rg/RBR-7yhr4w/]).

2013-01-01

246

Cold-air investigation of a turbine for high temperature-engine application. 5: Two-stage turbine performance as affected by variable stator area  

NASA Technical Reports Server (NTRS)

The stator areas of the design two-stage turbine were both decreased and increased by nominally 30 percent, and the performances of the two turbines are compared with that of the design stator area turbine. Turbine efficiency decreased with stator area changes. Closing the stator area resulted in the more severe efficiency loss. The decrease in efficiency for both turbines is attributable to rotor incidence, off-design blade-surface velocities, and adverse reaction changes across the blade rows.

Behning, F. P.; Schum, H. J.; Szanca, E. M.

1974-01-01

247

Conceptual design of two-stage-to-orbit hybrid launch vehicle  

NASA Technical Reports Server (NTRS)

The object of this design class was to design an earth-to orbit vehicle to replace the present NASA space shuttle. The major motivations for designing a new vehicle were to reduce the cost of putting payloads into orbit and to design a vehicle that could better service the space station with a faster turn-around time. Another factor considered in the design was that near-term technology was to be used. Materials, engines and other important technologies were to be realized in the next 10 to 15 years. The first concept put forth by NASA to meet these objectives was the National Aerospace Plane (NASP). The NASP is a single-stage earth-to-orbit air-breathing vehicle. This concept ran into problems with the air-breathing engine providing enough thrust in the upper atmosphere, among other things. The solution of this design class is a two-stage-to-orbit vehicle. The first stage is air-breathing and the second stage is rocket-powered, similar to the space shuttle. The second stage is mounted on the top of the first stage in a piggy-back style. The vehicle takes off horizontally using only air-breathing engines, flies to Mach six at 100,000 feet, and launches the second stage towards its orbital path. The first stage, or booster, will weigh approximately 800,000 pounds and the second stage, or orbiter will weigh approximately 300,000 pounds. The major advantage of this design is the full recoverability of the first stage compared with the present solid rocket booster that are only partially recoverable and used only a few times. This reduces the cost as well as providing a more reliable and more readily available design for servicing the space station. The booster can fly an orbiter up, turn around, land, refuel, and be ready to launch another orbiter in a matter of hours.

1991-01-01

248

High/variable mixture ratio oxygen/hydrogen engines  

NASA Technical Reports Server (NTRS)

A LOX/LH2 high/variable mixture ratio booster upper stage is described. The engine has high thrust-weight ratio as a booster and high specific impulse as an upper stage engine. Operation at high mixture ratio utilizes the propellants at high bulk density. The engine may use multiple turbopump-preburners for higher thrust ratings. The engine uses the full flow cycle to obtain minimum turbine inlet temperatures for a given chamber pressure and to avoid interpropellant shaft seals and other single point failure modes. A portion of the liquid hydrogen is used to regeneratively cool the thrust chamber assembly. The warmed hydrogen coolant is then used to drive the fuel boost turbopump. All propellants arrive at the gas-gas injector ready to burn. Shear mixing of the parallel flowing high velocity, low density fuel-rich gases with the high density, low velocity oxidizer-rich gases provides complete combustion with a modest chamber volume. Combustion stability is assured by the injection of the heated fuel-rich gases and the comparatively low volume ratio of the propellants before and after combustion. The high area ratio nozzle skirt is fitted with a low area ratio nozzle skirt insert for optimum low altitude performance. The overall engine characteristics make it a candidate for ALS, Shuttle-C, LRB, and SSTO applications.

Knuth, William H.; Beveridge, John H.

1988-01-01

249

Engine-Out Capabilities Assessment of Heavy Lift Launch Vehicles  

NASA Technical Reports Server (NTRS)

Engine-out (EO) is a condition that might occur during flight due to the failure of one or more engines. Protection against this occurrence can be called engine-out capability (EOC) whereupon significantly improved loss of mission may occur, in addition to reduction in performance and increased cost. A standardized engine-out capability has not been studied exhaustively as it pertains to space launch systems. This work presents results for a specific vehicle design with specific engines, but also uniquely provides an approach to realizing the necessity of EOC for any launch vehicle system design. A derived top-level approach to engine-out philosophy for a heavy lift launch vehicle is given herein, based on an historical assessment of launch vehicle capabilities. The methodology itself is not intended to present a best path forward, but instead provides three parameters for assessment of a particular vehicle. Of the several parameters affected by this EOC, the three parameters of interest in this research are reliability (Loss of Mission (LOM) and Loss of Crew (LOC)), vehicle performance, and cost. The intent of this effort is to provide insight into the impacts of EO capability on these parameters. The effects of EOC on reliability, performance and cost are detailed, including how these important launch vehicle metrics can be combined to assess what could be considered overall launch vehicle affordability. In support of achieving the first critical milestone (Mission Concept Review) in the development of the Space Launch System (SLS), a team assessed two-stage, large-diameter vehicles that utilized liquid oxygen (LOX)-RP propellants in the First Stage and LOX/LH2 propellant in the Upper Stage. With multiple large thrust-class engines employed on the stages, engine-out capability could be a significant driver to mission success. It was determined that LOM results improve by a factor of five when assuming EOC for both Core Stage (CS) (first stage) and Upper Stage (US) EO, assuming a reference launch vehicle with 5 RP engines on the CS and 3 LOX/LH2 engines on the US. The benefit of adding both CS and US engine-out capability is significant. When adding EOC for either first or second stages, there is less than a 20% benefit. Performance analysis has shown that if the vehicle is not protected for EO during the first part of the flight and only protected in the later part of the flight, there is a diminishing performance penalty, as indicated by failures occurring in the first stage at different times. This work did not consider any options to abort. While adding an engine for EOC drives cost upward, the impact depends on the number of needed engines manufactured per year and the launch manifest. There is a significant cost savings if multiple flights occur within one year. Flying two flights per year would cost approximately $4,000 per pound less than the same configuration with one flight per year, assuming both CS and US EOC. The cost is within 15% of the cost of one flight per year with no engine-out capability for the same vehicle. This study can be extended to other launch vehicles. While the numbers given in this paper are specific to a certain vehicle configuration, the process requires only a high level of data to allow an analyst to draw conclusions. The weighting of each of the identified parameters will determine the optimization of each launch vehicle. The results of this engine-out assessment provide a means to understand this optimization while maintaining an unbiased perspective.

Holladay, Jon; Baggett, Keithe; Thrasher, Chad; Bellamy, K. Scott; Feldman, Stuart

2012-01-01

250

A transient model of the RL10A-3-3A rocket engine  

NASA Technical Reports Server (NTRS)

RL10A-3-3A rocket engines have served as the main propulsion system for Centaur upper stage vehicles since the early 1980's. This hydrogen/oxygen expander cycle engine continues to play a major role in the American launch industry. The Space Propulsion Technology Division at the NASA Lewis Research Center has created a computer model of the RL10 engine, based on detailed component analyses and available test data. This RL10 engine model can predict the performance of the engine over a wide range of operating conditions. The model may also be used to predict the effects of any proposed design changes and anticipated failure scenarios. In this paper, the results of the component analyses are discussed. Simulation results from the new system model are compared with engine test and flight data, including the start and shut-down transient characteristics.

Binder, Michael P.

1995-01-01

251

Installation Restoration Program (IRP) Stage 3. Finding of no significant impact, operable Unit B. Engineering evaluation/cost analysis - environmental assessment and removal action. Final report  

SciTech Connect

The Department of the Air Force has prepared an Engineering Evaluation/Cost Analysis and assessment of environmental impact to respond to contaminated ground water in Operable Unit (OU) B at McClellan AFB, California. Proposed action involves: (1) installation of extraction wells; (2) extraction of contaminated ground water; (3) treatment of extracted groundwater; and (4) release of the treated groundwater. Additional ground water monitoring, abandonment of a contaminated production well, continued extraction from a production well, and restriction on the use of a third production well are also proposed as integral parts of the restoration and water reclamation activity. This action only covers short-term measures to reduce the potential for increased health risks from the migration of higher concentrations of contaminants to on- and off-base water supply wells.

Not Available

1991-04-01

252

Engine Optimization for a Solar Thermal Powered Orbit Transfer Vehicle  

NASA Astrophysics Data System (ADS)

Recent technological advancements in solar thermal rocket propulsion and solar orbit transfer vehicles make it critical to perform additional engine performance analyses. Several system level flight demonstrations are imminent. Space flight hardware component testing is being conducted at the Air Force Research Laboratory, Edwards AFB, California. The focus of current research is engine and nozzle configurations for a solar orbit transfer vehicle. The optimal design must produce 1-10 pounds thrust, perform at high lsp and be compatible in a hybrid of spiral, perigee, and apogee (multi-burn) configurations. The nozzle material must not ablate when subjected to extreme thermal loading, yet be durable enough to withstand widely varying temperature differentials during frequent thermal cycling. This paper addresses propulsive needs in the orbit transfer arena and defines governing upper stage vehicle engine equations. These equations are modified versions of rocket engine equations used for chemical systems. The correction factors and modifications are for Solar Thermal Propulsion specific hardware.

1998-06-01

253

Environmental protection requirements for scout/shuttle auxiliary stages  

NASA Technical Reports Server (NTRS)

The requirements for enabling the Scout upper stages to endure the expected temperature, mechanical shock, acoustical and mechanical vibration environments during a specified shuttle mission were determined. The study consisted of: determining a shuttle mission trajectory for a 545 kilogram (1200 pound) Scout payload; compilation of shuttle environmental conditions; determining of Scout upper stages environments in shuttle missions; compilation of Scout upper stages environmental qualification criteria and comparison to shuttle mission expected environments; and recommendations for enabling Scout upper stages to endure the exptected shuttle mission environments.

Qualls, G. L.; Kress, S. S.; Storey, W. W.; Ransdell, P. N.

1980-01-01

254

Intertonguing of the Lower Part of the Uinta Formation with the Upper Part of the Green River Formation in the Piceance Creek Basin During the Late Stages of Lake Uinta  

USGS Publications Warehouse

During most of middle Eocene time, a 1,500-mi2 area between the Colorado and White Rivers in northwestern Colorado was occupied by the Piceance lobe of Lake Uinta. This initially freshwater lake became increasingly saline throughout its history. Sediments accumulating in the lake produced mostly clay shale, limestone, and dolomite containing varying concentrations of organic matter. At the time of the maximum extent of the lake, the organic-rich Mahogany bed of the Green River Formation was deposited throughout the area. Shortly after its deposition, stream deposits began infilling the lake from the north through a series of contractions interspersed with minor expansions. This fluctuation of the shoreline resulted in the intertonguing of the stream sediments of the lower part of the overlying Uinta Formation with the lacustrine sediments of the upper part of the Green River over a distance of about 40 mi; construction of regional stratigraphic cross sections show the pattern of intertonguing in considerable detail. The data utilized in this study, which covered parts of Rio Blanco, Garfield, and Mesa counties, was derived from (1) geologic mapping of thirty-four 7 1/2-minute quadrangles and stratigraphic studies by geologists of the U.S. Geological Survey, and (2) shale-oil assay information from numerous cores. As a result of this previous work and the additional effort involved in the compilation here presented, more than a dozen Green River Formation tongues have been named, some formally, others informally. Middle Eocene strata above the Mahogany bed in the northern part of the study area are dominantly coarse clastics of the Uinta Formation. The sedimentary sequence becomes more calcareous and organic-rich to the south where, in a 400-mi2 area, a 250 ft-thick sequence of oil shale above the Mahogany bed contains an average of 16 gallons of oil per ton of shale and is estimated to contain 73 billion barrels of oil.

Donnell, John R.

2009-01-01

255

A cascade thermoacoustic engine  

Microsoft Academic Search

A cascade thermoacoustic engine is described, consisting of one standing-wave stage plus two traveling-wave stages in series. Most of the acoustic power is produced in the efficient traveling-wave stages. The straight-line series configuration is easy to build and allows no Gedeon streaming. The engine delivers up to 2 kW of acoustic power, with an efficiency (the ratio of acoustic power

D. L. Gardner; G. W. Swift

2003-01-01

256

Establishment of Design Method for Liquid Hydrogen Regenerative Cooling Combustor of LOX/Hydrogen Rocket Engine  

NASA Astrophysics Data System (ADS)

An optimum method for design of a liquid hydrogen regenerative cooling combustor for the LOX/hydrogen engine was constructed using the author’s previous empirical correlation of C* efficiency and calculation model for combustion characteristics, and the present calculation model for the heat load characteristics for LOX/hydrogen combustion. Using this method, the atomization characteristics of the injected LOX jet, the combustion performance including combustion stability, and the heat load on the combustor were evaluated for LOX/hydrogen upper-stage engines such as the LE-5, RL-10 and HM-7. This method was then applied to the LE-5B engine, which is the derivative engine of the LE-5 and has been used as the second stage of the H-2A launcher, to improve combustion stability and to optimize configuration of the injector and combustor. A reduction of about 30% in chamber length of it with sufficient combustion performance was achieved by such optimization.

Yatsuyanagi, Nobuyuki

257

Third Stage  

NASA Video Gallery

Once the third stage finishes its work, Kepler will have sufficient energy to leave the gravitational pull of Earth and go into orbit around the Sun, trailing behind Earth and slowly drifting away ...

258

Ares I-X First Stage Separation Loads and Dynamics Reconstruction  

NASA Technical Reports Server (NTRS)

The Ares I-X flight test provided NASA with the opportunity to test hardware and gather critical data to ensure the success of future Ares I flights. One of the primary test flight objectives was to evaluate the environment during First Stage separation to better understand the conditions that the J-2X second stage engine will experience at ignition [1]. A secondary objective was to evaluate the effectiveness of the stage separation motors. The Ares I-X flight test vehicle was successfully launched on October 29, 2009, achieving most of its primary and secondary test objectives. Ground based video camera recordings of the separation event appeared to show recontact of the First Stage and the Upper Stage Simulator followed by an unconventional tumbling of the Upper Stage Simulator. Closer inspection of the videos and flight test data showed that recontact did not occur. Also, the motion during staging was as predicted through CFD analysis performed during the Ares I-X development. This paper describes the efforts to reconstruct the vehicle dynamics and loads through the staging event by means of a time integrated simulation developed in TREETOPS, a multi-body dynamics software tool developed at NASA [2]. The simulation was built around vehicle mass and geometry properties at the time of staging and thrust profiles for the first stage solid rocket motor as well as for the booster deceleration motors and booster tumble motors. Aerodynamic forces were determined by models created from a combination of wind tunnel testing and CFD. The initial conditions such as position, velocity, and attitude were obtained from the Best Estimated Trajectory (BET), which is compiled from multiple ground based and vehicle mounted instruments. Dynamic loads were calculated by subtracting the inertial forces from the applied forces. The simulation results were compared to the Best Estimated Trajectory, accelerometer flight data, and to ground based video.

Demory, Lee; Rooker, BIll; Jarmulowicz, Marc; Glaese, John

2011-01-01

259

NASA/DOD Aerospace Knowledge Diffusion Research Project. Report 34: How early career-stage US aerospace engineers and scientists produce and use information  

NASA Technical Reports Server (NTRS)

The U.S. government technical report is a primary means by which the results of federally funded research and development (R&D) are transferred to the U.S. aerospace industry. However, little is known about this information product in terms of its actual use, importance, and value in the transfer of federally funded R&D. To help establish a body of knowledge, the U.S. government technical report is being investigated as part of the NASA/DOD Aerospace Knowledge Diffusion Research Project. In this report, we summarize the literature on technical reports and provide a model that depicts the transfer of federally funded aerospace R&D via the U.S. government technical report. We present results from our investigation of aerospace knowledge diffusion vis-a-vis the U.S. government technical report, and present the results of research that investigated aerospace knowledge diffusion vis-a-vis the production and use of information by U.S. aerospace engineers and scientists who had changed their American Institute of Aeronautics and Astronautics (AIAA) membership from student to professional in the past five years.

Pinelli, Thomas E.; Barclay, Rebecca O.; Kennedy, John M.

1995-01-01

260

New generation reusable single-stage shuttle and expendable single-stage launcher  

NASA Astrophysics Data System (ADS)

The design and development of a reusable single-stage shuttle and an expendable single-stage launcher are proposed. The design and specifications of a reusable dual fuel single-stage-to-orbit shuttle are diagramatically described. A graph depicting the aerodynamic capabilities of the shuttle is provided. A comparison of a dual expender engine with a separate engine for reusable and expendable single-stage-to-orbit surface and air launchers is presented. The specifications for ground or air launch dual expender engines are given. The performance capabilities of an expendable dual fuel single-stage-to-orbit launcher is examined.

Salkeld, R.

1985-10-01

261

Cysticercosis of the upper lip  

PubMed Central

Cysticercosis is a parasitic infestation caused by the larval stage of Taenia solium. It is common in regions where humans and animals live in close contact, with poor sanitation, and due to consumption of infected meat. The tissues affected are the subcutaneous layers, brain, muscle, heart, liver, lungs, and peritoneum. Oral manifestations are very rare. The most common intra-oral site is the tongue. Here, we present a case in a who sought treatment for an asymptomatic nodule in the upper lip. A gross specimen revealed a cystic cavity containing clear watery fluid and white membranous flecks. The histopathology showed features of cysticercosis.

Deshmukh, Atul; Avadhani, Avadhoot; Tupkari, JV; Sardar, Manisha

2011-01-01

262

Ariane 5 Plus Cryogenic Stage Development ESC-A: Qualification Achieved for the First Flight  

NASA Astrophysics Data System (ADS)

Within the frame of the Ariane 5 Plus programme, Europe is developing a new cryogenic upper stage ESC. In order to maintain the ARIANE 5 international competitive edge, Europe decided to enhance the payload capacity of its new workhorse by adding a cryogenic upper stage enabling up to 12 tons to be delivered into a Geostationary Transfer Orbit. A two-step approach was decided in order to meet the near future and long-term market demand. The first step consists of developing an intermediate version named ESC- A utilising the propulsion system components and engine from the Ariane 4 launcher vehicle 3rd (cryogenic) stage within a new structure. In the second step the B-version will follow based on ESC-A but utilising a new propulsion system and a new expander cycle engine. This paper describes the definition and performance characteristics of ESC-A and presents the qualification philosophy applied for the Ariane 4 reused equipment and also for the new equipment and substructures under the stringent schedule constraints. The qualification test phase is well under way with the first flight of ESC-A scheduled second half of 2002. On stage level two qualification test items are built and tested: one stage for mechanical qualification, and a second stage for qualifying the ground/launcher interface and thermal system during filling and draining of the stage. On subsystem level the mechanical qualification (stiffness and strength) for the new LH2-Tank, the Interstage Structure, and the stage internal structures are performed. Functional qualification of ESCA is performed without a hot firing test. The propulsion system and engine are already qualified for Ariane 4 - H10; therefore only complementary qualification for ESC-A environment is necessary (increased firing time, different dynamic and thermal environment). This is supported by specific functional tests, for example pressurisation loop tests, LH2 feeding system test, LH2 and LOX sloshing tests, LOX draining tests, and engine hot firing tests under the ESC-A conditions. An overview of these qualification tests is given resulting in a qualified stage ready for the first flight.

Lassmann, J.

2002-01-01

263

78 FR 9003 - Airworthiness Directives; Engine Alliance Turbofan Engines  

Federal Register 2010, 2011, 2012, 2013

...prompted by damage to the high-pressure compressor (HPC) stage 7-9 spool...This proposed AD would require initial and repetitive borescope inspections...GP7277 turbofan engines with a high-pressure compressor (HPC) stage 6...

2013-02-07

264

AJ26 Rocket Engine Test  

NASA Video Gallery

Engineers at NASAâ??s John C. Stennis Space Center conducts the second in a series of verification tests on an Aerojet AJ26 engine that will power the first stage of the Orbital Sciences Corporatio...

265

Stage Posts  

ERIC Educational Resources Information Center

Uncertainty about identity and the future is occurring at a stage of life when people do question what they have achieved and what they still want to achieve. The notion of midlife crisis has been in existence for some time but recently its occurrence has coincided with opportunities to take early retirement or redundancy. This has meant that the…

Soulsby, Jim

2004-01-01

266

Binary Stage.  

National Technical Information Service (NTIS)

The fluid amplifier is utilized in a computing system. The pure fluid binary counting stage comprises a pair of pure fluid amplifiers coupled together through a delay and energy storage system such that one of the fluid through a delay and energy storage ...

R. E. Bowles

1965-01-01

267

Ares I and Ares I-X Stage Separation Aerodynamic Testing  

NASA Technical Reports Server (NTRS)

The aerodynamics of the Ares I crew launch vehicle (CLV) and Ares I-X flight test vehicle (FTV) during stage separation was characterized by testing 1%-scale models at the Arnold Engineering Development Center s (AEDC) von Karman Gas Dynamics Facility (VKF) Tunnel A at Mach numbers of 4.5 and 5.5. To fill a large matrix of data points in an efficient manner, an injection system supported the upper stage and a captive trajectory system (CTS) was utilized as a support system for the first stage located downstream of the upper stage. In an overall extremely successful test, this complex experimental setup associated with advanced postprocessing of the wind tunnel data has enabled the construction of a multi-dimensional aerodynamic database for the analysis and simulation of the critical phase of stage separation at high supersonic Mach numbers. Additionally, an extensive set of data from repeated wind tunnel runs was gathered purposefully to ensure that the experimental uncertainty would be accurately quantified in this type of flow where few historical data is available for comparison on this type of vehicle and where Reynolds-averaged Navier-Stokes (RANS) computational simulations remain far from being a reliable source of static aerodynamic data.

Pinier, Jeremy T.; Niskey, Charles J.

2011-01-01

268

Stage-discharge relations for Black Warrior River at Warrior Dam near Eutaw, Alabama; updated 1985  

USGS Publications Warehouse

The construction of Warrior Dam, completed in 1962, has resulted in changes to the stage-discharge relations in the vicinity. The scarcity of current-meter measurements, coupled with backwater conditions, make definition of a single stage-discharge relation impossible without considerable error. However, as a useful alternative, limit curves were developed in 1983 that defined the limits of possible stage-discharge relations at the dam tailwater section. Since the 1983 report, 37 discharge values computed through the dam for the flood of December 1983 were used to verify or update the lower end of the limit curves. Data obtained from a current-meter measurement of the February 1961 flood (furnished by the U.S. Army Corps of Engineers) were used to update the upper end of the curves. This report presents the updated information. (USGS)

Nelson, G. H.; Ming, C. O.

1986-01-01

269

40 CFR 92.104 - Locomotive and engine testing; overview.  

Code of Federal Regulations, 2013 CFR

...s) may be used to maintain engine cooling during operation on the dynamometer. (iii) The engine air inlet system used during...restriction within 1 inch of water of the upper limit of a typical engine as installed with clean...

2013-07-01

270

FAST CHOPPER BUILDING, TRA665, INTERIOR. UPPER LEVEL. CONCRETE WALLS. INL ...  

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

FAST CHOPPER BUILDING, TRA-665, INTERIOR. UPPER LEVEL. CONCRETE WALLS. INL NEGATIVE NO. HD42-2. Mike Crane, Photographer, 3/2004 - Idaho National Engineering Laboratory, Test Reactor Area, Materials & Engineering Test Reactors, Scoville, Butte County, ID

271

78 FR 35747 - Special Conditions: Cirrus Design Corporation, Model SF50; Fire Extinguishing for Upper Aft...  

Federal Register 2010, 2011, 2012, 2013

...Corporation new model SF50. The model SF50 is a 7-seat (5 adults and 2 children), pressurized, retractable gear, carbon composite, airplane with one turbofan engine mounted partially in the upper aft fuselage. The single turbofan engine is...

2013-06-14

272

Nuclear Cryogenic Propulsion Stage  

NASA Technical Reports Server (NTRS)

The fundamental capability of Nuclear Thermal Propulsion (NTP) is game changing for space exploration. A first generation Nuclear Cryogenic Propulsion Stage (NCPS) based on NTP could provide high thrust at a specific impulse above 900 s, roughly double that of state of the art chemical engines. Characteristics of fission and NTP indicate that useful first generation systems will provide a foundation for future systems with extremely high performance. The role of the NCPS in the development of advanced nuclear propulsion systems could be analogous to the role of the DC-3 in the development of advanced aviation. Progress made under the NCPS project could help enable both advanced NTP and advanced NEP.

Houts, Michael G.; Borowski, S. K.; George, J. A.; Kim, T.; Emrich, W. J.; Hickman, R. R.; Broadway, J. W.; Gerrish, H. P.; Adams, R. B.

2012-01-01

273

Competitive and Cooperative Inventory Policies in a Two-Stage Supply Chain  

Microsoft Academic Search

We investigate a two-stage serial supply chain with stationary stochastic demand and fixed transportation times. Inventory holding costs are charged at each stage, and each stage may incur a consumer backorder penalty cost, e.g. the upper stage (the supplier) may dislike backorders at the lower stage (the retailer). We consider two games. In both, the stages independently choose base stock

Gérard P. Cachon; Paul H. Zipkin

1999-01-01

274

Two stage sorption type cryogenic refrigerator including heat regeneration system  

NASA Technical Reports Server (NTRS)

A lower stage chemisorption refrigeration system physically and functionally coupled to an upper stage physical adsorption refrigeration system is disclosed. Waste heat generated by the lower stage cycle is regenerated to fuel the upper stage cycle thereby greatly improving the energy efficiency of a two-stage sorption refrigerator. The two stages are joined by disposing a first pressurization chamber providing a high pressure flow of a first refrigerant for the lower stage refrigeration cycle within a second pressurization chamber providing a high pressure flow of a second refrigerant for the upper stage refrigeration cycle. The first pressurization chamber is separated from the second pressurization chamber by a gas-gap thermal switch which at times is filled with a thermoconductive fluid to allow conduction of heat from the first pressurization chamber to the second pressurization chamber.

Jones, Jack A. (inventor); Wen, Liang-Chi (inventor); Bard, Steven (inventor)

1989-01-01

275

J STAGE  

NSDL National Science Digital Library

Developed by the Japan Science and Technology Corporation (JST), J-STAGE (The Japan Science and Technology Aggregator, Electronic) is a recently launched electronic journal center that publishes and disseminates Japanese electronic scientific journals. At present, the site hosts four journals (one of which is Japanese only), but expects to add over a hundred in the near future. The three available English-language journals include the Japanese Journal of Applied Physics, the Journal of the Physical Society of Japan, and SHIGEN-TO-SOZAI, a journal of the Mining and Materials Processing Institute of Japan. The full-text articles are available free of charge with searchable back issues also available.

276

Next Generation: Unmanned Launch Vehicles and Upper Stages: The Needs.  

National Technical Information Service (NTIS)

The focus is on common vehicle elements, higher mission success, and lower transportation cost with respect to the common needs of the Department of Defense, NASA, and U.S. Industry. The following are presented in viewgraph form: (1) perspectives on missi...

C. R. Gunn

1991-01-01

277

Upper Stages Using Liquid Propulsion and Metallized Propellants.  

National Technical Information Service (NTIS)

Metallized propellants are liquid propellants with a metal additive suspended in a gelled fuel. Typically, aluminum particles are the metal additive. These propellants increase the density and/or the specific impulse of the propulsion system. Using metall...

B. A. Palaszewski

1992-01-01

278

Upper stage flight experiment (USFE) integral structure development effort  

Microsoft Academic Search

The Air Force Research Laboratory's Space Vehicle Directorate (AFRL\\/VS) has established a customer focused composite tankage development program that is targeted to existing and future aerospace applications. AFRL\\/VS is developing a wide range of tank concepts that include linerless cryogenic tankage, self-healing cryogenic tankage, hydrogen peroxide compatible tankage, volumetrically efficient toroidal (donut shaped) geometries, and more.This paper will summarize the

Jim Guerrero; Brent Hamilton; Randy Burton; Dave Crockett; Zach Taylor

2004-01-01

279

SolSTUS: Solar Source Thermal Upper Stage  

NASA Technical Reports Server (NTRS)

This paper was written by members of the Utah State University (USU) Space Systems Design class, fall quarter 1993. The class is funded by NASA and administered by the University Space Research Association (USRA). The focus of the class is to give students some experience in design of space systems and as a source of original ideas for NASA. This paper is a summary of the work done by members of the Space Systems Design class during the opening phase of the course. The class was divided into groups to work on different areas of the Solar Thermal Rocket (STR) booster in order to produce a design reference mission that would identify the key design issues. The design reference mission focused upon a small satellite mission to Mars. There are several critical components in a Solar Thermal Rocket. STR's produce a very low thrust, but have a high specific impulse, meaning that they take longer to reach the desired orbit, but use a lot less fuel in doing it. The complexity of the rocket is discussed in this paper. Some of the more critical design problems discussed are: (1) the structural and optical complexity of collecting and focusing sunlight onto a specific point, (2) long term storage of fuel (liquid hydrogen), (3) attitude control while thrusting in an elliptical orbit and orienting the mirrors to collect sunlight, and (4) power and communications for the rocket and it's internal systems. The design reference mission discussed here is a very general mission to Mars. A first order trajectory design has been done and a possible basic science payload for Mars has been suggested. This paper summarizes the design reference mission (DRM) formulated by the USU students during fall quarter and identifies major design challenges that will confront the design team during the next two quarters here at USU.

1994-01-01

280

Zero Gravity Cryogenic Vent System Concepts for Upper Stages  

NASA Astrophysics Data System (ADS)

The capability to vent in zero gravity without resettling is a technology need that involves practically all uses of sub-critical cryogenics in space. Venting without resettling would extend cryogenic orbital transfer vehicle capabilities. However, the lack of definition regarding liquid/ullage orientation coupled with the somewhat random nature of the thermal stratification and resulting pressure rise rates, lead to significant technical challenges. Typically a zero gravity vent concept, termed a thermodynamic vent system (TVS), consists of a tank mixer to destratify the propellant, combined with a Joule-Thomson (J-T) valve to extract thermal energy from the propellant. Marshall Space Flight Center's (MSFC's) Multipurpose Hydrogen Test Bed (MHTB) was used to test both spray bar and axial jet TVS concepts. The axial jet system consists of a recirculation pump heat exchanger unit. The spray bar system consists of a recirculation pump, a parallel flow concentric tube, heat exchanger, and a spray bar positioned close to the longitudinal axis of the tank. The operation of both concepts is similar. In the mixing mode, the recirculation pump withdraws liquid from the tank and sprays it into the tank liquid, ullage, and exposed tank surfaces. When energy extraction is required, a small portion of the recirculated liquid is passed sequentially through the J-T expansion valve, the heat exchanger, and is vented overboard. The vented vapor cools the circulated bulk fluid, thereby removing thermal energy and reducing tank pressure. The pump operates alone, cycling on and off, to destratify the tank liquid and ullage until the liquid vapor pressure reaches the lower set point. At that point, the J-T valve begins to cycle on and off with the pump. Thus, for short duration missions, only the mixer may operate, thus minimizing or even eliminating boil-off losses. TVS performance testing demonstrated that the spray bar was effective in providing tank pressure control within a 6.89 kPa (1psi) band for fill levels of 90%, 50%, and 25%. Complete destratification of the liquid and ullage was achieved at these fill levels. The axial jet was effective in providing tank pressure control within the same pressure control band at the 90% fill level. However, at the 50% level, the system reached a point at which it was unable to extract enough energy to keep up with the heat leak into the tank. Due to a hardware problem, the recirculation pump operated well below the axial jet design flow rate. Therefore, it is likely that the performance of the axial jet would have improved had the pump operated at the proper flow rate. A CFD model is being used to determine if the desired axial jet performance would be achieved if a higher pump flow rate were available. Testing conducted thus far has demonstrated that both TVS concepts can be effective in destratifying a propellant tank, rejecting stored heat energy, and thus, controlling tank pressure.

Ravex, Alain; Flachbart, Robin; Holt, Barney

281

Zero Gravity Cryogenic Vent System Concepts for Upper Stages  

NASA Technical Reports Server (NTRS)

The capability to vent in zero gravity without resettling is a technology need that involves practically all uses of sub-critical cryogenics in space. Venting without resettling would extend cryogenic orbital transfer vehicle capabilities. However, the lack of definition regarding liquid/ullage orientation coupled with the somewhat random nature of the thermal stratification and resulting pressure rise rates, lead to significant technical challenges. Typically a zero gravity vent concept, termed a thermodynamic vent system (TVS), consists of a tank mixer to destratify the propellant, combined with a Joule-Thomson (J-T) valve to extract thermal energy from the propellant. Marshall Space Flight Center's (MSFC's) Multipurpose Hydrogen Test Bed (MHTB) was used to test both spray bar and axial jet TVS concepts. The axial jet system consists of a recirculation pump heat exchanger unit. The spray bar system consists of a recirculation pump, a parallel flow concentric tube, heat exchanger, and a spray bar positioned close to the longitudinal axis of the tank. The operation of both concepts is similar. In the mixing mode, the recirculation pump withdraws liquid from the tank and sprays it into the tank liquid, ullage, and exposed tank surfaces. When energy is required. a small portion of the recirculated liquid is passed sequentially through the J-T expansion valve, the heat exchanger, and is vented overboard. The vented vapor cools the circulated bulk fluid, thereby removing thermal energy and reducing tank pressure. The pump operates alone, cycling on and off, to destratify the tank liquid and ullage until the liquid vapor pressure reaches the lower set point. At that point. the J-T valve begins to cycle on and off with the pump. Thus, for short duration missions, only the mixer may operate, thus minimizing or even eliminating, boil-off losses.

Flachbart, Robin H.; Holt, James B.; Hastings, Leon J.

1999-01-01

282

Zero Gravity Cryogenic Vent System Concepts for Upper Stages  

NASA Technical Reports Server (NTRS)

The capability to vent in zero gravity without resettling is a technology need that involves practically all uses of sub-critical cryogenics in space, and would extend cryogenic orbital transfer vehicle capabilities. However, the lack of definition regarding liquid/ullage orientation coupled with the somewhat random nature of the thermal stratification and resulting pressure rise rates, lead to significant technical challenges. Typically a zero gravity vent concept, termed a thermodynamic vent system (TVS), consists of a tank mixer to destratify the propellant, combined with a Joule-Thomson (J-T) valve to extract thermal energy from the propellant. Marshall Space Flight Center's (MSFC's) Multipurpose Hydrogen Test Bed (MHTB) was used to test both spray-bar and axial jet TVS concepts. The axial jet system consists of a recirculation pump heat exchanger unit. The spray-bar system consists of a recirculation pump, a parallel flow concentric tube heat exchanger, and a spray-bar positioned close to the longitudinal axis of the tank. The operation of both concepts is similar. In the mixing mode, the recirculation pump withdraws liquid from the tank and sprays it into the tank liquid, ullage, and exposed tank surfaces. When energy extraction is required, a small portion of the recirculated liquid is passed sequentially through the J-T expansion valve, the heat exchanger, and is vented overboard. The vented vapor cools the circulated bulk fluid, thereby removing thermal energy and reducing tank pressure. The pump operates alone, cycling on and off, to destratify the tank liquid and ullage until the liquid vapor pressure reaches the lower set point. At that point, the J-T valve begins to cycle on and off with the pump. Thus, for short duration missions, only the mixer may operate, thus minimizing or even eliminating boil-off losses.

Flachbart, Robin H.; Holt, James B.; Hastings, Leon J.

2001-01-01

283

Zero Gravity Cryogenic Vent System Concepts for Upper Stages  

Microsoft Academic Search

The capability to vent in zero gravity without resettling is a technology need that involves practically all uses of sub-critical cryogenics in space. Venting without resettling would extend cryogenic orbital transfer vehicle capabilities. However, the lack of definition regarding liquid\\/ullage orientation coupled with the somewhat random nature of the thermal stratification and resulting pressure rise rates, lead to significant technical

Alain Ravex; Robin Flachbart; Barney Holt

1999-01-01

284

[Upper airway resistance syndrome].  

PubMed

Upper Airway Resistance Syndrome (UARS) is characterized with daytime sleepiness and cardiovascular disturbances, because of the repetitive increase of upper airway resistance leading to arousals. UARS, can easily be overlooked because the conventional polysonographic measurements are not sensitive enough to diagnose this syndrome, therefore the prevalence and morbidity of this syndrome is not known. Measuring the increased inspiratory effort by an esophageal balloon during the rising upper airway resistance is the gold standard technique for the diagnosis. Treatment of UARS is similar with Obstructive Sleep Apnea Syndrome (OSAS). In this article the clinical picture, diagnosis, and management of the UARS is reviewed. PMID:15143431

Köktürk, O?uz; Güven, Selma Firat

2003-01-01

285

Linear Aerospike Engine Study.  

National Technical Information Service (NTIS)

Parametric data on split-combustor linear engine propulsion systems are presented for use in mixed-mode single-stage-to-orbit (SSTO) vehicle studies. Preliminary design data for two selected engine systems are included. The split combustor was investigate...

H. G. Diem F. M. Kirby

1977-01-01

286

Genetic engineering in biotechnology  

Microsoft Academic Search

The objective of this book is to encourage the use of genetic engineering for economic development. The report covers: (1) Precedents of genetic engineering; (2) a brief description of the technology, including the transfer of DNA in bacteria (vectors, E. coli and B. subtilis hosts, stages, and technical problems), practical examples of techniques used and their products (interferon; growth hormone;

C. A. Bedate; J. C. Morales; E. H. Lopez

1981-01-01

287

Rotorcraft convertible engine study  

NASA Technical Reports Server (NTRS)

The objective of the Rotorcraft Convertible Engine Study was to define future research and technology effort required for commercial development by 1988 of convertible fan/shaft gas turbine engines for unconventional rotorcraft transports. Two rotorcraft and their respective missions were defined: a Fold Tilt Rotor aircraft and an Advancing Blade Concept (ABC) rotorcraft. Sensitivity studies were conducted with these rotorcraft to determine parametrically the influence of propulsion characteristics on aircraft size, mission fuel requirements, and direct operating costs (DOC). The two rotorcraft were flown with conventional propulsion systems (separate lift/cruise engines) and with convertible propulsion systems to determine the benefits to be derived from convertible engines. Trade-off studies were conducted to determine the optimum engine cycle and staging arrangement for a convertible engine. Advanced technology options applicable to convertible engines were studied. Research and technology programs were identified which would ensure technology readiness for commercial development of convertible engines by 1988.

Gill, J. C.; Earle, R. V.; Mar, H. M.

1982-01-01

288

Advances in upper extremity prosthetics.  

PubMed

Until recently, upper extremity prostheses had changed little since World War II. In 2006, the Defense Advanced Research Projects Agency responded to an increasing number of military amputees with the Revolutionizing Prosthetics program. The program has yielded several breakthroughs both in the engineering of new prosthetic arms and in the control of those arms. Direct brain-wave control of a limb with 22° of freedom may be within reach. In the meantime, advances such as individually powered digits have opened the door to multifunctional full and partial hand prostheses. Restoring sensation to the prosthetic limb remains a major challenge to full integration of the limb into a patient's self-image. PMID:23101609

Zlotolow, Dan A; Kozin, Scott H

2012-11-01

289

Micron Mensuration Stage for M-5 Microscope.  

National Technical Information Service (NTIS)

This report describes the engineering, development concept, and final test results for development of the Micron Mensuration Stage. The report records in detail the major areas of mechanical, electronic, and optical development which resulted in completio...

F. L. Lewandowski

1969-01-01

290

Upper GI Endoscopy  

MedlinePLUS Videos and Cool Tools

... also called the gastrointestinal system or GI. Its internal lining consists of special tissue. The “upper GI” ... cause vomiting, creating complications. If you are taking medicines, ask your doctor whether you should take them ...

291

The upper intertidal zone  

NSDL National Science Digital Library

The upper intertidal zone is exposed most of the time and will become submerged only during high tide. This zone is least abundant of the intertidal zones but contains some mollusks, barnacles, and other animals adapted to avoid drying out.

Katie Hale (California State University, Fullerton;Student, Biological Sciences)

2007-01-04

292

The upper intertidal zone  

NSDL National Science Digital Library

The upper intertidal zone is exposed most of the time and will become submerged only during high tide. This zone is least abundant of the intertidal zones but contains some mollusks, barnacles, and other animals adapted to avoid drying out.

Katie Hale (CSUF;Biological Sciences)

2007-06-08

293

Qualification of Minuteman stage III motor for spin stabilized perigee stages  

Microsoft Academic Search

The third stage of the Minuteman III ICBM was recently qualified for Space Transportation System launch as a tailored upper stage in order to use its unique combination of performance (2.1 million lbf-sec), reliability (100% on 140 tests), and maturity (900 built). The motor was static fired while spinning at 70 rpm and 100 F, and the propellant was also

E. E. Day

1980-01-01

294

Shakespeare's Staging  

NSDL National Science Digital Library

The University of California at Berkeley's English Department has undertaken the enormous task of presenting "a survey of current information, opinions and visuals about...the original nature of Shakespearean performance during his lifetime, and of its development through four centuries thereafter." Visitors can click on "Performance Galleries" at the top of the homepage to be taken to ten albums of over 900 images. Some of the topics of the albums that you can link to are "Productions from the Sixteenth through the Twentieth Century", "Productions in Britain 1960-1998", and "Unusual Representations of Shakespeare Performances". The albums contain items such as playbills, photos and drawings of performances, and photos of the rebuilt Globe Theatre. On the far left side of the homepage, visitors can click on "Videos" to view a documentary series about Elizabethan life, as well as excerpts of performances staged by the Shakespeare Program of UC Berkeley at Shakespeare's Globe Theatre. The videos can be viewed by "Latest", "Most Viewed", "Highest Rated", and "Featured". Visitors interested in other websites that explore Shakespeare performance will want to click on "Relevant Websites" on the far left side of the homepage, to access a link that has 27 Shakespeare performance related websites.

295

Managing conflict in engineering organizations  

Microsoft Academic Search

We can all agree that conflict in engineering organizations is a reality. We can also agree that managing conflict can be a challenge. Every aspect of an engineering organization from low level task accomplishment or project management to upper level planning and establishment of organizational goals and objectives involves some degree of conflict. Conflict must be managed both locally and

Paul J. Breaux; San Antonio

2007-01-01

296

Upper Girdle Imaging in Facioscapulohumeral Muscular Dystrophy  

PubMed Central

Background In Facioscapulohumeral muscular dystrophy (FSHD), the upper girdle is early involved and often difficult to assess only relying on physical examination. Our aim was to evaluate the pattern and degree of involvement of upper girdle muscles in FSHD compared with other muscle diseases with scapular girdle impairment. Methods We propose an MRI protocol evaluating neck and upper girdle muscles. One hundred-eight consecutive symptomatic FSHD patients and 45 patients affected by muscular dystrophies and myopathies with prominent upper girdle involvement underwent this protocol. Acquired scans were retrospectively analyzed. Results The trapezius (100% of the patients) and serratus anterior (85% of the patients) were the most and earliest affected muscles in FSHD, followed by the latissimus dorsi and pectoralis major, whilst spinati and subscapularis (involved in less than 4% of the patients) were consistently spared even in late disease stages. Asymmetry and hyperintensities on short-tau inversion recovery (STIR) sequences were common features, and STIR hyperintensities could also be found in muscles not showing signs of fatty replacement. The overall involvement appears to be disease-specific in FSHD as it significantly differed from that encountered in the other myopathies. Conclusions The detailed knowledge of single muscle involvement provides useful information for correctly evaluating patients' motor function and to set a baseline for natural history studies. Upper girdle imaging can also be used as an additional tool helpful in supporting the diagnosis of FSHD in unclear situations, and may contribute with hints on the currently largely unknown molecular pathogenesis of this disease.

Tasca, Giorgio; Monforte, Mauro; Iannaccone, Elisabetta; Laschena, Francesco; Ottaviani, Pierfrancesco; Leoncini, Emanuele; Boccia, Stefania; Galluzzi, Giuliana; Pelliccioni, Marco; Masciullo, Marcella; Frusciante, Roberto; Mercuri, Eugenio; Ricci, Enzo

2014-01-01

297

Tripropellant engine study  

NASA Technical Reports Server (NTRS)

The potential for converting the space shuttle main engine (SSME) to a dual-fuel, dual-mode engine using LOX/hydrocarbon propellants in mode 1 and LOX/H2 in mode 2 was examined. Various engine system concepts were formulated that included staged combustion and gas generator turbine power cycles, and LOX/RP-1, LOX/CH4, and LOX/C3H8 mode 1 propellants. Both oxidizer and fuel regenerative cooling were considered. All of the SSME major components were examined to determine their adaptability to the candidate dual-fuel engines.

Wheeler, D. B.; Kirby, F. M.

1978-01-01

298

Stages of Adolescence  

MedlinePLUS

... Stages of Adolescence Ages & Stages Listen Stages of Adolescence Article Body Adolescence, these years from puberty to adulthood, may be roughly divided into three stages: early adolescence, generally ages eleven to fourteen; middle adolescence, ages ...

299

Stages of Esophageal Cancer  

MedlinePLUS

... the body. The following stages are used for squamous cell carcinoma of the esophagus: Stage 0 (High-grade Dysplasia) Stage I squamous cell carcinoma of the esophagus Stage II squamous cell carcinoma ...

300

Seven Stages of Alzheimer's  

MedlinePLUS

Seven Stages of Alzheimer's Tweet Alzheimer's symptoms vary. The stages below provide a general idea of how ... Moderately severe decline Stage 6: Severe decline Stage 7: Very severe decline Get our weekly e-newsletter ...

301

Second Stage Separation  

NASA Video Gallery

When the second stage burn is complete, the spacecraft and third stage are spun up to 55 rpm to stabilize the third stage during its short firing. The second stage is then jettisoned and the third ...

302

How Is Neuroblastoma Staged?  

MedlinePLUS

... diagnosed? Next Topic Neuroblastoma risk groups How is neuroblastoma staged? The stage of a cancer describes how ... you in a way you can understand. International Neuroblastoma Staging System A staging system is a standard ...

303

Web Engineering  

SciTech Connect

Web Engineering is the application of systematic, disciplined and quantifiable approaches to development, operation, and maintenance of Web-based applications. It is both a pro-active approach and a growing collection of theoretical and empirical research in Web application development. This paper gives an overview of Web Engineering by addressing the questions: (a) why is it needed? (b) what is its domain of operation? (c) how does it help and what should it do to improve Web application development? and (d) how should it be incorporated in education and training? The paper discusses the significant differences that exist between Web applications and conventional software, the taxonomy of Web applications, the progress made so far and the research issues and experience of creating a specialization at the master's level. The paper reaches a conclusion that Web Engineering at this stage is a moving target since Web technologies are constantly evolving, making new types of applications possible, which in turn may require innovations in how they are built, deployed and maintained.

White, Bebo

2003-06-23

304

Radiative Decay of Upper Tropospheric Anticyclones  

NASA Astrophysics Data System (ADS)

We investigate the dynamics and the decay of upper tropospheric anticyclones. First, we focus on the nature, the frequency and the formation of these atmospheric patterns. Standard Isentropic Potential Vorticity maps (using analysed fields from ECMWF) show that these synoptic situations are common in the northern hemisphere with a higher frequency during autumn. Massive back-trajectory calculations (using the kinematic trajectory model FLEX- TRA) reveal that most of air parcels are coming from the tropical or the subtropical boundary layer following "warm conveyor belts". Advection of humid air into upper tropospheric anticyclones is in agreement with aircraft data from SONEX and POLI- NAT airborne campaigns and with MOZAIC humidity measurements. In anticyclonic vorticies, these data show frequent relative humidity sursaturation with respect to ice. Mesoscale simulations (using MesoNH model from Meteo-France) has been per- formed to investigate more precisely the advection of boundary layer air into an upper tropospheric anticyclone. Online lagrangian calculations have been performed and we plan to estimate the meridian humidity flux induced by this process. In a second stage, decay of upper tropospheric anticyclones is studied. The presence of thin cirrus clouds in these anticyclonic vortices is an open question. Nevertheless, airborne lidar measurements during the SONEX III campaign show that thin cirrus are present during the first stage of the anticyclone life. These clouds may play a ma- jor role concerning radiative decay. Idealized mesoscale simulations (using MesoNH model) have been performed. At the present time, realistic decay is obtained only in clear sky conditions. Radiative decay induces a net mass flux from the troposphere to the stratosphere. This flux is increased with the moistening of upper tropospheric cy- clones. Using realistic humidity fields, it is found to be of the same order of magnitude that net flux from the stratosphere to the troposphere observed for cutoff cyclones in the literature. Parameterization of cirrus clouds in idealized and realistic simulations is in progress.

Daniel, Vincent; Legras, Bernard

305

Engine construction  

SciTech Connect

An engine has at least two piston-cylinder assemblies each comprising a cylinder formed in an engine block with a cylinder head and a piston therein in sliding relationship toward and away from the head, a piston rod operatively connected to the piston and to a crankshaft, motion producing member of shape-memory material, e.g. Nitinol, having a transformation temperature range, secured to the cylinder head and the side of the piston opposite from the connecting rod, the motion producing member having a heat treated high temperature extended shape memory position and a low temperature low energy compressed position, the Nitinol member being of hollow tubular form and having pressure and return hoses connected thereto for supplying and removing cooling fluid into and from the Nitinol member, an electrical heating device connected to the Nitinol member, whereby the Nitinol member is easily compressed with relatively little force from the extended shape memory position to the compressed position when cooling fluid is supplied thereto to reduce the temperature of the Nitinol member to or below the lower limit of the transformation temperature range and the Nitinol member is automatically extended with relatively great force from the compressed position to the shape memory position when heated by the heating device to or above the upper limit of the transformation temperature range.

Dillon, C.L.

1984-03-06

306

CLOSEUP VIEW OF THE FIRST STAGE OF THE SATURN I ...  

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

CLOSE-UP VIEW OF THE FIRST STAGE OF THE SATURN I ROCKET, SHOWING A DETAIL VIEW OF THE ENGINE CLUSTER. THE SATURN I ROCKET WAS THE FIRST UNITED STATES ROCKET TO HAVE MULTIPLE ENGINES ON A SINGLE STAGE. - Marshall Space Flight Center, Saturn Propulsion & Structural Test Facility, East Test Area, Huntsville, Madison County, AL

307

46. VIEW OF STAGE RECORDER AT END OF DOWNSTREAM GUIDEWALL, ...  

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

46. VIEW OF STAGE RECORDER AT END OF DOWNSTREAM GUIDEWALL, LOOKING SOUTH - Upper Mississippi River 9-Foot Channel, Lock & Dam No. 8, On Mississippi River near Houston County, MN, Genoa, Vernon County, WI

308

45. VIEW OF STAGE RECORDER AT END OF UPSTREAM GUIDEWALL, ...  

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

45. VIEW OF STAGE RECORDER AT END OF UPSTREAM GUIDEWALL, LOOKING NORTH - Upper Mississippi River 9-Foot Channel, Lock & Dam No. 8, On Mississippi River near Houston County, MN, Genoa, Vernon County, WI

309

Gasdynamic Inlet Isolation in Rotating Detonation Engine.  

National Technical Information Service (NTIS)

The Rotating Detonation Engine (RDE) concept represents the next- generation of detonation-based engines as it provides higher performance and near constant thrust with a simpler overall design. Since RDE systems are in the early stage of development, the...

W. H. Lim

2010-01-01

310

RS-84 Engine  

NASA Technical Reports Server (NTRS)

The RS-84 is the first reusable hydrocarbon staged combustion liquid rocket engine. This engine is being developed to meet NASA s crew safety goals with a highly reliable and low cost main engine as a part of the NASA Space Launch Initiative program for the next generation reusable launch system. The NASA-MSFC and Rocketdyne team brings over 50 years of successful rocket engine development experience to meet the challenges of this new program. This team s extensive design database has been anchored with almost five decades of hydrocarbon rocket engine development and flight operations experience including Delta, Atlas, and Saturn vehicles and nearly three decades of successfully operating the world s only reusable pump-fed rocket engine, the Space Shuttle Main Engine. The team also fully benefits from the proven and experienced engineering staffs that recently completed the successful MC-1 FASTRAC , XRS-2200, and RS-68 engine development programs and the ongoing IPD and RS-76 technology development. Advances in integrated parametric design and analysis tools, advanced materials knowledge base, and state-of-the-art fabrication processes anchored and refined during the recent engine development programs are already being used by the team to design this engine.

Stegman, E.

2003-01-01

311

Kinetics of stage ordering and stage transitions  

NASA Astrophysics Data System (ADS)

A model of intercalation is presented which can be used for sophisticated three-dimensional computer simulations of staging kinetics. A realistic microscopic description of the intercalation process and of the stage-3 to stage-2 transition has been obtained for the first time. Stage disorder and three-dimensional effects are shown to be key ingredients of these phenomena. This work makes possible the first critical appraisal of the Daumass-Herold model, which is shown to be valid for uniformly intercalated high- and low-stage crystals, and to provide a useful language for describing the stage transition.

Kirczenow, G.

1985-12-01

312

Space Shuttle Main Engine - The Relentless Pursuit of Improvement.  

National Technical Information Service (NTIS)

The Space Shuttle Main Engine (SSME) is the only reusable large liquid rocket engine ever developed. The specific impulse delivered by the staged combustion cycle, substantially higher than previous rocket engines, minimized volume and weight for the inte...

D. P. Bradley K. P. VanHooser

2011-01-01

313

A cascade thermoacoustic engine.  

PubMed

A cascade thermoacoustic engine is described, consisting of one standing-wave stage plus two traveling-wave stages in series. Most of the acoustic power is produced in the efficient traveling-wave stages. The straight-line series configuration is easy to build and allows no Gedeon streaming. The engine delivers up to 2 kW of acoustic power, with an efficiency (the ratio of acoustic power to heater power) of up to 20%. An understanding of the pressure and volume-velocity waves is very good. The agreement between measured and calculated powers and temperatures is reasonable. Some of the measured thermal power that cannot be accounted for by calculation can be attributed to Rayleigh streaming in the two thermal buffer tubes with the largest aspect ratios. A straightforward extension of this work should yield cascade thermoacoustic engines with efficiencies of around 35-40% of the Carnot efficiency. PMID:14587591

Gardner, D L; Swift, G W

2003-10-01

314

A cascade thermoacoustic engine  

NASA Astrophysics Data System (ADS)

A cascade thermoacoustic engine is described, consisting of one standing-wave stage plus two traveling-wave stages in series. Most of the acoustic power is produced in the efficient traveling-wave stages. The straight-line series configuration is easy to build and allows no Gedeon streaming. The engine delivers up to 2 kW of acoustic power, with an efficiency (the ratio of acoustic power to heater power) of up to 20%. An understanding of the pressure and volumevelocity waves is very good. The agreement between measured and calculated powers and temperatures is reasonable. Some of the measured thermal power that cannot be accounted for by calculation can be attributed to Rayleigh streaming in the two thermal buffer tubes with the largest aspect ratios. A straightforward extension of this work should yield cascade thermoacoustic engines with efficiencies of around 35-40% of the Carnot efficiency.

Gardner, D. L.; Swift, G. W.

2003-10-01

315

Upper gastrointestinal bleeding.  

PubMed

Upper gastrointestinal bleeding is a life threatening condition in children. Common sources of upper gastrointestinal bleeding in children include variceal hemorrhage (most commonly extra-hepatic portal venous obstruction in our settings) and mucosal lesions (gastric erosions and ulcers secondary to drug intake). While most gastrointestinal bleeding may not be life threatening, it is necessary to determine the source, degree and possible cause of the bleeding. A complete and thorough history and physical examination is therefore vital. Esophagogastroduodenoscopy and colonoscopy are currently considered the first-line diagnostic procedures of choice for upper and lower GI bleeding, respectively. The goals of therapy in a child with GI bleeding should involve hemodynamic resuscitation, cessation of bleeding from source and prevention of future episodes of GI bleeding. Antacids supplemented by H2- receptor antagonists and proton pump inhibitors are the mainstay in the treatment of bleeding from mucosal lesion. For variceal bleeds, therapeutic emergency endoscopy is the treatment of choice after initial hemodynamic stabilization of the patient. Independent prognostic factors are presence of shock and co-morbidities. Underlying diagnosis, coagulation disorder, failure to identify the bleeding site, anemia and excessive blood loss are other factors associated with poor prognosis. PMID:21153570

Bhatia, Vidyut; Lodha, Rakesh

2011-02-01

316

A technology data base for the design of 500 to 5000-lb thrust class liquid rocket engines utilizing hydrogen and oxygen as propellants  

NASA Technical Reports Server (NTRS)

This paper presents an overview of the results of experimental evaluations of candidate designs for igniters, injectors, and propellant-cooled thrust chambers applicable to restartable high-performance, high-reliability upper-stage engines and to pulsing-type reaction control engines (RCE). Injection element types best suited for liquid, gas, and liquid/gas phase propellant supply are identified. The resulting interactions between element type, combustion efficiency, and chamber wall heating are compared. The distinction between thrust chamber design requirements for upper stage vs RCE applications as measured by cycle life requirements is translated into design configurations consisting of all-film-cooled, all-regeneratively-cooled, and composites of the two cooling approaches. The validity of the design approaches is confirmed by data from engine durability testing involving over 90,000 starts and 9,000 thermal cycles on RCE-type designs and multiple long-duration burns (up to 2,000 sec) on regeneratively cooled upper-stage designs.

Schoenman, L.

1982-01-01

317

System Study for Axial Vane Engine Technology  

NASA Technical Reports Server (NTRS)

The purpose of this engine feasibility study was to determine the benefits that can be achieved by incorporating positive displacement axial vane compression and expansion stages into high bypass turbofan engines. These positive-displacement stages would replace some or all of the conventional compressor and turbine stages in the turbine engine, but not the fan. The study considered combustion occurring internal to an axial vane component (i.e., Diesel engine replacing the standard turbine engine combustor, burner, and turbine); and external continuous flow combustion with an axial vane compressor and an axial vane turbine replacing conventional compressor and turbine systems.

Badley, Patrick R.; Smith, Michael R.; Gould, Cedric O.

2008-01-01

318

Analysis of the second stage of the STAR 28 mm two-stage light gas gun  

Microsoft Academic Search

An engineering model of the second stage operation of the 28 mm two-stage light gas gun at the Shock Technology and Applied Research (STAR) facility of Sandia National Laboratories has been developed. It describes the piston motion and loading of the accelerated reservoir (AR) and the coupled projectile motion. The model was developed to better assess the safety of the

Donald B. Longcope

1995-01-01

319

Upper extremity neuromuscular injuries in athletes.  

PubMed

Upper extremity muscle and nerve injuries in athletes are important causes of lost playing time and suboptimal performance. Although most muscle injuries are self-limited, imaging may be indicated in select situations for diagnostic and prognostic purposes, to investigate potential complications of injury, and for instituting prompt therapy to hasten recovery. MRI is particularly sensitive to soft tissue abnormalities seen in muscle injury, and it can reliably diagnose and stage direct injuries such as contusions and lacerations, and indirect injuries such as strains, delayed-onset muscle soreness, and exertional compartment syndrome. Upper extremity peripheral nerve injuries may be compressive or noncompressive in etiology, with certain sports and activities rendering particular nerves vulnerable to characteristic injuries. Initial evaluation includes a complete history, physical examination, and electrodiagnostic studies. MRI and ultrasound assessment of the nerves, surrounding tissues, and innervated muscles can provide localizing, diagnostic, and prognostic information that complements clinical and electrodiagnostic testing. PMID:23047279

Demertzis, Jennifer L; Rubin, David A

2012-09-01

320

Nuclear stage configuration studies for Mars missions  

NASA Technical Reports Server (NTRS)

Several nuclear-propulsion stage configuration options for the February 2016 Mars Exploration Initiative mission are examined. Special attention is given to the 75,000-lb-thrust nuclear engine used for the major propulsive maneuvers. The reference mission, which will last 435 days, with the stay on Mars for 30 days, assumes that the nuclear thermal rocket (NTR) engine delivers a specific impulse of 925 sec with an engine thrust-to-weight ratio of 4. Results are given of trade studies performed on the NTR engine thrust level, engine thrust-to-weight ratio, and engine Isp. Attention is also given to the Mars transfer vehicle, the Mars transportation system (MTS), the MTS crew compartment, and the MTS tanks.

Emrich, W. J., Jr.; Young, A. C.; Mulqueen, J. A.

1990-01-01

321

Aerodynamics of the upper surface blow flap  

NASA Technical Reports Server (NTRS)

The results of some preliminary wind-tunnel investigations made to provide fundamental aerodynamic information on the upper surface blown jet-flap concept incorporating high-bypass-ratio turbofan engines are summarized. The results of the investigation have shown the concept to have aerodynamic performance generally similar to that of other externally blown high-lift systems. A few of the more critical problems associated with this concept have been identified and preliminary solutions to some of these problems have been found. These results have proven to be sufficiently encouraging to warrant continuation of fundamental research efforts on the concept.

Phelps, A. E., III

1972-01-01

322

Upper Gastrointestinal Stent  

PubMed Central

Gastrointestinal (GI) stent has been developed for palliation of obstructive symptoms in various diseases causing obstruction of GI tract. Self-expanding metal stent (SEMS) has replaced old type of plastic stent, and endoscopic insertion of stent has replaced fluoroscopy-guided insertion. Nowadays, newly-designed SEMSs have been developed for prevention of complications such as stent migration and re-obstruction, and indications of stent recently have been widened into benign conditions as well as malignant obstruction. In this review, the types, method of insertion, indications and clinical outcomes of stent in the upper GI tract would be discussed.

Kim, Sang Gyun

2012-01-01

323

VATS right upper lobectomy  

PubMed Central

Standard thoracotomy has been considered as the classic approach and only choice for the diagnosis and treatment of certain thoracic diseases especially in patients with peripheral lung cancer. Video-assisted thoracic surgery (VATS) is a new minimally invasive thoracic surgery through small incisions in the intercostal muscle of chest wall by using modern camera technology, high-tech equipment and surgical instrument. Consequently, VATS has become the preferred main method for peripheral lung cancer in the last two decades. The aim of the present paper is to describe and discuss the operative techniques of VATS for right upper lobectomy (RUL).

Kang, Gan-Jun; Jiang, Wen-Yang; Xie, Song-Ping

2013-01-01

324

Industrial Engineering Education: A Prospective.  

ERIC Educational Resources Information Center

Presents an overview of the origin of the industrial engineering discipline and how the subject was taught in the early stages of its development. Describes current changes in the curricula to meet new requirements in industry. (Author/CCM)

Elsayed, E. A.

1999-01-01

325

Supersonic Air-Breathing Stage For Commercial Launch Rocket  

NASA Technical Reports Server (NTRS)

Concept proposed to expand use of air-breathing, reusable stages to put more payload into orbit at less cost. Stage with supersonic air-breathing engines added to carry expendable stages from subsonic airplane to supersonic velocity. Carry payload to orbit. Expendable stages and payload placed in front of supersonic air-breathing stage. After releasing expendable stages, remotely piloted supersonic air-breathing stage returns to takeoff site and land for reuse. New concept extends use of low-cost reusable hardware and increases payload delivered from B-52.

Martin, James A.

1993-01-01

326

Pancreatic Cancer Stage 4  

MedlinePLUS

... My Pictures Browse Search Quick Search Image Details Pancreatic Cancer Stage 4 View/Download: Small: 533x576 View Download Add to My Pictures Title: Pancreatic Cancer Stage 4 Description: Stage IV pancreatic cancer; drawing ...

327

Pancreatic Cancer Stage 3  

MedlinePLUS

... Search Quick Search Image Details Pancreatic Cancer Stage 3 View/Download: Small: 720x576 View Download Add to My Pictures Title: Pancreatic Cancer Stage 3 Description: Stage III pancreatic cancer; drawing shows cancer ...

328

Stages of Hypopharyngeal Cancer  

MedlinePLUS

... are used for hypopharyngeal cancer: Stage 0 (Carcinoma in Situ) In stage 0 , abnormal cells are found in ... normal tissue . Stage 0 is also called carcinoma in situ . Enlarge Pea, peanut, walnut, and lime show tumor ...

329

42. VIEW OF STAGE RECORDER AT END OF UPSTREAM GUIDE ...  

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

42. VIEW OF STAGE RECORDER AT END OF UPSTREAM GUIDE WALL, LOOKING NORTHEAST. (Several hours after this view was taken, the stage recorder was hit a~d heavily damaged by a grain barge.) - Upper Mississippi River 9-Foot Channel, Lock & Dam No. 9, Lynxville, Crawford County, WI

330

Two-Stage Industrial Heat Pumps. A Design Study.  

National Technical Information Service (NTIS)

The two-stage heat pump, consisting of a closed cycle in the lower part and a steam compression in the upper part, is of interest for industrial applications, such as low pressure steam generation. The behaviour of the two-stage heat pump with different w...

M. Brun

1987-01-01

331

Rocket Engine Oscillation Diagnostics  

NASA Technical Reports Server (NTRS)

Rocket engine oscillating data can reveal many physical phenomena ranging from unsteady flow and acoustics to rotordynamics and structural dynamics. Because of this, engine diagnostics based on oscillation data should employ both signal analysis and physical modeling. This paper describes an approach to rocket engine oscillation diagnostics, types of problems encountered, and example problems solved. Determination of design guidelines and environments (or loads) from oscillating phenomena is required during initial stages of rocket engine design, while the additional tasks of health monitoring, incipient failure detection, and anomaly diagnostics occur during engine development and operation. Oscillations in rocket engines are typically related to flow driven acoustics, flow excited structures, or rotational forces. Additional sources of oscillatory energy are combustion and cavitation. Included in the example problems is a sampling of signal analysis tools employed in diagnostics. The rocket engine hardware includes combustion devices, valves, turbopumps, and ducts. Simple models of an oscillating fluid system or structure can be constructed to estimate pertinent dynamic parameters governing the unsteady behavior of engine systems or components. In the example problems it is shown that simple physical modeling when combined with signal analysis can be successfully employed to diagnose complex rocket engine oscillatory phenomena.

Nesman, Tom; Turner, James E. (Technical Monitor)

2002-01-01

332

High Head Unshrouded Impeller Pump Stage Technology  

NASA Technical Reports Server (NTRS)

A team of engineers at NASA/MSFC and Boeing, Rocketdyne division, are developing unshrouded impeller technologies that will increase payload and decrease cost of future reusable launch vehicles. Using the latest analytical techniques and experimental data, a two-stage unshrouded fuel pump is being designed that will meet the performance requirements of a three-stage shrouded pump. Benefits of the new pump include lower manufacturing costs, reduced weight, and increased payload to orbit.

Williams, Robert W.; Skelley, Stephen E.; Stewart, Eric T.; Droege, Alan R.; Prueger, George H.; Chen, Wei-Chung; Williams, Morgan; Turner, James E. (Technical Monitor)

2000-01-01

333

78 FR 35747 - Airworthiness Directives; Engine Alliance Turbofan Engines  

Federal Register 2010, 2011, 2012, 2013

...prompted by damage to the high-pressure compressor (HPC) stage 7-9...6 disks. This AD requires initial and repetitive borescope inspections...That NPRM proposed to require initial and repetitive borescope inspections...turbofan engines with a high-pressure compressor (HPC) stage...

2013-06-14

334

J-2 Engine Assembly Line  

NASA Technical Reports Server (NTRS)

J-2 engines for the Saturn IB/Saturn V launch vehicles are lined up in the assembly area at Rocketdyne's manufacturing plant in Canoga Park, California. Five J-2 engines provided more than 1,000,000 pounds of thrust to accelerate the second stage toward a Moon trajectory.

1963-01-01

335

Introductory mining engineering  

SciTech Connect

Provides treatment of the applications of mining engineering while reinforcing material with analyses of special topics as well as numerical examples and problems. Initial chapters are devoted to fundamentals, explaining the four stages of mining - prospecting, exploration, development, exploitation - and the unit operations of mining. The text continues with coverage of surface mining and underground mining.

Hartman, H.

1987-01-01

336

Geology and petroleum prospects of Upper Triassic sediments, Jordan  

Microsoft Academic Search

Subsurface Upper Triassic sediments of northern Jordan represent part of a regressive evaporitic-clastic succession that marks the shrinkage phase of the Late Triassic basin in the northern parts of the Arabian Plate. Sabkhas developed along the basin margin, whereas, oolitic shoals formed on the deeper parts of the carbonate platform. The basin reached a drewdown stage in the Risha, Palmyra

F. N Sadooni; A Dalqamouni

1998-01-01

337

Drift of Larval Fishes in the Upper Colorado River  

Microsoft Academic Search

Native as well as some non-native fishes in the upper Colorado River were found drifting during their larval and early juvenile stages of development. Five native fishes (flannelmouth sucker, bluehead sucker, roundtail chub, speckled dace, and mottled sculpin) dominated the drift with about 87 percent of the catch. The only 3 non-native species found in the drift (white sucker, fathead

John G. Carter; Vincent A. Lamarra; Ronald J. Ryel

1986-01-01

338

Expendable second stage reusable space shuttle booster. Volume 6: Interface control drawings  

NASA Technical Reports Server (NTRS)

The major expendable second stage interfaces which must be controlled in the development of the expendable second stage reusable space shuttle booster are defined. Interface control drawings are presented for the following configurations: (1) booster/expendable second stage (ESS), (2) space shuttle engine/expendable second stage, (3) expendable second stage/ground support equipment, (4) expendable second stage/payload, and (5) orbiter/expendable second stage.

1971-01-01

339

From Paper to Production to Test: An Update on NASA's J-2X Engine for Exploration  

NASA Technical Reports Server (NTRS)

The NASA/industry team responsible for developing the J-2X upper stage engine for the Space Launch System (SLS) Program has made significant progress toward moving beyond the design phase and into production, assembly, and test of development hardware. The J-2X engine exemplifies the SLS Program goal of using proven technology and experience from more than 50 years of United States spaceflight experience combined with modern manufacturing processes and approaches. It will power the second stage of the fully evolved SLS Program launch vehicle that will enable a return to human exploration of space beyond low earth orbit. Pratt & Whitney Rocketdyne (PWR) is under contract to develop and produce the engine, leveraging its flight-proven LH2/LOX, gas generator cycle J-2 and RS-68 engine capabilities, recent experience with the X-33 aerospike XRS-2200 engine, and development knowledge of the J-2S tap-off cycle engine. The J- 2X employs a gas generator operating cycle designed to produce 294,000 pounds of vacuum thrust in primary operating mode with its full nozzle extension. With a truncated nozzle extension suitable to support engine clustering on the stage, the nominal vacuum thrust level in primary mode is 285,000 pounds. It also has a secondary mode, during which it operates at 80 percent thrust by altering its mixture ratio. The J-2X development philosophy is based on proven hardware, an aggressive development schedule, and early risk reduction. NASA Marshall Space Flight Center (MSFC) and PWR began development of the J-2X in June 2006. The government/industry team of more than 600 people within NASA and PWR successfully completed the Critical Design Review (CDR) in November 2008, following extensive risk mitigation testing. Assembly of the first development engine was completed in May 2011 and the first engine test was conducted at the NASA Stennis Space Center (SSC), test stand A2, on 14 July 2011. Testing of the first development engine will continue through the autumn of 2011, be paused for test stand modifications to the passive diffuser, and then restart in the spring of 2012. This testing will be followed by specialized powerpack testing intended to examine the design and operating margins of the engine turbomachinery. The development plan beyond this point leads through more system-level, engine testing of several samples, analytical model validation activities, functional and performance verification, and then ultimate certification to support human spaceflight. This paper will discuss the J-2X development background, provide top-level information on design and development planning, and will explore some of the development challenges and mitigation activities pursued to date.

Kynard, Michael

2011-01-01

340

Stages of Chronic Lymphocytic Leukemia  

MedlinePLUS

... stages are used for chronic lymphocytic leukemia: Stage 0 In stage 0 chronic lymphocytic leukemia , there are ... or check-ups. Treatment Options by Stage Stage 0 Chronic Lymphocytic Leukemia Treatment of stage 0 chronic ...

341

Thermal Characterization of a Direct Gain Solar Thermal Engine  

NASA Technical Reports Server (NTRS)

A thermal/fluids analysis of a direct gain solar thermal upper stage engine is presented and the results are discussed. The engine was designed and constructed at the NASA Marshall Space Flight Center for ground testing in a facility that can provide about 10 kilowatts of concentrated solar energy to the engine. The engine transfers energy to a coolant (hydrogen) that is heated and accelerated through a nozzle to produce thrust. For the nominal design values and a hydrogen flowrate of 2 lb./hr., the results of the analysis show that the hydrogen temperature in the chamber (nozzle entrance) reaches about 3800 F after 30 minutes of heating and about 3850 F at steady-state (slightly below the desired design temperature of about 4100 F. Sensitivity analyses showed these results to be relatively insensitive to the values used for the absorber surface infrared emissivity and the convection coefficient within the cooling ducts but very sensitive to the hydrogen flowrate. Decreasing the hydrogen flowrate to 1 lb./hr. increases the hydrogen steady-state chamber temperature to about 4700 F, but also of course causes a decrease in thrust.

Alexander, Reginald A.; Coleman, Hugh W.

1999-01-01

342

Thermal Characterization of a Direct Gain Solar Thermal Engine  

NASA Technical Reports Server (NTRS)

A thermal/fluids analysis of a direct gain solar thermal upper stage engine is presented and the results are discussed. The engine has been designed and constructed at the NASA Marshall Space Flight Center for ground testing in a facility that can provide about 10 kilowatts of concentrated solar energy to the engine. The engine transfers that energy to a coolant (hydrogen) that is heated and accelerated through a nozzle to produce thrust. For the nominal design values and a hydrogen flowrate of 2 lb/hr., the results of the analysis show that the hydrogen temperature in the chamber (nozzle entrance) reaches about 3800 F after 30 minutes of heating and about 3850 F at steady-state (slightly below the desired design temperature of about 4100 F). Sensitivity analyses showed these results to be relatively insensitive to the values used for the absorber surface infrared emissivity and the convection coefficient within the cooling ducts but very sensitive to the hydrogen flowrate. Decreasing the hydrogen flowrate to 1 lb/hr. increases the hydrogen steady-state chamber temperature to about 4700 F, but also causes an undesirable decrease in thrust.

Alexander, Reginald A.; Coleman, Hugh W.

1998-01-01

343

Titan improvement study - Hydrogen core stages  

NASA Astrophysics Data System (ADS)

The performance benefits and comparative cost-effectiveness of Titan/Centaur launcher improvement options involving a new LH2/LOX second stage and/or a new LH2/LOX first stage are presented. This incremental improvement approach involves higher confidence due to high components-commonality with well-tested systems. The proposed second stage's capabilities are such as to allow it to serve as an OTV. This improvement to Titan constitutes one of several justifications for a new 500-1000 kN thrust liquid-fuel engine.

Martin, James A.

1991-06-01

344

Engineer Girl  

NSDL National Science Digital Library

This engineering website is geared towards girls and young women to encourage and inspire them to pursue careers in engineering. The site includes articles, links, contests, and biographies of current women engineers.

2013-01-01

345

Ergonomic stressors and upper extremity disorders in vehicle manufacturing: cross sectional exposure-response trends  

Microsoft Academic Search

OBJECTIVE: To evaluate the association between upper extremity soft tissue disorders and exposure to preventable ergonomic stressors in vehicle manufacturing operations. METHODS: A cross sectional study was conducted in one vehicle stamping plant and one engine assembly plant. A standardised physical examination of the upper extremities was performed on all subjects. An interviewer administered questionnaire obtained data on demographics, work

L. Punnett

1998-01-01

346

A compact, high-performance cryogenic stage  

NASA Astrophysics Data System (ADS)

This paper describes the design concept and performance for a compact, high performance cryogenic upper stage. The design concept, developed during the Compact LOX Feed System Study, involves a toroidal liquid oxygen tank for both high-thrust and low-thrust STS launched OTV's. Study results show that a 17,000 lbm payload having a 38.5 ft maximum length can be delivered by the stage to geosynchronous orbit following deployment from the Orbiter cargo bay. Detailed design and analysis of the storage vessel, fluid management, and thermal control hardware were performed in support of the overall integrated tank design. A single tank configuration was evaluated for both thrust levels and the minor penalties resulting from use of the common stage configuration were identified. Vehicle modifications to provide stage reusability and man rating were also assessed.

Fester, D. A.; Robinson, J. W.; Bicknell, B. A.

1986-06-01

347

Animated Engines  

NSDL National Science Digital Library

This remarkable Web site contains descriptions and animations of nineteen different kinds of engines. Engine types include internal combustion, steam, and sterling engines, and each page shows how the piston, crankshaft, and other components move together to generate power. The animations demonstrate the processes of intake, compression, and exhaust. Some of the featured engines have more detailed descriptions than others, and oftentimes, a brief account of the engine's history is included. One engine dates back to the early 1700s.

2000-01-01

348

The utilitarian upper eyelid operation.  

PubMed

Techniques in oculofacial surgery continue to develop as our understanding of anatomy and pathophysiology continue to evolve. While the centerpiece of the quest to rejuvenate the upper eyelid and brow has for years been the upper blepharoplasty, several modifications to traditional techniques have been developed that allow for enhanced outcomes utilizing less invasive approaches. Techniques discussed include removal of lower lid lateral fat via the upper blepharoplasty, a minimally invasive resuspension lateral canthoplasty performed via the upper eyelid exposure, brassiere lateral brow contouring closure, and correction of lower lid retraction by an "en-glove" technique. PMID:20524170

Lee, Seong; Taban, Mehryar; Strahan, Ronald

2010-08-01

349

Upper airway.4: Sarcoidosis of the upper respiratory tract (SURT)  

Microsoft Academic Search

Sarcoidosis of the upper respiratory tract (SURT) includes nasopharyngeal, laryngeal and tracheal disease. Documented SURT occurs in ?5% of patients, although upper airway symptoms are more common in patients with sarcoidosis. Wegener granulomatosis may have a similar appearance to SURT, but there are important differences in the manifestations of the disease locally as well as systemically. In some cases, topical

Robert P Baughman; Elyse E Lower; Thomas Tami

2010-01-01

350

Engineering analysis and test results of the pre-stage planetary gear trains for wrist rotation and pitch assembly and azimuth and elevation assembly of the extendable stiff arm manipulator kit assembly  

NASA Technical Reports Server (NTRS)

In order to improve the performance capability of the Extendable Stiff Arm Manipulator (ESAM) it was necessary to increase the overall gear ratio by a factor of approximately four. This is accomplished with minimum effect to existing hardware by the interposition of a planetary gear transmission between the respective drive motors and the harmonic drive transmissions. The engineering analysis in support of this design approach and the subsequent no-load test results are reported.

Morris, R. N.

1973-01-01

351

Adaptive hybrid system for automatic sleep staging.  

PubMed

We present a new adaptive system for automated sleep staging. The proposed system relies on each subject's own data for self-training. Conventional automatic sleep staging algorithms are either rule based, which typically fail to accurately model the complex nature of sleep signals, or numerical methods that use multi-patient training schemes, which suffer from inaccuracies caused by inherent inter-patient variability. The proposed system employs two stages. The first stage is a rule based reasoning engine that can be tuned conservatively to decrease or eliminate false positives, generating just enough samples to train the second stage, which is comprised of a neural network classifier. Results show that this hybrid approach provides an adaptive training scheme that performs more accurately compared to one of the popular commercially available systems. PMID:19162989

Hassaan, Amr A; Morsy, Ahmed A

2008-01-01

352

Upper respiratory infections.  

PubMed

It is estimated that >24 million cases of acute bacterial sinusitis occur annually in the United States. Recently, a number of medical societies have issued guidelines to aid in the management of upper respiratory tract infections (URIs). Although these guidelines serve to aid practitioners in the proper use of antibiotics, confusion remains regarding the disparity of guideline recommendations as well as some recommendations being outdated. This review presents 3 illustrative case studies designed to provide some clarity with regard to these guidelines. Case 1 is a typical presentation of a patient with worsening sinus conditions over the previous 2 weeks. Case 2 is a more challenging case of a patient with a sinus condition accompanied by a penicillin allergy that ultimately requires referral to an otolaryngologist. Case 3 is an atypical case with symptoms of a sinus infection accompanied by a normal sinus computed tomography scan. It is hoped that the presentation and discussion surrounding these cases will provide some helpful insights into the management of patients with URIs. PMID:20350632

Anon, Jack B

2010-04-01

353

Upper Hudson Dredging Debate  

NSDL National Science Digital Library

In preparation for the activity a lecture is given on the properties and history of polychlorinated biphenyls and other contaminants. Each student is assigned to one of six groups with an interest in the outcome of the debate. The teams must meet and prepare a position paper on the proposed environmental dredging in the Upper Hudson River. Each team must represent the interests of its assigned constituency. Data and background information is found on the world wide web and from the instructor's collection of related articles. On the day of the debate the student's orally present their position paper (some make posters or powerpoint presentations). After each group has made their opening statement the invited guest senators on the panel (other faculty, myself, interested students, those who were absent for the preparation) ask each group a series of questions related to their stance. After this a general debate begins with detailed and sometimes heated discussions between the groups and the panel. A few moments are saved at the end of class and everyone is allowed to drop their assumed affiliation and speak their mind on what should be done. Before leaving the class is give a series of big picture topics to think about over the weekend and these are discussed during the next class.

Chiarenzelli, Jeffrey R.

354

Engineering Practice and Engineering Ethics.  

ERIC Educational Resources Information Center

Offers ways of applying science and technology studies to the teaching of engineering ethics. Suggests modifications of both detailed case studies on engineering disasters and hypothetical, ethical dilemmas employed in engineering ethics classes. (Author/CCM)

Lynch, William T.; Kline, Ronald

2000-01-01

355

Neural network design for engineering applications  

Microsoft Academic Search

Computers are an integral part of day to day activities in engineering design and engineers have utilised various applications to assist them improve their design. Although computers are used to model a variety of engineering activities, currently the main focus of computer applications are areas with well defined rules. Activities related to the conceptual stage of the design process are

M. Y Rafiq; G Bugmann; D. J Easterbrook

2001-01-01

356

Training for Engineering Craftsmen: The Module System.  

ERIC Educational Resources Information Center

New arrangements for craft training in the British engineering industry call for a three stage structure: (1) a year of basic training in a wide variety of skills (welding, vehicle painting, electrical engineering, mechanical engineering, and others); (2) selected training in specialized skills under controlled conditions; (3) experience in using…

Engineering Industry Training Board, London (England).

357

Engineering and Software Engineering  

NASA Astrophysics Data System (ADS)

The phrase ‘software engineering' has many meanings. One central meaning is the reliable development of dependable computer-based systems, especially those for critical applications. This is not a solved problem. Failures in software development have played a large part in many fatalities and in huge economic losses. While some of these failures may be attributable to programming errors in the narrowest sense—a program's failure to satisfy a given formal specification—there is good reason to think that most of them have other roots. These roots are located in the problem of software engineering rather than in the problem of program correctness. The famous 1968 conference was motivated by the belief that software development should be based on “the types of theoretical foundations and practical disciplines that are traditional in the established branches of engineering.” Yet after forty years of currency the phrase ‘software engineering' still denotes no more than a vague and largely unfulfilled aspiration. Two major causes of this disappointment are immediately clear. First, too many areas of software development are inadequately specialised, and consequently have not developed the repertoires of normal designs that are the indispensable basis of reliable engineering success. Second, the relationship between structural design and formal analytical techniques for software has rarely been one of fruitful synergy: too often it has defined a boundary between competing dogmas, at which mutual distrust and incomprehension deprive both sides of advantages that should be within their grasp. This paper discusses these causes and their effects. Whether the common practice of software development will eventually satisfy the broad aspiration of 1968 is hard to predict; but an understanding of past failure is surely a prerequisite of future success.

Jackson, Michael

358

Upper Mississippi River, Pool 7  

USGS Multimedia Gallery

This is an aerial view looking south from above Pool 7 of the Upper Mississippi River near Trempealeau, WI.  The navigation dam which creates the pool appears slightly below the horizon in the upper left quadrant.  Wing dams are evidenced by the rippling water in the river channel as they direct the...

2010-08-18

359

Piston for internal combustion engine  

Microsoft Academic Search

This patent describes a piston for an internal combustion engine comprising: (a) a piston main body made of a first material and having an opening in a top surface thereof, the opening having an upper large diameter portion and a lower small diameter portion with a shoulder defined therebetween; (b) a cavity forming member having a combustion chamber cavity formed

H. Nagase; A. Umemoto

1986-01-01

360

How Is Osteosarcoma Staged?  

MedlinePLUS

... are the survival rates for osteosarcoma? How is osteosarcoma staged? The stage of a cancer is a ... in a way you understand. Localized versus metastatic osteosarcoma Localized osteosarcoma A localized osteosarcoma is seen only ...

361

Beyond First Stage Effects.  

National Technical Information Service (NTIS)

A first stage effect is something that creates greater efficiency. A Second stage effect impacts how people incorporate technologies into social systems. This incorporation causes changes in traditional organization and thought that result in true revolut...

J. L. Ledoux

2000-01-01

362

Orthogonal experimental study on high frequency cascade thermoacoustic engine  

Microsoft Academic Search

Orthogonal experiment design and variance analysis were adopted to investigate a miniature cascade thermoacoustic engine, which consisted of one standing wave stage and one traveling wave stage in series, operating at about 470Hz, using helium as the working gas. Optimum matching of the heater powers between stages was very important for the performance of a cascade thermoacoustic engine, which was

Zhong Jun Hu; Qing Li; Zheng Yu Li; Qiang Li

2008-01-01

363

TBCC Fan Stage Operability and Performance  

NASA Technical Reports Server (NTRS)

NASA s Fundamental Aeronautics Program is investigating turbine-based propulsion systems for access to space because it provides the potential for aircraft-like, space-launch operations that may significantly reduce launch costs and improve safety. Studies performed under NASA s NGLT and the NASP High Speed Propulsion Assessment (HiSPA) program indicated a variable cycle turbofan/ramjet was the best configuration to satisfy access-to-space mission requirements because this configuration maximizes the engine thrust-to-weight ratio while minimizing frontal area. To this end, NASA and GE teamed to design a Mach 4 variable cycle turbofan/ramjet engine for access to space. To enable the wide operating range of a Mach 4+ variable cycle turbofan ramjet required the development of a unique fan stage design capable of multi-point operation to accommodate variations in bypass ratio (10X), fan speed (7X), inlet mass flow (3.5X), inlet pressure (8X), and inlet temperature (3X). The primary goal of the fan stage was to provide a high pressure ratio level with good efficiency at takeoff through the mid range of engine operation, while avoiding stall and losses at the higher flight Mach numbers, without the use of variable inlet guide vanes. Overall fan performance and operability therefore requires major consideration, as competing goals at different operating points and aeromechanical issues become major drivers in the design. To mitigate risk of meeting the unique design requirements for the fan stage, NASA and GE teamed to design and build a 57% engine scaled fan stage to be tested in NASA s transonic compressor facility. The objectives of this test are to assess the aerodynamic and aero mechanic performance and operability characteristics of the fan stage over the entire range of engine operation including: 1) sea level static take-off, 2) transition over large swings in fan bypass ratio, 3) transition from turbofan to ramjet, and 4) fan windmilling operation at high Mach flight conditions. In addition, the fan stage design was validated by performing pre-test CFD analysis using both GE proprietary and NASA s APNASA codes. Herein we will discuss 1) the fan stage design, 2) the experiment including the unique facility and instrumentation, and 3) the comparison of pre-test CFD analysis to initial aerodynamic test results for the baseline fan stage configuration. Measurements and pre-test analysis will be compared at 37%, 50%, 80%, 90%, and 100% of design speed to assess the ability of state-of-the-art design and analysis tools to meet the fan stage performance and operability requirements for turbine based propulsion for access to space.

Suder, Kenneth L.

2007-01-01

364

Choice of organizational structure for software companies in growth stage  

Microsoft Academic Search

This text has analyzed IT enterprise's property and its product system from the angle of software engineering, furthermore, discuss the proper IT enterprise's organization structure in growing stage combined with the life cycle of business.

Li Jianshe; Li Ting

2010-01-01

365

Second Stage (S-II) Arrives at Marshall Space Flight Center For Testing  

NASA Technical Reports Server (NTRS)

The business end of a Second Stage (S-II) slowly emerges from the shipping container as workers prepare to transport the Saturn V component to the testing facility at MSFC. The Second Stage (S-II) underwent vibration and engine firing tests. The towering 363-foot Saturn V was a multi-stage, multi-engine launch vehicle standing taller than the Statue of Liberty. Altogether, the Saturn V engines produced as much power as 85 Hoover Dams.

2004-01-01

366

Upper carboniferous conodont zones of Russia and their global correlation  

NASA Astrophysics Data System (ADS)

The last decade has been marked by significant progress in the study of the stratigraphic ranges of the conodonts characteristic of the Kasimovian and Gzhelian stages in shallow-water sediments of the type sections in the Moscow Basin and the deeper facies of the South Urals. This paper discusses the history of studies of the Upper Carboniferous conodont zonation in Russia and abroad, and proposes a refined zonal conodont scale for the Kasimovian and Gzhelian stages, which may be included, as a standard, into the general Carboniferous scale of Russia. In this scale, the Kasimovian and Gzhelian stages correspond respectively to six ( subexcelsus, makhlinae, sagittalis, cancellosus, toretzianus, firmus) and five ( simulator, vitali, virgilicus, bellus, wabaunsensis) zones. The proposed scale works for the entire East European Platform and the Urals from the Novaya Zemlya Archipelago in the north to the Mugodzhary Mountains in the south. These regions of Russia are occupied by Upper Carboniferous marine facies. At several levels (especially in the Gzhelian Stage), the scale reliably correlates with zones of the Missourian and Virgilian stages in North America and also Dalaun and Mapingian stages in China.

Goreva, N. V.; Alekseev, A. S.

2010-12-01

367

FAST CHOPPER BUILDING, TRA665. DETAIL SHOWS UPPER AND LOWER LEVEL ...  

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

FAST CHOPPER BUILDING, TRA-665. DETAIL SHOWS UPPER AND LOWER LEVEL WALLS OF DIFFERING MATERIALS. NOTE DOORWAY TO MTR TO RIGHT OF CHOPPER BUILDING'S CLIPPED CORNER. CAMERA FACING WEST. INL NEGATIVE NO. HD42-1. Mike Crane, Photographer, 3/2004 - Idaho National Engineering Laboratory, Test Reactor Area, Materials & Engineering Test Reactors, Scoville, Butte County, ID

368

Forensic Engineering  

NSDL National Science Digital Library

The National Academy of Forensic Engineers (1) provides a short definition of forensic engineering as: "the application of the art and science of engineering in matters which are in, or may possibly relate to the jurisprudence system, inclusive of alternative dispute resolution." Specialty areas in forensic engineering include fire investigation, industrial accidents, product liability, traffic accidents, civil engineering and transportation disasters, and environmental systems failures. For example, forensic engineers investigate structural collapses, such as the 2004 Paris Airport collapse described in this article from the Institution of Structural Engineers (2) This website from Materials Evaluation and Engineering, Inc. (3) points out that materials engineering is useful in product failure analysis because many products fail due to materials problems. Given the role forensic engineers play in legal disputes, research in forensic engineering is also a topic on this engineering ethics website (4). Forensic-Evidence.com (5 ) offers The Forensic Center Newsletter, which aims "to stimulate interdisciplinary efforts and research that unite, explore, and advance knowledge in the broad areas of law, medicine, and forensic sciences." This website from the Engineering Forensics Research Institute provides some examples of current research in forensic engineering (6). Finally, Glendale High School offers this Civil Structures Module (7) as a resource for teaching about topics related to forensic engineering, using the 1981 Kansas City Hyatt Regency walkway collapse as an example for analysis.

369

Cetuximab, Cisplatin, and Radiation Therapy in Treating Patients With Stage IB, Stage II, Stage III, or Stage IVA Cervical Cancer  

ClinicalTrials.gov

Cervical Adenocarcinoma; Cervical Adenosquamous Cell Carcinoma; Cervical Small Cell Carcinoma; Cervical Squamous Cell Carcinoma; Stage IB Cervical Cancer; Stage IIA Cervical Cancer; Stage IIB Cervical Cancer; Stage III Cervical Cancer; Stage IVA Cervical Cancer

2013-12-12

370

Science Sampler: Engineering in the classroom  

NSDL National Science Digital Library

In an effort to educate students about engineering, teachers in the Bowling Green, Kentucky, area challenged their students to become engineers. Students were given the tools they needed to design, create, and race a vehicle constructed from plastic building blocks that would move down a predetermined course in the shortest amount of time. With a robotics competition as the culminating experience, upper elementary and middle school students were motivated to become engineers.

Matthew, Kathleen; Wilson, Stacy

2006-11-01

371

Upper extremity lymphedema index: a simple method for severity evaluation of upper extremity lymphedema.  

PubMed

Measurement of the circumference is the most commonly employed method for evaluating extremity lymphedema. However, comparison between different patients is difficult with this measurement. To resolve this problem, we have formulated a new index, upper extremity lymphedema (UEL) index, which can be easily obtained from measurements of the body. We evaluated correlation between UEL index and clinical stage in patients with UEL. The UEL indices were significantly correlated with clinical stages and could be used as a severity scale. The lower extremity lymphedema index makes objective assessment of the severity of lymphedema through a numerical rating, regardless of the body type. This numerical rating makes the index useful for evaluation of lymphedema severities between different cases. PMID:21734534

Yamamoto, Takumi; Yamamoto, Nana; Hara, Hisako; Mihara, Makoto; Narushima, Mitsunaga; Koshima, Isao

2013-01-01

372

Chemical engineer  

NSDL National Science Digital Library

What do chemical engineers actually do? This is the introductory page for a set of materials about chemical engineering as a career. Here the job of a chemical engineer is defined and described. Chemical engineers often work with industrial manufacturing processes that involve a mix of chemistry and engineering. In the rest of the resource, students can examine a specialized job title associated with chemical engineering: process engineer. Students can view a five-minute video clip of the process engineer as he works in a fertilizer plant making ammonia and urea. Students follow the engineer around the plant as he checks pressure in chemical lines. Students get a glimpse of the inside of a furnace during the chemical-making process. Copyright 2005 Eisenhower National Clearinghouse

Project, Iowa P.

2002-01-01

373

Catalyst Development for Hydrogen Peroxide Rocket Engines  

NASA Technical Reports Server (NTRS)

The development of various catalysts of hydrogen peroxide was conducted for the applications of liquid rocket engines. The catalyst development includes silver screen technology, solid catalyst technology, and homogeneous catalyst technology. The silver screen technology development was performed with 85% (by weight) hydrogen peroxide. The results of this investigation were used as the basis for the catalyst design of a pressure-fed liquid-fueled upper stage engine. Both silver-plated nickel 200 screens and pure silver screens were used as the active metal catalyst during the investigation, The data indicate that a high decomposition efficiency (greater than 90%) of 85% hydrogen peroxide can be achieved at a bed loading of 0.5 lbm/sq in/sec with both pure silver and silver plated screens. Samarium oxide coating, however, was found to retard the decomposition process and the catalyst bed was flooded at lower bed loading. A throughput of 200 lbm of hydrogen peroxide (1000 second run time) was tested to evaluate the catalyst aging issue and performance degradation was observed starting at approximately 400 seconds. Catalyst beds of 3.5 inch in diameter was fabricated using the same configuration for a 1,000-lbf rocket engine. High decomposition efficiency was obtained with a low pressure drop across the bed. Solid catalyst using precious metal was also developed for the decomposition of hydrogen peroxide from 85% to 98% by weight. Preliminary results show that the catalyst has a strong reactivity even after 15 minutes of peroxide decomposition. The development effort also includes the homogeneous catalyst technology. Various non-toxic catalysts were evaluated with 98% peroxide and hydrocarbon fuels. The results of open cup drop tests indicate an ignition delay around 11 ms.

Morlan, P. W.; Wu, P.-K.; Ruttle, D. W.; Fuller, R. P.; Nejad, A. S.; Anderson, W. E.

1999-01-01

374

Planning for Plume Diagnostics for Ground Testing of J-2X Engines at the SSC  

NASA Technical Reports Server (NTRS)

John C. Stennis Space Center (SSC) is the premier test facility for liquid rocket engine development and certification for the National Aeronautics and Space Administration (NASA). Therefore, it is no surprise that the SSC will play the most prominent role in the engine development testing and certification for the J-2X engine. The Pratt & Whitney Rocketdyne J-2X engine has been selected by the Constellation Program to power the Ares I Upper Stage Element and the Ares V Earth Departure Stage in NASA s strategy of risk mitigation for hardware development by building on the Apollo program and other lessons learned to deliver a human-rated engine that is on an aggressive development schedule, with first demonstration flight in 2010 and human test flights in 2012. Accordingly, J-2X engine design, development, test, and evaluation is to build upon heritage hardware and apply valuable experience gained from past development and testing efforts. In order to leverage SSC s successful and innovative expertise in the plume diagnostics for the space shuttle main engine (SSME) health monitoring,1-10 this paper will present a blueprint for plume diagnostics for various proposed ground testing activities for J-2X at SSC. Complete description of the SSC s test facilities, supporting infrastructure, and test facilities is available in Ref. 11. The A-1 Test Stand is currently being prepared for testing the J-2X engine at sea level conditions. The A-2 Test Stand is currently being used for testing the SSME and may also be used for testing the J-2X engine at sea level conditions in the future. Very recently, ground-breaking ceremony for the new A-3 rocket engine test stand took place at SSC on August 23, 2007. A-3 is the first large - scale test stand to be built at the SSC since the A and B stands were constructed in the 1960s. The A-3 Test Stand will be used for testing J-2X engines under vacuum conditions simulating high altitude operation at approximately 30,480 m (100,000 ft). To achieve the simulated altitude environment, chemical steam generators using isopropyl alcohol, LOX, and RELEASED - Printed documents may be obsolete; validate prior to use. water would run for the duration of the test and would generate approximately 2096 Kg/s of steam to reduce pressure in the test cell and downstream of the engine. The testing at the A-3 Test Stand is projected to begin in late 2010, meanwhile the J-2X component testing on A-1 is scheduled to begin later this year.

SaintCyr, William W.; Tejwani, Gopal D.; McVay, Gregory P.; Langford, Lester A.; SaintCyr, William W.

2010-01-01

375

Full scale upper surface blown flap noise  

NASA Technical Reports Server (NTRS)

A highly noise suppressed TF 34 engine was used to investigate the noise of several powered lift configurations involving upper surface blown (USB) flaps. The configuration variables were nozzle type (i.e. slot and circular with deflector), flap chord length, and flap angle. The results of velocity surveys at both the nozzle exit and the flap trailing edge are also presented and used for correlation of the noise data. Configurations using a long flap design were 4 db quieter than a short flap typical of current trends in USB flap design. The lower noise for the long flap is attributed primarily to the greater velocity decay of the jet at the flap trailing edge. The full-scale data revealed substantially more quadrupole noise in the region near the deflected jet than observed in previous sub-scale tests.

Heidelberg, L. J.; Homyak, L.; Jones, W. L.

1975-01-01

376

Two stage catalytic combustor  

NASA Technical Reports Server (NTRS)

A catalytic combustor (14) includes a first catalytic stage (30), a second catalytic stage (40), and an oxidation completion stage (49). The first catalytic stage receives an oxidizer (e.g., 20) and a fuel (26) and discharges a partially oxidized fuel/oxidizer mixture (36). The second catalytic stage receives the partially oxidized fuel/oxidizer mixture and further oxidizes the mixture. The second catalytic stage may include a passageway (47) for conducting a bypass portion (46) of the mixture past a catalyst (e.g., 41) disposed therein. The second catalytic stage may have an outlet temperature elevated sufficiently to complete oxidation of the mixture without using a separate ignition source. The oxidation completion stage is disposed downstream of the second catalytic stage and may recombine the bypass portion with a catalyst exposed portion (48) of the mixture and complete oxidation of the mixture. The second catalytic stage may also include a reticulated foam support (50), a honeycomb support, a tube support or a plate support.

Alvin, Mary Anne (Inventor); Bachovchin, Dennis (Inventor); Smeltzer, Eugene E. (Inventor); Lippert, Thomas E. (Inventor); Bruck, Gerald J. (Inventor)

2010-01-01

377

Preparation of a biphasic scaffold for osteochondral tissue engineering  

Microsoft Academic Search

Tissue engineering has been developed as a prospective approach for the repair of articular cartilage defects. Engineered osteochondral implants can facilitate the fixation and integration with host tissue, and therefore promote the regeneration of osteochondral defects. A biphasic scaffold with a stratified two-layer structure for osteochondral tissue engineering was developed from biodegradable synthetic and naturally derived polymers. The upper layer

Guoping Chen; Takashi Sato; Junzo Tanaka; Tetsuya Tateishi

2006-01-01

378

History of staged combustion cycle development  

NASA Astrophysics Data System (ADS)

The search for ever greater delivered specific impulse led to an interest in very high chamber pressure operation, and with it, exploration of the staged combustion cycle as a means to extract the most energy possible from the chemical reactants. A major effort was supported by the Air Force with possible application to engines in the 1-2 million pound thrust class which used storable liquid propellants. These programs advanced the art by demonstrating the use of supercritical N2O4 as a coolant and introducing the photo etched platelet technique for manufacturing both injector and thrust chamber hardware. NASA initiated advanced engine design studies which identified the promise of high-pressure staged combustion and then accomplished subscale staged combustion testing at 2500 psia to demonstrate the feasibility of the combustion system. The Air Force also initiated efforts on high discharge pressure hydrogen pumps and on a high chamber pressure H2/O2 staged combustion engine concept which established the turbomachinery and cycle groundwork for the SSME.

Bumb, Anu; Hawk, Clark W.

1993-06-01

379

Muscles of the Upper Extremity  

MedlinePLUS

... Citation Help Home » Cancer Registration & Surveillance Modules » Anatomy & Physiology » Muscular System » Muscle Groups » Upper Extremity Cancer Registration & Surveillance Modules Anatomy & Physiology Intro to the Human Body Body Functions & Life ...

380

Leading Studies of the Staged Combustion Hybrid Rocket  

Microsoft Academic Search

The staged combustion hybrid rocket is under development by our research group since 1999. This hybrid rocket engine consists of two combustion chambers. The primary combustion chamber is the fuel tank itself filled with granular solid fuels. The fuel rich gas generated by the first stage combustion flows into the secondary combustion chamber, which is located in the bottom of

Ryojiro Akiba; Yoshinori Aoki; Seiyu Kayuta; Atushi Fujii; Harunori Nagata; Shin Satori

2003-01-01

381

Prosthetic rehabilitation of the upper limb amputee  

PubMed Central

The loss of all or part of the arm is a catastrophic event for a patient and a significant challenge to rehabilitation professionals and prosthetic engineers. The large, upper extremity amputee population in India has, historically, been poorly served, with most having no access to support or being provided with ineffective prostheses. In recent years, the arrival of organisations like Otto Bock has made high quality service standards and devices accessible to more amputees. This review attempts to provide surgeons and other medical professionals with an overview of the multidisciplinary, multistage rehabilitation process and the solution options available. With worldwide upper extremity prosthesis rejection rates at significant levels, the review also describes some of the factors which influence the outcome. This is particularly relevant in the Indian context where the service can involve high cost investments. It is the responsibility of all contributing professionals to guide vulnerable patients through the process and try to maximise the benefit that can be obtained within the resources available.

O'Keeffe, Bernard

2011-01-01

382

The control system for the X-33 linear aerospike engine  

Microsoft Academic Search

The linear aerospike engine is being developed for single-stage-to-orbit (SSTO) applications. The primary advantages of a linear aerospike engine over a conventional bell nozzle engine include altitude compensation, which provides enhanced performance, and lower vehicle weight resulting from the integration of the engine into the vehicle structure. A feature of this integration is the ability to provide thrust vector control

J. E. Jackson; E. Espenschied; J. Klop

1998-01-01

383

[Infrequent etiology of upper airway resistance syndrome].  

PubMed

We present the case of a thirty-eight years-old man bearing of frequent crisis of asphyxiating wakefulness and breathnessless whenever he was asleep. There also were excessive daytime sleepiness and a strong snore before every wakefulness, but not for the rest of sleep. A polysomnographic study revealed normal values in the oxygen desaturation index, minimum oxygen saturation, an sleep structure alteration with a decrease of III-IV stages, high arousals index and RDI < 5. Pharyngeal diameters measured by mean of TC were normal, but sleepiness degree detected in the Epworth scale was high. Nasal fiberoptic endoscopy study allowed to see a swinging epiglottis that closed totally the upper airway during forced inspiration. The lack of desaturation episodes with numerous wakefulness along the sleep and excessive daytime sleepiness drove to the diagnosis of upper airway resistance syndrome (UARS). Treatment whit C-PAP just provoked an impairment in symptoms, but a CO2-laser partial epiglottectomy improved them. Patophysiological aspects of UARS, as well as its follow-up and therapeutic alternatives are commented. PMID:12584886

Fernández Julián, E; Esparcia Navarro, M; García Callejo, F J; Orts, M H; Morant, A; Ferris, G; Marco, J

2002-11-01

384

Computer Engineers.  

ERIC Educational Resources Information Center

Looks at computer engineers and describes their job, employment outlook, earnings, and training and qualifications. Provides a list of resources related to computer engineering careers and the computer industry. (JOW)

Moncarz, Roger

2000-01-01

385

Biochemical Engineering.  

ERIC Educational Resources Information Center

Biochemical engineering as a scientific discipline is becoming accepted in England and is drawing many young men and women to its ranks. This article focuses on how engineering came to embrace the biological sciences. (Author/SA)

Dunnill, P.

1979-01-01

386

Search Engines  

Microsoft Academic Search

If you want to find anything on the World Wide Web (WWW), you need to know about search engines. Hitherto, both Internet sceptics and ‘technophobes’ have criticised the various search engines for having the same failings as the WWW itself: that the overall quality and relevance of sites are poor. After all, what search engines retrieve for you is merely

Rustam Al-Shahi

2001-01-01

387

Genome engineering  

Microsoft Academic Search

For more than 50 years, those engineering genetic material have pursued increasingly challenging targets. During that time, the tools and resources available to the genetic engineer have grown to encompass new extremes of both scale and precision, opening up new opportunities in genome engineering. Today, our capacity to generate larger de novo assemblies of DNA is increasing at a rapid

George M Church; Peter A Carr

2009-01-01

388

Systems Engineering  

Microsoft Academic Search

Each year at the National Council of Systems Engineering (NCOSE) symposium lots of dedicated people spend a lot of energy assessing, measuring and educating people about an incomplete body of knowledge (systems engineering). The incompleteness is due to the lack of a definition of what that body of knowledge is supposed to cover. Now every systems engineer knows that it

Joe Kasser

1969-01-01

389

"High Stage" Organizing.  

ERIC Educational Resources Information Center

Although a psychological theory of stages of transformation in human development currently exists, organizational researchers have yet to elaborate and test any theory of organizational transformation of comparable elegance. According to the organizational stage theory being developed since 1974 by William Torbert, bureaucratic organization, which…

Torbert, William R.

390

ARIES Kick Stage.  

National Technical Information Service (NTIS)

The kick stage was designed as a means of separating contamination-sensitive payloads from ARIES vehicles to allow experiments to be performed in a clean environment. The kick stage is a liquid rocket - essentially a shortened version of the proven Aerobe...

R. G. Starke

1977-01-01

391

Aries kick stage  

Microsoft Academic Search

The kick stage was designed as a means of separating contamination-sensitive payloads from ARIES vehicles to allow experiments to be performed in a clean environment. The kick stage is a liquid rocket essentially a shortened version of the proven Aerobee family.

R. G. Starke

1977-01-01

392

Efficiency bounds for nonequilibrium heat engines  

SciTech Connect

We analyze the efficiency of thermal engines (either quantum or classical) working with a single heat reservoir like an atmosphere. The engine first gets an energy intake, which can be done in an arbitrary nonequilibrium way e.g. combustion of fuel. Then the engine performs the work and returns to the initial state. We distinguish two general classes of engines where the working body first equilibrates within itself and then performs the work (ergodic engine) or when it performs the work before equilibrating (non-ergodic engine). We show that in both cases the second law of thermodynamics limits their efficiency. For ergodic engines we find a rigorous upper bound for the efficiency, which is strictly smaller than the equivalent Carnot efficiency. I.e. the Carnot efficiency can be never achieved in single reservoir heat engines. For non-ergodic engines the efficiency can be higher and can exceed the equilibrium Carnot bound. By extending the fundamental thermodynamic relation to nonequilibrium processes, we find a rigorous thermodynamic bound for the efficiency of both ergodic and non-ergodic engines and show that it is given by the relative entropy of the nonequilibrium and initial equilibrium distributions. These results suggest a new general strategy for designing more efficient engines. We illustrate our ideas by using simple examples. -- Highlights: ? Derived efficiency bounds for heat engines working with a single reservoir. ? Analyzed both ergodic and non-ergodic engines. ? Showed that non-ergodic engines can be more efficient. ? Extended fundamental thermodynamic relation to arbitrary nonequilibrium processes.

Mehta, Pankaj; Polkovnikov, Anatoli, E-mail: asp@bu.edu

2013-05-15

393

Engine Lubricant  

NASA Technical Reports Server (NTRS)

PS 212, a plasma-sprayed coating developed by NASA, is used to coat valves in a new rotorcam engine. The coating eliminates the need for a liquid lubricant in the rotorcam, which has no crankshaft, flywheel, distributor or water pump. Developed by Murray United Development Corporation, it is a rotary engine only 10 inches long with four cylinders radiating outward from a central axle. Company officials say the engine will be lighter, more compact and cheaper to manufacture than current engines and will feature cleaner exhaust emissions. A licensing arrangement with a manufacturer is under negotiation. Primary applications are for automobiles, but the engine may also be used in light aircraft.

1993-01-01

394

Aircraft Engines  

NSDL National Science Digital Library

Presented by Florida International University and NASA, this website presents a brief tutorial on the schematics for different car and aircraft engines, their cooling mechanisms, and engine development history. Here, visitors will find information on air-breathing, turboprop, turbofan, prop-fan, and ramjet engines along with handy and clear illustrations of each. This is a useful resource for educators looking for a brief, introductory handout for students in mechanical engineering and aeronautics or for students seeking material to simply illustrate the differences between engine types.

2007-07-16

395

Vulcain engine tests prove reliability  

NASA Astrophysics Data System (ADS)

The development of the oxygen/hydrogen Vulcain first-stage engine for the Ariane 5 involves more than 30 European companies and $1.19-billion. These companies are using existing technology to produce a low-cost system with high thrust and reliability. This article describes ground test of this engine, and provides a comparison of the Vulcain's capabilities with the capabilities of other systems. A list of key Vulcain team members is also given.

Covault, Craig

1994-04-01

396

Upper incisors' positions after extraction.  

PubMed

The aim of this research was to verify the amount of horizontal and vertical movement and incisor inclination of upper incisors and correlate these with Edgewise and Alexander brackets use and the presence of overbite during anterior retraction in sliding mechanics. The sample was composed of 40 adult patients divided into 2 groups, treated with Edgewise and Alexander brackets (20 each) subdivided in 2 groups (10 each), according to the presence or absence of deep bite. Treatment consisted of 4 extraction cases with sliding mechanics with the 2 different brackets. Pre- and post-treatment cephalograms were measured and the values of interest submitted to descriptive statistical analysis, ANOVA at 5%, the Tukey test and Pearson's correlation. Upper incisor retraction was not related to the brackets used nor to the presence of deep bite, though lingual tipping was greater when Edgewise brackets were used and deep bite was absent. No statistically significant differences in upper incisor vertical movements were observed and no correlation was determined between upper incisor intrusion and lower incisor labial tipping in overbite correction or in upper incisor retraction and lower incisor labial tipping for overjet correction. Bracket prescription and its interaction with deep bite were significant and Edgewise brackets without deep bite showed the worst inclination control. It was concluded that bracket prescriptions are important to increase control of sliding mechanics. PMID:24812742

Werneck, Eduardo César; Mattos, Fernanda Silva; Cotrim-Ferreira, Flávio Augusto; Prado, Renata Falchete; Silva, Márcio Garcia; Araújo, Adriano Marotta

2014-01-01

397

How Is Pancreatic Cancer Staged?  

MedlinePLUS

... Topic Pancreatic cancer survival by stage How is pancreatic cancer staged? The stage of a pancreatic cancer (extent ... M1: Distant metastasis is present. Stage grouping for pancreatic cancer After the T, N, and M categories of ...

398

Engineering Writing/Writing Engineering.  

ERIC Educational Resources Information Center

Examines the writings of an engineer employed by a large manufacturing firm. Argues that the engineer's writing, although not the final product, is the essential means by which the product is created. Suggests that, because a report reflects final, agreed-upon knowledge about a product, the product and the document become one in the engineer's…

Winsor, Dorothy A.

1990-01-01

399

High Head Unshrouded Impeller Pump Stage Technology  

NASA Technical Reports Server (NTRS)

Objective to develop an unshrouded impeller design, which a meets the performance requirements of a 3-stage fuel pump with a 2-stage pump design, has been accomplished. Performance of the baseline unshrouded impeller has been experimentally verified. Unshrouded impeller trade study and final 6+6 unshrouded impeller configuration has been presented. Structurally viable, 6+6-impeller design concept has been produced. Based on results presented in this study, at a nominal 10% tip-clearance, the 6+6 impeller design would increase payload to orbit by almost 625 lbs. per engine. The RLV vehicle requires 7 engines, therefore, application of high head unshrouded technology would increase payload capability by as much as 4,375 lbs. per vehicle.

Williams, Robert W.; Skelley, Stephen E.; Stewart, Eric T.; Droege, Alan R.; Prueger, George H.; Chen, Wei-Chung; Williams, Morgan; Turner, James E. (Technical Monitor)

2000-01-01

400

Uncommon upper extremity compression neuropathies.  

PubMed

Hand surgeons routinely treat carpal and cubital tunnel syndromes, which are the most common upper extremity nerve compression syndromes. However, more infrequent nerve compression syndromes of the upper extremity may be encountered. Because they are unusual, the diagnosis of these nerve compression syndromes is often missed or delayed. This article reviews the causes, proposed treatments, and surgical outcomes for syndromes involving compression of the posterior interosseous nerve, the superficial branch of the radial nerve, the ulnar nerve at the wrist, and the median nerve proximal to the wrist. PMID:23895725

Knutsen, Elisa J; Calfee, Ryan P

2013-08-01

401

Simulation of Upper Limb Movements  

NASA Astrophysics Data System (ADS)

The paper deals with controlling an upper limb prosthesis based on the measurement of myoelectric signals (MES) while drinking. MES signals have been measured on healthy limbs to obtain the same response for the prosthesis. To simulate the drinking motion of a healthy upper limb, the program ADAMS was used, with all degrees of freedom and a hand after trans-radial amputation with an existing hand prosthesis. Modification of the simulation has the exact same logic of control, where the muscle does not have to be strenuous all the time, but it is the impulse of the muscle which drives the motor even though the impulse disappears and passed away.

Uher?ík, Filip; Hu?ko, Branislav

2011-12-01

402

Fuzzy Upper Bounds in Groupoids  

PubMed Central

The notion of a fuzzy upper bound over a groupoid is introduced and some properties of it are investigated. We also define the notions of an either-or subset of a groupoid and a strong either-or subset of a groupoid and study some of their related properties. In particular, we consider fuzzy upper bounds in Bin(X), where Bin(X) is the collection of all groupoids. Finally, we define a fuzzy-d-subset of a groupoid and investigate some of its properties.

Ahn, Sun Shin; Kim, Young Hee; Neggers, J.

2014-01-01

403

Bioimpedance Spectroscopy in Detecting Lower-Extremity Lymphedema in Patients With Stage I, Stage II, Stage III, or Stage IV Vulvar Cancer Undergoing Surgery and Lymphadenectomy  

ClinicalTrials.gov

Lymphedema; Perioperative/Postoperative Complications; Stage IA Vulvar Cancer; Stage IB Vulvar Cancer; Stage II Vulvar Cancer; Stage IIIA Vulvar Cancer; Stage IIIB Vulvar Cancer; Stage IIIC Vulvar Cancer; Stage IVA Vulvar Cancer; Stage IVB Vulvar Cancer

2014-04-15

404

120. STAGE RECORDER WELLS & HOUSES HOUSE DETAILS (ML877/4FS) ...  

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

120. STAGE RECORDER WELLS & HOUSES - HOUSE DETAILS (ML-8-77/4-FS) August 1936 - Upper Mississippi River 9-Foot Channel, Lock & Dam No. 8, On Mississippi River near Houston County, MN, Genoa, Vernon County, WI

405

Bladder Exstrophy: Evaluation of Factors Leading to Continence With Spontaneous Voiding After Staged Reconstruction  

Microsoft Academic Search

PurposeWe performed a long-term retrospective review of patients with bladder exstrophy to evaluate the results of staged surgical reconstruction in regard to urinary continence, spontaneous voiding and preservation of the upper urinary tract.

H. B. Lottmann; Y. Melin; M. Cendron; P. Lombrail; P. Beze-Beyrie; J. Cendron

1997-01-01

406

Hybrid Upper Surface Blown Flap Propulsive-Lift Concept for the Quiet Short-Haul Research Aircraft.  

National Technical Information Service (NTIS)

The hybrid upper surface blowing concept consists of wing-mounted turbofan engines with a major portion of the fan exhaust directed over the wing upper surface to provide high levels of propulsive lift, but with a portion of the fan airflow directed over ...

J. A. Cochrane R. J. Carros

1975-01-01

407

DENTAL PULP TISSUE ENGINEERING  

PubMed Central

Dental pulp is a highly specialized mesenchymal tissue, which have a restrict regeneration capacity due to anatomical arrangement and post-mitotic nature of odontoblastic cells. Entire pulp amputation followed by pulp-space disinfection and filling with an artificial material cause loss of a significant amount of dentin leaving as life-lasting sequelae a non-vital and weakened tooth. However, regenerative endodontics is an emerging field of modern tissue engineering that demonstrated promising results using stem cells associated with scaffolds and responsive molecules. Thereby, this article will review the most recent endeavors to regenerate pulp tissue based on tissue engineering principles and providing insightful information to readers about the different aspects enrolled in tissue engineering. Here, we speculate that the search for the ideal combination of cells, scaffolds, and morphogenic factors for dental pulp tissue engineering may be extended over future years and result in significant advances in other areas of dental and craniofacial research. The finds collected in our review showed that we are now at a stage in which engineering a complex tissue, such as the dental pulp, is no longer an unachievable and the next decade will certainly be an exciting time for dental and craniofacial research.

Demarco, FF; Conde, MCM; Cavalcanti, B; Casagrande, L; Sakai, V; Nor, JE

2013-01-01

408

A high frequency cascade thermoacoustic engine  

Microsoft Academic Search

A miniature cascade thermoacoustic engine, which consisted of one standing-wave stage and one traveling-wave stage in series, was built and tested, which length was about 1.2m, operating at 470Hz using helium as working gas. The cascade modeling, the simulation and the primary experimental results are described in this paper. Four different configurations of the miniature cascade thermoacoustic engines had been

Zhong Jun Hu; Qing Li; Qiang Li; Zheng Yu Li

2006-01-01

409

Depositional environments of Pennsylvanian Upper Strawn Group in McCulloch and San Saba Counties, Texas  

SciTech Connect

Upper Strawn Group (Desmoinesean) represents a transition to fluvial facies from progradational deltaic facies. The lower part of the upper Strawn is composed mostly of horizontally bedded, fine-grained sandstones and shales of a distal delta-front origin. These sandstones and shales exhibit foreset bed dips of up to 15/sup 0/. In addition to the dipping foreset beds, the delta-front facies on occasion contain small listric normal faults, resulting from periodic higher rates of sedimentation. The middle parts of the upper Strawn consist predominantly of massive, fine to medium-grained, mature sandstones which represent distributary-mouth-bar deposits, as well as other proximal delta-front deposits such as distributary channels. The upper part of the upper Strawn consists of fluvial trough cross-bedded sandstones and chert-pebble conglomerates. These overlie the deltaic facies and indicate the final stages of upper Strawn deposition. The upper Strawn is overlain by the Adams Branch limestone and shales which represent marine transgression and subsequent shallow-marine deposition. The upper Strawn Group in McCulloch and San Saba Counties, Texas, represents continued filling of the Fort Worth basin during Desmoinesean time. The upper Strawn overlies the lower Strawn, an older, deeper water facies, in most parts of the study area. The upper Strawn overlies the Atokan age Marble Falls Limestone in an isolated section of the study area due to its position there on the Concho arch.

Jamieson, W.H. Jr.

1983-03-01

410

Engineer Girl!  

NSDL National Science Digital Library

Operated by the National Academy of Engineering, Engineer Girl is a Web site that increases awareness of the opportunities that exist in this profession for women and girls. There is a lot of material covered on the site that will give anyone a good understanding of what engineering is and why it is important. Information about the many different disciplines within engineering are explained in such a way as to spark interest in girls. Tips that will help girls orient their education toward engineering are also included, like what classes to take, how to prepare for college, and how to get scholarships. Some links to other useful Internet resources are scattered around the site, as well as some interesting facts about women and engineering.

2001-01-01

411

Invisible Engineers  

NASA Astrophysics Data System (ADS)

Questionnaire to ask “mention three names of scientists you know” and “three names of engineers you know” was conducted and the answers from 140 adults were analyzed. The results indicated that the image of scientists is represented by Nobel laureates and that of engineers by great inventors like Thomas Edison and industry founders like Soichiro Honda. In order to reveal the image of engineers among young generation, questionnaire was conducted for pupils in middle and high schools. Answers from 1,230 pupils were analyzed and 226 names mentioned as engineers were classified. White votes reached 60%. Engineers who are neither big inventors nor company founders collected less than 1% of named votes. Engineers are astonishingly invisible from young generation. Countermeasures are proposed.

Ohashi, Hideo

412

Try Engineering  

NSDL National Science Digital Library

Admittedly, Dilbert and his fellow engineers haven't boosted the image of the engineering profession, but the website "TryEngineering" succeeds at making engineering seem a little cooler. Visitors will note that the site is sponsored by IBM, IEEE, and TryScience, and it provides information for parents, students, teachers and counselors. The "Lesson Plans" link "provides tips on how lessons can be integrated with other subject areas and offers background information on engineering and engineering careers." Visitors can search the lesson plans by age range, category or keyword, and there are over 100, so there is bound to be more than one that is of interest. Some of the lessons include "Can You Canoe?", "A Century of Plastics", and "Build Your Own Robot Arm". The "Play Games" link offers visitors such fun as "Solar Car Racing", "Roller Coaster Designer" and "Design a Parachute".

413

Teaching Engineering  

NSDL National Science Digital Library

Purdue University has one of the strongest schools of engineering in the United States, and they remain committed to providing new and interesting materials about the art and science of teaching engineering to their students. Professors Phillip C. Wankat and Frank S. Oreovicz recently created this very helpful textbook to aid engineering educators in the classroom, and it is exciting to see that it is available online here for free. Visitors can download the entire book, or they can just browse around through some of the seventeen chapters. These chapters include "Problem Solving and Creativity", "Lectures", and "Learning Theories". Additionally, there are several helpful appendices, such as "Obtaining an Academic Position" and "Sample Teaching Course Outline". Overall, it's an exemplary resource, and one that will be most useful to engineering educators. These materials can be used in a variety of engineering courses, including those that deal with chemical and mechanical engineering.

414

Adoption and Developmental Stages  

MedlinePLUS

... Parents How to Adopt Laws Related to Adoption Parenting After Adoption Preplacement Adoption Casework Practice Postplacement Adoption ... Statistics Systems of Care Stay Connected Home » Adoption » Parenting After Adoption » Adoption and Developmental Stages Adoption and ...

415

Staging Airliner Service  

NASA Technical Reports Server (NTRS)

There is a general consensus building that historically high fuel prices and greater public awareness of the emissions that result from burning fuel are going to be long-term concerns for those who design, build, and operate airliners. The possibility of saving both fuel and reducing emissions has rekindled interest in breaking very long-range airline flights into multiple stages or even adopting in-flight refueling. It is likely that staging will result in lower fuel burn, and recent published reports have suggested that the savings are substantial, particularly if the airliner is designed from the outset for this kind of operation. Given that staging runs against the design and operation historical trend, this result begs for further attention. This paper will examine the staging question, examining both analytic and numeric performance estimation methodologies to quantify the likely amount of fuel savings that can be expected and the resulting design impacts on the airliner.

Hahn, Andrew S.

2007-01-01

416

Cervical Cancer Stage IVA  

MedlinePLUS

... Home About My Pictures Browse Search Quick Search Image Details Cervical Cancer Stage IVA View/Download: Small: ... Added: 4/23/2012 Reuse Restrictions: Yes - This image is copyright protected. Any use of this image ...

417

Cervical Cancer Stage IVB  

MedlinePLUS

... Home About My Pictures Browse Search Quick Search Image Details Cervical Cancer Stage IVB View/Download: Small: ... Added: 4/23/2012 Reuse Restrictions: Yes - This image is copyright protected. Any use of this image ...

418

Cervical Cancer Stage IIIB  

MedlinePLUS

... Home About My Pictures Browse Search Quick Search Image Details Cervical Cancer Stage IIIB View/Download: Small: ... Added: 4/23/2012 Reuse Restrictions: Yes - This image is copyright protected. Any use of this image ...

419

Cervical Cancer Stage IB  

MedlinePLUS

... Home About My Pictures Browse Search Quick Search Image Details Cervical Cancer Stage IB View/Download: Small: ... Added: 4/23/2012 Reuse Restrictions: Yes - This image is copyright protected. Any use of this image ...

420

Cervical Cancer Stage IIIA  

MedlinePLUS

... Home About My Pictures Browse Search Quick Search Image Details Cervical Cancer Stage IIIA View/Download: Small: ... Added: 4/23/2012 Reuse Restrictions: Yes - This image is copyright protected. Any use of this image ...

421

Cervical Cancer Stage IA  

MedlinePLUS

... Home About My Pictures Browse Search Quick Search Image Details Cervical Cancer Stage IA View/Download: Small: ... Added: 4/23/2012 Reuse Restrictions: Yes - This image is copyright protected. Any use of this image ...

422

How Is Rhabdomyosarcoma Staged?  

MedlinePLUS

Early Detection, Diagnosis, and Staging TOPICS Document Topics GO » SEE A LIST » Can rhabdomyosarcoma be found early? How is ... About 1 out of 3 children with RMS fall into the low-risk group. It includes: Children ...

423

Life Stages Cards  

NSDL National Science Digital Library

All animals develop and grow over time. The animals in this document undergo one of the most dramatic developmental processes known: metamorphosis. See if you can place the developmental stages in their proper order.

Foundation, Wgbh E.

2003-09-26

424

Engine combustion chamber structure  

SciTech Connect

This patent describes a combustion chamber structure comprising an upper wall surface which is shaped like a pent-roof and into which an intake passage opens, a piston having on a head portion thereof a bulged portion conforming to the upper wall surface in shape, a first bowl portion which is formed substantially at the center of the bulged portion and which is substantially semispherical in shape, a pair of second bowl portions which respectively extend on opposite sides of the first bowl portion to the corresponding ends of the bulged portion of the piston along the edge of the bulged portion and are in communication with the first bowl portion, a swirl generating means which is adapted to generate a swirl of intake air in the combustion chamber when the engine load is light, and a spark plug disposed to substantially face the center of the first bowl portion from the upper wall surface; the swirl generating means being adapted to generate the swirl of intake air in a tangential direction in the combustion chamber; and the diameter of the first bowl portion being larger than the width of the second bowl portion.

Tanaka, H.

1988-09-13

425

Staging Bipolar Disorder  

Microsoft Academic Search

The purpose of this study was to analyze the evidence supporting a staging model for bipolar disorder. The authors conducted\\u000a an extensive Medline and Pubmed search of the published literature using a variety of search terms (staging, bipolar disorder,\\u000a early intervention) to find relevant articles, which were reviewed in detail. Only recently specific proposals have been made\\u000a to apply clinical

Eduard Vieta; M. Reinares; A. R. Rosa

2011-01-01

426

Clinical Staging: Endoscopic Techniques  

Microsoft Academic Search

\\u000a Patients with locally advanced rectal cancer benefit from neoadjuvant chemoradiation therapy followed by either a sphincter-sparing\\u000a operation or abdominoperineal resection. Clinical decisions regarding neoadjuvant therapy and type of surgical approach rely\\u000a on accurate preoperative staging. Computed tomography, magnetic resonance imaging, and endorectal ultrasound (ERUS) are the\\u000a main modalities used for staging rectal cancer. While each has its own advantages and

Hueylan Chern; W. Douglas Wong

427

Engineering Bridges  

NSDL National Science Digital Library

The overarching goal of this planning grant is for Rice University engineering faculty, TSU education faculty, and HISD teachers, counselors, and administrators to develop a comprehensive program designed to systemically change science, technology, engineering, and mathematics (STEM) instruction and culture in high-minority high schools in order to increase the number of underrepresented minority students that are excited, motivated, and well-prepared to enter engineering university majors and to complete those majors to graduation.