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Sample records for upper stage engine

  1. Upper Stage Engine Composite Nozzle Extensions

    NASA Technical Reports Server (NTRS)

    Valentine, Peter G.; Allen, Lee R.; Gradl, Paul R.; Greene, Sandra E.; Sullivan, Brian J.; Weller, Leslie J.; Koenig, John R.; Cuneo, Jacques C.; Thompson, James; Brown, Aaron; Shigley, John K.; Dovey, Henry N.; Roberts, Robert K.

    2015-01-01

    Carbon-carbon (C-C) composite nozzle extensions are of interest for use on a variety of launch vehicle upper stage engines and in-space propulsion systems. The C-C nozzle extension technology and test capabilities being developed are intended to support National Aeronautics and Space Administration (NASA) and United States Air Force (USAF) requirements, as well as broader industry needs. Recent and on-going efforts at the Marshall Space Flight Center (MSFC) are aimed at both (a) further developing the technology and databases for nozzle extensions fabricated from specific CC materials, and (b) developing and demonstrating low-cost capabilities for testing composite nozzle extensions. At present, materials development work is concentrating on developing a database for lyocell-based C-C that can be used for upper stage engine nozzle extension design, modeling, and analysis efforts. Lyocell-based C-C behaves in a manner similar to rayon-based CC, but does not have the environmental issues associated with the use of rayon. Future work will also further investigate technology and database gaps and needs for more-established polyacrylonitrile- (PAN-) based C-C's. As a low-cost means of being able to rapidly test and screen nozzle extension materials and structures, MSFC has recently established and demonstrated a test rig at MSFC's Test Stand (TS) 115 for testing subscale nozzle extensions with 3.5-inch inside diameters at the attachment plane. Test durations of up to 120 seconds have been demonstrated using oxygen/hydrogen propellants. Other propellant combinations, including the use of hydrocarbon fuels, can be used if desired. Another test capability being developed will allow the testing of larger nozzle extensions (13.5- inch inside diameters at the attachment plane) in environments more similar to those of actual oxygen/hydrogen upper stage engines. Two C-C nozzle extensions (one lyocell-based, one PAN-based) have been fabricated for testing with the larger-scale facility.

  2. Ares I Upper Stage Subscale Engine Test

    NASA Technical Reports Server (NTRS)

    2007-01-01

    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. The launch vehicle's first stage is a single, five-segment reusable solid rocket booster derived from the Space Shuttle Program's reusable solid rocket motor that burns a specially formulated and shaped solid propellant called polybutadiene acrylonitrile (PBAN). The second or upper stage will be propelled by a J-2X main engine fueled with liquid oxygen and liquid hydrogen. This HD video image depicts a test firing of a 40k subscale J2X injector at MSFC's test stand 115. (Highest resolution available)

  3. Ares I Crew Launch Vehicle Upper Stage/Upper Stage Engine Element Overview

    NASA Technical Reports Server (NTRS)

    McArthur, J. Craig

    2008-01-01

    The Ares I upper stage is an integral part of the Constellation Program transportation system. The upper stage provides guidance, navigation and control (GN and C) for the second stage of ascent flight for the Ares I vehicle. The Saturn-derived J-2X upper stage engine will provide thrust and propulsive impulse for the second stage of ascent flight for the Ares I launch vehicle. Additionally, the upper stage is responsible for the avionics system of the the entire Ares I. This brief presentation highlights the requirements, design, progress and production of the upper stage. Additionally, test facilities to support J-2X development are discussed and an overview of the operational and manufacturing flows are provided. Building on the heritage of the Apollo and Space Shuttle Programs, the Ares I Us and USE teams are utilizing extensive lessons learned to place NASA and the US into another era of space exploration. The NASA, Boeing and PWR teams are integrated and working together to make progress designing and building the Ares I upper stage to minimize cost, technical and schedule risks.

  4. Testing for the J-2X Upper Stage Engine

    NASA Technical Reports Server (NTRS)

    Buzzell, James C.

    2010-01-01

    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.

  5. Solar Thermal Upper Stage Cryogen System Engineering Checkout Test

    NASA Technical Reports Server (NTRS)

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

    1999-01-01

    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.

  6. Low-speed inducers for cryogenic upper-stage engines

    NASA Technical Reports Server (NTRS)

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

    1975-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

    Kynard, Mike

    2010-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

    Dorney, Daniel J.; Rothermel, Jeffry; Griffin, Lisa W.; Thornton, Randall J.; Forbes, John C.; Skelly, Stephen E.; Huber, Frank W.

    2006-01-01

    As part of the development of technologies for rocket engines that will power spacecraft to the Moon and Mars, a program was initiated to develop a conceptual upper stage engine with wide flow range capability. The resulting expander cycle engine design employs a radial turbine to allow higher pump speeds and efficiencies. In this paper, the design and analysis of the pump section of the engine are discussed. One-dimensional meanline analyses and three-dimensional unsteady computational fluid dynamics simulations were performed for the pump stage. Configurations with both vaneless and vaned diffusers were investigated. Both the meanline analysis and computational predictions show that the pump will meet the performance objectives. Additional details describing the development of a water flow facility test are also presented.

  9. Upper Stage Flight Experiment 10K Engine Design and Test Results

    NASA Technical Reports Server (NTRS)

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

    2000-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

    Byrd, THomas

    2008-01-01

    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.

  11. Overview of the Development Progress of the Ariane 5 Upper Stage VINCI Engine

    NASA Astrophysics Data System (ADS)

    Alliot, P.; Dalbies, E.

    2002-01-01

    The purpose of this paper is to present the major results of the VINCI engine development program at mid-2002. The VINCI engine will power the Ariane 5 ESC-B upper stage and will contribute to provide a 12 t payload capability in geo-stationary transfer orbit to the Ariane 5 launch system. It will also provide a multiple firing capability and therefore the potential to perform a broad array of missions. The VINCI engine is a cryogenic expander cycle engine combining the required features of this cycle, i.e. high performance chamber cooling and high performance hydrogen turbopump, with proven design concepts based on the accumulated experience from previous European cryogenic engines such as the HM7 and the Vulcain. High performance along with a constant focus on reliability, low cost and simplicity of architecture are the design goals of the VINCI program. The proposed paper will recall how the engine design choices were made taking into account these sometimes potentially conflicting criteria and using design to cost methods. The paper will also present the major achievements of the program over the 2001 - 2002 period, i.e. the completion of the engine detailed design, the manufacturing of the first subsystems, the first component and subsystem tests.

  12. Upper stage technology evaluation studies

    NASA Technical Reports Server (NTRS)

    1972-01-01

    Studies to evaluate advanced technology relative to chemical upper stages and orbit-to-orbit stages are reported. The work described includes: development of LH2/LOX stage data, development of data to indicate stage sensitivity to engine tolerance, modified thermal routines to accommodate storable propellants, added stage geometries to computer program for monopropellant configurations, determination of the relative gain obtainable through improvement of stage mass fraction, future propulsion concepts, effect of ultrahigh chamber-pressure increases, and relative gains obtainable through improved mass fraction.

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

    NASA Technical Reports Server (NTRS)

    Zachary, A. T.

    1973-01-01

    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.

  14. A 20k Payload Launch Vehicle Fast Track Development Concept Using an RD-180 Engine and a Centaur Upper Stage

    NASA Technical Reports Server (NTRS)

    Toelle, Ronald (compiler)

    1995-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

    Byrd, Thomas

    2010-01-01

    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 s exploration of deep space. The Constellation Program is developing the launch vehicles, spacecraft, surface systems, and ground systems to support those plans. Two launch vehicles will support those ambitious plans the Ares I and Ares V. (Figure 1) The J-2X Upper Stage Engine is a critical element of both of these new launchers. This paper will provide an overview of the J-2X design background, progress to date in design, testing, and manufacturing. The Ares I crew launch vehicle will lift the Orion crew exploration vehicle and up to four astronauts into low Earth orbit (LEO) to rendezvous with the space station or the first leg of mission to the Moon. The Ares V cargo launch vehicle is designed to lift a lunar lander into Earth orbit where it will be docked with the Orion spacecraft, and provide the thrust for the trans-lunar journey. While these vehicles bear some visual resemblance to the 1960s-era Saturn vehicles that carried astronauts to the Moon, the Ares vehicles are designed to carry more crew and more cargo to more places to carry out more ambitious tasks than the vehicles they succeed. The government/industry team designing the Ares rockets is mining a rich history of technology and expertise from the Shuttle, Saturn and other programs and seeking commonality where feasible between the Ares crew and cargo rockets as a way to minimize risk, shorten development times, and live within the budget constraints of its original guidance.

  16. CRYOGENIC UPPER STAGE SYSTEM SAFETY

    NASA Technical Reports Server (NTRS)

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

    2005-01-01

    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.

  17. Design and Development of the Turbopump for Cryogenic Upper-Stage Engine LE-5

    NASA Astrophysics Data System (ADS)

    Aoki, Hiroshi; Shimura, Takashi; Warashina, Shogo; Kamijo, Kenjiro

    The first flight of H-I launch vehicle was performed successfully on August 13 (1986). Her second stage was powered by the cryogenic engine LE-5 driven by turbopump systems, developed in Japan, for the first time. Later, requirement for turbopump’s flow-rate was increased as 40% to apply for the next generation launch vehicle, but fundamental turbopump configuration was not changed. In 19 flights data of LE-5s (including derivatives), no trouble caused by turbopumps is recorded. This paper reports research and development aspects of the turbopump systems of the LE-5 engine family.

  18. Ares I Upper Stage Element

    NASA Technical Reports Server (NTRS)

    Chojnacki, Kent

    2009-01-01

    This slide presentation reviews the elements that make up the Ares I launch vehicle, with particular attention devoted to the upper stage of the vehicle. The upper stage elememnts, a lunar mission profile, and the upper stage objectives are reviewed. The work that Marshall Space Flight Center is doing is highlighted: work on the full scale welding process, the vertical milling machining, and the thermal protection system.

  19. Upper-Stage Flight Experiment

    NASA Technical Reports Server (NTRS)

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

    1999-01-01

    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.

  20. Ares I Upper Stage Update

    NASA Technical Reports Server (NTRS)

    Davis, Daniel J.

    2010-01-01

    These presentation slides review the progress in the development of the Ares I upper stage. The development includes development of a manufacturing and processing assembly that will reduce the time required over 100 days, development of a weld tool that is a robotic tool that is the largest welder of its kind in the United States, development of avionics and software, and development of logisitics and operations systems.

  1. Ares I Upper Stage Fabrication

    NASA Technical Reports Server (NTRS)

    2006-01-01

    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. (Highest resolution available)

  2. Ares I Upper Stage Fabrication

    NASA Technical Reports Server (NTRS)

    2007-01-01

    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)

  3. Ares I Upper Stage Fabrication

    NASA Technical Reports Server (NTRS)

    2007-01-01

    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 confidence testing of a manufactured aluminum panel that will fabricate the Ares I upper stage barrel. In this test, 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)

  4. Ares I Upper Stage Fabrication

    NASA Technical Reports Server (NTRS)

    2007-01-01

    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 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. (Highest resolution available)

  5. Ares I Upper Stage Fabrication

    NASA Technical Reports Server (NTRS)

    2006-01-01

    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)

  6. Ares I Upper Stage Fabrication

    NASA Technical Reports Server (NTRS)

    2007-01-01

    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.

  7. Ares I Upper Stage Fabrication

    NASA Technical Reports Server (NTRS)

    2007-01-01

    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)

  8. ARES I Upper Stage Fabrication

    NASA Technical Reports Server (NTRS)

    2007-01-01

    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. 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. (Largest resolution available)

  9. Ares I Upper Stage Fabrication

    NASA Technical Reports Server (NTRS)

    2007-01-01

    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. (Highest resolution available)

  10. Ares I Upper Stage Fabrication

    NASA Technical Reports Server (NTRS)

    2006-01-01

    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 fabricate the Ares I upper stage barrel, undergoing a confidence panel test. In this test, 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)

  11. Space Launch System Upper Stage Technology Assessment

    NASA Technical Reports Server (NTRS)

    Holladay, Jon; Hampton, Bryan; Monk, Timothy

    2014-01-01

    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.

  12. Ares I Upper Stage Fabrication

    NASA Technical Reports Server (NTRS)

    2007-01-01

    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 manufacturing of aluminum panels that will be used to form the Ares I barrel. The 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)

  13. Electric Propulsion Upper-Stage for Launch Vehicle Capability Enhancement

    NASA Technical Reports Server (NTRS)

    Kemp, Gregory E.; Dankanich, John W.; Woodcock, Gordon R.; Wingo, Dennis R.

    2007-01-01

    The NASA In-Space Propulsion Technology Project Office initiated a preliminary study to evaluate the performance benefits of a solar electric propulsion (SEP) upper-stage with existing and near-term small launch vehicles. The analysis included circular and elliptical Low Earth Orbit (LEO) to Geosynchronous Earth Orbit (GEO) transfers, and LEO to Low Lunar Orbit (LLO) applications. SEP subsystem options included state-of-the-art and near-term solar arrays and electric thrusters. In-depth evaluations of the Aerojet BPT-4000 Hall thruster and NEXT gridded ion engine were conducted to compare performance, cost and revenue potential. Preliminary results indicate that Hall thruster technology is favored for low-cost, low power SEP stages, while gridded-ion engines are favored for higher power SEP systems unfettered by transfer time constraints. A low-cost point design is presented that details one possible stage configuration and outlines system limitations, in particular fairing volume constraints. The results demonstrate mission enhancements to large and medium class launch vehicles, and mission enabling performance when SEP system upper stages are mounted to low-cost launchers such as the Minotaur and Falcon 1. Study results indicate the potential use of SEP upper stages to double GEO payload mass capability and to possibly enable launch on demand capability for GEO assets. Transition from government to commercial applications, with associated cost/benefit analysis, has also been assessed. The sensitivity of system performance to specific impulse, array power, thruster size, and component costs are also discussed.

  14. Integrated Solar Upper Stage (ISUS) mission analysis

    NASA Astrophysics Data System (ADS)

    Frye, Patrick

    1997-01-01

    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.

  15. ARES I Upper Stage Subsystems Design and Development

    NASA Technical Reports Server (NTRS)

    Frate, David T.; Senick, Paul F.; Tolbert, Carol M.

    2011-01-01

    From 2005 through early 2011, NASA conducted concept definition, design, and development of the Ares I launch vehicle. The Ares I was conceived to serve as a crew launch vehicle for beyond-low-Earth-orbit human space exploration missions as part of the Constellation Program Architecture. The vehicle was configured with a single shuttle-derived solid rocket booster first stage and a new liquid oxygen/liquid hydrogen upper stage, propelled by a single, newly developed J-2X engine. The Orion Crew Exploration Vehicle was to be mated to the forward end of the Ares I upper stage through an interface with fairings and a payload adapter. The vehicle design passed a Preliminary Design Review in August 2008, and was nearing the Critical Design Review when efforts were concluded as a result of the Constellation Program s cancellation. At NASA Glenn Research Center, four subsystems were developed for the Ares I upper stage. These were thrust vector control (TVC) for the J-2X, electrical power system (EPS), purge and hazardous gas (P&HG), and development flight instrumentation (DFI). The teams working each of these subsystems achieved 80 percent or greater design completion and extensive development testing. These efforts were extremely successful representing state-of-the-art technology and hardware advances necessary to achieve Ares I reliability, safety, availability, and performance requirements. This paper documents the designs, development test activity, and results.

  16. Integrated Solar Upper Stage Technical Support

    NASA Technical Reports Server (NTRS)

    Jaworske, Donald A.

    1998-01-01

    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.

  17. Ares I Crew Launch Vehicle Upper Stage Element Overview

    NASA Technical Reports Server (NTRS)

    McArthur, J. Craig

    2008-01-01

    This viewgraph presentation gives an overview of NASA's Ares I Crew Launch Vehicle Upper Stage Element. The topics include: 1) What is NASA s Mission?; 2) NASA s Exploration Roadmap What is our time line?; 3) Building on a Foundation of Proven Technologies Launch Vehicle Comparisons; 4) Ares I Upper Stage; 5) Upper Stage Primary Products; 6) Ares I Upper Stage Development Approach; 7) What progress have we made?; 8) Upper Stage Subsystem Highlights; 9) Structural Testing; 10) Common Bulkhead Processing; 11) Stage Installation at Stennis Space Center; 12) Boeing Producibility Team; 13) Upper Stage Low Cost Strategy; 14) Ares I and V Production at Michoud Assembly Facility (MAF); 15) Merged Manufacturing Flow; and 16) Manufacturing and Assembly Weld Tools.

  18. Upper Stage Tank Thermodynamic Modeling Using SINDA/FLUINT

    NASA Technical Reports Server (NTRS)

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

    2006-01-01

    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.

  19. Camera Layout Design for the Upper Stage Thrust Cone

    NASA Technical Reports Server (NTRS)

    Wooten, Tevin; Fowler, Bart

    2010-01-01

    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.

  20. NASA Ares I Crew Launch Vehicle Upper Stage Overview

    NASA Technical Reports Server (NTRS)

    McArthur, J. Craig

    2008-01-01

    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.

  1. NASA Ares I Crew Launch Vehicle Upper Stage Overview

    NASA Technical Reports Server (NTRS)

    Davis, Daniel J.

    2008-01-01

    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 1-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.

  2. Ares I-X Upper Stage Simulator Residual Stress Analysis

    NASA Technical Reports Server (NTRS)

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

    2008-01-01

    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.

  3. Upper stages using liquid propulsion and metallized propellants

    NASA Technical Reports Server (NTRS)

    Palaszewski, Bryan A.

    1992-01-01

    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.

  4. 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)

    Wingard, Doug

    2013-01-01

    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.

  5. 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)

    Wingard, Doug

    2013-01-01

    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.

  6. Ares I Upper Stage Parachute Drop Test

    NASA Technical Reports Server (NTRS)

    2006-01-01

    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, the first stage reentry parachute drop test is conducted at the Yuma, Arizona proving ground. The parachute tests demonstrated a three-stage deployment sequence that included the use of an Orbiter drag chute to properly stage the unfurling of the main chute. The parachute recovery system for Orion will be similar to the system used for Apollo command module landings and include two drogue, three pilot, and three main parachutes. (Highest resolution available)

  7. Ares I Upper Stage Parachute Drop Test

    NASA Technical Reports Server (NTRS)

    2007-01-01

    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, the first stage reentry parachute drop test is conducted at the Yuma, Arizona proving ground. The parachute tests demonstrated a three-stage deployment sequence that included the use of an Orbiter drag chute to properly stage the unfurling of the main chute. The parachute recovery system for Orion will be similar to the system used for Apollo command module landings and include two drogue, three pilot, and three main parachutes. (Highest resolution available)

  8. Staged combustion with piston engine and turbine engine supercharger

    DOEpatents

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

    2011-11-01

    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.

  9. Staged combustion with piston engine and turbine engine supercharger

    DOEpatents

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

    2006-05-09

    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.

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

    NASA Technical Reports Server (NTRS)

    1974-01-01

    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.

  11. Low Cost Upper Stage-Class Propulsion (LCUSP)

    NASA Technical Reports Server (NTRS)

    Vickers, John

    2015-01-01

    NASA is making space exploration more affordable and viable by developing and utilizing innovative manufacturing technologies. Technology development efforts at NASA in propulsion are committed to continuous innovation of design and manufacturing technologies for rocket engines in order to reduce the cost of NASA's journey to Mars. The Low Cost Upper Stage-Class Propulsion (LCUSP) effort will develop and utilize emerging Additive Manufacturing (AM) to significantly reduce the development time and cost for complex rocket propulsion hardware. Benefit of Additive Manufacturing (3-D Printing) Current rocket propulsion manufacturing techniques are costly and have lengthy development times. In order to fabricate rocket engines, numerous complex parts made of different materials are assembled in a way that allow the propellant to collect heat at the right places to drive the turbopump and simultaneously keep the thrust chamber from melting. The heat conditioned fuel and oxidizer come together and burn inside the combustion chamber to provide thrust. The efforts to make multiple parts precisely fit together and not leak after experiencing cryogenic temperatures on one-side and combustion temperatures on the other is quite challenging. Additive manufacturing has the potential to significantly reduce the time and cost of making rocket parts like the copper liner and Nickel-alloy jackets found in rocket combustion chambers where super-cold cryogenic propellants are heated and mixed to the extreme temperatures needed to propel rockets in space. The Selective Laser Melting (SLM) machine fuses 8,255 layers of copper powder to make a section of the chamber in 10 days. Machining an equivalent part and assembling it with welding and brazing techniques could take months to accomplish with potential failures or leaks that could require fixes. The design process is also enhanced since it does not require the 3D model to be converted to 2-D drawings. The design and fabrication process can be sped up and improved with fewer errors to be accomplished in weeks instead of months.

  12. Additive Manufacturing of Low Cost Upper Stage Propulsion Components

    NASA Technical Reports Server (NTRS)

    Protz, Christopher; Bowman, Randy; Cooper, Ken; Fikes, John; Taminger, Karen; Wright, Belinda

    2014-01-01

    NASA is currently developing Additive Manufacturing (AM) technologies and design tools aimed at reducing the costs and manufacturing time of regeneratively cooled rocket engine components. These Low Cost Upper Stage Propulsion (LCUSP) tasks are funded through NASA's Game Changing Development Program in the Space Technology Mission Directorate. The LCUSP project will develop a copper alloy additive manufacturing design process and develop and optimize the Electron Beam Freeform Fabrication (EBF3) manufacturing process to direct deposit a nickel alloy structural jacket and manifolds onto an SLM manufactured GRCop chamber and Ni-alloy nozzle. In order to develop these processes, the project will characterize both the microstructural and mechanical properties of the SLMproduced GRCop-84, and will explore and document novel design techniques specific to AM combustion devices components. These manufacturing technologies will be used to build a 25K-class regenerative chamber and nozzle (to be used with tested DMLS injectors) that will be tested individually and as a system in hot fire tests to demonstrate the applicability of the technologies. These tasks are expected to bring costs and manufacturing time down as spacecraft propulsion systems typically comprise more than 70% of the total vehicle cost and account for a significant portion of the development schedule. Additionally, high pressure/high temperature combustion chambers and nozzles must be regeneratively cooled to survive their operating environment, causing their design to be time consuming and costly to build. LCUSP presents an opportunity to develop and demonstrate a process that can infuse these technologies into industry, build competition, and drive down costs of future engines.

  13. Orbit decay analysis of STS upper stage boosters

    NASA Technical Reports Server (NTRS)

    Graf, O. F., Jr.; Mueller, A. C.

    1979-01-01

    An orbit decay analysis of the space transportation system upper stage boosters is presented. An overview of the computer trajectory programs, DSTROB, algorithm is presented. Atmospheric drag and perturbation models are described. The development of launch windows, such that the transfer orbit will decay within two years, is discussed. A study of the lifetimes of geosynchronous transfer orbits is presented.

  14. Staged direct injection diesel engine

    DOEpatents

    Baker, Quentin A. (San Antonio, TX)

    1985-01-01

    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.

  15. Comparative evaluation of existing expendable upper stages for space shuttle

    NASA Technical Reports Server (NTRS)

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

    1974-01-01

    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.

  16. Propellant Management in Booster and Upper Stage Propulsion Systems

    NASA Technical Reports Server (NTRS)

    Fisher, Mark F.

    1997-01-01

    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.

  17. Mission applications of an Integrated Solar Upper Stage (ISUS)

    SciTech Connect

    Kennedy, F.G. III; Jacox, M.G.

    1995-12-31

    The Integrated Solar Upper Stage (ISUS) Program at the US Air Force`s Phillips Laboratory is directing its efforts to solving endemic national spacelift architecture problems. Air Force Space Command has called spacelift both unaffordable and nonresponsive; today`s space launch systems are descendants of 1950`s era ICBM technologies and require prolonged on-pad processing. Advanced propulsion techniques, reusability, and modular architectures have not been generally incorporated into US systems. The ISUS system is an advanced, integrated upper stage concept that would permit payload realignment, allowing large payloads to be moved to smaller, less expensive boosters; such realignment both reduces cost and enhances responsiveness, as smaller boosters cost less to launch and require less vehicle and payload processing time. Three ISUS operational concepts are discussed, allowing the realignment of payloads currently launched aboard Titan IV/Centaur, Atlas IIAS, and Delta 2. A space demonstration of ISUS is examined. The Integrated Solar Upper Stage is a single piece of hardware that provides electric power and orbit transfer propulsion to a spacecraft. There are three major subsystems that comprise the ISUS; the receiver/absorber/converter or RAC, the concentrators, and the hydrogen tankage and feed subsystem.

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

    SciTech Connect

    Metzger, John D.

    1998-01-15

    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.

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

    NASA Astrophysics Data System (ADS)

    Metzger, John D.

    1998-01-01

    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.

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

    NASA Astrophysics Data System (ADS)

    Mueller, Mark

    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.

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

    NASA Technical Reports Server (NTRS)

    Bhat, Biliyar N.

    2008-01-01

    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.

  2. Electrodynamic Tether Propulsion for Spacecraft and Upper Stages

    NASA Technical Reports Server (NTRS)

    Johnson, Les; Gilchrist, Brian; Estes, Robert D.; Lorenzini, Rnrico; Martinez-Sanchez, Manuel; Sanmartin, Juan

    1998-01-01

    Relatively short electrodynamic tethers can use solar power to 'push' against a planetary magnetic field to achieve propulsion without the expenditure of propellant. The groundwork has been laid for this type of propulsion. Important recent milestones include retrieval of a tether in space (TSS-1, 1992), successful deployment of a 20-km-long tether in space (SEDS-1, 1993), and operation of an electrodynamic tether with tether current driven in both directions (PMG, 1993). The planned Propulsive Small Expendable Deployer System (ProSEDS) experiment will use the flight-proven Small Expendable Deployer System (SEDS) to deploy a 5 km bare copper tether from a Delta II upper stage to achieve approximately 0.4 N drag thrust, thus deorbiting the stage. The experiment will use a predominantly 'bare' tether for current collection in lieu of the endmass collector and insulated tether approach used on previous missions. The flight experiment is a precursor to utilization of the technology on the International Space Station for reboost and the electrodynamic tether upper stage demonstration mission which will be capable of orbit raising, lowering and inclination changes, all using electrodynamic thrust. In addition, the use of this type of propulsion may be attractive for future missions at Jupiter.

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

    NASA Technical Reports Server (NTRS)

    Aggarwal, Pravin

    2007-01-01

    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.

  4. Optimization, an Important Stage of Engineering Design

    ERIC Educational Resources Information Center

    Kelley, Todd R.

    2010-01-01

    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…

  5. Solar thermal upper stage: Economic advantage and development status

    NASA Technical Reports Server (NTRS)

    Adams, Alan M.

    1995-01-01

    A solar thermal upper stage (STUS) is envisioned as a propulsive concept for the future. The STUS will be used for low Earth orbit (LEO) to geostationary-Earth orbit (GEO) transfer and for planetary exploration missions. The STUS offers significant performance gains over conventional chemical propulsion systems. These performance gains translate into a more economical, more efficient method of placing useful payloads in space and maximizing the benefits derived from space activity. This paper will discuss the economical advantages of an STUS compared to conventional chemical propulsion systems, the potential market for an STUS, and the recent activity in the development of an STUS. The results of this assessment combined with the performance gains, will provide a strong justification for the development of an STUS.

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

    SciTech Connect

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

    1997-01-01

    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.}

  7. Stir Friction Welding Used in Ares I Upper Stage Fabrication

    NASA Technical Reports Server (NTRS)

    2007-01-01

    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)

  8. Stir Friction Welding Used in Ares I Upper Stage Fabrication

    NASA Technical Reports Server (NTRS)

    2007-01-01

    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)

  9. Stir Friction Welding Used in Ares I Upper Stage Fabrication

    NASA Technical Reports Server (NTRS)

    2007-01-01

    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)

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

    NASA Technical Reports Server (NTRS)

    Anderson, Joel M.

    2011-01-01

    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.

  11. Seal Analysis for the Ares-I Upper Stage Fuel Tank Manhole Covers

    NASA Technical Reports Server (NTRS)

    Phillips, Dawn R.; Wingate, Robert J.

    2010-01-01

    Naflex seals have long history of use in launch vehicle components, including Saturn stages and Space Shuttle External Tank. Ares-I Upper Stage tank pressures are higher than ET pressures, requiring performance verification of heritage seal design in new manhole cover configurations. Heritage external tank analyses are reviewed for potential application to Upper Stage.

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

    NASA Technical Reports Server (NTRS)

    Williams, J. Hunter; Holt, Kimberly A.

    2010-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

    Wilson, S. W.

    1980-01-01

    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.

  14. NASA Ares I Crew Launch Vehicle Upper Stage Avionics and Software Overview

    NASA Technical Reports Server (NTRS)

    Nola, Charles L.; Blue, Lisa

    2008-01-01

    Building on the heritage of the Saturn and Space Shuttle Programs for the Design, Development, Test, and Evaluation (DDT and E) of avionics and software for NASA's Ares I Crew Launch Vehicle (CLV), the Ares I Upper Stage Element is a vital part of the Constellation Program's transportation system. The Upper Stage Element's Avionics Subsystem is actively proceeding toward its objective of delivering a flight-certified Upper Stage Avionics System for the Ares I CLV.

  15. Ares I Crew Launch Vehicle Upper Stage Avionics and Software Overview

    NASA Technical Reports Server (NTRS)

    Nola, Charles L.

    2008-01-01

    This viewgraph presentation gives an overall description of the avionics and software functions of the Ares I Upper Stage Crew Launch Vehicle. The contents include: 1) IUA Team - Development Approach Roadmap; 2) Ares I US Avionics and Software Development Approach; 3) NDT Responsibilities; 4) Ares I Upper Stage Avionics Locations; 5) Ares I Overall Avionics & Software Functions; 6) Block Diagram Version of Avionics Architecture; 7) Instrument Unit Avionics Preliminary Design; and 8) Upper Stage Avionics External Interfaces.

  16. Preventing Accidental Ignition of Upper-Stage Rocket Motors

    NASA Technical Reports Server (NTRS)

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

    2005-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

    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

    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.

  18. 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

  19. 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

  20. Reflections on Centaur Upper Stage Integration by the NASA Lewis (Glenn) Research Center

    NASA Technical Reports Server (NTRS)

    Graham, Scott R.

    2014-01-01

    The NASA Glenn (then Lewis) Research Center (GRC) led several expendable launch vehicle (ELV) projects from 1963 to 1998, most notably the Centaur upper stage. These major, comprehensive projects included system management, system development, integration (both payload and stage), and launch operations. The integration role that GRC pioneered was truly unique and highly successful. Its philosophy, scope, and content were not just invaluable to the missions and vehicles it supported, but also had significant Agencywide benefits. An overview of the NASA Lewis Research Center (now the NASA Glenn Research Center) philosophy on ELV integration is provided, focusing on Atlas/Centaur, Titan/Centaur, and Shuttle/Centaur vehicles and programs. The necessity of having a stable, highly technically competent in-house staff is discussed. Significant depth of technical penetration of contractor work is another critical component. Functioning as a cohesive team was more than a concept: GRC senior management, NASA Headquarters, contractors, payload users, and all staff worked together. The scope, content, and history of launch vehicle integration at GRC are broadly discussed. Payload integration is compared to stage development integration in terms of engineering and organization. Finally, the transition from buying launch vehicles to buying launch services is discussed, and thoughts on future possibilities of employing the successful GRC experience in integrating ELV systems like Centaur are explored.

  1. Reflections on Centaur Upper Stage Integration by the NASA Lewis (Glenn) Research Center

    NASA Technical Reports Server (NTRS)

    Graham, Scott R.

    2015-01-01

    The NASA Glenn (then Lewis) Research Center (GRC) led several expendable launch vehicle (ELV) projects from 1963 to 1998, most notably the Centaur upper stage. These major, comprehensive projects included system management, system development, integration (both payload and stage), and launch operations. The integration role that GRC pioneered was truly unique and highly successful. Its philosophy, scope, and content were not just invaluable to the missions and vehicles it supported, but also had significant Agency-wide benefits. An overview of the NASA Lewis Research Center (now the NASA Glenn Research Center) philosophy on ELV integration is provided, focusing on Atlas/Centaur, Titan/Centaur, and Shuttle/Centaur vehicles and programs. The necessity of having a stable, highly technically competent in-house staff is discussed. Significant depth of technical penetration of contractor work is another critical component. Functioning as a cohesive team was more than a concept: GRC senior management, NASA Headquarters, contractors, payload users, and all staff worked together. The scope, content, and history of launch vehicle integration at GRC are broadly discussed. Payload integration is compared to stage development integration in terms of engineering and organization. Finally, the transition from buying launch vehicles to buying launch services is discussed, and thoughts on future possibilities of employing the successful GRC experience in integrating ELV systems like Centaur are explored.

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

    NASA Technical Reports Server (NTRS)

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

    2010-01-01

    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

  3. Seal Analysis for the Ares-I Upper Stage Fuel Tank Manhole Cover

    NASA Technical Reports Server (NTRS)

    Phillips, Dawn R.; Wingate, Robert J.

    2010-01-01

    Techniques for studying the performance of Naflex pressure-assisted seals in the Ares-I Upper Stage liquid hydrogen tank manhole cover seal joint are explored. To assess the feasibility of using the identical seal design for the Upper Stage as was used for the Space Shuttle External Tank manhole covers, a preliminary seal deflection analysis using the ABAQUS commercial finite element software is employed. The ABAQUS analyses are performed using three-dimensional symmetric wedge finite element models. This analysis technique is validated by first modeling a heritage External Tank liquid hydrogen tank manhole cover joint and correlating the results to heritage test data. Once the technique is validated, the Upper Stage configuration is modeled. The Upper Stage analyses are performed at 1.4 times the expected pressure to comply with the Constellation Program factor of safety requirement on joint separation. Results from the analyses performed with the External Tank and Upper Stage models demonstrate the effects of several modeling assumptions on the seal deflection. The analyses for Upper Stage show that the integrity of the seal is successfully maintained.

  4. Ares I Upper Stage Pressure Tests in Wind Tunnel

    NASA Technical Reports Server (NTRS)

    2007-01-01

    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, the first stage reentry 1/2% model is undergoing pressure measurements inside the wind tunnel testing facility at MSFC. (Highest resolution available)

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

    NASA Technical Reports Server (NTRS)

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

    2012-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

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

    2003-01-01

    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.

  7. NASA Ares 1 Crew Launch Vehicle Upper Stage Configuration Selection Process

    NASA Technical Reports Server (NTRS)

    Cook, Jerry R.

    2006-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

    Hammes, Steven M.

    1990-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

    Mitchell, Michael S.; Winner, David R.

    2010-01-01

    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.

  10. Simulink Model of the Ares I Upper Stage Main Propulsion System

    NASA Technical Reports Server (NTRS)

    Burchett, Bradley T.

    2008-01-01

    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.

  11. 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

  12. 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

  13. Mass-driver reaction engine as Shuttle upper-stage

    NASA Technical Reports Server (NTRS)

    Oneill, G. K.

    1977-01-01

    Optimization has been carried out on the design of a mass-driver intended for upgrading the Shuttle to geosynchronous and lunar-orbit capability. The machine accelerates 2,100 tons/yr of external tankage, in 14-gram segments, to exhaust velocities of 8,000-10,000 m/s. The resulting reaction force raises 1,700 tons/yr. of Shuttle payloads to high orbit, in two round trips. Exhaust velocity and thrust can be optimized for each mission segment. For a mission requiring an exhaust velocity of 8,000 m/sec, thrust is 560 newtons, power is 2.9 megawatts, and efficiency is 75%. Total electrical component mass including power supplies and waste-heat radiators is 89 tons. To insure that reaction mass does not constitute a hazard, segments may be in the form of powder, electrostatically dispersed after acceleration, and/or thrust may be vectored.

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

    NASA Technical Reports Server (NTRS)

    Scott, David W.

    2009-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

    Scott, David W.

    2009-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

    Borowski, Stanley K.

    1995-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

    Williams, Jonathan H.

    2010-01-01

    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.

  18. Stage-by-Stage and Parallel Flow Path Compressor Modeling for a Variable Cycle Engine

    NASA Technical Reports Server (NTRS)

    Kopasakis, George; Connolly, Joseph W.; Cheng, Larry

    2015-01-01

    This paper covers the development of stage-by-stage and parallel flow path compressor modeling approaches for a Variable Cycle Engine. The stage-by-stage compressor modeling approach is an extension of a technique for lumped volume dynamics and performance characteristic modeling. It was developed to improve the accuracy of axial compressor dynamics over lumped volume dynamics modeling. The stage-by-stage compressor model presented here is formulated into a parallel flow path model that includes both axial and rotational dynamics. This is done to enable the study of compressor and propulsion system dynamic performance under flow distortion conditions. The approaches utilized here are generic and should be applicable for the modeling of any axial flow compressor design.

  19. Preburner of Staged Combustion Rocket Engine

    NASA Technical Reports Server (NTRS)

    Yost, M. C.

    1978-01-01

    A regeneratively cooled LOX/hydrogen staged combustion assembly system with a 400:1 expansion area ratio nozzle utilizing an 89,000 Newton (20,000 pound) thrust regeneratively cooled thrust chamber and 175:1 tubular nozzle was analyzed, assembled, and tested. The components for this assembly include two spark/torch oxygen-hydrogen igniters, two servo-controlled LOX valves, a preburner injector, a preburner combustor, a main propellant injector, a regeneratively cooled combustion chamber, a regeneratively cooled tubular nozzle with an expansion area ratio of 175:1, an uncooled heavy-wall steel nozzle with an expansion area ratio of 400:1, and interconnecting ducting. The analytical effort was performed to optimize the thermal and structural characteristics of each of the new components and the ducting, and to reverify the capabilities of the previously fabricated components. The testing effort provided a demonstration of the preburner/combustor chamber operation, chamber combustion efficiency and stability, and chamber and nozzle heat transfer.

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

    NASA Technical Reports Server (NTRS)

    Seiler, James; Brasfield, Fred; Cannon, Scott

    2008-01-01

    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.

  1. Characterization of the 2012-044c Briz-M Upper Stage Breakup

    NASA Technical Reports Server (NTRS)

    Matney, M. J.; Hamilton, Joseph; Papanyan, Valen

    2013-01-01

    On 6 August, 2012, Russia launched two commercial satellites aboard a Proton rocket, and attempted to place them in geosynchronous orbit using a Briz-M upper stage (2012-044C, SSN 38746). Unfortunately, the upper stage failed early in its burn and was left stranded in an elliptical orbit with a perigee in low Earth orbit (LEO). Because the stage failed with much of its fuel on board, it was deemed a significant breakup risk. These fears were confirmed when it broke up 16 October, creating a large cloud of debris with perigees below that of the International Space Station. The debris cloud was tracked by the US Space Surveillance Network (SSN), which can reliably detect and track objects down to about 10 cm in size. Because of the unusual geometry of the breakup, there was an opportunity for NASA Orbital Debris Program Office to request radar assets to characterize the extent of the debris cloud in sizes smaller than the standard debris tracked by the SSN. This paper will describe the observation campaign to measure the small particle distributions of this cloud, and presents the results of the analysis of the data. We shall compare the data to the modelled size distribution, number, and shape of the cloud, and what implications this may have for future breakup debris models. We shall conclude the paper with a discussion how this measurement process can be improved for future breakups.

  2. Characterization of the 2012-044C Briz-M Upper Stage Breakup

    NASA Technical Reports Server (NTRS)

    Matney, M. J.; Hamilton, J.; Horstman, M.; Papanyan, V.

    2013-01-01

    On 6 August, 2012, Russia launched two commercial satellites aboard a Proton rocket, and attempted to place them in geosynchronous orbit using a Briz-M upper stage (2012-044C, SSN 38746). Unfortunately, the upper stage failed early in its burn and was left stranded in an elliptical orbit with a perigee in low Earth orbit (LEO). Because the stage failed with much of its fuel on board, it was deemed a significant breakup risk. These fears were confirmed when it broke up 16 October, creating a large cloud of debris with perigees below that of the International Space Station. The debris cloud was tracked by the US Space Surveillance Network (SSN), which can reliably detect and track objects down to about 10 cm in size. Because of the unusual geometry of the breakup, there was an opportunity for NASA Orbital Debris Program Office to use specialized radar assets to characterize the extent of the debris cloud in sizes smaller than the standard debris tracked by the SSN. This paper will describe the observation campaign to measure the small particle distributions of this cloud, and presents the results of the analysis of the data. We shall compare the data to the modelled size distribution, number, and shape of the cloud, and what implications this may have for future breakup debris models. We shall conclude the paper with a discussion how this measurement process can be improved for future breakups.

  3. Characterization of the 2012-044C BRIZ-M Upper Stage Breakup

    NASA Astrophysics Data System (ADS)

    Matney, M. J.; Hamilton, J.; Horstman, M.; Papanyan, V.

    2013-08-01

    On 6 August 2012, Russia launched two commercial satellites aboard a Proton rocket, and attempted to place them in geosynchronous orbit using a Briz-M upper stage (2012-044C, SSN 38746). Unfortunately, the upper stage failed early in its burn and was left stranded in an elliptical orbit with a perigee in low Earth orbit (LEO). Because the stage failed with much of its fuel on board, it was deemed a significant breakup risk. These fears were confirmed when it broke up 16 October, creating a large cloud of debris with perigees below that of the International Space Station. The debris cloud was tracked by the U.S. Space Surveillance Network (SSN), which can reliably detect and track objects down to about 10 cm in size. Because of the unusual geometry of the breakup, there was an opportunity for the NASA Orbital Debris Program Office to use specialized radar assets to characterize the extent of the debris cloud in sizes smaller than the standard debris tracked by the SSN. This paper describes the observation campaign to measure the small particle distributions of this cloud and presents the results of the data analysis. We shall compare the data to the modelled size distribution, number, and shape of the cloud, and what implications this may have for future breakup debris models. We shall conclude the paper with a discussion about how this measurement process can be improved for future breakups.

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

    USGS Publications Warehouse

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

    1983-01-01

    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.

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

    PubMed Central

    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

    2014-01-01

    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

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

    NASA Technical Reports Server (NTRS)

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

    2011-01-01

    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.

  7. A common solar electric upper stage for multi-mission applications.

    NASA Technical Reports Server (NTRS)

    Meissinger, H. F.; Goldin, D. S.; Mascy, A. C.

    1972-01-01

    The concept of using a solar-electric upper stage for multi-mission application is practical, economical, and versatile approach to space expMission capabilities include a Mercury orbiter, asteroid and comet rendezvous, a solar probe, and extra-ecliptic probe, and outer planet flybys and orbiters. The 17.5-kw vehicle has an injected mass of 1500 to 2500 kg and carries up to 500 kg of attached or separable payload packages. Mission characteristics, performance tradeoffs and a concepegn configuration are presented, and program plans, cost estimates and advanced technology requirements are identified.

  8. Operations analysis (study 2.1): Shuttle upper stage software requirements

    NASA Technical Reports Server (NTRS)

    Wolfe, R. R.

    1974-01-01

    An investigation of software costs related to space shuttle upper stage operations with emphasis on the additional costs attributable to space servicing was conducted. The questions and problem areas include the following: (1) the key parameters involved with software costs; (2) historical data for extrapolation of future costs; (3) elements of the basic software development effort that are applicable to servicing functions; (4) effect of multiple servicing on complexity of the operation; and (5) are recurring software costs significant. The results address these questions and provide a foundation for estimating software costs based on the costs of similar programs and a series of empirical factors.

  9. A palynological biozonation for the Maastrichtian Stage (Upper Cretaceous) of South Carolina, USA

    USGS Publications Warehouse

    Christopher, R.A.; Prowell, D.C.

    2002-01-01

    Three palynological biozones are proposed for the Maastrichtian Stage of South Carolina. In ascending stratigraphic order, the biozones are the Carolinapollis triangularis (Ct) Interval Biozone, the Holkopollenites chemardensis (Hc) Interval Biozone, and the Sparganiaceaepollenites uniformis (Su) Interval Biozone. Integration of the biostratigraphy with lithologic and geophysical log data suggests that within the study area, the upper and lower boundaries of each zone are bounded by regional unconformities, and that a three-fold subdivision of the Maastrichtian Stage is warranted. The biozonation is based on the analysis of 114 samples from 24 subsurface and three outcrop sections from the Coastal Plain of South Carolina; samples from an additional seven subsurface and 18 outcrop sections from North Carolina and Georgia were examined to evaluate the geographic extent of the biozones. One new genus and five new species of pollen are described, and emendations are presented for two genera and one species of pollen. ?? 2003 Published by Elsevier Science Ltd.

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

    NASA Technical Reports Server (NTRS)

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

    2012-01-01

    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.

  11. APOLLO 5 SATURN-APOLLO 204 LAUNCH VEHICLE UPPER STAGE IS ERECTED AT LAUNCH COMPLEX 37B

    NASA Technical Reports Server (NTRS)

    1967-01-01

    The Douglas-built upper stage for the Saturn-Apollo 204/Lunar Module space vehicle was erected today at Cape Kennedy's Launch Complex 37. The two-stage rocket will send an unmanned lunar module into Earth orbit later this year.

  12. Dinoflagellates: Fossil motile-stage tests from the upper cretaceous of the Northern New Jersey coastal plain

    USGS Publications Warehouse

    May, F.E.

    1976-01-01

    Fossil dinoflagellate tests have been considered to represent encysted, nonmotile stages. The discovery of flagellar porelike structures and probable trichocyst pores in the Upper Cretaceous genus Dinogymnium suggests that motile stage tests are also preserved as acid-resistant, organic-walled microfossils.

  13. Distribution of early life history stages of fishes in selected pools of the upper Mississippi River

    USGS Publications Warehouse

    Holland, L.E.

    1986-01-01

    Effective management of the fishery resources of the Upper Mississippi River and successful mitigation of the loss of critical habitat depend in part on an understanding of the reproductive and early life history requirements of the affected fishes. However, little is known about the use of nursery areas by fishes in the river. Of the nearly 130 species identified in the adult ichthyofauna, only a few are represented proportionally in the available data on early life stages because study designs have not included consideration of the early stages, collection gears have not adequately sampled the young, and eggs and larvae of some species are difficult to sample by conventional approaches. For the species collected, information is available on seasonal variations in total densities, composition, and catch among different habitat types. However, the data are most accurate for species with buoyant early life stages, such as freshwater drum (Aplodinotus grunniens) and gizzard shad (Dorosoma cepedianum). Eggs and larvae of freshwater drum dominate collections made in the main channel, whereas other larval fishes are usually most abundant in backwater habitats. The species found there usually deposit eggs on the substrate or on vegetation. Habitat preferences (as indicated by relative abundance) often shift as development proceeds and physical and behavioral changes occur in the larvae. Only limited information is available on the distribution of larvae within habitats, but it is clear that variations within habitats are significant.

  14. Massive upper gastrointestinal bleeding originating from a fourth-stage duodenal diverticulum: a case report and review of the literature

    PubMed Central

    Rioux, Louis; Groseilliers, Sylvain Des; Fortin, Michel; Mutch, David O.

    1996-01-01

    Duodenal diverticulum is well-known pathologic entity. Most such diverticula are asymptomatic and located on the second stage of the duodenum. The diagnosis is most often established by endoscopy or upper gastrointestinal radiography. Hemorrhage has been described but is an infrequent complication. We report on a patient who presented with massive upper gastrointestinal bleeding, originating from a fourth-stage duodenal diverticulum. The diagnosis was made with a combination of arteriography and scanning with technetium 99-labelled red cells. Diverticulectomy was performed with a successful outcome. This report underlines the diagnostic limits of fiberoptic endoscopy for hemorrhagic lesions located past the third stage of the duodenum. PMID:8956821

  15. 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)

    Kromis, Phillip A.

    2010-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

    1975-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

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

    2011-01-01

    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.

  18. A palynological biozonation for the uppermost Santonian and Campanian Stages (Upper Cretaceous) of South Carolina, USA

    USGS Publications Warehouse

    Christopher, R.A.; Prowell, D.C.

    2010-01-01

    Five palynological biozones are proposed for the uppermost Santonian and Campanian Stages of South Carolina. In ascending stratigraphic order, these highest-occurrence interval zones are the Osculapollis vestibulus (Ov) Biozone, the Holkopollenites propinquus (Hp) Biozone, the Holkopollenites forix (Hf) Biozone, the Complexiopollis abditus (Ca) Biozone, and the Osculapollis aequalis (Oa) Biozone. These biozones are based on an analysis of more than 400 subsurface and outcrop samples throughout the Coastal Plain Province of South Carolina, and the adjacent states of Georgia and North Carolina. Integration of the biostratigraphy with lithostratigraphy and geophysical log data suggests that the lower and upper boundaries of each biozone are bounded by regional unconformities. Five new species are described, and an emendation is presented for one additional species. ?? 2009 Elsevier Ltd.

  19. Attitude Dynamics of Debris Resulting From Upper Stage Fragmentation in Low Earth Orbit

    NASA Astrophysics Data System (ADS)

    Marie, Killian

    This thesis addresses the analysis of the attitude dynamics of pieces of space debris that could result from the fragmentation of a spent upper stage in low Earth orbit (LEO). Up to now only whole objects of axisymmetric shape have been studied with the purpose of estimating their tumbling rates in LEO. Three shapes have been considered to be representative for the purpose of the study: a thin plate, a monocoque shell, an half conical shell and a spherical shell, and it has been assumed that they are fabricated from aluminum alloy. The motion of conducting body in a magnetic field generates eddy currents which create a torque in the opposite direction of the change in the magnetic flux and thus reduce the rotational rate of the body. The eddy currents that generate torques are described by Maxwell's equations. and the generalized Ohm's law is set up a Poisson problem with Neumann boundary conditions. The electrical potential, solution of Poisson problem and calculated by a finite element solver, defines the density current in the body and thus determines the torque applied on the debris. The results presented here can be used for the analysis of the initial propagation of a cloud of orbital debris resulting from the explosion of an upper stage or a satellite as well as for orbital debris remediation. Analysis of the attitude dynamics of space debris shows that, for a reasonable initial angular rate, the object is partially stabilized in less than 70 days for the thin plate and totally stabilized in less than 60 days for the monocoque shell, 12 days for the half conical shell, 30 days for an one fourth spherical shell and 90 days an one eighth spherical shell.

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

    NASA Technical Reports Server (NTRS)

    Dawson, Virginia P.; Bowles, Mark D.

    2004-01-01

    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.

  1. Seal Joint Analysis and Design for the Ares-I Upper Stage LOX Tank

    NASA Technical Reports Server (NTRS)

    Phillips, Dawn R.; Wingate, Robert J.

    2011-01-01

    The sealing capability of the Ares-I Upper Stage liquid oxygen tank-to-sump joint is assessed by analyzing the deflections of the joint components. Analyses are performed using three-dimensional symmetric wedge finite element models and the ABAQUS commercial finite element software. For the pressure loads and feedline interface loads, the analyses employ a mixed factor of safety approach to comply with the Constellation Program factor of safety requirements. Naflex pressure-assisted seals are considered first because they have been used successfully in similar seal joints in the Space Shuttle External Tank. For the baseline sump seal joint configuration with a Naflex seal, the predicted joint opening greatly exceeds the seal design specification. Three redesign options of the joint that maintain the use of a Naflex seal are studied. The joint openings for the redesigned seal joints show improvement over the baseline configuration; however, these joint openings still exceed the seal design specification. RACO pressure-assisted seals are considered next because they are known to also be used on the Space Shuttle External Tank, and the joint opening allowable is much larger than the specification for the Naflex seals. The finite element models for the RACO seal analyses are created by modifying the models that were used for the Naflex seal analyses. The analyses show that the RACO seal may provide sufficient sealing capability for the sump seal joint. The results provide reasonable data to recommend the design change and plan a testing program to determine the capability of RACO seals in the Ares-I Upper Stage liquid oxygen tank sump seal joint.

  2. Epistaxis in end stage liver disease masquerading as severe upper gastrointestinal hemorrhage

    PubMed Central

    Camus, Marine; Jensen, Dennis M; Matthews, Jason D; Ohning, Gordon V; Kovacs, Thomas O; Jutabha, Rome; Ghassemi, Kevin A; Machicado, Gustavo A; Dulai, Gareth S

    2014-01-01

    AIM: To describe the prevalence, diagnosis, treatment, and outcomes of end stage liver disease (ESLD) patients with severe epistaxis thought to be severe upper gastrointestinal hemorrhage (UGIH). METHODS: This observational single center study included all consecutive patients with ESLD and epistaxis identified from consecutive subjects hospitalized with suspected UGIH and prospectively enrolled in our databases of severe UGIH between 1998 and 2011. RESULTS: A total of 1249 patients were registered for severe UGIH in the data basis, 461 (36.9%) were cirrhotics. Epistaxis rather than UGIH was the bleeding source in 20 patients. All patients had severe coagulopathy. Epistaxis was initially controlled in all cases. Fifteen (75%) subjects required posterior nasal packing and 2 (10%) embolization in addition to correction of coagulopathy. Five (25%) patients died in the hospital, 12 (60%) received orthotopic liver transplantation (OLT), and 3 (15%) were discharged without OLT. The mortality rate was 63% in patients without OLT. CONCLUSION: Severe epistaxis in patients with ESLD is (1) a diagnosis of exclusion that requires upper endoscopy to exclude severe UGIH; and (2) associated with a high mortality rate in patients not receiving OLT. PMID:25320538

  3. Computed Tomography-Guided Tissue Engineering of Upper Airway Cartilage

    PubMed Central

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

    2014-01-01

    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

  4. Ares I-X Upper Stage Simulator Structural Analyses Supporting the NESC Critical Initial Flaw Size Assessment

    NASA Technical Reports Server (NTRS)

    Knight, Norman F., Jr.; Phillips, Dawn R.; Raju, Ivatury S.

    2008-01-01

    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. The structural analysis effort for the NESC assessment had three thrusts: shell buckling analyses, detailed stress analyses of the single-bolt joint test; and stress analyses of two-segment 10 degree-wedge models for the peak axial tensile running load. Elasto-plastic, large-deformation simulations were performed. Stress analysis results indicated that the stress levels were well below the material yield stress for the bounding axial tensile design load. This report also summarizes the analyses and results from parametric studies on modeling the shell-to-gusset weld, flange-surface mismatch, bolt preload, and washer-bearing-surface modeling. These analyses models were used to generate the stress levels specified for the fatigue crack growth assessment using the design load with a factor of safety.

  5. Performance of the Spacecraft Propulsion Research Facility During Altitude Firing Tests of the Delta 3 Upper Stage

    NASA Technical Reports Server (NTRS)

    Meyer, Michael L.; Dickens, Kevin W.; Skaff, Tony F.; Cmar, Mark D.; VanMeter, Matthew J.; Haberbusch, Mark S.

    1998-01-01

    The Spacecraft Propulsion Research Facility at the NASA Lewis Research Center's Plum Brook Station was reactivated in order to conduct flight simulation ground tests of the Delta 3 cryogenic upper stage. The tests were a cooperative effort between The Boeing Company, Pratt and Whitney, and NASA. They included demonstration of tanking and detanking of liquid hydrogen, liquid oxygen and helium pressurant gas as well as 12 engine firings simulating first, second, and third burns at altitude conditions. A key to the success of these tests was the performance of the primary facility systems and their interfaces with the vehicle. These systems included the structural support of the vehicle, propellant supplies, data acquisition, facility control systems, and the altitude exhaust system. While the facility connections to the vehicle umbilical panel simulated the performance of the launch pad systems, additional purge and electrical connections were also required which were unique to ground testing of the vehicle. The altitude exhaust system permitted an approximate simulation of the boost-phase pressure profile by rapidly pumping the test chamber from 13 psia to 0.5 psia as well as maintaining altitude conditions during extended steady-state firings. The performance of the steam driven ejector exhaust system has been correlated with variations in cooling water temperature during these tests. This correlation and comparisons to limited data available from Centaur tests conducted in the facility from 1969-1971 provided insight into optimizing the operation of the exhaust system for future tests. Overall, the facility proved to be robust and flexible for vehicle space simulation engine firings and enabled all test objectives to be successfully completed within the planned schedule.

  6. 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)

    Lyles, Garry; Otte, Neil E.

    2008-01-01

    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.

  7. Axially staged combustion system for a gas turbine engine

    DOEpatents

    Bland, Robert J. (Oviedo, FL)

    2009-12-15

    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.

  8. Two-stage ignition and NTC phenomenon in diesel engines Xiao Fu, Suresh K. Aggarwal

    E-print Network

    Aggarwal, Suresh K.

    Two-stage ignition and NTC phenomenon in diesel engines Xiao Fu, Suresh K. Aggarwal Department-fuel diesel engine characterized. a r t i c l e i n f o Article history: Received 20 August 2014 Received-stage ignition NTC phenomenon Diesel spray Dual-fuel engine a b s t r a c t Two-stage ignition and NTC phenomenon

  9. Three Orbital Burns to Molniya Orbit Via Shuttle_Centaur G Upper Stage

    NASA Technical Reports Server (NTRS)

    Williams, Craig H.

    2015-01-01

    An unclassified analytical trajectory design, performance, and mission study was done for the 1982 to 1986 joint National Aeronautics and Space Administration (NASA)-United States Air Force (USAF) Shuttle/Centaur G upper stage development program to send performance-demanding payloads to high orbits such as Molniya using an unconventional orbit transfer. This optimized three orbital burn transfer to Molniya orbit was compared to the then-baselined two burn transfer. The results of the three dimensional trajectory optimization performed include powered phase steering data and coast phase orbital element data. Time derivatives of the orbital elements as functions of thrust components were evaluated and used to explain the optimization's solution. Vehicle performance as a function of parking orbit inclination was given. Performance and orbital element data was provided for launch windows as functions of launch time. Ground track data was given for all burns and coasts including variation within the launch window. It was found that a Centaur with fully loaded propellant tanks could be flown from a 37 deg inclination low Earth parking orbit and achieve Molniya orbit with comparable performance to the baselined transfer which started from a 57 deg inclined orbit: 9,545 versus 9,552 lb of separated spacecraft weight, respectively. There was a significant reduction in the need for propellant launch time reserve for a 1 hr window: only 78 lb for the three burn transfer versus 320 lb for the two burn transfer. Conversely, this also meant that longer launch windows over more orbital revolutions could be done for the same amount of propellant reserve. There was no practical difference in ground tracking station or airborne assets needed to secure telemetric data, even though the geometric locations of the burns varied considerably. There was a significant adverse increase in total mission elapsed time for the three versus two burn transfer (12 vs. 1-1/4 hr), but could be accommodated by modest modifications to Centaur systems. Future applications were discussed. The three burn transfer was found to be a viable, arguably preferable, alternative to the two burn transfer.

  10. Three Orbital Burns to Molniya Orbit via Shuttle Centaur G Upper Stage

    NASA Technical Reports Server (NTRS)

    Williams, Craig H.

    2014-01-01

    An unclassified analytical trajectory design, performance, and mission study was done for the 1982-86 joint NASA-USAF Shuttle/Centaur G upper stage development program to send performance-demanding payloads to high orbits such as Molniya using an unconventional orbit transfer. This optimized three orbital burn transfer to Molniya orbit was compared to the then-baselined two burn transfer. The results of the three dimensional trajectory optimization performed include powered phase steering data and coast phase orbital element data. Time derivatives of the orbital elements as functions of thrust components were evaluated and used to explain the optimization's solution. Vehicle performance as a function of parking orbit inclination was given. Performance and orbital element data was provided for launch windows as functions of launch time. Ground track data was given for all burns and coasts including variation within the launch window. It was found that a Centaur with fully loaded propellant tanks could be flown from a 37deg inclination low Earth parking orbit and achieve Molniya orbit with comparable performance to the baselined transfer which started from a 57deg inclined orbit: 9,545 lb vs. 9,552 lb of separated spacecraft weight respectively. There was a significant reduction in the need for propellant launch time reserve for a one hour window: only 78 lb for the three burn transfer vs. 320 lb for the two burn transfer. Conversely, this also meant that longer launch windows over more orbital revolutions could be done for the same amount of propellant reserve. There was no practical difference in ground tracking station or airborne assets needed to secure telemetric data, even though the geometric locations of the burns varied considerably. There was a significant adverse increase in total mission elapsed time for the three vs. two burn transfer (12 vs. 11/4 hrs), but could be accommodated by modest modifications to Centaur systems. Future applications were discussed. The three burn transfer was found to be a viable, arguably preferable, alternative to the two burn transfer.

  11. 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

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

    SciTech Connect

    Hauer, K.L.; Grant, N.K. . Dept. of Geology)

    1992-01-01

    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.

  13. Engineering human hepatic tissue for modeling liver-stage malaria

    E-print Network

    Ng, Shengyong

    2014-01-01

    The Plcsmodium liver stage is an attractive target for the development of antimalarial drugs and vaccines, as it provides an opportunity to interrupt the life cycle of the parasite at a critical early stage. However, ...

  14. TITRE: Stage Energies Marines Renouvelables SOCIETE : D2M Engineering Ref : CTR201210

    E-print Network

    TITRE: Stage Energies Marines Renouvelables SOCIETE : D2M Engineering Ref : CTR201210 DUREE : 6 mois Début : Janvier 2012 Fin : Juillet 2012 PRESENTATION DU STAGE : Les énergies marines renouvelables'un nouveau système houlomoteur nommé l' « Energie Marine Bilboquet » (EM Bilboquet). Le stage proposé s

  15. Validating NEXRAD MPE and Stage III precipitation products for uniform rainfall on the Upper Guadalupe

    E-print Network

    Texas at San Antonio, University of

    -density rain gauge network located on the Upper Guadalupe River Basin of the Texas Hill Country. As point Guadalupe River Basin of the Texas Hill Country Xianwei Wang a , Hongjie Xie a,*, Hatim Sharif b , Jon Zeitler c a Laboratory for Remote Sensing and Geoinformatics, University of Texas at San Antonio, One UTSA

  16. Large-Scale Liquid Hydrogen Tank Rapid Chill and Fill Testing for the Advanced Shuttle Upper Stage Concept

    NASA Technical Reports Server (NTRS)

    Flachbart, R. H.; Hedayat, A.; Holt, K. A.; Sims, J.; Johnson, E. F.; Hastings, L. J.; Lak, T.

    2013-01-01

    Cryogenic upper stages in the Space Shuttle program were prohibited primarily due to a safety risk of a 'return to launch site' abort. An upper stage concept addressed this concern by proposing that the stage be launched empty and filled using shuttle external tank residuals after the atmospheric pressure could no longer sustain an explosion. However, only about 5 minutes was allowed for tank fill. Liquid hydrogen testing was conducted within a near-ambient environment using the multipurpose hydrogen test bed 638.5 ft3 (18m3) cylindrical tank with a spray bar mounted longitudinally inside. Although the tank was filled within 5 minutes, chilldown of the tank structure was incomplete, and excessive tank pressures occurred upon vent valve closure. Elevated tank wall temperatures below the liquid level were clearly characteristic of film boiling. The test results have substantial implications for on-orbit cryogen transfer since the formation of a vapor film would be much less inhibited due to the reduced gravity. However, the heavy tank walls could become an asset in normal gravity testing for on-orbit transfer, i.e., if film boiling in a nonflight weight tank can be inhibited in normal gravity, then analytical modeling anchored with the data could be applied to reduced gravity environments with increased confidence.

  17. Optimization of dual-expander rocket engines in single-stage-to-orbit vehicles

    NASA Astrophysics Data System (ADS)

    Manski, Detlef; Hagemann, Gerald; Sa?nick, Hagen D.

    1997-01-01

    Dual-expander rocket engines offer a trajectory adapted dual-mode operation during the ascent of a launcher, which may be of significant advantage for single-stage earth-to-orbit vehicles, when compared to conventional rocket engines with bell-type nozzles. This paper investigates a reusable single-stage earth-to-orbit vehicle with a constant payload capability of 16.5 Mg into low earth orbit, for the comparison of the dual-expander rocket engines with conventional rocket engines, using only hydrogen and oxygen as propellant combination in all engines.

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

    NASA Technical Reports Server (NTRS)

    Hastings, Leon; Martin, James

    1998-01-01

    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.

  19. Three-dimensional transient thermal analysis of a receiver-absorber-converter system in the Integrated Solar Upper Stage Unit

    SciTech Connect

    Tong, W.

    1999-12-01

    The Integrated Solar Upper Stage (ISUS) program is directing its efforts at solving endemic national spacecraft architecture problems. The ISUS is an advanced, integrated upper stage concept that would permit payload realignment, allowing large payloads to be moved by smaller and less expensive boosters. A receiver-absorber-converter (RAC) system in the ISUS unit is designed to convert solar energy to kinetic energy in the propulsion phase or electrical energy in the power generation phase for spacecraft control and operation. In this study a three-dimensional, transient, turbulent hydrogen gas flow through the RAC system was simulated using a finite element thermal-hydraulic model. With this model, transient temperature, pressure, and flow fields in the RAC system were obtained. Numerical results of the mass flow rate distribution through hydrogen heating channels reveal that higher mass flow rates occur through those channels near either the hydrogen channels reveal that higher mass flow rates occur through those channels near either the hydrogen inlet or exit. It takes about 18.5 min for the hydrogen exhaust temperature to drop below 2,000 K. The results obtained from this work have been applied for validating and optimizing the present RAC design, as well as for performing the thermal stress analysis.

  20. RL-10 Engine

    NASA Technical Reports Server (NTRS)

    1960-01-01

    RL-10 engine characteristics. The RL-10 engine was developed under the management of the Marshall Space Flight Center (MSFC) to power the Saturn I upper stage (S-IV stage). The six RL-10 engines, which used liquid hydrogen and liquid oxygen as propellants, were arranged in a circle on the aft end of the S-IV stage.

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

    NASA Technical Reports Server (NTRS)

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

    2001-01-01

    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.

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

    NASA Astrophysics Data System (ADS)

    Habets, F.; Vergnes, J.

    2013-12-01

    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.

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

    NASA Technical Reports Server (NTRS)

    Russell, Sam; Ezell, David

    2010-01-01

    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.

  4. The Influence of Immersion and Presence in Early Stage Engineering Designing and Building

    E-print Network

    Yang, Maria

    1 The Influence of Immersion and Presence in Early Stage Engineering Designing and Building Daniela of engagement in early stage design. In the field of virtual reality, presence and immersion are standard designers who are more engaged in design activity, as measured by presence and immersive tendency

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

    NASA Astrophysics Data System (ADS)

    Rubio Hervas, Jaime; Reyhanoglu, Mahmut

    2014-05-01

    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.

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

    NASA Technical Reports Server (NTRS)

    Plachta, David; Kittel, Peter

    2003-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

    Knauber, R. N.

    1982-01-01

    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.

  8. The dynamics of a gas-dust cloud expansion in the upper atmosphere at a shutdown of solid-propellant rocket engines

    NASA Astrophysics Data System (ADS)

    Nikolaishvili, S. Sh.; Platov, Yu. V.; Chernouss, S. A.

    2015-09-01

    The velocity of spherical gas-dust cloud expansion in the situation when the stages of solid-propellant rocket separate in the upper atmosphere have been determined. The measured velocity vary from 2.5 to 7.5 km/s. The dispersed component accelerates at the front of a shock that develops at engine-thrust shutdown. The model calculations of the gas-dust cloud luminosity intensity qualitatively coincide with the photometric profiles of object images. Such formations can vary from almost homogeneous ball-shaped clouds to rather thin spherical shells depending on the gas-dust cloud mass and the matter distribution within this cloud.

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

    PubMed Central

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

    2011-01-01

    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. PMID:21347420

  10. Installation of H-1 Engines to Saturn IB S-IB Stage

    NASA Technical Reports Server (NTRS)

    1967-01-01

    Workers at the Michoud Assembly Facility (MAF) near New Orleans, Louisiana, install the H-1 engines into the Saturn I, S-IB (first) stage. Developed by the Marshall Space Flight Center and built by the Chrysler Corporation at MAF, the 90,000-pound booster utilized eight H-1 engines. Each produced 200,000 pounds of thrust, a combined thrust of 1,600,000 pounds.

  11. Closed-Loop Simulation Study of the Ares I Upper Stage Thrust Vector Control Subsystem for Nominal and Failure Scenarios

    NASA Technical Reports Server (NTRS)

    Chicatelli, Amy; Fulton, Chris; Connolly, Joe; Hunker, Keith

    2010-01-01

    As a replacement to the current Shuttle, the Ares I rocket and Orion crew module are currently under development by the National Aeronautics and Space Administration (NASA). This new launch vehicle is segmented into major elements, one of which is the Upper Stage (US). The US is further broken down into subsystems, one of which is the Thrust Vector Control (TVC) subsystem which gimbals the US rocket nozzle. Nominal and off-nominal simulations for the US TVC subsystem are needed in order to support the development of software used for control systems and diagnostics. In addition, a clear and complete understanding of the effect of off-nominal conditions on the vehicle flight dynamics is desired. To achieve these goals, a simulation of the US TVC subsystem combined with the Ares I vehicle as developed. This closed-loop dynamic model was created using Matlab s Simulink and a modified version of a vehicle simulation, MAVERIC, which is currently used in the Ares I project and was developed by the Marshall Space Flight Center (MSFC). For this report, the effects on the flight trajectory of the Ares I vehicle are investigated after failures are injected into the US TVC subsystem. The comparisons of the off-nominal conditions observed in the US TVC subsystem with those of the Ares I vehicle flight dynamics are of particular interest.

  12. Computer program for prediction of capture maneuver probability for an on-off reaction controlled upper stage

    NASA Technical Reports Server (NTRS)

    Knauber, R. N.

    1982-01-01

    A FORTRAN coded computer program which computes the capture transient of a launch vehicle upper stage at the ignition and/or separation event is presented. It is for a single degree-of-freedom on-off reaction jet attitude control system. The Monte Carlo method is used to determine the statistical value of key parameters at the outcome of the event. Aerodynamic and booster induced disturbances, vehicle and control system characteristics, and initial conditions are treated as random variables. By appropriate selection of input data pitch, yaw and roll axes can be analyzed. Transient response of a single deterministic case can be computed. The program is currently set up on a CDC CYBER 175 computer system but is compatible with ANSI FORTRAN computer language. This routine has been used over the past fifteen (15) years for the SCOUT Launch Vehicle and has been run on RECOMP III, IBM 7090, IBM 360/370, CDC6600 and CDC CYBER 175 computers with little modification.

  13. Upper bound on the effective error coefficient of two-stage decoding, and good two-level decompositions of some Reed-Muller codes

    NASA Astrophysics Data System (ADS)

    Wu, Jiantian; Lin, Shu; Fujiwara, Toru; Takata, Toyoo

    1994-02-01

    In this letter, an upper bound on the effective error coefficient of a two-level code with two-stage decoding is presented. This bound provides a guideline for constructing two-level codes to achieve a good trade-off between the error performance and decoding complexity. Based on this bound, good two-level decompositions of some Reed-Muller codes for two-stage decoding are found. Simulation results on the error performances of some Reed-Muller codes of lengths up to 64 with two-stage soft-decision suboptimum decoding based on their two-level decompositions are given.

  14. Affordable Development and Demonstration of a Small NTR Engine and Stage: How Small is Big Enough?

    NASA Technical Reports Server (NTRS)

    Borowski, Stanley K.; Sefcik, Robert J.; Fittje, James E.; McCurdy, David R.; Qualls, Arthur L.; Schnitzler, Bruce G.; Werner, James E.; Weitzberg (Abraham); Joyner, Claude R.

    2015-01-01

    The Nuclear Thermal Rocket (NTR) derives its energy from fission of uranium-235 atoms contained within fuel elements that comprise the engine's reactor core. It generates high thrust and has a specific impulse potential of approximately 900 seconds - a 100% increase over today's best chemical rockets. The Nuclear Thermal Propulsion (NTP) project, funded by NASA's AES program, includes five key task activities: (1) Recapture, demonstration, and validation of heritage graphite composite (GC) fuel (selected as the "Lead Fuel" option); (2) Engine Conceptual Design; (3) Operating Requirements Definition; (4) Identification of Affordable Options for Ground Testing; and (5) Formulation of an Affordable Development Strategy. During FY'14, a preliminary DDT&E plan and schedule for NTP development was outlined by GRC, DOE and industry that involved significant system-level demonstration projects that included GTD tests at the NNSS, followed by a FTD mission. To reduce cost for the GTD tests and FTD mission, small NTR engines, in either the 7.5 or 16.5 klbf thrust class, were considered. Both engine options used GC fuel and a "common" fuel element (FE) design. The small approximately 7.5 klbf "criticality-limited" engine produces approximately 157 megawatts of thermal power (MWt) and its core is configured with parallel rows of hexagonal-shaped FEs and tie tubes (TTs) with a FE to TT ratio of approximately 1:1. The larger approximately 16.5 klbf Small Nuclear Rocket Engine (SNRE), developed by LANL at the end of the Rover program, produces approximately 367 MWt and has a FE to TT ratio of approximately 2:1. Although both engines use a common 35 inch (approximately 89 cm) long FE, the SNRE's larger diameter core contains approximately 300 more FEs needed to produce an additional 210 MWt of power. To reduce the cost of the FTD mission, a simple "1-burn" lunar flyby mission was considered to reduce the LH2 propellant loading, the stage size and complexity. Use of existing and flight proven liquid rocket and stage hardware (e.g., from the RL10B-2 engine and Delta Cryogenic Second Stage) was also maximized to further aid affordability. This paper examines the pros and cons of using these two small engine options, including their potential to support future human exploration missions to the Moon, near Earth asteroids, and Mars, and recommends a preferred size. It also provides a preliminary assessment of the key activities, development options, and schedule required to affordably build, ground test and fly a small NTR engine and stage within a 10-year timeframe.

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

    NASA Technical Reports Server (NTRS)

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

    2006-01-01

    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

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

    ERIC Educational Resources Information Center

    Mannion, Ken

    2012-01-01

    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…

  17. First Saturn V S-IC Stage Five F-1 Engine Testing

    NASA Technical Reports Server (NTRS)

    1965-01-01

    This photograph depicts a dramatic view of the first test firing of all five F-1 engines for the Saturn V S-IC stage at the Marshall Space Flight Center. The testing lasted a full duration of 6.5 seconds. It also marked the first test performed in the new S-IC static test stand and the first test using the new control blockhouse. The S-IC stage is the first stage, or booster, of a 364-foot long rocket that ultimately took astronauts to the Moon. Operating at maximum power, all five of the engines produced 7,500,000 pounds of thrust. Required to hold down the brute force of a 7,500,000-pound thrust, the S-IC static test stand was designed and constructed with the strength of hundreds of tons of steel and cement, planted down to bedrock 40 feet below ground level. The structure was topped by a crane with a 135-foot boom. With the boom in the up position, the stand was given an overall height of 405 feet, placing it among the highest structures in Alabama at the time. When the Saturn V S-IC first stage was placed upright in the stand , the five F-1 engine nozzles pointed downward on a 1,900 ton, water-cooled deflector. To prevent melting damage, water was sprayed through small holes in the deflector at the rate 320,000 gallons per minute.

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

    NASA Technical Reports Server (NTRS)

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

    2009-01-01

    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;

  19. CHaracteristics of Two-Stage Absorption Heat Pump Cycler Driven by Waste Heat From Gas Engine

    NASA Astrophysics Data System (ADS)

    Kojima, Hiroshi; Akisawa, Atsushi; Kashiwagi, Takao

    Recently the energy conservation is expected from the global environment protection view point. In this study, a new concept of a compound gas cooling system using treated sewage water combining a gas engine heat pump and an absorption heat pump is proposed. In this system, the absorption heat pump is driven by the waste heat from the gas engine. In this paper, first, the best absorption cycle for this absorption heat pump is selected for the cooling and heating mode. And finally the simulation model of the two-stage absorption heat pumps for heating mode is demonstrated and the static characteristics are clarified.

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

    NASA Technical Reports Server (NTRS)

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

    1973-01-01

    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.

  1. Impact of Postoperative Chemoradiotherapy versus Chemotherapy Alone on Recurrence and Survival in Patients with Stage II and III Upper Rectal Cancer: A Propensity Score-Matched Analysis

    PubMed Central

    Kim, Jae-Sung; Oh, Heung-Kwon; Kim, Duck-Woo; Lee, Keun-Wook; Kim, Jee Hyun; Eom, Keun-Yong; Kim, In Ah; Kang, Sung-Bum

    2015-01-01

    Purpose To compare the impact of postoperative chemoradiotherapy (CRT) versus adjuvant chemotherapy alone on recurrence and survival in patients with stage II and III upper rectal cancer undergoing curative resection. Materials and Methods From our institutional database, 190 patients who underwent primary curative resection between 2003 and 2010 for stage II or III upper rectal cancer were identified. None of the patients received preoperative CRT. Of these, 136 patients received postoperative chemotherapy alone (the CTx group) and 54 patients received postoperative CRT (the CRT group). The CRT group had poorer prognostic features (pT4, pN2, poor differentiation, or involved resection margin) compared with the CTx group. To reduce the impact of treatment selection bias on treatment outcomes, propensity score-matching analysis was used. Results The matched cohort consisted of 50 CRT and 50 CTx patients with a median follow-up period of 76 and 63 months, respectively. In the matched cohort, CRT resulted in an improved 5-year local control (98.0% vs. 85.2%, p = 0.024) and overall survival rate (89.9% vs. 69.8%, p = 0.021) compared with CTx. In the subgroup analysis to identify subpopulations of patients that benefit most from receiving CRT, local recurrence did not occur in patients who did not have poor prognostic features regardless of the receipt of CRT. For patients with any poor prognostic features, CRT resulted in an improved 5-year local control compared with CTx (96.4% vs. 70.7%, p = 0.013). Conclusions After adjusting for clinicopathologic factors by propensity score-matching, postoperative CRT was associated with improved local control and overall survival in stage II and III upper rectal cancer. Our results suggest that surgery followed by chemotherapy alone is acceptable for patients who did not have poor prognostic features, while additional radiotherapy should be given for patients who have any poor prognostic features. PMID:25902069

  2. 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)

    1982-01-01

    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.

  3. Validating NEXRAD MPE and Stage III precipitation products for uniform rainfall on the Upper Guadalupe River Basin of the Texas Hill Country

    NASA Astrophysics Data System (ADS)

    Wang, Xianwei; Xie, Hongjie; Sharif, Hatim; Zeitler, Jon

    2008-01-01

    SummaryThis study examines the performance of the Next Generation Weather Radar (NEXRAD) Multisensor Precipitation Estimator (MPE) and Stage III precipitation products, using a high-density rain gauge network located on the Upper Guadalupe River Basin of the Texas Hill Country. As point-area representativeness error of gauge rainfall is a major concern in assessment of radar rainfall estimation, this study develops a new method to automatically select uniform rainfall events based on coefficient of variation criterion of 3 by 3 radar cells. Only gauge observations of those uniform rainfall events are used as ground truth to evaluate radar rainfall estimation. This study proposes a new parameter probability of rain detection (POD) instead of the conditional probability of rain detection (CPOD) commonly used in previous studies to assess the capability that a radar or gauge detects rainfall. Results suggest that: (1) gauge observations of uniform rainfall better represent ground truth of a 4 × 4 km 2 radar cell than non-uniform rainfall; (2) the MPE has higher capability of rain detection than either gauge-only or Stage III; (3) the MPE has much higher linear correlation and lower mean relative difference with gauge measurements than the Stage III does; (4) the Stage III tends to overestimate precipitation (20%), but the MPE tends to underestimate (7%).

  4. Assessment of a multi-stage underwater vehicle concept using a fossil-fuel Stirling engine

    SciTech Connect

    Reader, G.T.; Potter, I.J.

    1995-12-31

    The Stirling Engine because of its inherent closed-cycle operation can be readily modified to work in an airless environment even if the primary source of energy is a fossil fuel. Thus, Stirling engines are well suited for use in the underwater environment and have been operated successfully in manned military submarines since the early 1980s. In recent years fossil fueled Stirling systems have been also proposed for use in small unmanned underwater vehicles (UUVs). However, in this case the need to carry an onboard oxygen supply in a very confined space has presented a number of design difficulties. These are identified in the paper. However, if the oxidant supply to the engine is provided by the membrane extraction of dissolved oxygen from seawater and/or disposable fuel/oxidant pods are used then the UUV Stirling system becomes more attractive. If this latter concept is extended to include multi-stage vehicles then it can be shown that fossil fueled Stirlings could also be put to effective use in long range-long endurance underwater vehicular operations.

  5. Stage-by-Stage and Parallel Flow Path Compressor Modeling for a Variable Cycle Engine, NASA Advanced Air Vehicles Program - Commercial Supersonic Technology Project - AeroServoElasticity

    NASA Technical Reports Server (NTRS)

    Kopasakis, George; Connolly, Joseph W.; Cheng, Larry

    2015-01-01

    This paper covers the development of stage-by-stage and parallel flow path compressor modeling approaches for a Variable Cycle Engine. The stage-by-stage compressor modeling approach is an extension of a technique for lumped volume dynamics and performance characteristic modeling. It was developed to improve the accuracy of axial compressor dynamics over lumped volume dynamics modeling. The stage-by-stage compressor model presented here is formulated into a parallel flow path model that includes both axial and rotational dynamics. This is done to enable the study of compressor and propulsion system dynamic performance under flow distortion conditions. The approaches utilized here are generic and should be applicable for the modeling of any axial flow compressor design accurate time domain simulations. The objective of this work is as follows. Given the parameters describing the conditions of atmospheric disturbances, and utilizing the derived formulations, directly compute the transfer function poles and zeros describing these disturbances for acoustic velocity, temperature, pressure, and density. Time domain simulations of representative atmospheric turbulence can then be developed by utilizing these computed transfer functions together with the disturbance frequencies of interest.

  6. A Rocket Powered Single-Stage-to-Orbit Launch Vehicle With U.S. and Soviet Engineers

    NASA Technical Reports Server (NTRS)

    MacConochie, Ian O.; Stnaley, Douglas O.

    1991-01-01

    A single-stage-to-orbit launch vehicle is used to assess the applicability of Soviet Energia high-pressure-hydrocarbon engine to advanced U.S. manned space transportation systems. Two of the Soviet engines are used with three Space Shuttle Main Engines. When applied to a baseline vehicle that utilized advanced hydrocarbon engines, the higher weight of the Soviet engines resulted in a 20 percent loss of payload capability and necessitated a change in the crew compartment size and location from mid-body to forebody in order to balance the vehicle. Various combinations of Soviet and Shuttle engines were evaluated for comparison purposes, including an all hydrogen system using all Space Shuttle Main Engines. Operational aspects of the baseline vehicle are also discussed. A new mass properties program entitles Weights and Moments of Inertia (WAMI) is used in the study.

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

    NASA Technical Reports Server (NTRS)

    Schoenman, L.

    1981-01-01

    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.

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

    PubMed Central

    Garrison, Howard

    2013-01-01

    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. PMID:24006384

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

    NASA Technical Reports Server (NTRS)

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

    2013-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

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

    2007-01-01

    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.

  11. Space Shuttle guidance for multiple main engine failures during first stage

    NASA Technical Reports Server (NTRS)

    Sponaugle, Steven J.; Fernandes, Stanley T.

    1987-01-01

    This paper presents contingency abort guidance schemes recently developed for multiple Space Shuttle main engine failures during the first two minutes of flight (first stage). The ascent and entry guidance schemes greatly improve the possibility of the crew and/or the Orbiter surviving a first stage contingency abort. Both guidance schemes were required to meet certain structural and controllability constraints. In addition, the systems were designed with the flexibility to allow for seasonal variations in the atmosphere and wind. The ascent scheme guides the vehicle to a desirable, lofted state at solid rocket booster burnout while reducing the structural loads on the vehicle. After Orbiter separation from the solid rockets and the external tank, the entry scheme guides the Orbiter through one of two possible entries. If the proper altitude/range/velocity conditions have been met, a return-to-launch-site 'Split-S' maneuver may be attempted. Otherwise, a down-range abort to an equilibrium glide and subsequent crew bailout is performed.

  12. Evaluation of the dosimetric impact of applying flattening filter-free beams in intensity-modulated radiotherapy for early-stage upper thoracic carcinoma of oesophagus

    SciTech Connect

    Zhang, Wuzhe; Lin, Zhixiong; Yang, Zhining; Fang, Weisheng; Lai, Peibo; Lu, Jiayang; Wu, Vincent WC

    2015-06-15

    Flattening filter-free (FFF) radiation beams have recently become clinically available on modern linear accelerators in radiation therapy. This study aimed to evaluate the dosimetric impact of using FFF beams in intensity-modulated radiotherapy (IMRT) for early-stage upper thoracic oesophageal cancer. Eleven patients with primary stage upper thoracic oesophageal cancer were recruited. For each patient, two IMRT plans were computed using conventional beams (Con-P) and FFF beams (FFF-P), respectively. Both plans employed a five-beam arrangement and were prescribed with 64 Gy to (planning target volume) PTV1 and 54 Gy to PTV2 in 32 fractions using 6 MV photons. The dose parameters of the target volumes and organs at risks (OARs), and treatment parameters including the monitor units (MU) and treatment time (TT) for Con-P and FFF-P were recorded and compared. The mean D{sub 5} of PTV1 and PTV2 were higher in FFF-P than Con-P by 0.4 Gy and 0.3 Gy, respectively. For the OARs, all the dose parameters did not show significant difference between the two plans except the mean V{sub 5} and V{sub 10} of the lung in which the FFF-P was lower (46.7% vs. 47.3% and 39.1% vs. 39.6%, respectively). FFF-P required 54% more MU but 18.4% less irradiation time when compared to Con-P. The target volume and OARs dose distributions between the two plans were comparable. However, FFF-P was more effective in sparing the lung from low dose and reduced the mean TT compared with Con-P. Long-term clinical studies are suggested to evaluate the radiobiological effects of FFF beams.

  13. Evaluation of the dosimetric impact of applying flattening filter-free beams in intensity-modulated radiotherapy for early-stage upper thoracic carcinoma of oesophagus

    PubMed Central

    Zhang, Wuzhe; Lin, Zhixiong; Yang, Zhining; Fang, Weisheng; Lai, Peibo; Lu, Jiayang; Wu, Vincent WC

    2015-01-01

    Introduction Flattening filter-free (FFF) radiation beams have recently become clinically available on modern linear accelerators in radiation therapy. This study aimed to evaluate the dosimetric impact of using FFF beams in intensity-modulated radiotherapy (IMRT) for early-stage upper thoracic oesophageal cancer. Methods Eleven patients with primary stage upper thoracic oesophageal cancer were recruited. For each patient, two IMRT plans were computed using conventional beams (Con-P) and FFF beams (FFF-P), respectively. Both plans employed a five-beam arrangement and were prescribed with 64 Gy to (planning target volume) PTV1 and 54 Gy to PTV2 in 32 fractions using 6 MV photons. The dose parameters of the target volumes and organs at risks (OARs), and treatment parameters including the monitor units (MU) and treatment time (TT) for Con-P and FFF-P were recorded and compared. Results The mean D5 of PTV1 and PTV2 were higher in FFF-P than Con-P by 0.4 Gy and 0.3 Gy, respectively. For the OARs, all the dose parameters did not show significant difference between the two plans except the mean V5 and V10 of the lung in which the FFF-P was lower (46.7% vs. 47.3% and 39.1% vs. 39.6%, respectively). FFF-P required 54% more MU but 18.4% less irradiation time when compared to Con-P. Conclusion The target volume and OARs dose distributions between the two plans were comparable. However, FFF-P was more effective in sparing the lung from low dose and reduced the mean TT compared with Con-P. Long-term clinical studies are suggested to evaluate the radiobiological effects of FFF beams. PMID:26229675

  14. 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)

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

    2001-01-01

    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.

  15. Comparison of NEXRAD Stage III and MPE precipitation products with constraints from high quality and density of raingauge networks in the Upper Guadalupe River Basin, Central Texas

    NASA Astrophysics Data System (ADS)

    Xie, H.; Wang, X.

    2006-05-01

    NEXRAD's Multisensor Precipitation Estimator (MPE) product replaced the Stage III product started in October 2003 at the West Gulf River Forecast Center (WGRFC) where includes most of the Texas and New Mexico. The MPE is an integrated product of rain gauge, NEXRAD, and satellite (GOES) precipitation estimates. The main objective of MPE is to reduce both areal-mean bias error and local bias error. The overall improved quality of MPE over Stage 3 is evident at the WGRFC. However, so far, there is no quantitative evaluation in a relative long period (one year or more) of a large area. In this study, high quality and density of 50 raingauge networks (6 minutes temporal resolution) in the Upper Guadalupe River Basin, Central Texas are used to evaluate both the Stage III (years 2001 and 2002) and MPE (year 2004) products. In this study, we propose two types of comparison (1) directly compare collocated radar cell and gauge of all rainfall events and (2) only compare collocated radar cell and gauge of homogeneous/uniform rainfall events. To find uniform rainfall events, 6-mintutes raingauge rainfall were used to calculate the correlation coefficient (CC) and coefficient of variation (CV) of a hour among one central gauge and its surrounding gauges (>= 4). For a particular rainfall hour, when CV is < 0.5 and CC is > 0.5, or CV is <0.1, the rainfall event of this hour is thus selected as a uniform or homogeneous rainfall event. Our preliminary results of CC from all rainfall events and homogeneous rainfall events for year 2004 (MPE) are 0.79 and 0.96, respectively. This indicates an overall good quality of MPE product in comparison with raingauge rainfall, especially for the homogeneous rainfall events. Work is in progress.

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

    ERIC Educational Resources Information Center

    Miyamoto, S.; Nakayama, K.

    1983-01-01

    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…

  17. Core compressor exit stage study. Volume 1: Blading design. [turbofan engines

    NASA Technical Reports Server (NTRS)

    Wisler, D. C.

    1977-01-01

    A baseline compressor test stage was designed as well as a candidate rotor and two candidate stators that have the potential of reducing endwall losses relative to the baseline stage. These test stages are typical of those required in the rear stages of advanced, highly-loaded core compressors. The baseline Stage A is a low-speed model of Stage 7 of the 10 stage AMAC compressor. Candidate Rotor B uses a type of meanline in the tip region that unloads the leading edge and loads the trailing edge relative to the baseline Rotor A design. Candidate Stator B embodies twist gradients in the endwall region. Candidate Stator C embodies airfoil sections near the endwalls that have reduced trailing edge loading relative to Stator A. Tests will be conducted using four identical stages of blading so that the designs described will operate in a true multistage environment.

  18. 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)

    Pool, Kirby V.

    1989-01-01

    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.

  19. Deciphering tectonic, climatic-induced and hydrothermal signals in the late-stage exhumation history of the upper Rhône valley (Swiss Alps)

    NASA Astrophysics Data System (ADS)

    Valla, Pierre; Rahn, Meinert; Shuster, David; van der Beek, Peter

    2015-04-01

    Neogene exhumation of the European Alps is understood as the interplay between tectonics and climatic-induced erosion. While the former has been influenced by a decrease in plate convergence, the latter has been suggested to be affected by climatic variation and the onset of Plio-Quaternary glaciations, leading to relief amplification. However, even though geomorphologic and sedimentologic studies both suggest topographic relief change and transition from fluvial to oscillations between glacial/fluvial conditions, precise quantification on both the timing and magnitude of this transition are yet sparse. Our study focuses on the upper Rhône valley (Swiss Central Alps) within the Visp-Brig area (Aar massif). This area encompasses some of the most spectacular reliefs within the Alps with several nearby summits around or above 4000 m crosscut by the glacially overdeepened Rhône valley. It also shows among the highest late Neogene exhumation rates within the Western-Central European Alps, influenced by tectonic activity along the major Simplon-Rhône extensional fault system. Moreover, the upper Rhône valley has experienced enhanced glacial erosion associated with strong relief development during the Pliocene-Quaternary period. Finally, structural inheritance, late-stage tectonics and rapid exhumation may have promoted recent hydrothermal activity in this region, although timing of its onset and its precise causes remain poorly understood. We investigated the late-stage cooling history by using different low-temperature thermochronometers along a pseudo-vertical bedrock profile (elevation between 600 and 2900 m) and additional samples from an on-site 500-m geothermal well, resulting in a total elevation difference of nearly 3 km. Apatite fission-track (AFT) ages and track-length data have been added to previously published and new apatite (U-Th-Sm)/He (AHe) and 4He/3He data. Our results confirm high-exhumation rates (0.6 to 0.9 km/Myr) within late-Cenozoic to Pliocene times. Combined with AFT data from the literature, our age pattern reveals no exhumation difference across the Simplon fault system during the last 6-8 Ma, suggesting only strike-slip detachment activity of the structure during that period. Thermal modelling using HeFTy confirms rapid exhumation and evidences a late-stage cooling contrast between high-elevation and valley-bottom/geothermal well samples, in agreement with previous 4He/3He data. This late-stage exhumation is associated to the onset of major Alpine glaciation triggering the Rhône valley carving at ~1 Ma. Apatite track length measurements suggest that the well samples have been affected by recent hydrothermal activity. This agrees well with the present-day observation of high geothermal activity below the Rhône valley floor, whose origin has been primarily linked to structural inheritance (Simplon-Rhône extensional fault system). Our thermochronology data helps to put constrain on the onset timing of this geothermal activity, which we propose to be concordant with the onset of major alpine glaciations, glacial erosion and bedrock-fracture development promoting localized fluid circulation and hydrothermal activity below the Rhône valley floor.

  20. 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)

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

    2001-01-01

    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.

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

    NASA Astrophysics Data System (ADS)

    Samson, P. J.

    2002-12-01

    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.

  2. Feasibility of the Ultrasound Checking of the First-Stage Engine of the Zenith Rocket Carrier. 2. Results of the Ultrasound Diagnostics of the Engine Defectiveness

    NASA Astrophysics Data System (ADS)

    Bezmyannyi, Yu. G.; Borovik, V. G.; Galas, M. I.; Trefilov, V. I.; Frolov, G. A.

    The authors investigate the possibility revealing a gap in the juncture of the terminal welding junction on the assembled first-stage engine of the Zenith rocket carrier by the non-destructive ultrasound checking methods. Principles of ultrasound diagnostics were developed, and methods for measuring the diagnostic parameters were selected. A technique for their realization based on an original apparatus complex for ultrasound measurements is described, as well as some results of the experimental measurements of selected diagnostic parameters which were obtained on samples produced of full-size engines. The analysis of the results obtained shows that the task set can be solved in principle.

  3. Affordable Development and Demonstration of a Small NTR Engine and Stage: A Preliminary NASA, DOE, and Industry Assessment

    NASA Technical Reports Server (NTRS)

    Borowski, Stanley K.; Sefcik, Robert J.; Fittje, James E.; McCurdy, David R.; Qualls, Arthur L.; Schnitzler, Bruce G.; Werner, James E.; Weitzberg, Abraham; Joyner, Claude R.

    2015-01-01

    The Nuclear Thermal Rocket (NTR) represents the next evolutionary step in cryogenic liquid rocket engines. Deriving its energy from fission of uranium-235 atoms contained within fuel elements that comprise the engine's reactor core, the NTR can generate high thrust at a specific impulse of approx. 900 seconds or more - twice that of today's best chemical rockets. In FY'11, as part of the AISP project, NASA proposed a Nuclear Thermal Propulsion (NTP) effort that envisioned two key activities - "Foundational Technology Development" followed by system-level "Technology Demonstrations". Five near-term NTP activities identified for Foundational Technology Development became the basis for the NCPS project started in FY'12 and funded by NASA's AES program. During Phase 1 (FY'12-14), the NCPS project was focused on (1) Recapturing fuel processing techniques and fabricating partial length "heritage" fuel elements for the two candidate fuel forms identified by NASA and the DOE - NERVA graphite "composite" and the uranium dioxide (UO2) in tungsten "cermet". The Phase 1 effort also included: (2) Engine Conceptual Design; (3) Mission Analysis and Requirements Definition; (4) Identification of Affordable Options for Ground Testing; and (5) Formulation of an Affordable and Sustainable NTP Development Strategy. During FY'14, a preliminary plan for DDT&E was outlined by GRC, the DOE and industry for NASA HQ that involved significant system-level demonstration projects that included GTD tests at the NNSS, followed by a FTD mission. To reduce development costs, the GTD and FTD tests use a small, low thrust (approx. 7.5 or 16.5 klbf) engine. Both engines use graphite composite fuel and a "common" fuel element design that is scalable to higher thrust (approx. 25 klbf) engines by increasing the number of elements in a larger diameter core that can produce greater thermal power output. To keep the FTD mission cost down, a simple "1-burn" lunar flyby mission was considered along with maximizing the use of existing and flight proven liquid rocket and stage hardware (e.g., from the RL10-B2 engine and Delta Cryogenic Second Stage) to further ensure affordability. This paper provides a preliminary NASA, DOE and industry assessment of what is required - the key DDT&E activities, development options, and the associated schedule - to affordably build, ground test and fly a small NTR engine and stage within a 10-year timeframe.

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

    NASA Technical Reports Server (NTRS)

    Byrd, Thomas

    2008-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

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

    1973-01-01

    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.

  6. The influence of immersion and presence in early stage engineering designing and building

    E-print Network

    Faas, Daniela

    This paper explores the role of a designer's sense of engagement in early stage design. In the field of virtual reality, presence and immersion are standard measures of an individual's sense of engagement and involvement ...

  7. Liquid Rocket Engine Testing Overview

    NASA Technical Reports Server (NTRS)

    Rahman, Shamim

    2005-01-01

    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.

  8. Reliability as an Independent Variable Applied to Liquid Rocket Engine Test Plans

    E-print Network

    Herrmann, Jeffrey W.

    solid propellant stages and a cryogenic upper-stage engine. Although innovative technologiesReliability as an Independent Variable Applied to Liquid Rocket Engine Test Plans Richard Strunz and a number of hot-fire tests necessary to develop and qualify/certify a liquid rocket engine against a stated

  9. Humans as the third evolutionary stage of biosphere engineering of rivers

    E-print Network

    Williams, Mark; Zalasiewicz, Jan; Davies, Neil; Mazzini, Ilaria; Goiran, Jean-Philippe; Kane, Stephanie

    2015-03-20

    ‘reverse engineering’ of the terrestrial biosphere include deforestation, irrigation and agriculture. Sediment retention has been encouraged by the construction of dams. Modern river systems are associated with extensive human trace fossils that show a...

  10. Transition of Benthic Nutrient Sources after Engineered Levee Breaches Adjacent to Upper Klamath and Agency Lakes, Oregon

    NASA Astrophysics Data System (ADS)

    Kuwabara, J. S.; Topping, B. R.; Carter, J. L.; Parchaso, F.; Cameron, J. M.; Asbill, J. R.; Carlson, R. A.; Fend, S. V.; Engelstad, A. C.

    2010-12-01

    Nonmetallic pore-water profilers were deployed during four sampling trips between November 2007 and July 2009 after engineered levee breaches on 30 October 2007, hydrologically reconnected both Upper Klamath Lake and Agency Lake, Oregon, to adjacent wetlands. Centimeter-scale measurements of the vertical dissolved-nutrient concentration gradients from the profilers served as the basis for diffusive-flux determinations. Wetland areas undergoing restoration and those being used for water storage around these lakes function very differently than nearby established wetlands within the Upper Klamath National Wildlife Refuge. Consistent with previous results from Upper Klamath Lake, benthic flux of soluble reactive phosphorus (SRP) in the wetlands was consistently positive, and when areally and seasonally averaged over the 13 km2 newly restored wetlands, an SRP flux to the overlying water column (~87,000 kg over the 3-month cyanophyte bloom of Aphanizomenon flos-aquae (AFA)) exceeded the magnitude of riverine inputs (42,000 kg for that season). SRP benthic flux at a site within the restored wetland area ~0.5 km from the breach was elevated relative to all other lake and wetland sites (including another wetland site <0.1 km from the breached levee) in 2009 suggests that the restored wetlands, at least chemically, remain in a transition period following the hydrologic reconnection of the lake and wetland environments. Ammonium fluxes to the water column remained consistently positive throughout the sampling period, generating a toxicological concern for endangered fish populations at elevated summer pH. Soluble reactive phosphorus (SRP) concentrations were lower than detection limits (<0.03 mg-P/L) at all lake and wetland sites following the levee breaches. As indicated in previous studies, SRP concentrations for 2009 sampling trips indicated higher concentrations at the end of the annual AFA bloom relative to its beginning, suggesting a limiting factor or factors other than SRP. Our results indicated that benthic flux of iron and manganese may serve as a significant source of these essential micronutrients to the lake water column. However, for other trace metals, including those that could retard algal growth (for example, dissolved copper and zinc), water-column and porewater concentrations were low and relatively constant across the sediment-water interface. The lake and wetland benthos substantively contribute to both macro- and micronutrients in the water column. It may therefore be prudent, in terms of developing long-term management strategies for water quality in the Upper Klamath Basin, to examine the dynamics of this transition toward seasonal function that is typical of established wetlands in the vicinity with regard to nutrient (both metal and ligand) fluxes. Funding support : U.S. Bureau of Reclamation, Klamath Falls, Oregon; U.S.G.S. Toxic Substances Hydrology Program

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

    SciTech Connect

    Machrafi, Hatim; Cavadias, Simeon

    2008-12-15

    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)

  12. Gas Turbine Engine Staged Fuel Injection Using Adjacent Bluff Body and Swirler Fuel Injectors

    NASA Technical Reports Server (NTRS)

    Snyder, Timothy S. (Inventor)

    2015-01-01

    A fuel injection array for a gas turbine engine includes a plurality of bluff body injectors and a plurality of swirler injectors. A control operates the plurality of bluff body injectors and swirler injectors such that bluff body injectors are utilized without all of the swirler injectors at least at low power operation. The swirler injectors are utilized at higher power operation.

  13. Low-speed wind-tunnel investigation of a large scale advanced arrow-wing supersonic transport configuration with engines mounted above wing for upper-surface blowing

    NASA Technical Reports Server (NTRS)

    Shivers, J. P.; Mclemore, H. C.; Coe, P. L., Jr.

    1976-01-01

    Tests have been conducted in a full scale tunnel to determine the low speed aerodynamic characteristics of a large scale advanced arrow wing supersonic transport configuration with engines mounted above the wing for upper surface blowing. Tests were made over an angle of attack range of -10 deg to 32 deg, sideslip angles of + or - 5 deg, and a Reynolds number range of 3,530,000 to 7,330,000. Configuration variables included trailing edge flap deflection, engine jet nozzle angle, engine thrust coefficient, engine out operation, and asymmetrical trailing edge boundary layer control for providing roll trim. Downwash measurements at the tail were obtained for different thrust coefficients, tail heights, and at two fuselage stations.

  14. 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)

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

    1974-01-01

    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.

  15. Affordable Development and Demonstration of a Small NTR Engine and Stage: How Small is Big Enough?

    NASA Technical Reports Server (NTRS)

    Borowski, S. K.; Sefcik, R. J.; Fittje, J. E.; McCurdy, D. R.; Qualls, A. L.; Schnitzler, B. G.; Werner, J.; Weitzberg, A.; Joyner, C. R.

    2015-01-01

    In FY11, NASA formulated a plan for Nuclear Thermal Propulsion (NTP) development that included Foundational Technology Development followed by system-level Technology Demonstrations The ongoing NTP project, funded by NASAs Advanced Exploration Systems (AES) program, is focused on Foundational Technology Development and includes 5 key task activities:(1) Fuel element fabrication and non-nuclear validation testing of heritage fuel options;(2) Engine conceptual design;(3) Mission analysis and engine requirements definition;(4) Identification of affordable options for ground testing; and(5) Formulation of an affordable and sustainable NTP development program Performance parameters for Point of Departure designs for a small criticality-limited and full size 25 klbf-class engine were developed during FYs 13-14 using heritage fuel element designs for both RoverNERVA Graphite Composite (GC) and Ceramic Metal (Cermet) fuel forms To focus the fuel development effort and maximize use of its resources, the AES program decided, in FY14, that a leader-follower down selection between GC and cermet fuel was required An Independent Review Panel (IRP) was convened by NASA and tasked with reviewing the available fuel data and making a recommendation to NASA. In February 2015, the IRP recommended and the AES program endorsed GC as the leader fuel In FY14, a preliminary development schedule DDTE plan was produced by GRC, DOE industry for the AES program. Assumptions, considerations and key task activities are presented here Two small (7.5 and 16.5 klbf) engine sizes were considered for ground and flight technology demonstration within a 10-year timeframe; their ability to support future human exploration missions was also examined and a recommendation on a preferred size is provided.

  16. Primary stage I-IIE non-Hodgkin's lymphoma of uterine cervix and upper vagina: evidence for a conservative approach in a study on three patients.

    TOXLINE Toxicology Bibliographic Information

    Garavaglia E; Taccagni G; Montoli S; Panacci N; Ponzoni M; Frigerio L; Mangili G

    2005-04-01

    BACKGROUND: Non-Hodgkin's Lymphomas (NHL) frequently affect the uterine corpus, cervix, and vagina in cases of advanced disease. However, these organs are rarely the site of origin of this type of neoplasia. Because of the rarity of primary genital tract lymphomas, a standard treatment has not been defined.CASE: Three patients with large B-cell primary Non-Hodgkin's lymphoma of the lower genital tract (vaginal, cervical and cervico-vaginal) presented with bulky lesions and underwent diagnostic evaluation, staging, and chemotherapy with adriamycin-containing regimens. All three patients, including two with stage IIE and one with stage IE disease demonstrated complete remission and are alive and well without evidence of disease at 10, 7, and 6 years of follow-up, respectively.CONCLUSIONS: Our observations suggest that young patients with large B-cell lymphomas of lower genital tract stages I-IIE, even with bulky lesions, may benefit from chemotherapy alone as initial treatment.

  17. Cold-air investigation of a 3 1/2-stage fan-drive turbine with a stage loading factor of 4 designed for an integral lift engine. 1: Turbine design and performance of first stage

    NASA Technical Reports Server (NTRS)

    Whitney, W. J.; Schum, H. J.; Behning, F. P.

    1975-01-01

    The design of the 3 1/2-stage turbine is described, and the cold-air performance of the first stage, modified for axial inlet conditions, is presented. The performance of the modified single-stage turbine and of two comtemporary high-stage-loading-factor turbines is compared with that estimated with a reference prediction method.

  18. Cold-air investigation of a 31/2-stage fan-drive turbine with a stage loading factor of 4 designed for an integral lift engine. 2: Performance of 2-, 3- and 3 1/2-stage configurations

    NASA Technical Reports Server (NTRS)

    Whitney, W. J.

    1977-01-01

    The stage work distribution among the three stages was very close to the design value. The specific work output-mass flow characteristics of the three stages were closely matched. The efficiency of the 3 1/2 stage turbine at design specific work output and design speed was within 0.008 of the estimated value, and this agreement was felt to demonstrate the adequacy of the prediction method in the high stage loading factor regime.

  19. Adenosine deaminase-deficient mice generated using a two-stage genetic engineering strategy exhibit a combined immunodeficiency.

    PubMed

    Blackburn, M R; Datta, S K; Kellems, R E

    1998-02-27

    Adenosine deaminase (ADA) deficiency in humans leads to a combined immunodeficiency. The mechanisms involved in the lymphoid specificity of the disease are not fully understood due to the inaccessibility of human tissues for detailed analysis and the absence of an adequate animal model for the disease. We report the use of a two-stage genetic engineering strategy to generate ADA-deficient mice that retain many features associated with ADA deficiency in humans, including a combined immunodeficiency. Severe T and B cell lymphopenia was accompanied by a pronounced accumulation of 2'-deoxyadenosine and dATP in the thymus and spleen, and a marked inhibition of S-adenosylhomocysteine hydrolase in these organs. Accumulation of adenosine was widespread among all tissues examined. ADA-deficient mice also exhibited severe pulmonary insufficiency, bone abnormalities, and kidney pathogenesis. These mice have provided in vivo information into the metabolic basis for the immune phenotype associated with ADA deficiency. PMID:9478961

  20. Home-based neurologic music therapy for upper limb rehabilitation with stroke patients at community rehabilitation stage—a feasibility study protocol

    PubMed Central

    Street, Alexander J.; Magee, Wendy L.; Odell-Miller, Helen; Bateman, Andrew; Fachner, Jorg C.

    2015-01-01

    Background: Impairment of upper limb function following stroke is more common than lower limb impairment and is also more resistant to treatment. Several lab-based studies with stroke patients have produced statistically significant gains in upper limb function when using musical instrument playing and techniques where rhythm acts as an external time-keeper for the priming and timing of upper limb movements. Methods: For this feasibility study a small sample size of 14 participants (3–60 months post stroke) has been determined through clinical discussion between the researcher and study host in order to test for management, feasibility and effects, before planning a larger trial determined through power analysis. A cross-over design with five repeated measures will be used, whereby participants will be randomized into either a treatment (n = 7) or wait list control (n = 7) group. Intervention will take place twice weekly over 6 weeks. The ARAT and 9HPT will be used to measure for quantitative gains in arm function and finger dexterity, pre/post treatment interviews will serve to investigate treatment compliance and tolerance. A lab based EEG case comparison study will be undertaken to explore audio-motor coupling, brain connectivity and neural reorganization with this intervention, as evidenced in similar studies. Discussion: Before evaluating the effectiveness of a home-based intervention in a larger scale study, it is important to assess whether implementation of the trial methodology is feasible. This study investigates the feasibility, efficacy and patient experience of a music therapy treatment protocol comprising a chart of 12 different instrumental exercises and variations, which aims at promoting measurable changes in upper limb function in hemiparetic stroke patients. The study proposes to examine several new aspects including home-based treatment and dosage, and will provide data on recruitment, adherence and variability of outcomes. PMID:26441586

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

    NASA Technical Reports Server (NTRS)

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

    1983-01-01

    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.

  2. Advanced expander test bed engine

    NASA Technical Reports Server (NTRS)

    Mitchell, J. P.

    1992-01-01

    The Advanced Expander Test Bed (AETB) is a key element in NASA's Space Chemical Engine Technology Program for development and demonstration of expander cycle oxygen/hydrogen engine and advanced component technologies applicable to space engines as well as launch vehicle upper stage engines. The AETB will be used to validate the high pressure expander cycle concept, study system interactions, and conduct studies of advanced mission focused components and new health monitoring techniques in an engine system environment. The split expander cycle AETB will operate at combustion chamber pressures up to 1200 psia with propellant flow rates equivalent to 20,000 lbf vacuum thrust.

  3. Cyclothem [“digital”] correlation and biostratigraphy across the global Moscovian-Kasimovian-Gzhelian stage boundary interval (Middle-Upper Pennsylvanian) in North America and eastern Europe

    NASA Astrophysics Data System (ADS)

    Heckel, Philip H.; Alekseev, Aleksandr S.; Barrick, James E.; Boardman, Darwin R.; Goreva, Natalya V.; Nemyrovska, Tamara I.; Ueno, Katsumi; Villa, Elisa; Work, David M.

    2007-07-01

    The long-standing difficulty of correlating Pennsylvanian strata among provincial faunal regions is resolved by effecting “digital” correlation of major glacial-eustatic cyclothems that represent high-stands when certain species achieved more global distribution than usual. In the late Moscovian-early Gzhelian (late Desmoinesian-early Virgilian) succession in the midcontinent United States, several major cyclothems are correlated, by both conodont species in common and cyclothem scale, with cyclothems in Russia (Moscow Basin) and Ukraine (Donets Basin), and the remaining cyclothems fit into the framework by position and scale. In this way the suggested event marker for the global Kasimovian-Gzhelian stage boundary (first appearance of Idiognathodus simulator) is supported, while possible event markers for the Moscovian-Kasimovian boundary await further evaluation.

  4. Regional anesthesia for an upper extremity amputation for palliative care in a patient with end-stage osteosarcoma complicated by a large anterior mediastinal mass

    PubMed Central

    Hakim, Mumin; Burrier, Candice; Bhalla, Tarun; Raman, Vidya T; Martin, David P; Dairo, Olamide; Mayerson, Joel L; Tobias, Joseph D

    2015-01-01

    Tumor progression during end-of-life care can lead to significant pain, which at times may be refractory to routine analgesic techniques. Although regional anesthesia is commonly used for postoperative pain care, there is limited experience with its use during home hospice care. We present a 24-year-old male with end-stage metastatic osteosarcoma who required anesthetic care for a right-sided above-the-elbow amputation. The anesthetic management was complicated by the presence of a large mediastinal mass, limited pulmonary reserve, and severe chronic pain with a high preoperative opioid requirement. Intraoperative anesthesia and postoperative pain management were provided by regional anesthesia using an interscalene catheter. He was discharged home with the interscalene catheter in place with a continuous local anesthetic infusion that allowed weaning of his chronic opioid medications and the provision of effective pain control. The perioperative applications of regional anesthesia in palliative and home hospice care are discussed. PMID:26442759

  5. Post-disposal orbital evolution of satellites and upper stages used by the GPS and GLONASS navigation constellations: The long-term impact on the Medium Earth Orbit environment

    NASA Astrophysics Data System (ADS)

    Pardini, Carmen; Anselmo, Luciano

    2012-08-01

    The long-term evolution and environmental impact in MEO of all the abandoned spacecraft and upper stages associated with the GPS and GLONASS navigation constellations were analyzed. The orbits of the disposed objects, as of 1 May 2011, were propagated for 200 years and snapshots of their evolving distribution were obtained, together with an estimation of the changing collision probability with the spacecraft of the operational navigation systems existing or planned in MEO, i.e., GLONASS, GPS, Beidou and Galileo. The probability that the abandoned objects considered will collide with the operational spacecraft of the navigation constellations is very low, even taking into account the intrinsic eccentricity instability of the disposal orbits. Assuming the present or envisaged configuration of the constellations in MEO, the probability of collision, integrated over 200 years, would be <1/300 with a GLONASS spacecraft, <1/15,000 with a GPS or Beidou spacecraft, and <1/250,000 with a Galileo spacecraft. The worst disposal strategy consists in abandoning satellites and upper stages close to the altitude of the operational constellation (GLONASS), while a re-orbiting a few hundred km away (GPS) is able to guarantee an effective long-term dilution of the collision risk, irrespective of the eccentricity instability due to geopotential and luni-solar perturbations. The disposal strategies applied so far to the GPS satellites should be able to guarantee for at least a few centuries a sustainable MEO environment free of collisions among intact objects. Consequently, there would be no need to adopt disposal schemes targeting also the optimal value of the eccentricity vector. However, it should be pointed out that the GPS disposal strategy was devised well in advance of the Beidou constellation announcement, so most of the abandoned satellites were re-orbited fairly close to the altitude of the new Chinese system. A new re-orbiting approach will be therefore needed in the future.

  6. Performance of a 13-Stage Development Compressor for the J40-WE-24 Engine at Equivalent Speeds from 30 to 112 Percent of Design

    NASA Technical Reports Server (NTRS)

    Hatch, James E.; Lucas, James G.; Finger, Harold B.

    1953-01-01

    The performance of a 13-stage development comressor for the J40-WE-24 engine has been determined at equivalent speeds from 30 to 112 percent of design. The design total-pressure ratio of 6.0 and the design weight flow of 164 pounds per second were not attained, An analysis was conducted to determine the reasons for the poor performance at the design and over-design speed. The analysis indicated that most of the difficulty could be attributed to the fact that the first stage was overcompromised to favor part-speed performance,

  7. J-2X, The Engine of the Future

    NASA Technical Reports Server (NTRS)

    Smith, Gail

    2009-01-01

    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.

  8. Energia's next stage

    NASA Astrophysics Data System (ADS)

    Clark, Phillip S.

    1990-02-01

    The current status and future of the Soviet Energia heavy-lift launcher is reviewed. A rational use for this vehicle is being explored that would justify its high development and per-mission cost, and help to silence the vocal criticism of this expenditure. Operational experience and some possible developments of this launcher are discussed. It is noted that two totally different powerplants are being developed as upper stages for Energia. This disproves earlier theories that the Zenit second stage was destined for this role. According to mission requirements, either engine may be used alone, or both may be enclosed in the cargo container. Mention is made of a two-booster version that could fly as soon as 1995. With a lift capability of 65 t to LEO, this would be almost an exact counterpart to NASA's proposed Shuttle-C. It is concluded, that at some future time, Lunar and Mars missions will almost certainly be undertaken, in cooperation with NASA or other agencies. When the time is appropriate for such ventures, the Energia system should be well proven as a ready-made transportation mode, and a very valid contender for Soviet participation.

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

    SciTech Connect

    Ernest A. Mancini

    2001-09-14

    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.

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

    SciTech Connect

    Ernest A. Mancini

    2002-09-25

    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 2 of the project has been reservoir characterization, 3-D modeling and technology transfer. This effort has included six tasks: (1) the study of rockfluid interactions, (2) petrophysical and engineering characterization, (3) data integration, (4) 3-D geologic modeling, (5) 3-D reservoir simulation and (6) technology transfer. This work was scheduled for completion in Year 2. 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 is near completion. 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 has been essentially completed. Porosity and permeability data at Appleton and Vocation Fields have been analyzed, and well performance analysis has been conducted. Data integration is up to date, 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. 3-D geologic modeling of the structures and reservoirs at Appleton and Vocation Fields has been completed. The model represents an integration of geological, petrophysical and seismic data. 3-D reservoir simulation of the reservoirs at Appleton and Vocation Fields has been completed. The 3-D geologic model served as the framework for the simulations. A technology workshop on reservoir characterization and modeling at Appleton and Vocation Fields was conducted to transfer the results of the project to the petroleum industry.

  11. 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)

    1976-01-01

    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.

  12. Effect of Modifications to Induction System on Altitude Performance of V-1710-93 Engine III : Use of Parabolic Rotating Guide Vanes and NACA Designed Auxiliary-stage Inlet Elbow and Interstage Duct

    NASA Technical Reports Server (NTRS)

    Standahar, Ray M; Mccarty, James S

    1947-01-01

    Bench runs of a modified V-1710-93 engine equipped with a two-stage supercharger, interstage carburetor, aftercooler assembly, and backfire screens have been made at a simulated altitude of 29,000 feet to determine the effect of several induction-system modifications on the engine and supercharger performance. The standard guide vanes on the auxiliary- and engine-stage superchargers were replaced by rotating guide vanes with a parabolic blade profile. The auxiliary-stage inlet elbow and interstage duct were replaced with new units of NACA design. These modifications were made one at a time and data were obtained after each change to determine the effect of each modification. All runs were made at a constant engine speed of 3000 rpm at a simulated altitude of 29,000 feet and all changes in engine power were made by varying the speed of the auxiliary-stage supercharger.

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

    NASA Technical Reports Server (NTRS)

    Williams, Tom; Cannon, Scott

    2006-01-01

    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.

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

    SciTech Connect

    Ernest A. Mancini

    2003-09-25

    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 that 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 3 of the project has been reservoir characterization, 3-D modeling, testing of the geologic-engineering model, and technology transfer. This effort has included six tasks: (1) the study of seismic attributes, (2) petrophysical characterization, (3) data integration, (4) the building of the geologic-engineering model, (5) the testing of the geologic-engineering model and (6) technology transfer. This work was scheduled for completion in Year 3. Progress on the project is as follows: geoscientific reservoir characterization is 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 completed. 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 has been completed. Porosity and permeability data at Appleton and Vocation Fields have been analyzed, and well performance analysis has been conducted. Data integration is up to date, 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. 3-D geologic modeling of the structures and reservoirs at Appleton and Vocation Fields has been completed. The models represent an integration of geological, petrophysical and seismic data. 3-D reservoir simulation of the reservoirs at Appleton and Vocation Fields has been completed. The 3-D geologic models served as the framework for the simulations. The geologic-engineering models of the Appleton and Vocation Field reservoirs have been developed. These models are being tested. The geophysical interpretation for the paleotopographic feature being tested has been made, and the study of the data resulting from drilling of a well on this paleohigh is in progress. Numerous presentations on reservoir characterization and modeling at Appleton and Vocation Fields have been made at professional meetings and conferences and a short course on microbial reservoir characterization and modeling based on these fields has been prepared.

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

    USGS Publications Warehouse

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

    2012-01-01

    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.

  16. The Role of Functionality in the Mental Representations of Engineering Students: Some Differences in the Early Stages of Expertise

    ERIC Educational Resources Information Center

    Moss, Jarrod; Kotovsky, Kenneth; Cagan, Jonathan

    2006-01-01

    As engineers gain experience and become experts in their domain, the structure and content of their knowledge changes. Two studies are presented that examine differences in knowledge representation among freshman and senior engineering students. The first study examines recall of mechanical devices and chunking of components, and the second…

  17. Planar LIF observation of unburned fuel escaping the upper ring-land crevice in an SI engine

    SciTech Connect

    Green, R.M.; Cloutman, L.D.

    1997-01-01

    PLIF has been used to observe the in-cylinder transport of unburned fuel that, while trapped in the ring-land and ring-groove crevices, survives combustion in the propagating flame. Away from the top-ring gap, we detect a wall-jet comprised of unburned charge exiting the top ring-land crevice opening. At the location of the top-ring gap, we observed unburned fuel lying in the cool boundary layer along the cylinder wall during the later stages of the expansion stroke. This layer is scraped into the roll-up vortex during the exhaust stroke. These data lead us to conclude that away from the end gap, unburned, high pressure charge, trapped between the two compression rings escapes as a wall jet after ring-reversal near the bottom center. Conversely, at the ring gap, when the cylinder pressure drops below the pressure between the compression rings, the trapped charge escapes through the gap and forms a thin layer on the cylinder wall.

  18. SLS Dual Use Upper Stage (DUUS) Opportunities

    NASA Technical Reports Server (NTRS)

    Creech, Steve; Holladay, Jon; Jones, Davey

    2013-01-01

    Objective: Provide an overview of SLS DUUS type capability requirements to provide context for possible International Partner collaboration. Addition of a DUUS would greatly increase exploration mission capture and performance margin for cis-Lunar and Near Earth System exploration campaigns.

  19. Low speed inducers for cryogenic upper stages

    NASA Technical Reports Server (NTRS)

    King, J. A.

    1973-01-01

    Briefing charts are presented, which were used in an oral presentation of the results and recommendations for the design and analysis of low speed hydrogen and oxygen inducers and their drive systems applicable to the space tug. A discussion of the design of the 15K and RL-10 inducers is included.

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

    SciTech Connect

    Ernest A. Mancini

    2004-02-25

    The University of Alabama, in cooperation with Texas A&M University, McGill University, Longleaf Energy Group, Strago Petroleum Corporation, and Paramount Petroleum Company, has undertaken 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 goal 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. Geoscientific reservoir property, geophysical seismic attribute, petrophysical property, and engineering property characterization has shown that reef (thrombolite) and shoal reservoir lithofacies developed on the flanks of high-relief crystalline basement paleohighs (Vocation Field example) and on the crest and flanks of low-relief crystalline basement paleohighs (Appleton Field example). The reef thrombolite lithofacies have higher reservoir quality than the shoal lithofacies due to overall higher permeabilities and greater interconnectivity. Thrombolite dolostone flow units, which are dominated by dolomite intercrystalline and vuggy pores, are characterized by a pore system comprised of a higher percentage of large-sized pores and larger pore throats. Rock-fluid interactions (diagenesis) studies have shown that although the primary control on reservoir architecture and geographic distribution of Smackover reservoirs is the fabric and texture of the depositional lithofacies, diagenesis (chiefly dolomitization) is a significant factor that preserves and enhances reservoir quality. The evaporative pumping mechanism is favored to explain the dolomitization of the thrombolite doloboundstone and dolostone reservoir flow units at Appleton and Vocation Fields. Geologic modeling, reservoir simulation, and the testing and applying the resulting integrated geologic-engineering models have shown that little oil remains to be recovered at Appleton Field and a significant amount of oil remains to be recovered at Vocation Field through a strategic infill drilling program. The drive mechanisms for primary production in Appleton and Vocation Fields remain effective; therefore, the initiation of a pressure maintenance program or enhanced recovery project is not required at this time. The integrated geologic-engineering model developed for a low-relief paleohigh (Appleton Field) was tested for three scenarios involving the variables of present-day structural elevation and the presence/absence of potential reef thrombolite lithofacies. In each case, the predictions based upon the model were correct. From this modeling, the characteristics of the ideal prospect in the basement ridge play include a low-relief paleohigh associated with dendroidal/chaotic thrombolite doloboundstone and dolostone that has sufficient present-day structural relief so that these carbonates rest above the oil-water contact. Such a prospect was identified from the modeling, and it is located northwest of well Permit No. 3854B (Appleton Field) and south of well No. Permit No.11030B (Northwest Appleton Field).

  1. Cold-air performance of compressor-drive turbine of Department of Energy upgraded automobile gas turbine engine. 2: Stage performance

    NASA Technical Reports Server (NTRS)

    Roelke, R. J.; Haas, J. E.

    1982-01-01

    The aerodynamic performance of the compressor-drive turbine of the DOE upgraded gas turbine engine was determined in low temperature air. The as-received cast rotor blading had a significantly thicker profile than design and a fairly rough surface finish. Because of these blading imperfections a series of stage tests with modified rotors were made. These included the as-cast rotor, a reduced-roughness rotor, and a rotor with blades thinned to near design. Significant performance changes were measured. Tests were also made to determine the effect of Reynolds number on the turbine performance. Comparisons are made between this turbine and the compressor-drive turbine of the DOE baseline gas turbine engine.

  2. The effects of compressor seventh-stage bleed air extraction on performance of the F100-PW-220 afterburning turbofan engine

    NASA Technical Reports Server (NTRS)

    Evans, Alison B.

    1991-01-01

    A study was conducted to determine the effects of seventh-stage compressor bleed on the performance of the F100 afterburning turbofan engine. The effects of bleed on thrust, specific fuel consumption, fan turbine inlet temperature, bleed total pressure, and bleed total temperature were obtained from the engine manufacturer's status deck computer simulation. These effects were determined for power settings of intermediate, partial afterburning, and maximum afterburning for Mach numbers between 0.6 and 2.2 and for altitudes of 30,000, 40,000, and 50,000 ft. It was found that thrust loss and specific fuel consumption increase were approximately linear functions of bleed flow and, based on a percent-thrust change basis, were approximately independent of power setting.

  3. Staged cascade fluidized bed combustor

    DOEpatents

    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

    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.

  4. Assessment of crack growth in a space shuttle main engine first-stage, high-pressure fuel turbopump blade

    NASA Technical Reports Server (NTRS)

    Abdul-Aziz, Ali

    1993-01-01

    A two-dimensional finite element fracture mechanics analysis of a space shuttle main engine (SSME) turbine blade firtree was performed using the MARC finite element code. The analysis was conducted under combined effects of thermal and mechanical loads at steady-state conditions. Data from a typical engine stand cycle of the SSME were used to run a heat transfer analysis and, subsequently, a thermal structural fracture mechanics analysis. Temperature and stress contours for the firtree under these operating conditions were generated. High stresses were found at the firtree lobes where crack initiation was triggered. A life assessment of the firtree was done by assuming an initial and a final crack size.

  5. Affordable Development and Demonstration of a Small NTR engine and Stage: A Preliminary NASA, DOE, and Industry Assessment

    NASA Technical Reports Server (NTRS)

    Borowski, S. K.; Sefcik, R. J.; Fittje, J. E.; McCurdy, D. R.; Qualls, A. L.; Schnitzler, B. G; Werner, J.; Weitzberg, A.; Joyner, C. R.

    2015-01-01

    In FY'11, Nuclear Thermal Propulsion (NTP) was identified as a key propulsion option under the Advanced In-Space Propulsion (AISP) component of NASA's Exploration Technology Development and Demonstration (ETDD) program A strategy was outlined by GRC and NASA HQ that included 2 key elements -"Foundational Technology Development" followed by specific "Technology Demonstration" projects. The "Technology Demonstration "element proposed ground technology demonstration (GTD) testing in the early 2020's, followed by a flight technology demonstration (FTD) mission by approx. 2025. In order to reduce development costs, the demonstration projects would focus on developing a small, low thrust (approx. 7.5 -16.5 klb(f)) engine that utilizes a "common" fuel element design scalable to the higher thrust (approx. 25 klb(f)) engines used in NASA's Mars DRA 5.0 study(NASA-SP-2009-566). Besides reducing development costs and allowing utilization of existing, flight proven engine hard-ware (e.g., hydrogen pumps and nozzles), small, lower thrust ground and flight demonstration engines can validate the technology and offer improved capability -increased payloads and decreased transit times -valued for robotic science missions identified in NASA's Decadal Study.

  6. 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)

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

    1995-01-01

    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.

  7. Two-stage Supercharging

    NASA Technical Reports Server (NTRS)

    Buck, Richard S

    1941-01-01

    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.

  8. Two stage turbine for rockets

    NASA Astrophysics Data System (ADS)

    Veres, Joseph P.

    1993-11-01

    The aerodynamic design and rig test evaluation of a small counter-rotating turbine system is described. The advanced turbine airfoils were designed and tested by Pratt & Whitney. The technology represented by this turbine is being developed for a turbopump to be used in an advanced upper stage rocket engine. The advanced engine will use a hydrogen expander cycle and achieve high performance through efficient combustion of hydrogen/oxygen propellants, high combustion pressure, and high area ratio exhaust nozzle expansion. Engine performance goals require that the turbopump drive turbines achieve high efficiency at low gas flow rates. The low mass flow rates and high operating pressures result in very small airfoil heights and diameters. The high efficiency and small size requirements present a challenging turbine design problem. The shrouded axial turbine blades are 50 percent reaction with a maximum thickness to chord ratio near 1. At 6 deg from the tangential direction, the nozzle and blade exit flow angles are well below the traditional design minimum limits. The blade turning angle of 160 deg also exceeds the maximum limits used in traditional turbine designs.

  9. Engineering and Two-Stage Evolution of a Lignocellulosic Hydrolysate-Tolerant Saccharomyces cerevisiae Strain for Anaerobic Fermentation of Xylose from AFEX Pretreated Corn Stover

    PubMed Central

    Parreiras, Lucas S.; Breuer, Rebecca J.; Avanasi Narasimhan, Ragothaman; Higbee, Alan J.; La Reau, Alex; Tremaine, Mary; Qin, Li; Willis, Laura B.; Bice, Benjamin D.; Bonfert, Brandi L.; Pinhancos, Rebeca C.; Balloon, Allison J.; Uppugundla, Nirmal; Liu, Tongjun; Li, Chenlin; Tanjore, Deepti; Ong, Irene M.; Li, Haibo; Pohlmann, Edward L.; Serate, Jose; Withers, Sydnor T.; Simmons, Blake A.; Hodge, David B.; Westphall, Michael S.; Coon, Joshua J.; Dale, Bruce E.; Balan, Venkatesh; Keating, David H.; Zhang, Yaoping; Landick, Robert; Gasch, Audrey P.; Sato, Trey K.

    2014-01-01

    The inability of the yeast Saccharomyces cerevisiae to ferment xylose effectively under anaerobic conditions is a major barrier to economical production of lignocellulosic biofuels. Although genetic approaches have enabled engineering of S. cerevisiae to convert xylose efficiently into ethanol in defined lab medium, few strains are able to ferment xylose from lignocellulosic hydrolysates in the absence of oxygen. This limited xylose conversion is believed to result from small molecules generated during biomass pretreatment and hydrolysis, which induce cellular stress and impair metabolism. Here, we describe the development of a xylose-fermenting S. cerevisiae strain with tolerance to a range of pretreated and hydrolyzed lignocellulose, including Ammonia Fiber Expansion (AFEX)-pretreated corn stover hydrolysate (ACSH). We genetically engineered a hydrolysate-resistant yeast strain with bacterial xylose isomerase and then applied two separate stages of aerobic and anaerobic directed evolution. The emergent S. cerevisiae strain rapidly converted xylose from lab medium and ACSH to ethanol under strict anaerobic conditions. Metabolomic, genetic and biochemical analyses suggested that a missense mutation in GRE3, which was acquired during the anaerobic evolution, contributed toward improved xylose conversion by reducing intracellular production of xylitol, an inhibitor of xylose isomerase. These results validate our combinatorial approach, which utilized phenotypic strain selection, rational engineering and directed evolution for the generation of a robust S. cerevisiae strain with the ability to ferment xylose anaerobically from ACSH. PMID:25222864

  10. The Scribble Stage

    ERIC Educational Resources Information Center

    Douglas, Katherine

    2012-01-01

    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…

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

    SciTech Connect

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

    1989-01-01

    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.

  12. Integrated Modular Engine technology needs

    NASA Astrophysics Data System (ADS)

    Harmon, Timothy J.; Briley, Gary; Pauckert, Ron; Vilja, John

    1993-06-01

    An Integrated Modular Engine (IME) system conceptual design has been developed for meeting the upper stage propulsion requirements. This design was used to identify key technical areas for further development and demonstration. A number of factors are favorable for introducing advanced technologies: new materials are available, controls and health monitoring are vastly more capable, and new fabrication methods are coming on-line. Furthermore, recent innovative integrated propulsion system architecture designs leverage the benefits throughout the stage. All needed technologies are compatible with near-term initial launch capability around the year 2000. These technologies do not require extensive, time-consuming, or expensive development programs to bring these technologies to fruition. This paper describes those technologies that need to be developed to support an IME development program which would result in an affordable propulsion system applicable to a wide range of missions, i.e., upper stage, space-based, transfer, lunar lander, lunar ascent, and Mars lander propulsion systems.

  13. J-2 Engine Test

    NASA Technical Reports Server (NTRS)

    1963-01-01

    Smokeless flame juts from the diffuser of a unique vacuum chamber in which the upper stage rocket engine, the hydrogen fueled J-2, was tested at a simulated space altitude in excess of 60,000 feet. The smoke you see is actually steam. In operation, vacuum is established by injecting steam into the chamber and is maintained by the thrust of the engine firing through the diffuser. The engine was tested in this environment for start, stop, coast, restart, and full-duration operations. The chamber was located at Rocketdyne's Propulsion Field Laboratory, in the Santa Susana Mountains, near Canoga Park, California. The J-2 engine was developed by Rocketdyne for the Marshall Space Flight Center.

  14. 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)

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

    2000-01-01

    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.

  15. Stage Separation Failure: Model Based Diagnostics and Prognostics

    NASA Technical Reports Server (NTRS)

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

    2010-01-01

    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.

  16. Lernpunkt Deutsch--Stage 1.

    ERIC Educational Resources Information Center

    Theil, Elvira

    1997-01-01

    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…

  17. 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)

    Phelps, A. E., III

    1977-01-01

    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.

  18. One-stage tissue engineering of bladder wall patches for an easy-to-use approach at the surgical table.

    PubMed

    Ajalloueian, Fatemeh; Zeiai, Said; Rojas, Ramiro; Fossum, Magdalena; Hilborn, Jöns

    2013-09-01

    We present a method for producing a cell-scaffold hybrid construct at the bedside. The construct is composed of plastic-compressed collagen together with a poly(?-caprolactone) (PCL)-knitted mesh that yields an integrated, natural-synthetic scaffold. This construct was evaluated by seeding of minced bladder mucosa, followed by proliferation in vitro. High mechanical strength in combination with a biological environment suitable for tissue growth was achieved through the creation of a hybrid construct that showed an increased tensile strength (17.9 ± 2.6?MPa) when compared to plastic-compressed collagen (0.6 ± 0.12?MPa). Intimate contact between the collagen and the PCL fabric was required to ensure integrity without delamination of the construct. This contact was achieved by surface alkaline hydrolysis of the PCL, followed by adsorption of poly(vinyl) alcohol. The improvement in hydrophilicity of the PCL-knitted mesh was confirmed through water contact angle measurements, and penetration of the collagen into the mesh was evaluated by scanning electron microscopy (SEM). Particles of minced bladder mucosa tissue were seeded onto this scaffold, and the proliferation was followed for 6 weeks in vitro. Results obtained from phase contrast microscopy, SEM, and histological staining indicated that cells migrated from the minced tissue particles and reorganized on the scaffold. Cells were viable and proliferative, with morphological features characteristic of urothelial cells. Proliferation reached the point at which a multilayer with a resemblance to stratified urothelium was achieved. This successful method could potentially be used for in vivo applications in reconstructive urology as an engineered autologous tissue transplant without the requirement for in vitro culture before transplantation. PMID:23327166

  19. Cryogenic Propulsion Stage

    NASA Technical Reports Server (NTRS)

    Jones, David

    2011-01-01

    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.

  20. Stennis engineer part of LCROSS moon mission

    NASA Technical Reports Server (NTRS)

    2009-01-01

    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.'

  1. Upper ministernotomy.

    PubMed

    Reser, Diana; Holubec, Tomas; Scherman, Jacques; Yilmaz, Murat; Guidotti, Andrea; Maisano, Francesco

    2015-01-01

    During the past 50 years, median sternotomy has been the gold standard approach in cardiac surgery with excellent long-term outcomes. However, since the 1990s, minimally invasive cardiac surgery (MICS) has gained wide acceptance due to patient and economic demand. The advantages include less surgical trauma, less bleeding, less wound infections, less pain and faster recovery of the patients. One of these MICS approaches is the J-shaped upper ministernotomy which results in favourable long-term outcomes even in elderly and redo patients when compared with conventional sternotomy. Owing to its similarity to a full midline sternotomy, it has become the most popular MICS approach besides a mini-thoracotomy. It is a safe and feasible access, but certain recognized principles are mandatory to minimize complications. After identification of the landmarks, the 5-cm skin incision is performed in the midline between the second and fourth rib. The third or fourth right intercostal space is located and dissected laterally off the sternum. After osteotomy, the pericardium is pulled up with stay sutures which allow excellent exposure. The surgical procedures are performed in a standard fashion with central cannulation. Continuous CO2 insufflation is used to minimize the risk of air embolism. Epicardial pacing wires are placed before the removal of the aortic cross-clamp and one chest tube is used. Sternal closure is achieved with three to five stainless steel wires. The pectoral muscle, subcutaneous tissue and skin are adapted with resorbable running sutures. When performed properly, complications are rare (conversion, bleeding and wound infection) and well manageable. PMID:26530961

  2. Identifying the ionically bound cell wall and intracellular glycoside hydrolases in late growth stage Arabidopsis stems: implications for the genetic engineering of bioenergy crops.

    PubMed

    Wei, Hui; Brunecky, Roman; Donohoe, Bryon S; Ding, Shi-You; Ciesielski, Peter N; Yang, Shihui; Tucker, Melvin P; Himmel, Michael E

    2015-01-01

    Identifying the cell wall-ionically bound glycoside hydrolases (GHs) in Arabidopsis stems is important for understanding the regulation of cell wall integrity. For cell wall proteomics studies, the preparation of clean cell wall fractions is a challenge since cell walls constitute an open compartment, which is more likely to contain a mixture of intracellular and extracellular proteins due to cell leakage at the late growth stage. Here, we utilize a CaCl2-extraction procedure to isolate non-structural proteins from Arabidopsis whole stems, followed by the in-solution and in-gel digestion methods coupled with Nano-LC-MS/MS, bioinformatics and literature analyses. This has led to the identification of 75 proteins identified using the in-solution method and 236 proteins identified by the in-gel method, among which about 10% of proteins predicted to be secreted. Together, eight cell wall proteins, namely AT1G75040, AT5G26000, AT3G57260, AT4G21650, AT3G52960, AT3G49120, AT5G49360, and AT3G14067, were identified by the in-solution method; among them, three were the GHs (AT5G26000, myrosinase 1, GH1; AT3G57260, ?-1,3-glucanase 2, GH17; AT5G49360, bifunctional XYL 1/?-L-arabinofuranosidase, GH3). Moreover, four more GHs: AT4G30270 (xyloglucan endotransferase, GH16), AT1G68560 (bifunctional ?-l-arabinofuranosidase/XYL, GH31), AT1G12240 (invertase, GH32) and AT2G28470 (?-galactosidase 8, GH35), were identified by the in-gel solution method only. Notably, more than half of above identified GHs are xylan- or hemicellulose-modifying enzymes, and will likely have an impact on cellulose accessibility, which is a critical factor for downstream enzymatic hydrolysis of plant tissues for biofuels production. The implications of these cell wall proteins identified at the late growth stage for the genetic engineering of bioenergy crops are discussed. PMID:26029221

  3. Identifying the ionically bound cell wall and intracellular glycoside hydrolases in late growth stage Arabidopsis stems: implications for the genetic engineering of bioenergy crops

    PubMed Central

    Wei, Hui; Brunecky, Roman; Donohoe, Bryon S.; Ding, Shi-You; Ciesielski, Peter N.; Yang, Shihui; Tucker, Melvin P.; Himmel, Michael E.

    2015-01-01

    Identifying the cell wall-ionically bound glycoside hydrolases (GHs) in Arabidopsis stems is important for understanding the regulation of cell wall integrity. For cell wall proteomics studies, the preparation of clean cell wall fractions is a challenge since cell walls constitute an open compartment, which is more likely to contain a mixture of intracellular and extracellular proteins due to cell leakage at the late growth stage. Here, we utilize a CaCl2-extraction procedure to isolate non-structural proteins from Arabidopsis whole stems, followed by the in-solution and in-gel digestion methods coupled with Nano-LC-MS/MS, bioinformatics and literature analyses. This has led to the identification of 75 proteins identified using the in-solution method and 236 proteins identified by the in-gel method, among which about 10% of proteins predicted to be secreted. Together, eight cell wall proteins, namely AT1G75040, AT5G26000, AT3G57260, AT4G21650, AT3G52960, AT3G49120, AT5G49360, and AT3G14067, were identified by the in-solution method; among them, three were the GHs (AT5G26000, myrosinase 1, GH1; AT3G57260, ?-1,3-glucanase 2, GH17; AT5G49360, bifunctional XYL 1/?-L-arabinofuranosidase, GH3). Moreover, four more GHs: AT4G30270 (xyloglucan endotransferase, GH16), AT1G68560 (bifunctional ?-l-arabinofuranosidase/XYL, GH31), AT1G12240 (invertase, GH32) and AT2G28470 (?-galactosidase 8, GH35), were identified by the in-gel solution method only. Notably, more than half of above identified GHs are xylan- or hemicellulose-modifying enzymes, and will likely have an impact on cellulose accessibility, which is a critical factor for downstream enzymatic hydrolysis of plant tissues for biofuels production. The implications of these cell wall proteins identified at the late growth stage for the genetic engineering of bioenergy crops are discussed. PMID:26029221

  4. Engineeringtechnology COLLEGE of ENGINEERING

    E-print Network

    Berdichevsky, Victor

    . Engineering Technologists (ET) literally create the objects we depend on, from smartphones to suspension bridges and everything in between. While traditional engineers work mainly in the conceptual stage

  5. 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

    2013-01-01

    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/]). PMID:24103561

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

    NASA Technical Reports Server (NTRS)

    1991-01-01

    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.

  7. H-1 Engine

    NASA Technical Reports Server (NTRS)

    2004-01-01

    H-1 engine major components with callouts (chart 1). The H-1 engine was used in a cluster of eight on the the first stage of Saturn I (S-I stage) and Saturn IB (S-IB stage). The engines were arranged in a double pattern: four engines, located inboard, were fixed in a square pattern around the stage axis, while the remaining four engines were located outboard in a larger square pattern and each outer engine was gimbaled. Each H-1 engine had a thrust of 188,000 pounds for a combined thrust of over 1,500,000 pounds.

  8. H-1 Engine

    NASA Technical Reports Server (NTRS)

    2004-01-01

    H-1 Engine major components with callouts (chart 1): The H-1 engine was used in a cluster of eight on the the first stage of Saturn I (S-I stage) and Saturn IB (S-IB stage). The engines were arranged in a double pattern: four engines, located inboard, were fixed in a square pattern around the stage axis, while the remaining four engines were located outboard in a larger square pattern and each outer engine was gimbaled. Each H-1 engine had a thrust of 188,000 pounds for a combined thrust of over 1,500,000 pounds.

  9. The use of retro- and scenario-modeling to assess effects of 100+ years river of engineering and land-cover change on Middle and Lower Mississippi River flood stages

    NASA Astrophysics Data System (ADS)

    Remo, Jonathan W. F.; Pinter, Nicholas; Heine, Reuben

    2009-10-01

    SummarySince the 19th century, the Middle and Lower Mississippi River (MMR and LMR) have been intensively modified for flood protection and commercial navigation. In order to quantify the effects of levee expansion, channel modification, and land-cover change upon flood stages, we have developed 1-D unsteady-flow models of multiple historical reference conditions ("retro-models") for three large study reaches (225-315 km each): one along the MMR and two reaches along the LMR. For each reference condition, four 1-D unsteady-flow models were developed. These models include a calibrated model of actual conditions and three "scenario" models: (1) a model with levees of the next time step, (2) a model with the channel geometry of the next time step, and (3) a model with floodplain roughness (i.e., land cover) of the next time step. Comparison of the model for actual conditions and the scenario models provide a quantitative assessment of levee expansion, channel modification, and land-cover change on stage. Scenario modeling suggests that the majority (38-70%) of the changes in flood stage on the LMR and MMR study reaches can be attributed to changes in channel geometry and hydraulic roughness. Levees were the next largest contributor to changes in flood stage. For time steps with significant levee expansion, these structures increase stage up to 1.0 m. Observed changes in floodplain land cover were associated with little (or none) of the increase in flood stage. These result show changes in channel geometry and roughness related to river engineering tools employed for improving navigation and flood protection are the principal drivers of historic changes in flood stages along these investigated reaches.

  10. Ares I-X First Stage Separation Loads and Dynamics Reconstruction

    NASA Technical Reports Server (NTRS)

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

    2011-01-01

    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.

  11. Engineering support services for the DOE/GRI coal-gasification research program. Evaluation of the data base for single-stage gasification of peat. [IGT 6 inch, single stage, fluidized bed (not PEATGAS)

    SciTech Connect

    Bostwick, L.E.; Hubbard, D.A.; Shah, K.V.; Do, L.T.

    1982-03-01

    Kellogg has reviewed the data base generated by IGT in the 6 inch PDU for the single stage fluidized bed gasification of peat. Kellogg's central finding is that the existing data base should be expanded by further testing in the PDU, after necessary modifications, to investigate further the effects of operating parameters within the ranges of interest. The existing data base consists of 20 PDU runs. Kellogg has concentrated on the Minnesota peat data base, since an insufficient number of runs exist for Maine and North Carolina peats to establish any valid trends. Consequently, the evaluation presented concerns only the Minnesota peat data base with respect to ranges of operating parameters studied, the criteria for good fluidized-bed operation and the effects of the key operating parameters on the performance. In Kellogg's opinion the existing data base demonstrates that: gasification of peat at 90+% carbon conversion is possible in a single stage fluidized bed reactor; the most significant operating parameters have been identified; the single stage fluidized bed peat gasifier has merit because of simplicity of operation, near-zero production of liquids and potential of operation without steam and at low pressure. However, Kellogg notes the following shortcomings:relatively small number of experimental runs and lack of data at certain levels of operating parameters studied; sintering occurred in 35% of the runs; in all the 20 test runs, fines losses exceeded in 5% of the feed and for the Minnesota peat data base, fines losses averaged 12.8%; use of large amounts of fluidizing gas (in this case N/sub 2/), which does not reflect commercial operation; and lack of data with higher peat feed moisture content. Thus, in Kellogg's opinion, considerable advantage is to be gained by expanding the existing data base and lists its specific recommendations.

  12. Engine Gimbal Requirements for Ground Testing of J-2X

    NASA Technical Reports Server (NTRS)

    Kovalcik, Julia; Leahy, Joe

    2009-01-01

    Based on the Apollo-era J-2 that powered the second and third stages of the Saturn V, the current J-2X is the liquid hydrogen and oxygen high-altitude rocket engine in development for both the Ares I Upper Stage and Ares V Earth Departure Stage. During my summer 2009 internship, J-2X was at a stage in its design maturity where verification testing needed to be considered for the benefit of adequate test facility preparation. My task was to focus on gimbal requirements and gimbal related hot-fire test plans. Facility capabilities were also of interest, specifically for hot-fire testing slated to occur at test stands A-1, A-2, and A-3 at Stennis Space Center(SSC) in Bay St. Louis, Mississippi. Gimbal requirements and stage interface conditions were investigated by applying a top-to-bottom systems engineering approach, which involved system level requirements, engine level requirements from both government and engine contractor perspectives, component level requirements, and the J-2X to Upper Stage and Earth Departure Stage interface control documents. Previous hydrogen and oxygen liquid rocket engine gimbal verification methods were researched for a glimpse at lessons learned. Discussion among the J-2X community affected by gimballing was organized to obtain input relative to proper verification of their respective component. Implementing suggestions such as gimbal pattern, angulated dwell time, altitude testing options, power level, and feed line orientation, I was able to match tests to test stands in the A Complex at SSC. Potential test capability gaps and risks were identified and pursued. The culmination of all these efforts was to coordinate with SSC to define additional facility requirements for both the A-3 altitude test stand that is currently under construction and the A-1 sea level test stand which is being renovated

  13. Two-stage airbreathing launcher trajectory optimization including first-stage return

    NASA Astrophysics Data System (ADS)

    Christophe, B.

    1992-12-01

    The open-loop guidance system presented for a two-stage-to-orbit (TSTO) vehicle is based on ONERA's 'generalized project gradient' method. The TSTO in question has an airbreathing first stage, which returns to its launch pad after separation, and a rocket-powered upper stage that raises a 17-ton payload to transfer orbit. The software is shown to be capable of finding the airbreathing ascents and return flights for the case of fixed stage-separation conditions.

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

    NASA Technical Reports Server (NTRS)

    Holanda, R.; Frause, L. M.

    1977-01-01

    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.

  15. System Engineering and Technical Challenges Overcome in the J-2X Rocket Engine Development Project

    NASA Technical Reports Server (NTRS)

    Ballard, Richard O.

    2012-01-01

    Beginning in 2006, NASA initiated the J-2X engine development effort to develop an upper stage propulsion system to enable the achievement of the primary objectives of the Constellation program (CxP): provide continued access to the International Space Station following the retirement of the Space Station and return humans to the moon. The J-2X system requirements identified to accomplish this were very challenging and the time expended over the five years following the beginning of the J- 2X effort have been noteworthy in the development of innovations in both the fields for liquid rocket propulsion and system engineering.

  16. Two-Stage Combustor Reduces Pollutant Emissions

    NASA Technical Reports Server (NTRS)

    Clayton, R. M.

    1982-01-01

    By controlling fuel-to-air ratio of local reactants, pollutant emissions would be minimized in a proposed two-stage combustor for gas-turbine engines. It would use fuel-rich partial-oxidation stage and air-rich combustion stage to reduce emissions of nitrogen oxide, carbon monoxide and hydrocarbons. Combustor fuel-lean burning limit would be extended simultaneously.

  17. Multiple angle single stage scrubber

    SciTech Connect

    Ostlie, L.

    1982-02-02

    A scrubber for cleansing flue gases is disclosed. The scrubber includes a housing which defines a channel. The channel includes a scrubber stage wherein vertically spaced rows of deflecting members of l-shaped cross-section are disposed. In a given row of deflecting members, a plurality of flow paths are defined between horizontally adjacent deflecting members. Each deflecting member has an upper arm and a lower arm. The lowermost edge of the lower arms of the deflecting members in one row are disposed between vertical projections from the uppermost edges of upper arms of deflecting members in a row below the last mentioned row.

  18. Multi-stage Continuous Culture Fermentation of Glucose-Xylose Mixtures to Fuel Ethanol using Genetically Engineered Saccharomyces cerevisiae 424A

    EPA Science Inventory

    Multi-stage continuous (chemostat) culture fermentation (MCCF) with variable fermentor volumes was carried out to study utilizing glucose and xylose for ethanol production by means of mixed sugar fermentation (MSF). Variable fermentor volumes were used to enable enhanced sugar u...

  19. Two stage sorption type cryogenic refrigerator including heat regeneration system

    NASA Technical Reports Server (NTRS)

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

    1989-01-01

    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.

  20. Ares I and Ares I-X Stage Separation Aerodynamic Testing

    NASA Technical Reports Server (NTRS)

    Pinier, Jeremy T.; Niskey, Charles J.

    2011-01-01

    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.

  1. CVD Rhenium Engines for Solar-Thermal Propulsion Systems

    NASA Technical Reports Server (NTRS)

    Williams, Brian E.; Fortini, Arthur J.; Tuffias, Robert H.; Duffy, Andrew J.; Tucker, Stephen P.

    1999-01-01

    Solar-thermal upper-stage propulsion systems have the potential to provide specific impulse approaching 900 seconds, with 760 seconds already demonstrated in ground testing. Such performance levels offer a 100% increase in payload capability compared to state-of-the-art chemical upper-stage systems, at lower cost. Although alternatives such as electric propulsion offer even greater performance, the 6- to 18- month orbital transfer time is a far greater deviation from the state of the art than the one to two months required for solar propulsion. Rhenium metal is the only material that is capable of withstanding the predicted thermal, mechanical, and chemical environment of a solar-thermal propulsion device. Chemical vapor deposition (CVD) is the most well-established and cost-effective process for the fabrication of complex rhenium structures. CVD rhenium engines have been successfully constructed for the Air Force ISUS program (bimodal thrust/electricity) and the NASA Shooting Star program (thrust only), as well as under an Air Force SBIR project (thrust only). The bimodal engine represents a more long-term and versatile approach to solar-thermal propulsion, while the thrust-only engines provide a potentially lower weight/lower cost and more near-term replacement for current upper-stage propulsion systems.

  2. Comprehensive Management of Upper Tract Urothelial Carcinoma

    PubMed Central

    Koukourakis, Georgios; Zacharias, Georgios; Koukourakis, Michael; Pistevou-Gobaki, Kiriaki; Papaloukas, Christos; Kostakopoulos, Athanasios; Kouloulias, Vassilios

    2009-01-01

    Urothelial carcinoma of the upper urinary tract represents only 5% of all urothelial cancers. The 5-year cancer-specific survival in the United States is roughly 75% with grade and stage being the most powerful predictors of survival. Nephroureterectomy with excision of the ipsilateral ureteral orifice and bladder cuff en bloc remains the gold standard treatment of the upper urinary tract urothelial cancers, while endoscopic and laparoscopic approaches are rapidly evolving as reasonable alternatives of care depending on grade and stage of disease. Several controversies remain in their management, including a selection of endoscopic versus laparoscopic approaches, management strategies on the distal ureter, the role of lymphadenectomy, and the value of chemotherapy in upper tract disease. Aims of this paper are to critically review the management of such tumors, including endoscopic management, laparoscopic nephroureterectomy and management of the distal ureter, the role of lymphadenectomy, and the emerging role of chemotherapy in their treatment. PMID:19096525

  3. Nuclear Cryogenic Propulsion Stage

    NASA Technical Reports Server (NTRS)

    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

    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.

  4. RL-10 Engines

    NASA Technical Reports Server (NTRS)

    1963-01-01

    The RL-10 engines were developed by Pratt Whitney and tested by the Marshall Space Flight Center (MSFC). Pictured are MSFC engineers working on the mechanics of the RL-10 engines. Originally developed in 1963 as the first liquid hydrogen-fueled engine to operate successfully in space, the RL-10 engines were used on the second stage (S-IV stage) of the Saturn I launch vehicle.

  5. Stages and Behaviors

    MedlinePLUS

    ... Stage Caregiving Middle-Stage Caregiving Late-Stage Caregiving Behaviors Aggression & Anger Anxiety & Agitation Depression Hallucinations Memory Loss & ... Legal Documents alz.org » Caregiver Center » Stages and Behaviors Text size: A A A Stages / Behaviors As ...

  6. Non-Toxic Orbital Maneuvering System Engine Development

    NASA Technical Reports Server (NTRS)

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

    1999-01-01

    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.

  7. SolSTUS: Solar Source Thermal Upper Stage

    NASA Technical Reports Server (NTRS)

    1994-01-01

    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.

  8. Zero Gravity Cryogenic Vent System Concepts for Upper Stages

    NASA Technical Reports Server (NTRS)

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

    1999-01-01

    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.

  9. Zero Gravity Cryogenic Vent System Concepts for Upper Stages

    NASA Technical Reports Server (NTRS)

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

    2001-01-01

    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.

  10. Design and analysis report for the RL10-2B breadboard low thrust engine

    NASA Technical Reports Server (NTRS)

    Brown, J. R.; Foust, R. R.; Galler, D. E.; Kanic, P. G.; Kmiec, T. D.; Limerick, C. D.; Peckham, R. J.; Swartwout, T.

    1984-01-01

    The breadboard low thrust RL10-2B engine is described. A summary of the analysis and design effort to define the multimode thrust concept applicable to the requirements for the upper stage vehicles is provided. Baseline requirements were established for operation of the RL10-2B engine under the following conditions: (1) tank head idle at low propellant tank pressures without vehicle propellant conditioning or settling thrust; (2) pumped idle at a ten percent thrust level for low G deployment and/or vehicle tank pressurization; and (3) full thrust (15,000 lb.). Several variations of the engine configuration were investigated and results of the analyses are included.

  11. Development of a CFRP Engine Thrust Frame for the Next Generation Launchers

    NASA Astrophysics Data System (ADS)

    Fatemi, Javad; van der Bas, Finn; Cruijssen, Henk

    2012-07-01

    This paper addresses the activities related to the development of technologies for a composite Engine Thrust Frame (ETF) for the next generation launchers. In particular, the design and analyses of a full Carbon Fibre Reinforced Plastic (CFRP) engine thrust frame are presented in more detail. The ETF concept is composed of three main parts, i.e. an aluminium top-ring which connects the ETF to the upper-stage tank, a CFRP cone, and a CFRP cone-cap which connects the Vinci engine to the ETF. The main challenging requirements for development of a CFRP ETF are recalled. The ETF concept and its mechanical performances are assessed.

  12. Upper Yosemite Falls

    USGS Multimedia Gallery

    In this image, Upper Yosemite Falls may be seen from the Yosemite Falls Trail. Upper Yosemite Falls has a total plunge of 1,430 ft (440 m). Yosemite Falls is one of the most famous waterfalls within Yosemite National Park....

  13. Upper Yosemite Falls

    USGS Multimedia Gallery

    In this image, Upper Yosemite Falls may be seen. Upper Yosemite Falls is the highest of the three sectiosn of Yosemite Falls. It is about 1,430 ft (440 m) high. Yosemite Falls is one of the most famous waterfalls within Yosemite National Park....

  14. Upper Yosemite Falls Detail

    USGS Multimedia Gallery

    In this image, a detailed view Upper Yosemite Falls may be seen from the Yosemite Falls Trail. Upper Yosemite Falls has a total plunge of 1,430 ft (440 m). Yosemite Falls is one of the most famous waterfalls within Yosemite National Park....

  15. 38. DETAIL OF CYLINDER LEVELING SYSTEM SHOWING TYPICAL UPPER AND ...

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

    38. DETAIL OF CYLINDER LEVELING SYSTEM SHOWING TYPICAL UPPER AND LOWER PULLEY BRACKET. F.C. TORKELSON DRAWING NUMBER 842-ARVFS-701-S-8. INEL INDEX CODE - Idaho National Engineering Laboratory, Advanced Reentry Vehicle Fusing System, Scoville, Butte County, ID

  16. TRIDENT 1 third stage motor separation system

    NASA Technical Reports Server (NTRS)

    Welch, B. H.; Richter, B. J.; Sue, P.

    1977-01-01

    The third stage engine separation system has shown through test and analysis that it can effectively and reliably perform its function. The weight of the hardware associated with this system is well within the targeted value.

  17. Stages of Esophageal Cancer

    MedlinePLUS

    ... cancer cells. The following stages are used for squamous cell carcinoma of the esophagus: Stage 0 (High-grade Dysplasia) ... is also called high-grade dysplasia . Stage I squamous cell carcinoma of the esophagus Stage I is divided into ...

  18. Engine-Out Capabilities Assessment of Heavy Lift Launch Vehicles

    NASA Technical Reports Server (NTRS)

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

    2012-01-01

    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.

  19. 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)

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

    1995-01-01

    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.

  20. Orbiter Trajectory Analysis for a Two-Stage Reusable Launch Vehicle

    NASA Technical Reports Server (NTRS)

    Cowling, Adam L.

    2011-01-01

    Trajectory analysis performed on NASA's reference two-stage-to-orbit launch vehicle upper stage will be presented. The work was completed in support of the Hypersonics Multidisciplinary Analysis and Optimization effort for the NASA-Air Force Joint System Study. Three degree-of-freedom (3-DOF) untrimmed trajectory analysis was performed for the orbiter ascent, closure and re-entry. An iterative closure process resulted in a 333,000 lb initial mass for the orbiter. The re-entry trajectory satisfied heating constraints for all payload out cases and met the constraints with reduced margins for payload in cases. Abort trajectories for engine out at staging, engine out during ascent, and failure to circularize in orbit, gave insight to the robustness of the orbiter. A trimmed ascent trajectory defined an engine gimbal location and the body flap angle best suited for maximizing injected mass. A trimmed re-entry trajectory revealed a need to update the trim routine to accommodate full flap aerodynamic data.

  1. 49. LOCK AND DAM NO. 26 (REPLACEMENT). FIRST STAGE DAM ...

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

    49. LOCK AND DAM NO. 26 (REPLACEMENT). FIRST STAGE DAM -- DAM CONCRETE -- TYPICAL PIER ISOMETRIC. M-L 26(R) 40/1 - Upper Mississippi River 9-Foot Channel Project, Lock & Dam 26R, Alton, Madison County, IL

  2. 50. LOCK AND DAM NO. 26 (REPLACEMENT). FIRST STAGE DAM ...

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

    50. LOCK AND DAM NO. 26 (REPLACEMENT). FIRST STAGE DAM -- DAM CONCRETE -- GENERAL ARRANGEMENT -- SECTION AND ELEVATIONS. M-L 26(R) 40/3 - Upper Mississippi River 9-Foot Channel Project, Lock & Dam 26R, Alton, Madison County, IL

  3. Name: ______________________ MASTER OF FINE ARTS PROGRAM: DRAMA: Stage Management

    E-print Network

    Loudon, Catherine

    Requirements (2015-2016) Seven Drama 254 (Studios in Stage Management (Professional Internship): _______ Drama 257E (Thesis Writing Project): _______ Electives: You must have a minimum of 112 quarter units in graduate (#200+) or approved upper-division undergraduate (#100

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

    NASA Technical Reports Server (NTRS)

    Binder, Michael P.

    1995-01-01

    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.

  5. Psoriatic Disease: Clinical Staging.

    PubMed

    Scarpa, Raffaele; Caso, Francesco; Costa, Luisa; Peluso, Rosario; Spanò, Angelo; Lubrano, Ennio; Del Puente, Antonio; Moll, John M H

    2015-11-01

    In 2006, the introduction of the concept "psoriatic disease" (PsD) extended the traditional idea of a condition confined to skin and joints. Now we consider PsD a systemic condition, in which the increased activity of tumor necrosis factor acts as the most potent engine for a series of molecular interactions. These lead not only to the genesis of skin and joint symptoms, but also to other clinical aspects such as inflammatory bowel disease, eye involvement, and metabolic syndrome. The blocking of a precise molecular target has dramatically modified therapeutic strategies, making possible adequate control of all the clinical aspects of the condition. Therefore, an expanded clinical staging of patients could now be considered in order to ensure the best therapeutic approach and prognosis. PMID:26523050

  6. 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

  7. www.ictas.vt.edu Predicting Turbofan Fan-Stage

    E-print Network

    Crawford, T. Daniel

    aircraft's engines are throttled down, the fan stage becomes the main engine noise source.The noise exists funding from both GEAE and Boeing for work related to aircraft and engine noise. Currently, she is funded Engineering Boston University Professor Grace's research interests lie in the fields of unsteady aerodynamics

  8. Upper Girdle Imaging in Facioscapulohumeral Muscular Dystrophy

    PubMed Central

    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

    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. PMID:24932477

  9. Transfer orbit stage (TOS) guidance and control

    NASA Astrophysics Data System (ADS)

    Stuart, James R.; Kaplan, Marshall H.; Coffey, Randall E.; White, Thomas W.

    This paper describes the strap-down, ring laser gyro-based guidance and control system of the current Transfer Orbit Stage (TOS) family of orbital transfer vehicles being developed by Orbital Sciences Corporation. The paper begins with a summary review of the key features and guidance and control approaches used by that employed by the TOS family of upper stages. The TOS system design overview is presented, covering the major subsystems and flight operations. The major components and functions of the TOS avionics system are described, highlighting the Laser Inertial Navigation System (LINS). The LINS components, operations, performance and reliability are discussed. The hardware and software redundancy and built-in-test failure detection techniques are examined. Finally, the paper discusses some future developments for the LINS and TOS family of upper stages.

  10. Pancreatic Cancer Stage 3

    MedlinePLUS

    ... My Pictures Browse 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 ...

  11. 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 ...

  12. Ovarian Cancer Stage II

    MedlinePLUS

    Three-panel drawing of stage IIA, IIB, and IIC ovarian cancer; first panel shows two stage IIA tumors, one inside each ... to the uterus and fallopian tube. The second panel shows two stage IIB tumors, one inside each ...

  13. Stages of HIV Infection

    MedlinePLUS

    ... HIV Infection Translate Text Size Print Stages of HIV Infection How Does HIV Progress In Your Body? Without treatment, HIV advances ... are the three stages of HIV infection: Acute HIV Infection Stage Within 2-4 weeks after HIV ...

  14. Cervical Cancer Stage IVA

    MedlinePLUS

    ... My Pictures Browse Search Quick Search Image Details Cervical Cancer Stage IVA View/Download: Small: 756x576 View Download Add to My Pictures Title: Cervical Cancer Stage IVA Description: Stage IVA cervical cancer; drawing ...

  15. Cervical Cancer Stage IVB

    MedlinePLUS

    ... My Pictures Browse Search Quick Search Image Details Cervical Cancer Stage IVB View/Download: Small: 594x640 View Download Add to My Pictures Title: Cervical Cancer Stage IVB Description: Stage IVB cervical cancer; drawing ...

  16. Cervical Cancer Stage IB

    MedlinePLUS

    ... My Pictures Browse Search Quick Search Image Details Cervical Cancer Stage IB View/Download: Small: 774x576 View Download Add to My Pictures Title: Cervical Cancer Stage IB Description: Stage IB1 and IB2 cervical ...

  17. Cervical Cancer Stage IIIA

    MedlinePLUS

    ... My Pictures Browse Search Quick Search Image Details Cervical Cancer Stage IIIA View/Download: Small: 612x612 View Download Add to My Pictures Title: Cervical Cancer Stage IIIA Description: Stage IIIA cervical cancer; drawing ...

  18. Cervical Cancer Stage IIIB

    MedlinePLUS

    ... My Pictures Browse Search Quick Search Image Details Cervical Cancer Stage IIIB View/Download: Small: 684x636 View Download Add to My Pictures Title: Cervical Cancer Stage IIIB Description: Stage IIIB cervical cancer; drawing ...

  19. Cervical Cancer Stage IA

    MedlinePLUS

    ... My Pictures Browse Search Quick Search Image Details Cervical Cancer Stage IA View/Download: Small: 720x576 View Download Add to My Pictures Title: Cervical Cancer Stage IA Description: Stage IA1 and IA2 cervical ...

  20. Ares I Stage Separation Test

    NASA Technical Reports Server (NTRS)

    2007-01-01

    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, an Ares I x-test involves the upper stage separating from the first stage. This particular test was conducted at the NASA Langley Research Center in July 2007. (Highest resolution available)

  1. 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

  2. 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

  3. Upper Atmospheric Density Profiles

    E-print Network

    Withers, Paul

    Presentation 2003.03.06 #12;Layout of Talk · Relevant datasets, MGS and others · Deriving p, T profiles from in planetary exploration · About 800 passes through upper atmosphere to reduce orbit energy and semi-major axis · Uncertainties in aerodynamics, problems with signals from shaking solar panel, rotation of instrument about

  4. View down and east from the Upper Tier of Upper ...

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

    View down and east from the Upper Tier of Upper Raceway, Rogers Storage Building immediate right, Rogers Frame Fitting Shop (HAER No. NJ-3-B) in background - Great Falls/S. U. M. Power Canal System, Paterson, Passaic County, NJ

  5. 7. UPPER INSIDE CHORD, VERTICAL, LATERAL STRUT, UPPER LATERAL & ...

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

    7. UPPER INSIDE CHORD, VERTICAL, LATERAL STRUT, UPPER LATERAL & GUSSET PLATE, TWO DIAGONAL BRACES - Enterprise Parker Truss Bridge, Spanning Smoky Hill River on K-43 Highway, Enterprise, Dickinson County, KS

  6. 8. UPPER INSIDE CHORD, VERTICAL, LATERAL STRUT, UPPER LATERAL & ...

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

    8. UPPER INSIDE CHORD, VERTICAL, LATERAL STRUT, UPPER LATERAL & GUSSET PLATE, ONE DIAGONAL BRACE - Enterprise Parker Truss Bridge, Spanning Smoky Hill River on K-43 Highway, Enterprise, Dickinson County, KS

  7. 4. SHOWING BRIDGE AT UPPER LEFT, UPPER FALLS AND TOP ...

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

    4. SHOWING BRIDGE AT UPPER LEFT, UPPER FALLS AND TOP OF MAIN WATERFALL, FACING NORTHEAST - Paradise River First Crossing Bridge, Spanning Paradise River at Narada Falls on Service Road, Longmire, Pierce County, WA

  8. A Historical Systems Study of Liquid Rocket Engine Throttling Capabilities

    NASA Technical Reports Server (NTRS)

    Betts, Erin M.; Frederick, Robert A., Jr.

    2010-01-01

    This is a comprehensive systems study to examine and evaluate throttling capabilities of liquid rocket engines. The focus of this study is on engine components, and how the interactions of these components are considered for throttling applications. First, an assessment of space mission requirements is performed to determine what applications require engine throttling. A background on liquid rocket engine throttling is provided, along with the basic equations that are used to predict performance. Three engines are discussed that have successfully demonstrated throttling. Next, the engine system is broken down into components to discuss special considerations that need to be made for engine throttling. This study focuses on liquid rocket engines that have demonstrated operational capability on American space launch vehicles, starting with the Apollo vehicle engines and ending with current technology demonstrations. Both deep throttling and shallow throttling engines are discussed. Boost and sustainer engines have demonstrated throttling from 17% to 100% thrust, while upper stage and lunar lander engines have demonstrated throttling in excess of 10% to 100% thrust. The key difficulty in throttling liquid rocket engines is maintaining an adequate pressure drop across the injector, which is necessary to provide propellant atomization and mixing. For the combustion chamber, cooling can be an issue at low thrust levels. For turbomachinery, the primary considerations are to avoid cavitation, stall, surge, and to consider bearing leakage flows, rotordynamics, and structural dynamics. For valves, it is necessary to design valves and actuators that can achieve accurate flow control at all thrust levels. It is also important to assess the amount of nozzle flow separation that can be tolerated at low thrust levels for ground testing.

  9. High Head Unshrouded Impeller Pump Stage Technology

    NASA Technical Reports Server (NTRS)

    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

    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.

  10. Stages of Adolescence

    MedlinePLUS

    ... Español Text Size Email Print Share 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 ...

  11. Stages of Gallbladder Cancer

    MedlinePLUS

    ... Serosal (outer) layer. Between these layers is supporting connective tissue . Primary gallbladder cancer starts in the inner layer ... has spread beyond the muscle layer to the connective tissue around the muscle. Stage IIIA In stage IIIA , ...

  12. Lunar Module Ascent Stage

    NASA Technical Reports Server (NTRS)

    1969-01-01

    The Lunar Module 'Spider' ascent stage is photographed from the Command/Service Module on the fifth day of the Apollo 9 earth-orbital mission. The Lunar Module's descent stage had already been jettisoned.

  13. Upper Extremity Regional Anesthesia

    PubMed Central

    Neal, Joseph M.; Gerancher, J.C.; Hebl, James R.; Ilfeld, Brian M.; McCartney, Colin J.L.; Franco, Carlo D.; Hogan, Quinn H.

    2009-01-01

    Brachial plexus blockade is the cornerstone of the peripheral nerve regional anesthesia practice of most anesthesiologists. As part of the American Society of Regional Anesthesia and Pain Medicine’s commitment to providing intensive evidence-based education related to regional anesthesia and analgesia, this article is a complete update of our 2002 comprehensive review of upper extremity anesthesia. The text of the review focuses on (1) pertinent anatomy, (2) approaches to the brachial plexus and techniques that optimize block quality, (4) local anesthetic and adjuvant pharmacology, (5) complications, (6) perioperative issues, and (6) challenges for future research. PMID:19282714

  14. Altitude Testing of Large Liquid Propellant Engines

    NASA Technical Reports Server (NTRS)

    Maynard, Bryon T.; Raines, Nickey G.

    2010-01-01

    The National Aeronautics and Space Administration entered a new age on January 14, 2004 with President Bush s announcement of the creation the Vision for Space Exploration that will take mankind back to the Moon and on beyond to Mars. In January, 2006, after two years of hard, dedicated labor, engineers within NASA and its contractor workforce decided that the J2X rocket, based on the heritage of the Apollo J2 engine, would be the new engine for the NASA Constellation Ares upper stage vehicle. This engine and vehicle combination would provide assured access to the International Space Station to replace that role played by the Space Shuttle and additionally, would serve as the Earth Departure Stage, to push the Crew Excursion Vehicle out of Earth Orbit and head it on a path for rendezvous with the Moon. Test as you fly, fly as you test was chosen to be the guiding philosophy and a pre-requisite for the engine design, development, test and evaluation program. An exhaustive survey of national test facility assets proved the required capability to test the J2X engine at high altitude for long durations did not exist so therefore, a high altitude/near space environment testing capability would have to be developed. After several agency concepts the A3 High Altitude Testing Facility proposal was selected by the J2X engine program on March 2, 2007 and later confirmed by a broad panel of NASA senior leadership in May 2007. This facility is to be built at NASA s John C. Stennis Space Center located near Gulfport, Mississippi. 30 plus years of Space Shuttle Main Engine development and flight certification testing makes Stennis uniquely suited to support the Vision For Space Exploration Return to the Moon. Propellant handling infrastructure, engine assembly facilities, a trained and dedicated workforce and a broad and varied technical support base will all ensure that the A3 facility will be built on time to support the schedule needs of the J2X engine and the ultimate flight of the first Ares I vehicle. The A3 facility will be able to simulate pre-ignition altitude from sea-level to 100,000 feet and maintain it up to 650 seconds. Additionally the facility will be able to accommodate initial ignition, shutdown and then restart test profiles. A3 will produce up to 5000 lbm/sec of superheated steam utilizing a Chemical Steam generation system. Two separate inline steam ejectors will be used to produce a test cell vacuum to simulate the 100,000 ft required altitude. Operational capability will ensure that the facility can start up and shutdown without producing adverse pressure gradients across the J2X nozzle. The facility will have a modern thrust measurement system for accurate determination of engine performance. The latest advances in data acquisition and control will be incorporated to measure performance parameters during hotfire testing. Provisions are being made in the initial design of the new altitude facility to allow for testing of other, larger engines and potential upper stage launch vehicles that might require vacuum start testing of the engines. The new facility at Stennis Space Center will be complete and ready for hotfire operations in late 2010.

  15. TO TELESCOPE Translation Stage

    E-print Network

    Weisstein, Eric

    (Back Side) Holography Stepper Motors Optical Encoder/Translation Stage Electronics Box Limit Switch Controller RS-232 Cable To Telescope To P1 P1 45° Flat Mirror to P2 & Bolometer Stepper Motor Power Supplies Electronics Box Manual Translation Stage Paddle Box Limit Switches Translation Stage Motor+Rotary Encoder Heat

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

    ClinicalTrials.gov

    2014-12-29

    Cervical Adenocarcinoma; Cervical Adenosquamous 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

  17. Upper respiratory tract infections.

    PubMed

    Jain, N; Lodha, R; Kabra, S K

    2001-12-01

    Acute respiratory infections accounts for 20-40% of outpatient and 12-35% of inpatient attendance in a general hospital. Upper respiratory tract infections including nasopharyngitis, pharyngitis, tonsillitis and otitis media constitute 87.5% of the total episodes of respiratory infections. The vast majority of acute upper respiratory tract infections are caused by viruses. Common cold is caused by viruses in most circumstances and does not require antimicrobial agent unless it is complicated by acute otitis media with effusion, tonsillitis, sinusitis, and lower respiratory tract infection. Sinusitis is commonly associated with common cold. Most instances of rhinosinusitis are viral and therefore, resolve spontaneously without antimicrobial therapy. The most common bacterial agents causing sinusitis are S. pneumoniae, H. influenzae, M. catarrhalis, S. aureus and S. pyogenes. Amoxycillin is antibacterial of choice. The alternative drugs are cefaclor or cephalexin. The latter becomes first line if sinusitis is recurrent or chronic. Acute pharyngitis is commonly caused by viruses and does not need antibiotics. About 15% of the episodes may be due to Group A beta hemolytic streptococcus (GABS). Early initiation of antibiotics in pharyngitis due to GABS can prevent complications such as acute rheumatic fever. The drug of choice is penicillin for 10-14 days. The alternative medications include oral cephalosporins (cefaclor, cephalexin), amoxicillin or macrolides. PMID:11838568

  18. ENGINEERING TECHNOLOGY Engineering Technology

    E-print Network

    specialized program concentrations: Aircraft Maintenance Technology, Engineering Technology Management: aerospace, computer, electrical, industrial, bioengineering, manufacturing, mechanical, and engineeringENGINEERING TECHNOLOGY Engineering Technology Program The Bachelor of Science in Engineering

  19. Apollo 15 Lunar Module 'Falcon' seen before ascent stage liftoff

    NASA Technical Reports Server (NTRS)

    1971-01-01

    The Apollo 15 Lunar Module 'Falcon' is seen only seconds before ascent stage liftoff in this black and white reproduction taken from a color transmission made by the RCA color television camera mounted on the Lunar Roving Vehicle (LRV). The LRV was parked about 300 feet east of the Lunar Module (LM). The LM liftoff was at 171:37 ground elapsed time. The LM descent stage is used as a launching platform and remains behind on the Moon (41511); The flame from the Apollo 15 LM ascent stage engine creates a kaleidoscope effect during lunar liftoff. In this view, the two stages are beginning to separate (41512); The LM descent stage rests alone on the Moon shortly after the ascent stage liftoff from the lunar surface. The lunar soil dust cloud stirred up by the ascent stage engine thrust has already settled (41513).

  20. Design and Fabrication Development of J-2X Engine Metallic Nozzle Extension

    NASA Technical Reports Server (NTRS)

    Kopicz, C.; Gradl, P.

    2015-01-01

    Maximized rocket engine performance is in part derived from expanding combustion gasses through the rocket nozzle. For upper stage engines the nozzles can be quite large. On the J-2X engine, an uncooled extension of a regeneratively cooled nozzle is used to expand the combustion gasses to a targeted exit pressure which is defined by an altitude for the desired maximum performance. Creating a J-2X nozzle extension capable of surviving the loads of test and flight environments while meeting engine system performance requirements required development of new processes and facilities. Meeting the challenges of the development resulted in concurrent J-2X nozzle extension design and fabrication. This paper describes how some of the design and fabrication challenges were resolved.

  1. Age and correlation of California Paleogene benthic foraminiferal stages

    USGS Publications Warehouse

    Poore, Richard Z.

    1980-01-01

    Comparisons of age determinations and correlations derived from calcareous plankton with those derived from benthic foraminifers in a number of sections in California show significant overlap in time of the Ynezian through the Ulatisian Stages. Thus interbasin time correlations deduced from these stage assignments must be treated with caution. Calcareous plankton occasionally associated with benthic foraminifers diagnostic of the Narizian through the Zemorrian Stages indicate that the Narizian-Refugian boundary is within the upper Eocene of international usage and that the Refugian is entirely upper Eocene. Overlap of the Narizian and the Refugian appears to be minimal. The Zemorrian correlates, mostly, with the Oligocene, although the upper limit of the Zemorrian might be in the lower Miocene.

  2. 75 FR 20516 - Special Conditions: Cirrus Design Corporation, Model SF50; Fire Extinguishing for Upper Aft...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-04-20

    ...; Fire Extinguishing for Upper Aft Fuselage Mounted Engine AGENCY: Federal Aviation Administration (FAA... protect such installed engines from fires, were not envisioned in the development of the part 23 normal... fire extinguishing system for the engine on the model SF50 is required. Regulations requiring...

  3. Upper Permian vertebrates and their sedimentological context in the South Urals, Russia

    E-print Network

    Benton, Michael

    on mudflats and in small rivers flowing off the Ural Mountain chain, span the last two stages of the PermianUpper Permian vertebrates and their sedimentological context in the South Urals, Russia Valentin P in the Upper Permian of the Southern Urals area of European Russia. The first sites were found in the 1940s

  4. 2nd International Conodont Symposium 2009 TheWuchiapingian-Changhsingianboundary(Upper

    E-print Network

    1 2nd International Conodont Symposium 2009 TheWuchiapingian-Changhsingianboundary(Upper Permian stage of the Upper Permian, which is also known as the Lopingian Series. It is officially referred of Section D was ratified by IUGS as the GSSP for the Permian-Triassic boundary (Yin et al., 2001). The lower

  5. Two stage catalytic combustor

    NASA Technical Reports Server (NTRS)

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

    2010-01-01

    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.

  6. 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)

    Schoenman, L.

    1982-01-01

    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.

  7. Aerodynamic performance of 0.5 meter-diameter, 337 meter-per-second tip speed, 1.5 pressure-ratio, single-stage fan designed for low noise aircraft engines

    NASA Technical Reports Server (NTRS)

    Gelder, T. F.; Lewis, G. W., Jr.

    1974-01-01

    Overall and blade-element aerodynamic performance of a 0.271-scale model of QF-1 are presented, examined, and then compared and evaluated with that from similar low noise fan stage designs. The tests cover a wide range of speeds and weight flows along with variations in stator setting angle and stator axial spacing from the rotor. At design speed with stator at design setting angle and a fixed distance between stage measuring stations, there were no significant effects of increasing the axial spacing between rotor stator from 1.0 to 3.5 rotor chords on stage overall pressure ratio, efficiency or stall margin.

  8. The development of an index for the proximal upper extremity 

    E-print Network

    Walline, Erin Kurusz

    2006-08-16

    for the degree of DOCTOR OF PHILOSOPHY May 2005 Major Subject: Interdisciplinary Engineering Approved as to style and content by: John S. Moore (Chair of Committee) Jerome J. Congleton (Member) Rodger J. Koppa (Member) N.K. Anand (Head... CHAPTER I INTRODUCTION.................................................................................................1 Proximal Upper Extremity Anatomy and Function ..............................................3 Pathogenesis of Tendon Disorders...

  9. AERODYNAMICS RESEARCH CENTER MECHANICAL AND AEROSPACE ENGINEERING

    E-print Network

    Texas at Arlington, University of

    for a compressor stage found in turbofan, turbojet engines. Thisurbojet engines. This reduces complexity of engine08/03/2007 16:39 1 AERODYNAMICS RESEARCH CENTER MECHANICAL AND AEROSPACE ENGINEERING DEPARTMENT Associate, ARC, MAE, UT Arlington Co-authors: Daniel T. H. New, Lecturer, Department of Engineering

  10. "High Stage" Organizing.

    ERIC Educational Resources Information Center

    Torbert, William R.

    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…

  11. Diagnosis and Staging

    Cancer.gov

    Cancer can cause many different symptoms. The doctor will order tests to determine if symptoms are caused by cancer or some other problem. If cancer is diagnosed, the doctor will run tests to determine the stage. Knowing the stage helps the doctor plan treatment and discuss prognosis.

  12. Infarction of the lingula following left upper lobe trisegmentectomy.

    PubMed

    Brunswicker, Annemarie; Farid, Shakil; Van Tornout, Filip

    2016-01-01

    Anatomical segmentectomy has emerged as the procedure of choice for early-stage non-small-cell lung cancer, especially in the presence of poor cardiopulmonary reserve. The most common postoperative complications are pneumonia, persistent air leak, and rarely, vascular compromise of the remaining lobe. We report the case of a 74-year-old woman who underwent thoracotomy and left upper lobe trisegmentectomy for T1bN0Mo squamous cell carcinoma and subsequently developed infarction and hepatization of the remaining lingula. A completion left upper lobectomy was performed and the patient made a full recovery. PMID:26438406

  13. 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...

  14. 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

    2014-12-23

    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

  15. MANUFACTURING ENGINEERING Manufacturing engineering

    E-print Network

    MANUFACTURING ENGINEERING Manufacturing engineering transforms raw materials, parts, and operations, following a well- organized plan for each activity. Manufacturing engineering involves designing assuring a competitive level of productivity. The manufacturing engineering curriculum at WSU focuses

  16. Second Stage (S-II) Plays Key Role in Apollo missions

    NASA Technical Reports Server (NTRS)

    1970-01-01

    This photograph of the Saturn V Second Stage (S-II) clearly shows the cluster of five powerful J-2 engines needed to boost the Apollo spacecraft into earth orbit following first stage separation. 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.

  17. Trilobite biostratigraphy in the Middle and Upper Ordovician of western Leningrad Region

    NASA Astrophysics Data System (ADS)

    Dolgov, O.; Meidla, T.

    2011-12-01

    Biostatigraphical significance of trilobites of the Middle and Upper Ordovician in the eastern Baltic area is discussed, based on a new material from numerous outcrops from Leningrad Region. The study of the Middle and Upper Ordovician trilobites in the Mednikovo, Viivikonna, Gryazno, Khrevitsa and Elizavetino formations allows establishing two trilobite interval-zones. The zone of Chasmops odini in the upper part of the Uhaku and Kukruse stages, and the zone of Chasmops marginatus in the lower part of the Haljala Stage (the Idavere Substage). The upper part of the Haljala Stage (J~ohvi Substage) is characterized by the occurrence of Rollmops wenjukowi. Distribution and biostratigraphical significance of some trilobite taxa ( Asaphus ( Neoasaphus) lepidus, Illaenus intermedius, Toxochasmops maximus) is discussed.

  18. OVERVIEW OF UPPER TRAM TERMINAL, TRAM TRESTLE, PRIMARY ORE BIN,OVERBURDEN ...

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

    OVERVIEW OF UPPER TRAM TERMINAL, TRAM TRESTLE, PRIMARY ORE BIN,OVERBURDEN PILE, AND DEBRIS SCATTER,LOOKING NORTH NORTHWEST. THE MAIN ACCESS TRAIL BETWEEN THE LOWER MILL AREA GOES ACROSS THE CENTER LEFT TO RIGHT. WINCHING ENGINE AND FOUNDATION IN UPPER RIGHT CORNER (SEE CA-291-37). - Keane Wonder Mine, Park Route 4 (Daylight Pass Cutoff), Death Valley Junction, Inyo County, CA

  19. Chemotherapy Toxicity On Quality of Life in Older Patients With Stage I, Stage II, Stage III, or Stage IV Ovarian Epithelial, Primary Peritoneal Cavity, or Fallopian Tube Cancer

    ClinicalTrials.gov

    2014-12-23

    Stage I Ovarian Cancer; Stage IA Fallopian Tube Cancer; Stage IB Fallopian Tube Cancer; Stage IC Fallopian Tube Cancer; Stage II Ovarian Cancer; Stage IIA Fallopian Tube Cancer; Stage IIB Fallopian Tube Cancer; Stage IIC Fallopian Tube Cancer; Stage III Ovarian Cancer; Stage III Primary Peritoneal Cancer; Stage IIIA Fallopian Tube Cancer; Stage IIIB Fallopian Tube Cancer; Stage IIIC Fallopian Tube Cancer; Stage IV Fallopian Tube Cancer; Stage IV Ovarian Cancer; Stage IV Primary Peritoneal Cancer

  20. Engineering Careers: Software Engineering

    E-print Network

    Fenster, Sam

    Engineering Careers: Software Engineering Tony Aiuto Google #12;Who Am I? Software Engineer engineer means Talk about careers #12;Some Topics Why Software Matters What is Software Engineering Skills electronic device #12;Software tools Software engineers build their own tools The OS on your laptop

  1. Staging for vulvar cancer.

    PubMed

    Hacker, Neville F; Barlow, Ellen L

    2015-08-01

    Vulvar cancer has been staged by the International Federation of Gynaecology and Obstetrics (FIGO) since 1969, and the original staging system was based on clinical findings only. This system provided a very good spread of prognostic groupings. Because vulvar cancer is virtually always treated surgically, the status of the lymph nodes is the most important prognostic factor and this can only be determined with certainty by histological examination of resected lymph nodes, FIGO introduced a surgical staging system in 1988. This was modified in 1994 to include a category of microinvasive vulvar cancer (stage IA), because such patients have virtually no risk of lymph node metastases. This system did not give a reasonably even spread of prognostic groupings. In addition, patients with stage III disease were shown to be a heterogeneous group prognostically, and the number of positive nodes and the morphology of those nodes were not taken into account. A new surgical staging system for vulvar cancer was introduced by FIGO in 2009. Initial retrospective analyses have suggested that this new staging system has overcome the major deficiencies in the 1994 system. PMID:25842047

  2. A Modular Aerospike Engine Design Using Additive Manufacturing

    NASA Technical Reports Server (NTRS)

    Peugeot, John; Garcia, Chance; Burkhardt, Wendel

    2014-01-01

    A modular aerospike engine concept has been developed with the objective of demonstrating the viability of the aerospike design using additive manufacturing techniques. The aerospike system is a self-compensating design that allows for optimal performance over the entire flight regime and allows for the lowest possible mass vehicle designs. At low altitudes, improvements in Isp can be traded against chamber pressure, staging, and payload. In upper stage applications, expansion ratio and engine envelope can be traded against nozzle efficiency. These features provide flexibility to the System Designer optimizing a complete vehicle stage. The aerospike concept is a good example of a component that has demonstrated improved performance capability, but traditionally has manufacturing requirements that are too expensive and complex to use in a production vehicle. In recent years, additive manufacturing has emerged as a potential method for improving the speed and cost of building geometrically complex components in rocket engines. It offers a reduction in tooling overhead and significant improvements in the integration of the designer and manufacturing method. In addition, the modularity of the engine design provides the ability to perform full scale testing on the combustion devices outside of the full engine configuration. The proposed design uses a hydrocarbon based gas-generator cycle, with plans to take advantage of existing powerhead hardware while focusing DDT&E resources on manufacturing and sub-system testing of the combustion devices. The major risks for the modular aerospike concept lie in the performance of the propellant feed system, the structural integrity of the additive manufactured components, and the aerodynamic efficiency of the exhaust flow.

  3. 78 FR 5710 - Airworthiness Directives; Engine Alliance Turbofan Engines

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-01-28

    ... Executive Order 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR... applies to all Engine Alliance GP7270 and GP7277 turbofan engines with a high-pressure turbine (HPT) stage...-45-AD; Amendment 39-17327; AD 2013-02-06] RIN 2120-AA64 Airworthiness Directives; Engine...

  4. S-IB Stage Entering Point Barrow

    NASA Technical Reports Server (NTRS)

    1968-01-01

    The Saturn 1B first stage (S-IB) enters the NASA barge Point Barrow, in March 1968. The Marshall Space Flight Center (MSFC) utilized a number of water transportation craft to transport the Saturn stages to-and-from the manufacturing facilities and test sites, as well as delivery to the Kennedy Space Center for launch. Developed by the Marshall Space Flight Center and built by the Chrysler Corporation at Michoud Assembly Facility (MAF), the S-IB utilized the eight H-1 engines and each produced 200,000 pounds of thrust, a combined thrust of 1,600,000 pounds.

  5. The Nuclear Cryogenic Propulsion Stage

    NASA Technical Reports Server (NTRS)

    Houts, Michael G.; Kim, Tony; Emrich, William J.; Hickman, Robert R.; Broadway, Jeramie W.; Gerrish, Harold P.; Doughty, Glen; Belvin, Anthony; Borowski, Stanley K.; Scott, John

    2014-01-01

    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. Progres made under the NCPS project could help enable both advanced NTP and advanced Nuclear Electric Propulsion (NEP).

  6. The Nuclear Cryogenic Propulsion Stage

    NASA Technical Reports Server (NTRS)

    Houts, Michael G.; Kim, Tony; Emrich, William J.; Hickman, Robert R.; Broadway, Jeramie W.; Gerrish, Harold P.; Doughty, Glen; Belvin, Anthony; Borowski, Stanley K.; Scott, John

    2014-01-01

    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 Nuclear Electric Propulsion (NEP). Nuclear propulsion can be affordable and viable compared to other propulsion systems and must overcome a biased public fear due to hyper-environmentalism and a false perception of radiation and explosion risk.

  7. Staging Airliner Service

    NASA Technical Reports Server (NTRS)

    Hahn, Andrew S.

    2007-01-01

    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.

  8. Stages of Pregnancy

    MedlinePLUS

    ... your baby in these three stages. First trimester (week 1-week 12) First trimester See how your baby is ... is each pregnancy. Return to top Second trimester (week 13-week 28) Second trimester See how your ...

  9. Rotorcraft convertible engine study

    NASA Technical Reports Server (NTRS)

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

    1982-01-01

    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.

  10. Precision adjustable stage

    DOEpatents

    Cutburth, Ronald W. (Tracy, CA); Silva, Leonard L. (Livermore, CA)

    1988-01-01

    An improved mounting stage of the type used for the detection of laser beams is disclosed. A stage center block is mounted on each of two opposite sides by a pair of spaced ball bearing tracks which provide stability as well as simplicity. The use of the spaced ball bearing pairs in conjunction with an adjustment screw which also provides support eliminates extraneous stabilization components and permits maximization of the area of the center block laser transmission hole.

  11. Multiple stage railgun

    DOEpatents

    Hawke, Ronald S. (Livermore, CA); Scudder, Jonathan K. (Pleasanton, CA); Aaland, Kristian (Livermore, CA)

    1982-01-01

    A multiple stage magnetic railgun accelerator (10) for accelerating a projectile (15) by movement of a plasma arc (13) along the rails (11,12). The railgun (10) is divided into a plurality of successive rail stages (10a-n) which are sequentially energized by separate energy sources (14a-n) as the projectile (15) moves through the bore (17) of the railgun (10). Propagation of energy from an energized rail stage back towards the breech end (29) of the railgun (10) can be prevented by connection of the energy sources (14a-n) to the rails (11,12) through isolation diodes (34a-n). Propagation of energy from an energized rail stage back towards the breech end of the railgun can also be prevented by dividing the rails (11,12) into electrically isolated rail sections (11a-n, 12a-n). In such case means (55a-n) are used to extinguish the arc at the end of each energized stage and a fuse (31) or laser device (61) is used to initiate a new plasma arc in the next energized rail stage.

  12. System Engineering for J-2X Development: The Simpler, the Better

    NASA Technical Reports Server (NTRS)

    Kelly, William M.; Greasley, Paul; Greene, William D.; Ackerman, Peter

    2008-01-01

    The Ares I and Ares V Vehicles will utilize the J-2X rocket engine developed for NASA by the Pratt and Whitney Rocketdyne Company (PWR) as the upper stage engine (USE). The J-2X is an improved higher power version of the original J-2 engine used for Apollo. System Engineering (SE) facilitates direct and open discussions of issues and problems. This simple idea is often overlooked in large, complex engineering development programs. Definition and distribution of requirements from the engine level to the component level is controlled by Allocation Reports which breaks down numerical design objectives (weight, reliability, etc.) into quanta goals for each component area. Linked databases of design and verification requirements help eliminate redundancy and potential mistakes inherent in separated systems. Another tool, the Architecture Design Description (ADD), is used to control J-2X system architecture and effectively communicate configuration changes to those involved in the design process. But the proof of an effective process is in successful program accomplishment. SE is the methodology being used to meet the challenge of completing J-2X engine certification 2 years ahead of any engine program ever developed at PWR. This paper describes the simple, better SE tools and techniques used to achieve this success.

  13. 64 IRE TRANSACTIONS ON ENGINEERING MANAGEMENT July Systenas Engineering-Key to Modern Development

    E-print Network

    Rhoads, James

    64 IRE TRANSACTIONS ON ENGINEERING MANAGEMENT July Systenas Engineering-Key to Modern Development, integration, emphasis on the field of systems engineering. Though and evaluation. In a sense, these terms describe the five engineers with system functions can be found in almost stages -of the systems engineering

  14. Black breast cancer survivors experience greater upper extremity disability.

    PubMed

    Dean, Lorraine T; DeMichele, Angela; LeBlanc, Mously; Stephens-Shields, Alisa; Li, Susan Q; Colameco, Chris; Coursey, Morgan; Mao, Jun J

    2015-11-01

    Over one-third of breast cancer survivors experience upper extremity disability. Black women present with factors associated with greater upper extremity disability, including: increased body mass index (BMI), more advanced disease stage at diagnosis, and varying treatment type compared with Whites. No prior research has evaluated the relationship between race and upper extremity disability using validated tools and controlling for these factors. Data were drawn from a survey study among 610 women with stage I-III hormone receptor positive breast cancer. The disabilities of the arm, shoulder and hand (QuickDASH) is an 11-item self-administered questionnaire that has been validated for breast cancer survivors to assess global upper extremity function over the past 7 days. Linear regression and mediation analysis estimated the relationships between race, BMI and QuickDASH score, adjusting for demographics and treatment types. Black women (n = 98) had 7.3 points higher average QuickDASH scores than White (n = 512) women (p < 0.001). After adjusting for BMI, age, education, cancer treatment, months since diagnosis, and aromatase inhibitor status, Black women had an average 4-point (95 % confidence interval 0.18-8.01) higher QuickDASH score (p = 0.04) than White women. Mediation analysis suggested that BMI attenuated the association between race and disability by 40 %. Even several years post-treatment, Black breast cancer survivors had greater upper extremity disability, which was partially mediated by higher BMIs. Close monitoring of high BMI Black women may be an important step in reducing disparities in cancer survivorship. More research is needed on the relationship between race, BMI, and upper extremity disability. PMID:26420404

  15. High Head Unshrouded Impeller Pump Stage Technology

    NASA Technical Reports Server (NTRS)

    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

    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.

  16. A Mechanism for Upper Airway Stability during Slow Wave Sleep

    PubMed Central

    McSharry, David G.; Saboisky, Julian P.; DeYoung, Pam; Matteis, Paul; Jordan, Amy S.; Trinder, John; Smales, Erik; Hess, Lauren; Guo, Mengshuang; Malhotra, Atul

    2013-01-01

    Study Objectives: The severity of obstructive sleep apnea is diminished (sometimes markedly) during slow wave sleep (SWS). We sought to understand why SWS stabilizes the upper airway. Increased single motor unit (SMU) activity of the major upper airway dilating muscle (genioglossus) should improve upper airway stability. Therefore, we hypothesized that genioglossus SMUs would increase their activity during SWS in comparison with Stage N2 sleep. Design: The activity of genioglossus SMUs was studied on both sides of the transition between Stage N2 sleep and SWS. Setting: Sleep laboratory. Participants: Twenty-nine subjects (age 38 ± 13 yr, 17 males) were studied. Intervention: SWS. Measurement and Results: Subjects slept overnight with fine-wire electrodes in their genioglossus muscles and with full polysomnographic and end tidal carbon dioxide monitors. Fifteen inspiratory phasic (IP) and 11 inspiratory tonic (IT) units were identified from seven subjects and these units exhibited significantly increased inspiratory discharge frequencies during SWS compared with Stage N2 sleep. The peak discharge frequency of the inspiratory units (IP and IT) was 22.7 ± 4.1 Hz in SWS versus 20.3 ± 4.5 Hz in Stage N2 (P < 0.001). The IP units also fired for a longer duration (expressed as a percentage of inspiratory time) during SWS (104.6 ± 39.5 %TI) versus Stage N2 sleep (82.6 ± 39.5 %TI, P < 0.001). The IT units fired faster during expiration in SWS (14.2 ± 1.8 Hz) versus Stage N2 sleep (12.6 ± 3.1 Hz, P = 0.035). There was minimal recruitment or derecruitment of units between SWS and Stage N2 sleep. Conclusion: Increased genioglossus SMU activity likely makes the airway more stable and resistant to collapse throughout the respiratory cycle during SWS. Citation: McSharry DG; Saboisky JP; DeYoung P; Matteis P; Jordan AS; Trinder J; Smales E; Hess L; Guo M; Malhotra A. A mechanism for upper airway stability during slow wave sleep. SLEEP 2013;36(4):555-563. PMID:23565001

  17. Principles of Melanoma Staging.

    PubMed

    Boland, Genevieve M; Gershenwald, Jeffrey E

    2016-01-01

    Although now commonplace in contemporary cancer care, the systematic approach to classification of disease-specific cancers into a formalized staging system is a relatively modern concept. Overall, the goals of cancer staging are to characterize the status of cancer at a specific moment in time, risk stratify, facilitate prognostication, and inform clinical decision making. The revisions to the American Joint Committee on Cancer (AJCC) melanoma staging system over time reflect changes in our understanding of the biology of the disease. Since the 1st edition, where tumor thickness was defined anatomically by its relationship to the reticular or papillary dermis (Clark level) as well as tumor thickness (Breslow thickness), there have been significant strides in our use of clinicopathological variables to stratify low- versus high-risk patients. Management of the regional nodal basin has also changed dramatically over time, impacted by techniques such as lymphatic mapping and sentinel lymph node biopsy (SLNB) and changes in pathological evaluation of the regional lymph nodes. Additionally, stratification of distant metastases has evolved as survival outcomes have been shown to vary based upon anatomic site of metastases and serum lactate dehydrogenase levels. The variables in use in the current (7th edition) AJCC staging system are surrogate markers of biology with validated impact of survival outcomes. Going forward, it is likely that these and additional clinicopathological factors will be integrated with molecular and other correlates of melanoma tumor biology to further refine and personalize melanoma staging. PMID:26601861

  18. Pancreatic Cancer Stage 2B

    MedlinePLUS

    ... My Pictures Browse Search Quick Search Image Details Pancreatic Cancer Stage 2B View/Download: Small: 720x576 View Download Add to My Pictures Title: Pancreatic Cancer Stage 2B Description: Stage IIB pancreatic cancer; illustration ...

  19. Pancreatic Cancer Stage 2A

    MedlinePLUS

    ... My Pictures Browse Search Quick Search Image Details Pancreatic Cancer Stage 2A View/Download: Small: 720x576 View Download Add to My Pictures Title: Pancreatic Cancer Stage 2A Description: Stage IIA pancreatic cancer; drawing ...

  20. Stages of Renal Cell Cancer

    MedlinePLUS

    ... of disease. Urinalysis : A test to check the color of urine and its contents, such as sugar, ... staging . The information gathered from the staging process determines the stage of the disease. It is important ...

  1. UPPER PENITENCIA CREEK HISTORICAL ECOLOGY ASSESSMENT

    E-print Network

    ................................................................................................................8 Origin of the Upper Penitencia-Coyote Creek connection Upper Penitencia Creek drains a 24 square mile area within the Coyote Creek watershed in Santa Clara

  2. Combustion Stability Verification for the Thrust Chamber Assembly of J-2X Developmental Engines 10001, 10002, and 10003

    NASA Technical Reports Server (NTRS)

    Morgan, C. J.; Hulka, J. R.; Casiano, M. J.; Kenny, R. J.; Hinerman, T. D.; Scholten, N.

    2015-01-01

    The J-2X engine, a liquid oxygen/liquid hydrogen propellant rocket engine available for future use on the upper stage of the Space Launch System vehicle, has completed testing of three developmental engines at NASA Stennis Space Center. Twenty-one tests of engine E10001 were conducted from June 2011 through September 2012, thirteen tests of the engine E10002 were conducted from February 2013 through September 2013, and twelve tests of engine E10003 were conducted from November 2013 to April 2014. Verification of combustion stability of the thrust chamber assembly was conducted by perturbing each of the three developmental engines. The primary mechanism for combustion stability verification was examining the response caused by an artificial perturbation (bomb) in the main combustion chamber, i.e., dynamic combustion stability rating. No dynamic instabilities were observed in the TCA, although a few conditions were not bombed. Additional requirements, included to guard against spontaneous instability or rough combustion, were also investigated. Under certain conditions, discrete responses were observed in the dynamic pressure data. The discrete responses were of low amplitude and posed minimal risk to safe engine operability. Rough combustion analyses showed that all three engines met requirements for broad-banded frequency oscillations. Start and shutdown transient chug oscillations were also examined to assess the overall stability characteristics, with no major issues observed.

  3. 2-Stage Classification Modeling

    Energy Science and Technology Software Center (ESTSC)

    1994-11-01

    CIRCUIT2.4 is used to design optimum two-stage classification configurations and operating conditions for energy conservation. It permits simulation of five basic grinding-classification circuits, including one single-stage and four two-stage classification arrangements. Hydrocyclones, spiral classifiers, and sieve band screens can be simulated, and the user may choose the combination of devices for the flowsheet simulation. In addition, the user may select from four classification modeling methods to achieve the goals of a simulation project using themore »most familiar concepts. Circuit performance is modeled based on classification parameters or equipment operating conditions. A modular approach was taken in designing the program, which allows future addition of other models with relatively minor changes.« less

  4. Staged quantum energy teleportation

    NASA Astrophysics Data System (ADS)

    Frey, Michael R.

    2015-05-01

    Quantum energy teleportation (QET) is a protocol facilitated by a coupled particle pair to enable a sender to transfer energy to a receiver. A variant of the standard QET protocol is proposed in which energy transfer occurs in stages. This allows multiple transfers of energy via the same particle pair, achieving both greater overall efficiency and greater total energy throughput compared to standard QET. Two-stage QET is shown for a particular spin- 1 2 particle pair to simultaneously increase throughput by 36.9% and efficiency by 26.0% over standard QET, while for the same pair three-stage QET increases throughput 38.1% and efficiency 26.7% over standard QET.

  5. J-2 Engine Test Firing

    NASA Technical Reports Server (NTRS)

    2004-01-01

    This image is a close-up view of the test firing of a J-2 engine. The J-2, developed by Rocketdyne under the direction of Marshall Space Flight Center, was propelled by liquid hydrogen and liquid oxygen. A single J-2 was utilized in the S-IVB stage (the second stage for the Saturn IB and third stage for the Saturn V) and in a cluster of five for the second stage (S-II) of the Saturn V. Initially rated at 200,000 pounds of thrust, the engine was later uprated in the Saturn V program to 230,000 pounds.

  6. Staged fluidized bed

    DOEpatents

    Mallon, R.G.

    1983-05-13

    The invention relates to oil shale retorting and more particularly to staged fluidized bed oil shale retorting. Method and apparatus are disclosed for narrowing the distribution of residence times of any size particle and equalizing the residence times of large and small particles in fluidized beds. Particles are moved up one fluidized column and down a second fluidized column with the relative heights selected to equalize residence times of large and small particles. Additional pairs of columns are staged to narrow the distribution of residence times and provide complete processing of the material.

  7. System Study for Axial Vane Engine Technology

    NASA Technical Reports Server (NTRS)

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

    2008-01-01

    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.

  8. 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

  9. PROCESS WATER BUILDING, TRA605. FLASH EVAPORATORS ARE PLACED ON UPPER ...

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

    PROCESS WATER BUILDING, TRA-605. FLASH EVAPORATORS ARE PLACED ON UPPER LEVEL OF EAST SIDE OF BUILDING. WALLS WILL BE FORMED AROUND THEM. WORKING RESERVOIR BEYOND. CAMERA FACING EASTERLY. EXHAUST AIR STACK IS UNDER CONSTRUCTION AT RIGHT OF VIEW. INL NEGATIVE NO. 2579. Unknown Photographer, 6/18/1951 - Idaho National Engineering Laboratory, Test Reactor Area, Materials & Engineering Test Reactors, Scoville, Butte County, ID

  10. Tripropellant engine study

    NASA Technical Reports Server (NTRS)

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

    1978-01-01

    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.

  11. V160 Stirling engine program update

    SciTech Connect

    Johansson, L.; Torstensson, B.; Williams, T. Y.; Houtman, W.H.; Monahan, R.

    1988-01-01

    Development efforts being made toward the preproduction stage of the V160 Stirling engine are examined. The history of continued reliability encompassing all engine models is reviewed, and efforts towards engine manufacturing and cost reduction are addressed. A preview is given of the initial product line based on the V160 engine and substantiated through testing of the offered configurations.

  12. An Introduction to Complex-System Engineering

    NASA Astrophysics Data System (ADS)

    Kuras, Michael L.

    This is an introduction to complex-system engineering (cSE). cSE is going to become the second branch of system engineering. It is still in its formative stages. All of cSE's presently known ideas are briefly discussed. A familiarity with the first branch of system engineering, so called traditional system engineering (TSE), is assumed.

  13. Lung cancer staging now and in the future.

    PubMed

    Liam, Chong-Kin; Andarini, Sita; Lee, Pyng; Ho, James Chung-Man; Chau, Ngo Quy; Tscheikuna, Jamsak

    2015-05-01

    For a long time lung cancer was associated with a fatalistic approach by healthcare professionals. In recent years, advances in imaging, improved diagnostic techniques and more effective treatment modalities are reasons for optimism. Accurate lung cancer staging is vitally important because treatment options and prognosis differ significantly by stage. The staging algorithm should include a contrast computed tomography (CT) of the chest and the upper abdomen including adrenals, positron emission tomography/CT for staging the mediastinum and to rule out extrathoracic metastasis in patients considered for surgical resection, endosonography-guided needle sampling procedure replacing mediastinoscopy for near complete mediastinal staging, and brain imaging as clinically indicated. Applicability of evidence-based guidelines for staging of lung cancer depends on the available expertise and level of resources and is directly impacted by financial issues. Considering the diversity of healthcare infrastructure and economic performance of Asian countries, optimal and cost-effective use of staging methods appropriate to the available resources is prudent. The pulmonologist plays a central role in the multidisciplinary approach to lung cancer diagnosis, staging and management. Regional respiratory societies such as the Asian Pacific Society of Respirology should work with national respiratory societies to strive for uniform standards of care. For developing countries, a minimum set of care standards should be formulated. Cost-effective delivery of optimal care for lung cancer patients, including staging within the various healthcare systems, should be encouraged and most importantly, tobacco control implementation should receive an absolute priority status in all countries in Asia. PMID:25682805

  14. End-Stage.

    ERIC Educational Resources Information Center

    Moua, Mai Neng

    2001-01-01

    Through her reflections on dealing with dialysis for end-stage renal disease and awaiting a kidney transplant, the author presents insights into how her experience was shaped by the physical, emotional, and multicultural forces she faced. Among the issues discussed are her ambivalent feelings between pursuing a regular lifestyle and receiving…

  15. Staging of Lung Cancer

    MedlinePLUS

    ... is important for two reasons. First, staging your lung cancer helps decide which therapy (or therapies) should be used. Second, lung cancer ... 422-6237 http://www.cancer.gov/cancertopics/wyntk/lung/page8 http://www.cancer.gov/cancertopics/pdq/treatment/non- small-cell-lung/Patient/page2 National Lung ...

  16. Stage a Water Show

    ERIC Educational Resources Information Center

    Frasier, Debra

    2008-01-01

    In the author's book titled "The Incredible Water Show," the characters from "Miss Alaineus: A Vocabulary Disaster" used an ocean of information to stage an inventive performance about the water cycle. In this article, the author relates how she turned the story into hands-on science teaching for real-life fifth-grade students. The author also…

  17. Early-Stage Caregiving

    MedlinePLUS

    ... for additional supervision or care. Learn more: Living Alone Coping with Memory Loss Long-Distance Caregiving Home Safety We Can Help If you are a care partner for someone with early-stage Alzheimer's, you aren't alone. Get the support and resources you need. Find ...

  18. Saturn IB S-IB Stage at Michoud Assembly Facility (MAF)

    NASA Technical Reports Server (NTRS)

    1967-01-01

    Workers at the Michoud Assembly Facility (MAF) near New Orleans, Louisiana, install the last engine on the S-IB stage. Developed by the Marshall Space Flight Center (MSFC) and built by the Chrysler Corporation at MAF, the S-IB stage utilized eight H-1 engines to produce a combined thrust of 1,600,000 pounds.

  19. Language Learning at Key Stage 2: Findings from a Longitudinal Study

    ERIC Educational Resources Information Center

    Cable, Carrie; Driscoll, Patricia; Mitchell, Rosamond; Sing, Sue; Cremin, Teresa; Earl, Justine; Eyres, Ian; Holmes, Bernardette; Martin, Cynthia; Heins, Barbara

    2012-01-01

    This paper discusses some of the findings from a 3-year longitudinal study of language learning in the upper stage of English primary schools, i.e. at Key Stage 2. This largely qualitative study (commissioned by the then Department for Children, Schools and Families) was designed to explore and document developing provision and practice in a…

  20. Optical engine initiation: multiple compartment applications

    NASA Astrophysics Data System (ADS)

    Hunt, Jeffrey H.

    2009-05-01

    Modern day propulsion systems are used in aerospace applications for different purposes. The aerospace industry typically requires propulsion systems to operate in a rocket mode in order to drive large boost vehicles. The defense industry generally requires propulsion systems to operate in an air-breathing mode in order to drive missiles. A mixed system could use an air-breathing first stage and a rocket-mode upper stage for space access. Thus, propulsion systems can be used for high mass payloads and where the payload is dominated by the fuel/oxidizer mass being used by the propulsion system. The pulse detonation wave engine (PDWE) uses an alternative type of detonation cycle to achieve the same propulsion results. The primary component of the PDWE is the combustion chamber (or detonation tube). The PDWE represents an attractive propulsion source since its engine cycle is thermodynamically closest to that of a constant volume reaction. This characteristic leads to the inference that a maximum of the potential energy of the PDWE is put into thrust and not into flow work. Consequently, the volume must be increased. The technical community has increasingly adopted the alternative choice of increasing total volume by designing the engine to include a set of banks of smaller combustion chambers. This technique increases the complexity of the ignition subsystem because the inter-chamber timing must be considered. Current approaches to igniting the PDWE have involved separate shock or blast wave initiators and chemical additives designed to enhance detonatibility. An optical ignition subsystem generates a series of optical pulses, where the optical pulses ignite the fuel/oxidizer mixture such that the chambers detonate in a desired order. The detonation system also has an optical transport subsystem for transporting the optical pulses from the optical ignition subsystem to the chambers. The use of optical ignition and transport provides a non-toxic, small, lightweight, precisely controlled detonation system.

  1. 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)

    Morris, R. N.

    1973-01-01

    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.

  2. A cascade thermoacoustic engine.

    PubMed

    Gardner, D L; Swift, G W

    2003-10-01

    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

  3. A cascade thermoacoustic engine

    NASA Astrophysics Data System (ADS)

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

    2003-10-01

    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.

  4. ENGINEERING Master of Engineering

    E-print Network

    Toronto, University of

    ENGINEERING GRADUATE STUDIES MEng Master of Engineering #12;"If you're considering an MEng program chose the MEng program at U of T." DOM LEE, MEng STUDENT #12;TAKE YOUR ENGINEERING CAREER TO THE NEXT knowledge. But to get ahead in today's workplace, engineers also have to communicate, manage, innovate

  5. MASTER OF SCIENCE MECHANICAL ENGINEERING

    E-print Network

    COMPRESSORS TO FOULING AT VARIOUS STAGES Jonathan D. Baker -Lieutenant, United States Coast Guard B.S., United States Coast Guard Academy, 1996 Master of Science in Mechanical Engineering-September 2002 Advisor: Knox

  6. Industrial Engineering Education: A Prospective.

    ERIC Educational Resources Information Center

    Elsayed, E. A.

    1999-01-01

    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)

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

    NASA Technical Reports Server (NTRS)

    Kynard, Michael

    2011-01-01

    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.

  8. Taking centre stage...

    NASA Astrophysics Data System (ADS)

    1998-11-01

    HAMLET (Highly Automated Multimedia Light Enhanced Theatre) was the star performance at the recent finals of the `Young Engineer for Britain' competition, held at the Commonwealth Institute in London. This state-of-the-art computer-controlled theatre lighting system won the title `Young Engineers for Britain 1998' for David Kelnar, Jonathan Scott, Ramsay Waller and John Wyllie (all aged 16) from Merchiston Castle School, Edinburgh. HAMLET replaces conventional manually-operated controls with a special computer program, and should find use in the thousands of small theatres, schools and amateur drama productions that operate with limited resources and without specialist expertise. The four students received a £2500 prize between them, along with £2500 for their school, and in addition they were invited to spend a special day with the Royal Engineers. A project designed to improve car locking systems enabled Ian Robinson of Durham University to take the `Working in industry award' worth £1000. He was also given the opportunity of a day at sea with the Royal Navy. Other prizewinners with their projects included: Jun Baba of Bloxham School, Banbury (a cardboard armchair which converts into a desk and chair); Kobika Sritharan and Gemma Hancock, Bancroft's School, Essex (a rain warning system for a washing line); and Alistair Clarke, Sam James and Ruth Jenkins, Bishop of Llandaff High School, Cardiff (a mechanism to open and close the retractable roof of the Millennium Stadium in Cardiff). The two principal national sponsors of the competition, which is organized by the Engineering Council, are Lloyd's Register and GEC. Industrial companies, professional engineering institutions and educational bodies also provided national and regional prizes and support. During this year's finals, various additional activities took place, allowing the students to surf the Internet and navigate individual engineering websites on a network of computers. They also visited the Millennium Dome site, constructing a model of the Dome and designing a range of Dome exhibits from innovative assembly kits. Details of the 1999 competition will be available from the Engineering Council at 10 Maltravers Street, London WC2R 3ER (tel: 0171 240 7891, http://www.engc.org.uk).

  9. Staged depressurization system

    DOEpatents

    Schulz, T.L.

    1993-11-02

    A nuclear reactor having a reactor vessel disposed in a containment shell is depressurized in stages using depressurizer valves coupled in fluid communication with the coolant circuit. At least one sparger submerged in the in-containment refueling water storage tank which can be drained into the containment sump communicates between one or more of the valves and an inside of the containment shell. The depressurizer valves are opened in stages, preferably at progressively lower coolant levels and for opening progressively larger flowpaths to effect depressurization through a number of the valves in parallel. The valves can be associated with a pressurizer tank in the containment shell, coupled to a coolant outlet of the reactor. At least one depressurization valve stage openable at a lowest pressure is coupled directly between the coolant circuit and the containment shell. The reactor is disposed in the open sump in the containment shell, and a further valve couples the open sump to a conduit coupling the refueling water storage tank to the coolant circuit for adding water to the coolant circuit, whereby water in the containment shell can be added to the reactor from the open sump. 4 figures.

  10. Staged depressurization system

    DOEpatents

    Schulz, Terry L. (Murrysville Boro, Westmoreland County, PA)

    1993-01-01

    A nuclear reactor having a reactor vessel disposed in a containment shell is depressurized in stages using depressurizer valves coupled in fluid communication with the coolant circuit. At least one sparger submerged in the in-containment refueling water storage tank which can be drained into the containment sump communicates between one or more of the valves and an inside of the containment shell. The depressurizer valves are opened in stages, preferably at progressively lower coolant levels and for opening progressively larger flowpaths to effect depressurization through a number of the valves in parallel. The valves can be associated with a pressurizer tank in the containment shell, coupled to a coolant outlet of the reactor. At least one depressurization valve stage openable at a lowest pressure is coupled directly between the coolant circuit and the containment shell. The reactor is disposed in the open sump in the containment shell, and a further valve couples the open sump to a conduit coupling the refueling water storage tank to the coolant circuit for adding water to the coolant circuit, whereby water in the containment shell can be added to the reactor from the open sump.

  11. Nile behaviour and Upper Palaeolithic humans in Upper Egypt

    NASA Astrophysics Data System (ADS)

    Vermeersch, Pierre M.

    2014-05-01

    There is evidence of a decreasing human occupation of the Upper Egyptian Nile valley during the MIS 5 to MIS 3 period. Whereas very large extraction sites of the Middle Stone Age have been recorded, only very few sites of the Upper Palaeolithic have been found. The best explanation of this fact is that during the Late Middle Stone Age and the Upper Palaeolithc there was nearly no need for raw materials because there was only a very restricted population present in Upper Egypt. From about 22 ka BP an important population increase is registered by the presence of numerous Late Palaeolithic sites. During the whole LGM there is abundant presence of humans along the Nile Valley in Upper Egypt. This population was mainly living from fishing. There seems to be an abrupt end of the Palaeolithic occupation after 12.8 ka BP. Until now, no sites were found in the Valley until some rare Epipaleolithic sites occur about 8.0 ka BP. It will be suggested that these population changes are influenced by the river Nile behaviour. The best interpretation of the observations in the Upper Egyptian Nile Valley is the hypothesis that at the same time that Nile flow was reduced because of the dryness in its source area, the impact of aeolian activity was increased over Northeast Africa. The increased aeolian activity by northern winds in the Fayum and Wadi Ryan during the LGM resulted in the accumulation of aeolian sand in the valley. That aeolian sand was transported along the western Nile valley cliffs until it was accumulated when the Nile Valley change it S-N direction, such as at Nag'Hammadi. At other places sand was invading the Nile valley, directly from the Western Desert, creating a damming of the Nile at several places such as Armant and Aswan. As Nile flow was quite reduced, the Nile was unable to erode all the incoming sand and the Nile water with its important clay content was dammed. At several places large lakes were created in the Nile Valley. Those lakes were an ideal place for the settlement of the Late Palaeolithic fishers. There came an abrupt end to this situation when the Nile returned to its meandering regime at the end of the LGM. This situation created an catastrophic food crisis for the

  12. Changes in Brain Function in Patients With Stage I, Stage II, Stage III, or Stage IV Ovarian, Primary Peritoneal, or Fallopian Tube Cancer Who Are Receiving Chemotherapy

    ClinicalTrials.gov

    2014-12-23

    Cognitive Side Effects of Cancer Therapy; Malignant Ovarian Mixed Epithelial Tumor; Malignant Ovarian Surface Epithelial-Stromal Tumor; Ovarian Brenner Tumor; Ovarian Carcinosarcoma; Ovarian Choriocarcinoma; Ovarian Clear Cell Cystadenocarcinoma; Ovarian Dysgerminoma; Ovarian Embryonal Carcinoma; Ovarian Endometrioid Adenocarcinoma; Ovarian Mixed Germ Cell Tumor; Ovarian Mucinous Cystadenocarcinoma; Ovarian Polyembryoma; Ovarian Sarcoma; Ovarian Serous Cystadenocarcinoma; Ovarian Teratoma; Ovarian Yolk Sac Tumor; Stage I Ovarian Cancer; Stage IA Fallopian Tube Cancer; Stage IA Ovarian Cancer; Stage IA Ovarian Germ Cell Tumor; Stage IB Fallopian Tube Cancer; Stage IB Ovarian Cancer; Stage IB Ovarian Germ Cell Tumor; Stage IC Fallopian Tube Cancer; Stage IC Ovarian Cancer; Stage IC Ovarian Germ Cell Tumor; Stage II Ovarian Cancer; Stage IIA Fallopian Tube Cancer; Stage IIA Ovarian Cancer; Stage IIA Ovarian Germ Cell Tumor; Stage IIB Fallopian Tube Cancer; Stage IIB Ovarian Cancer; Stage IIB Ovarian Germ Cell Tumor; Stage IIC Fallopian Tube Cancer; Stage IIC Ovarian Cancer; Stage IIC Ovarian Germ Cell Tumor; Stage IIIA Fallopian Tube Cancer; Stage IIIA Ovarian Cancer; Stage IIIA Ovarian Germ Cell Tumor; Stage IIIA Primary Peritoneal Cancer; Stage IIIB Fallopian Tube Cancer; Stage IIIB Ovarian Cancer; Stage IIIB Ovarian Germ Cell Tumor; Stage IIIB Primary Peritoneal Cancer; Stage IIIC Fallopian Tube Cancer; Stage IIIC Ovarian Cancer; Stage IIIC Ovarian Germ Cell Tumor; Stage IIIC Primary Peritoneal Cancer; Stage IV Fallopian Tube Cancer; Stage IV Ovarian Cancer; Stage IV Ovarian Germ Cell Tumor; Stage IV Primary Peritoneal Cancer; Undifferentiated Ovarian Carcinoma

  13. Low energy stage study. Volume 3: Conceptual design, interface analysis, flight and ground operations. [launching space shuttle payloads

    NASA Technical Reports Server (NTRS)

    1978-01-01

    Low energy conceptual stage designs and adaptations to existing/planned shuttle upper stages were developed and their performance established. Selected propulsion modes and subsystems were used as a basis to develop airborne support equipment (ASE) design concepts. Orbiter installation and integration (both physical and electrical interfaces) were defined. Low energy stages were adapted to the orbiter and ASE interfaces. Selected low energy stages were then used to define and describe typical ground and flight operations.

  14. Web Engineering

    SciTech Connect

    White, Bebo

    2003-06-23

    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.

  15. The current status of rehabilitation engineering

    NASA Technical Reports Server (NTRS)

    Reswick, J. B.

    1974-01-01

    Mechanical and electrical engineering devices for paralytic patient care are discussed as they are applied to medical problems. These include means of preventing bedsores, mobility aids, upper extremity orthoses, and electrical stimulation.

  16. Infrasound as upper atmospheric monitor

    NASA Astrophysics Data System (ADS)

    Assink, Jelle D.

    Understanding and specification of the higher altitudes of the atmosphere with global coverage over all local times is hampered by the challenges of obtaining direct measurements in the upper atmosphere. Methods to measure the properties of the atmosphere above the stratopause is an active area of scientific research. In this thesis, we revisit the use of infrasound as a passive remote sensing technique for the upper atmosphere. Signals from the Tungurahua volcano in Ecuador are used to investigate the behavior of the upper atmosphere. Depending on the atmospheric conditions, stratospheric, mesospheric and thermospheric arrivals are observed during intervals of explosive volcanic activity. It is found that the travel times and dominant frequencies of the thermospheric arrivals exhibit a coherent variability with periods equal to those of the tidal harmonics. Theoretical predictions using atmospheric specifications show that the stratospheric arrivals are predicted within 1% of the observed value. For thermospheric arrivals, this error can be as high as 10%. The error in thermospheric celerities is found to be in accord with the typical uncertainty in upper atmospheric winds. Given the observed response of the infrasound celerities to upper atmospheric tidal variability, it is suggested that infrasound observations may be used as an additional source of information to constrain the atmospheric specifications in the upper atmosphere. We present corrected wind profiles that have been obtained by minimizing misfits in traveltime and source location using a Bayesian statistics grid search algorithm. Also, a Levenberg-Marquardt search algorithm is developed. Additionally, a new numerical method has been developed to solve the problem of infrasound propagation in a stratified medium with (high Mach number) background flow, based on a modal expansion. The underlying mathematics is by no means new and has been earlier described. This solution goes beyond the effective sound speed approximation, which is typically used in infrasound propagation modeling for computational efficiency reasons. Using the wide-angle high Mach number modal solution, it is shown that traveltimes and shadow zones are under predicted using the effective sound speed approximation, with increasing grazing angle and Mach number.

  17. The Nuclear Cryogenic Propulsion Stage

    NASA Technical Reports Server (NTRS)

    Houts, Michael G.; Kim, Tony; Emrich, William J.; Hickman, Robert R.; Broadway, Jeramie W.; Gerrish, Harold P.; Belvin, Anthony D.; Borowski, Stanley K.; Scott, John H.

    2014-01-01

    Nuclear Thermal Propulsion (NTP) development efforts in the United States have demonstrated the technical viability and performance potential of NTP systems. For example, Project Rover (1955 - 1973) completed 22 high power rocket reactor tests. Peak performances included operating at an average hydrogen exhaust temperature of 2550 K and a peak fuel power density of 5200 MW/m3 (Pewee test), operating at a thrust of 930 kN (Phoebus-2A test), and operating for 62.7 minutes in a single burn (NRX-A6 test). Results from Project Rover indicated that an NTP system with a high thrust-to-weight ratio and a specific impulse greater than 900 s would be feasible. Excellent results were also obtained by the former Soviet Union. Although historical programs had promising results, many factors would affect the development of a 21st century nuclear thermal rocket (NTR). Test facilities built in the US during Project Rover no longer exist. However, advances in analytical techniques, the ability to utilize or adapt existing facilities and infrastructure, and the ability to develop a limited number of new test facilities may enable affordable development, qualification, and utilization of a Nuclear Cryogenic Propulsion Stage (NCPS). Bead-loaded graphite fuel was utilized throughout the Rover/NERVA program, and coated graphite composite fuel (tested in the Nuclear Furnace) and cermet fuel both show potential for even higher performance than that demonstrated in the Rover/NERVA engine tests.. NASA's NCPS project was initiated in October, 2011, with the goal of assessing the affordability and viability of an NCPS. FY 2014 activities are focused on fabrication and test (non-nuclear) of both coated graphite composite fuel elements and cermet fuel elements. Additional activities include developing a pre-conceptual design of the NCPS stage and evaluating affordable strategies for NCPS development, qualification, and utilization. NCPS stage designs are focused on supporting human Mars missions. The NCPS is being designed to readily integrate with the Space Launch System (SLS). A wide range of strategies for enabling affordable NCPS development, qualification, and utilization should be considered. These include multiple test and demonstration strategies (both ground and in-space), multiple potential test sites, and multiple engine designs. Two potential NCPS fuels are currently under consideration - coated graphite composite fuel and tungsten cermet fuel. During 2014 a representative, partial length (approximately 16") coated graphite composite fuel element with prototypic depleted uranium loading is being fabricated at Oak Ridge National Laboratory (ORNL). In addition, a representative, partial length (approximately 16") cermet fuel element with prototypic depleted uranium loading is being fabricated at Marshall Space Flight Center (MSFC). During the development process small samples (approximately 3" length) will be tested in the Compact Fuel Element Environmental Tester (CFEET) at high temperature (approximately 2800 K) in a hydrogen environment to help ensure that basic fuel design and manufacturing process are adequate and have been performed correctly. Once designs and processes have been developed, longer fuel element segments will be fabricated and tested in the Nuclear Thermal Rocket Element Environmental Simulator (NTREE) at high temperature (approximately 2800 K) and in flowing hydrogen.

  18. S-IB Stage at the Michoud Assembly Facility (MAF)

    NASA Technical Reports Server (NTRS)

    1968-01-01

    The Saturn 1B S-IB (first) stage being prepared for shipment at Michoud Assembly Facility (MAF), near New Orleans, Louisiana. Developed by the Marshall Space Flight Center and built by the Chrysler Corporation at MAF, the S-IB stage utilized the eight H-1 engines and each produced 200,000 pounds of thrust, a combined thrust of 1,600,000 pounds.

  19. 76 FR 78863 - Airworthiness Directives; Rolls-Royce Corporation Turboshaft Engines

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-12-20

    ...the 3rd stage turbine wheel and the 4th stage turbine wheel for cracks in the turbine blades, for each engine. The average labor...Formerly Allison Engine Company and Allison Gas Turbine Division of General Motors): Docket No....

  20. Two-dimensional myoelectric control of a robotic arm for upper limb amputees

    NASA Astrophysics Data System (ADS)

    López Celani, Natalia M.; Soria, Carlos M.; Orosco, Eugenio C.; di Sciascio, Fernando A.; Valentinuzzi, Max E.

    2007-11-01

    Rehabilitation engineering and medicine have become integral and significant parts of health care services, particularly and unfortunately in the last three or four decades, because of wars, terrorism and large number of car accidents. Amputees show a high rate of rejection to wear prosthetic devices, often because of lack of an adequate period of adaptation. A robotic arm may appear as a good preliminary stage. To test the hypothesis, myoelectric signals from two upper limb amputees and from four normal volunteers were fed, via adequate electronic conditioning and using MATLAB, to an industrial robotic arm. Proportional strength control was used for two degrees of freedom (x-y plane) by means of eight signal features of control (four traditional statistics plus energy, integral of the absolute value, Willison's amplitude, waveform length and envelope) for comparison purposes, and selecting the best of them as final reference. Patients easily accepted the system and learned in short time how to operate it. Results were encouraging so that valuable training, before prosthesis is implanted, appears as good feedback; besides, these patients can be hired as specialized operators in semi-automatized industry.

  1. Low Noise Research Fan Stage Design

    NASA Technical Reports Server (NTRS)

    Hobbs, David E.; Neubert, Robert J.; Malmborg, Eric W.; Philbrick, Daniel H.; Spear, David A.

    1995-01-01

    This report describes the design of a Low Noise ADP Research Fan stage. The fan is a variable pitch design which is designed at the cruise pitch condition. Relative to the cruise setting, the blade is closed at takeoff and opened for reverse thrust operation. The fan stage is a split flow design with fan exit guide vanes and core stators. This fan stage design was combined with a nacelle and engine core duct to form a powered fan/nacelle, subscale model. This model is intended for use in aerodynamic performance, acoustic and structural testing in a wind tunnel. The model has a 22-inch outer fan diameter and a hub-to-top ratio of 0.426 which permits the use of existing NASA fan and cowl force balance designs and rig drive system. The design parameters were selected to permit valid acoustic and aerodynamic comparisons with the PW 17-inch rig previously tested under NASA contract. The fan stage design is described in detail. The results of the design axisymmetric analysis at aerodynamic design condition are included. The structural analysis of the fan rotor and attachment is described including the material selections and stress analysis. The blade and attachment are predicted to have adequate low cycle fatigue life, and an acceptable operating range without resonant stress or flutter. The stage was acoustically designed with airfoil counts in the fan exit guide vane and core stator to minimize noise. A fan-FEGV tone analysis developed separately under NASA contract was used to determine these airfoil counts. The fan stage design was matched to a nacelle design to form a fan/nacelle model for wind tunnel testing. The nacelle design was developed under a separate NASA contract. The nacelle was designed with an axisymmetric inlet, cowl and nozzle for convenience in testing and fabrication. Aerodynamic analysis of the nacelle confirmed the required performance at various aircraft operating conditions.

  2. Mirror therapy enhances upper extremity motor recovery in stroke patients.

    PubMed

    Mirela Cristina, Luca; Matei, Daniela; Ignat, Bogdan; Popescu, Cristian Dinu

    2015-12-01

    The purpose of this study was to evaluate the effects of mirror therapy program in addition with physical therapy methods on upper limb recovery in patients with subacute ischemic stroke. 15 subjects followed a comprehensive rehabilitative treatment, 8 subjects received only control therapy (CT) and 7 subjects received mirror therapy (MT) for 30 min every day, five times a week, for 6 weeks in addition to the conventional therapy. Brunnstrom stages, Fugl-Meyer Assessment (upper extremity), the Ashworth Scale, and Bhakta Test (finger flexion scale) were used to assess changes in upper limb motor recovery and motor function after intervention. After 6 weeks of treatment, patients in both groups showed significant improvements in the variables measured. Patients who received MT showed greater improvements compared to the CT group. The MT treatment results included: improvement of motor functions, manual skills and activities of daily living. The best results were obtained when the treatment was started soon after the stroke. MT is an easy and low-cost method to improve motor recovery of the upper limb. PMID:25850528

  3. Two stages splicing system

    NASA Astrophysics Data System (ADS)

    Mudaber, Mohammad Hassan; Yusof, Yuhani

    2015-05-01

    The study of the biological process of deoxyribonucleic acid (DNA) splicing system in a translucent approach was investigated in 2012 by Yusof under the framework of formal language theory. In this work, the concepts of splicing system in two stages as well as splicing languages are mathematically and biologically discussed. Additionally, some theorems based on recognition site factor of initial strings at the existence of two initial strings and two rules are provided via Yusof-Goode (Y-G) approach. Besides, an example is also given in showing the biological meaning of the introduced concept.

  4. Chimpanzee sleep stages.

    NASA Technical Reports Server (NTRS)

    Freemon, F. R.; Mcnew, J. J.; Adey, W. R.

    1971-01-01

    The electroencephalogram and electro-oculogram of two unrestrained juvenile chimpanzees was monitored for 7 consecutive nights using telemetry methods. Of the sleeping time, 23% was spent in the rapid eye movement of REM type of sleep, whereas 8, 4, 15, and 10% were spent in non-REM stages 1 through 4, respectively. Seven to nine periods of REM sleep occurred per night. The average time from the beginning of one REM period to the beginning of the next was approximately 85 min.

  5. Upper disparity limit after LASIK.

    PubMed

    Jiménez, José R; Castro, José J; Hita, Enrique; Anera, Rosario G

    2008-06-01

    We evaluate the effect of the emmetropization technique LASIK (laser-assisted in situ keratomileusis) on stereoscopic vision. For this, we used a mirror stereoscope to measure the upper disparity limit D(max) before (with best correction) and after LASIK for 30 patients. The results show that the upper disparity limit declines from 41.1 min of arc on average to 31.3 min of arc after LASIK, being significant in 83% of the patients. This deterioration is significantly correlated with an increase in the postsurgical interocular differences in higher-order aberrations, corneal asphericity, and presurgical anisometropia. New ablation algorithms should minimize interocular differences in order to improve binocular visual performance. PMID:18516131

  6. The Art and Science of Systems Engineering

    NASA Technical Reports Server (NTRS)

    Singer, Christopher E.

    2009-01-01

    The National Aeronautics and Space Administration (NASA) was established in 1958, and its Marshall Space Flight Center was founded in 1960, as space-related work was transferred from the Army Ballistic Missile Agency at Redstone Arsenal, where Marshall is located. With this heritage, Marshall contributes almost 50 years of systems engineering experience with human-rated launch vehicles and scientific spacecraft to fulfill NASA's mission exploration and discovery. These complex, highly specialized systems have provided vital platforms for expanding the knowledge base about Earth, the solar system, and cosmos; developing new technologies that also benefit life on Earth; and opening new frontiers for America's strategic space goals. From Mercury and Gemini, to Apollo and the Space Shuttle, Marshall's systems engineering expertise is an unsurpassed foundational competency for NASA and the nation. Current assignments comprise managing Space Shuttle Propulsion systems; developing environmental control and life support systems and coordinating science operations on the International Space Station; and a number of exploration-related responsibilities. These include managing and performing science missions, such as the Lunar Crater Observation and Sensing Satellite and the Lunar Reconnaissance Orbiter slated to launch for the Moon in April 2009, to developing the Ares I crew launch vehicle upper stage and integrating the vehicle stack in house, as well as designing the Ares V cargo launch vehicle and contributing to the development of the Altair Lunar Lander and an International Lunar Network with communications nodes and other infrastructure.

  7. ENVIRONMENTAL ENGINEERING

    E-print Network

    Walter, M.Todd

    ENVIRONMENTAL ENGINEERING UNDERGRADUATEHANDBOOK #12;Environmental Engineering 2015-2016 2015-16 UNDERGRADUATE HANDBOOK FOR ENVIRONMENTAL ENGINEERING MISSION STATEMENT FOR ENVIRONMENTAL ENGINEERING PROGRAM · Educate the next generation of environmental engineering professionals and assist in the education

  8. Development and Applications of a Stage Stacking Procedure

    NASA Technical Reports Server (NTRS)

    Kulkarni, Sameer; Celestina, Mark L.; Adamczyk, John J.

    2012-01-01

    The preliminary design of multistage axial compressors in gas turbine engines is typically accomplished with mean-line methods. These methods, which rely on empirical correlations, estimate compressor performance well near the design point, but may become less reliable off-design. For land-based applications of gas turbine engines, off-design performance estimates are becoming increasingly important, as turbine plant operators desire peaking or load-following capabilities and hot-day operability. The current work develops a one-dimensional stage stacking procedure, including a newly defined blockage term, which is used to estimate the off-design performance and operability range of a 13-stage axial compressor used in a power generating gas turbine engine. The new blockage term is defined to give mathematical closure on static pressure, and values of blockage are shown to collapse to curves as a function of stage inlet flow coefficient and corrected shaft speed. In addition to these blockage curves, the stage stacking procedure utilizes stage characteristics of ideal work coefficient and adiabatic efficiency. These curves are constructed using flow information extracted from computational fluid dynamics (CFD) simulations of groups of stages within the compressor. Performance estimates resulting from the stage stacking procedure are shown to match the results of CFD simulations of the entire compressor to within 1.6% in overall total pressure ratio and within 0.3 points in overall adiabatic efficiency. Utility of the stage stacking procedure is demonstrated by estimation of the minimum corrected speed which allows stable operation of the compressor. Further utility of the stage stacking procedure is demonstrated with a bleed sensitivity study, which estimates a bleed schedule to expand the compressors operating range.

  9. The upper atmosphere of Uranus

    NASA Technical Reports Server (NTRS)

    Strobel, Darrell F.; Yelle, Roger V.; Shemansky, Donald E.; Atreya, Sushil K.

    1991-01-01

    Voyager measurements of the upper atmosphere of Uranus are analyzed and developed. The upper atmosphere of Uranus is predominantly H2, with at most 10 percent He by volume, and the dominant constituent of the exosphere is H. The thermosphere is warm, with an asymptotic isothermal temperature of about 800 K. Atomic hydrogen at this temperature forms an extensive thermal corona and creates gas drag that severely limits the lifetime of small ring particles. The upper atmosphere emits copious amounts of UV radiation from pressures greater than 0.01 microbar. The depth of this emission level imposes a powerful constraint on permissible emission mechanisms. Electron excitation from a thin layer near the exobase appears to violate this constraint. Solar fluorescence is consistent with the observed trend in solar zenith-angle variation of the emissions and is absent from the night side of the planet. On Uranus, it accounts for the observed Lyman beta to H2 bands intensity ratio and an important fraction of the observed intensity (about 55 percent).

  10. [Stages of breast cancer].

    PubMed

    Savran, V R; Fetsych, T H; Savran, V V; Tril', O V; Myshakivs'ky?, O M

    2006-01-01

    A comparative analysis of several systems of the assessment of the degree of spreading of malignant process is presented in the article. Stage principles of malignant neoplasms, which are used by the National Cancer Register do not respond current requirements as these principles do not single out preinvasive carcinoma and even more patients with I and II stages malignant neoplasms are brought into one group. Last reduction of the International TNM breast cancer classification (2002, TNM-6) reflects further progress in understanding biology of this localization and possibilities of the diagnostics. This classification differs considerably from previous reductions (TNM-4 and TNM-5) and especially Soviet classification dated 1985. The study carried out by the authors showed importance of differential approach to the assessment of regional lymphatic nodes lesion on depending their quantity (in diapason from 1 to 3; 4-9; 10 and more). The authors stated in the article that there is a certain discrepancy of some clinical and pathohistological parameters (N not equal to pN) in the last reduction of TNM classification of breast cancer and interpretation of some categories of the system is over-complex. PMID:17100177

  11. Engineering COLLEGE of ENGINEERING

    E-print Network

    Berdichevsky, Victor

    American universities chosen to compete in EcoCAR 2 Resumebooster Our 16-credit EDGE Engineering Entrepreneur Certificate Program is a great addition to a biomedical engineering degree. The EDGE program job prospects. Focused on medical sciences and interventions, biomedical engineers create new, game

  12. Rhinovirus infections in the upper airway.

    PubMed

    Winther, Birgit

    2011-03-01

    The majority of cold and flulike illnesses are caused by human rhinoviruses (HRVs). Improved detection of HRV has shown that HRVs are also associated with more serious illness, such as exacerbation of asthma, wheezing illnesses in children, chronic obstructive pulmonary disease, cardiopulmonary disease, and fatal pneumonia in immune-compromised patients. HRV is a major cause of acute viral respiratory tract infections in hospitalized children and is among the leading causes of childhood mortality worldwide. Detection of the HRV genome by reverse transcriptase-polymerase chain reaction and genomic sequencing has brought to light a new clade, HRV-C, to the already recognized HRV-A and HRV-B clades. The clinical complications related to all rhinovirus infections include acute otitis media, acute sinusitis, and acute bronchitis. The enormous public health implications from those diseases far overshadow those of the common cold. This article provides an overview of the pathogenesis of rhinovirus infection in the upper airways. Most research has been done in young healthy adults with self-limiting experimental and natural rhinovirus infections, and this may set the stage for understanding rhinovirus infections in the ear, sinus, and lower airways. PMID:21364225

  13. 4. INTERIOR OF ENGINE ROOM, CONTAINING UNITEDTOD TWINTANDEM ENGINE, FOR ...

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

    4. INTERIOR OF ENGINE ROOM, CONTAINING UNITED-TOD TWIN-TANDEM ENGINE, FOR 40" BLOOMING MILL; AS SEEN FROM THE UPPER LEVEL BRIDGE CRANE, THIS ENGINE WAS THE DIRECT DRIVE TO THE 40" BLOOMING MILL LOCATED IN THE ADJACENT ROOM TO THE LEFT. THE UNITED-TOD ENGINE, A TWIN TANDEM COMPOUND STEAM ENGINE, WAS RATED AT 20,000 MP. IN 1946 NEW HIGH PRESSURE CYLINDERS WERE INSTALLED AND THE ENGINE RAN ON 200 PSI STEAM, WITH A 44"X76"X60" STROKE, TO A BUILT-UP COUNTER-BALANCED CENTER CRANK. - Republic Iron & Steel Company, Youngstown Works, Blooming Mill & Blooming Mill Engines, North of Poland Avenue, Youngstown, Mahoning County, OH

  14. BOSTON UNIVERSITY COLLEGE OF ENGINEERING

    E-print Network

    Lin, Xi

    for achieving high quality · Quality in design vs. quality in production · Robustness · How to achieve high purpose, how to design, how is it used in different stages of quality control and improvement) 4. ProcessBOSTON UNIVERSITY COLLEGE OF ENGINEERING DEPARTMENT OF MANUFACTURING ENGINEERING Product Quality

  15. Student Briefing College Of Engineering

    E-print Network

    Hickman, Mark

    Student Briefing College Of Engineering February 2009 #12;"Going Home Uninjured" · Our objective safety at some stage. · You are responsible for your own safety. · The College of Engineering has 4 phone numbers · Fire and earthquake procedures #12;Telephone Numbers · Emergency services 111 (from cell

  16. Improved Mars Upper Atmosphere Climatology

    NASA Technical Reports Server (NTRS)

    Bougher, S. W.

    2004-01-01

    The detailed characterization of the Mars upper atmosphere is important for future Mars aerobraking activities. Solar cycle, seasonal, and dust trends (climate) as well as planetary wave activity (weather) are crucial to quantify in order to improve our ability to reasonably depict the state of the Mars upper atmosphere over time. To date, our best information is found in the Mars Global Surveyor (MGS) Accelerometer (ACC) database collected during Phase 1 (Ls = 184 - 300; F10.7 = 70 - 90) and Phase 2 (Ls = 30 - 90; F10.7 = 90 - 150) of aerobraking. This database (100 - 170 km) consists of thermospheric densities, temperatures, and scale heights, providing our best constraints for exercising the coupled Mars General Circulation Model (MGCM) and the Mars Thermospheric General Circulation Model (MTGCM). The Planetary Data System (PDS) contains level 0 and 2 MGS Accelerometer data, corresponding to atmospheric densities along the orbit track. Level 3 products (densities, temperatures, and scale heights at constant altitudes) are also available in the PDS. These datasets provide the primary model constraints for the new MGCM-MTGCM simulations summarized in this report. Our strategy for improving the characterization of the Mars upper atmospheres using these models has been three-fold : (a) to conduct data-model comparisons using the latest MGS data covering limited climatic and weather conditions at Mars, (b) to upgrade the 15-micron cooling and near-IR heating rates in the MGCM and MTGCM codes for ad- dressing climatic variations (solar cycle and seasonal) important in linking the lower and upper atmospheres (including migrating tides), and (c) to exercise the detailed coupled MGCM and MTGCM codes to capture and diagnose the planetary wave (migrating plus non-migrating tidal) features throughout the Mars year. Products from this new suite of MGCM-MTGCM coupled simulations are being used to improve our predictions of the structure of the Mars upper atmosphere for the upcoming MRO aerobraking exercises in 2006. A Michigan website, containing MTGCM output fields from previous climate simulations, is being expanded to include new MGCM-MTGCM simulations addressing planetary wave influences upon thermospheric aerobraking fields (densities and temperatures). In addition, similar MTGCM output fields have been supplied to the MSFC MARSGRAM - 200X empirical model, which will be used in mission operations for conducting aerobraking maneuvers.

  17. Pumping stage for multi-stage centrifugal pump

    SciTech Connect

    Erickson, J.W.

    1981-07-14

    An improved diffusion bowl and pumping vanes of a centrifugal pump stage are employed in axially stacked, multi-stage pumps for use in oil wells. The wall thickness of the annular casing portion of the diffusion bowl element is reduced to a minimum consistent with the axial loading on the pump stage and the impeller vanes are radially extended to terminate closely adjacent the minimum wall thickness portion of the casing, thereby significantly increasing the pumping pressure developed by the stage without reducing the efficiency of the stage.

  18. COLLEGE OF ENGINEERING Biological Engineering

    E-print Network

    Walter, M.Todd

    COLLEGE OF ENGINEERING Biological Engineering Undergraduate Class of 2013 Post-Graduation Report The Department Biological and Environmental Engineering (BEE) offers a bachelor degree program in Biological Engineering and a bachelor degree program in Environmental Engineering. Cornell Career Services surveys

  19. 76 FR 77378 - Airworthiness Directives; Turbomeca Arriel 1 Series Turboshaft Engines

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-12-13

    ...Remove from service gas generator second stage turbine discs, P/N 0 292...since-new. (f) Gas Generator Second Stage Turbine Installation Prohibition...install into any engine gas generator second stage turbine discs, P/N 0...

  20. Breast Cancer Stage and Survival

    MedlinePLUS Videos and Cool Tools

    ... gov/medlineplus/videos/news/Cancer_Stage_100715.html Breast Cancer Stage and Survival HealthDay News Video - October 8, ... on this page, please enable JavaScript. Play video: Breast Cancer Stage and Survival For closed captioning, click the ...

  1. Ares First Stage Element Status

    NASA Technical Reports Server (NTRS)

    Tiller, Bruce K.

    2009-01-01

    This slide presentation summarizes the status of the various elements of the first stage of the Ares I vehicle. It includes views of the first stage in relation to the complete Ares rocket, details of the first stage, upgrades for the Ares, the Avionics system, and the thrust oscillation system. There are also pictures from the testing.

  2. Study of blade aspect ratio on a compressor front stage

    NASA Technical Reports Server (NTRS)

    Behlke, R. F.; Brooky, J. D.; Canal, E., Jr.

    1980-01-01

    A single stage, low aspect ratio, compressor with a 442.0 m/sec (1450 ft/sec) tip speed and a 0.597 hub/tip ratio typical of an advanced core compressor front stage was tested. The test stage incorporated an inlet duct which was representative of an engine transition duct between fan and high pressure compressors. At design speed, the rotor stator stage achieved a peak adiabatic efficiency of 86.6 percent at a flow of 44.35 kg/sec (97.8 lbm/sec) and a pressure ratio of 1.8. Surge margin was 12.5 percent from the peak stage efficiency point.

  3. Upper Endoscopy for Gastroesophageal Reflux Disease

    MedlinePLUS

    Annals of Internal Medicine Summaries for Patients Upper Endoscopy for Gastroesophageal Re?ux Disease The full report is titled “Upper Endoscopy for Gastroesophageal Re?ux Disease: Best Practice Advice From ...

  4. X-Ray Exam: Femur (Upper Leg)

    MedlinePLUS

    ... Sports: Keeping Kids Safe Concussions: What to Know X-Ray Exam: Femur (Upper Leg) KidsHealth > Parents > Doctors & Hospitals > Medical Tests & Exams > X-Ray Exam: Femur (Upper Leg) Print A A A ...

  5. The NASA program on upper atmospheric research

    NASA Technical Reports Server (NTRS)

    1976-01-01

    The purpose of the NASA Upper Atmospheric Research Program is to develop a better understanding of the physical and chemical processes that occur in the earth's upper atmosphere with emphasis on the stratosphere.

  6. Bryan Mound SPR cavern 113 remedial leach stage 1 analysis.

    SciTech Connect

    Rudeen, David Keith; Weber, Paula D.; Lord, David L.

    2013-08-01

    The U.S. Strategic Petroleum Reserve implemented the first stage of a leach plan in 2011-2012 to expand storage volume in the existing Bryan Mound 113 cavern from a starting volume of 7.4 million barrels (MMB) to its design volume of 11.2 MMB. The first stage was terminated several months earlier than expected in August, 2012, as the upper section of the leach zone expanded outward more quickly than design. The oil-brine interface was then re-positioned with the intent to resume leaching in the second stage configuration. This report evaluates the as-built configuration of the cavern at the end of the first stage, and recommends changes to the second stage plan in order to accommodate for the variance between the first stage plan and the as-built cavern. SANSMIC leach code simulations are presented and compared with sonar surveys in order to aid in the analysis and offer projections of likely outcomes from the revised plan for the second stage leach.

  7. Experimental Investigation of a High Pressure Ratio Aspirated Fan Stage

    NASA Technical Reports Server (NTRS)

    Merchant, Ali; Kerrebrock, Jack L.; Adamczyk, John J.; Braunscheidel, Edward

    2004-01-01

    The experimental investigation of an aspirated fan stage designed to achieve a pressure ratio of 3.4:1 at 1500 ft/sec is presented in this paper. The low-energy viscous flow is aspirated from diffusion-limiting locations on the blades and flowpath surfaces of the stage, enabling a very high pressure ratio to be achieved in a single stage. The fan stage performance was mapped at various operating speeds from choke to stall in a compressor facility at fully simulated engine conditions. The experimentally determined stage performance, in terms of pressure ratio and corresponding inlet mass flow rate, was found to be in good agreement with the three-dimensional viscous computational prediction, and in turn close to the design intent. Stage pressure ratios exceeding 3:1 were achieved at design speed, with an aspiration flow fraction of 3.5 percent of the stage inlet mass flow. The experimental performance of the stage at various operating conditions, including detailed flowfield measurements, are presented and discussed in the context of the computational analyses. The sensitivity of the stage performance and operability to reduced aspiration flow rates at design and off design conditions are also discussed.

  8. Bevacizumab, Cisplatin, Radiation Therapy, and Fluorouracil in Treating Patients With Stage IIB, Stage III, Stage IVA, or Stage IVB Nasopharyngeal Cancer

    ClinicalTrials.gov

    2014-04-21

    Stage II Squamous Cell Carcinoma of the Nasopharynx; Stage III Lymphoepithelioma of the Nasopharynx; Stage III Squamous Cell Carcinoma of the Nasopharynx; Stage IV Lymphoepithelioma of the Nasopharynx; Stage IV Squamous Cell Carcinoma of the Nasopharynx

  9. Oblimersen Sodium and Combination Chemotherapy in Treating Patients With Newly Diagnosed Stage I, Stage II, Stage III, or Stage IV Diffuse Large B-Cell Lymphoma

    ClinicalTrials.gov

    2012-10-11

    Contiguous Stage II Adult Diffuse Large Cell Lymphoma; Noncontiguous Stage II Adult Diffuse Large Cell Lymphoma; Stage I Adult Diffuse Large Cell Lymphoma; Stage III Adult Diffuse Large Cell Lymphoma; Stage IV Adult Diffuse Large Cell Lymphoma

  10. Cisplatin and Radiation Therapy Followed by Paclitaxel and Carboplatin in Treating Patients With Stage I, Stage II, Stage III, or Stage IV Cervical Cancer

    ClinicalTrials.gov

    2014-12-23

    Cervical Adenocarcinoma; Cervical Adenosquamous 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

  11. Transport and Use of a Centaur Second Stage in Space

    NASA Technical Reports Server (NTRS)

    Strong, James M.; Morgowicz, Bernard; Drucker, Eric; Tompkins, Paul D.; Kennedy, Brian; Barber, Robert D,; Luzod, Louie T.; Kennedy, Brian Michael; Luzod, Louie T.

    2010-01-01

    As nations continue to explore space, the desire to reduce costs will continue to grow. As a method of cost reduction, transporting and/or use of launch system components as integral components of missions may become more commonplace in the future. There have been numerous scenarios written for using launch vehicle components (primarily space shuttle used external tanks) as part of flight missions or future habitats. Future studies for possible uses of launch vehicle upper stages might include asteroid diverter using gravity orbital perturbation, orbiting station component, raw material at an outpost, and kinetic impactor. The LCROSS (Lunar CRater Observation and Sensing Satellite) mission was conceived as a low-cost means of determining whether water exists at the polar regions of the moon. Manifested as a secondary payload with the LRO (Lunar Reconnaissance Orbiter) spacecraft aboard an Atlas V launch vehicle, LCROSS guided its spent Centaur Earth Departure Upper Stage (EDUS) into the lunar crater Cabeu's, as a kinetic impactor. This paper describes some of the challenges that the LCROSS project encountered in planning, designing, launching with and carrying the Centaur upper stage to the moon.

  12. A Rare Cause of Testicular Metastasis: Upper Tract Urothelial Carcinoma

    PubMed Central

    Manav, Alper Nesip; Kazan, Ercan; Ertek, Mehmet ?irin; Amasyal?, Ak?n Soner; Çulhac?, Nil; Erol, Haluk

    2014-01-01

    Metastatic testicular cancers are rare. Primary tumor sources are prostate, lung, and gastrointestinal tract for metastatic testicular cancers. Metastasis of urothelial carcinoma (UC) to the testis is extremely rare. Two-thirds of upper tract urothelial carcinoma (UTUC) is of invasive stage at diagnosis and metastatic sites are the pelvic lymph nodes, liver, lung, and bone. We report a rare case of metastatic UTUC to the testis which has not been reported before, except one case in the literature. Testicular metastasis of UC should be considered in patients with hematuria and testicular swelling. PMID:25120937

  13. Tissue engineering.

    PubMed

    Katari, Ravi S; Peloso, Andrea; Orlando, Giuseppe

    2014-01-01

    Ultimately much work remains to be done in the companion fields of biomaterials and stem cells. Nonetheless, the monumental progress in TE that has been reported in the studies summarized here demonstrates that regenerative approaches to problems in general surgery need to be explored in more depth. Furthermore, the surgical disciplines of reconstruction and transplantation need to recognize their research counterparts in TE, given its potential to actualize freedom from immunosuppression, one of the most elusive goals in modern surgery. The engineering and proliferation of autologous cells, tissues, and organs ex vivo before surgical operation can significantly reduce the obstacles current practitioners are intimately familiar with: donor site morbidity and immunologic rejection. Therefore, in addition to the truly exciting research and development prospects and implications for the commercial sector, patients with end-stage diseases and debilitating injury stand to gain the most from clinically adapted TE therapies. PMID:25293612

  14. PREDICTING TURBINE STAGE PERFORMANCE

    NASA Technical Reports Server (NTRS)

    Boyle, R. J.

    1994-01-01

    This program was developed to predict turbine stage performance taking into account the effects of complex passage geometries. The method uses a quasi-3D inviscid-flow analysis iteratively coupled to calculated losses so that changes in losses result in changes in the flow distribution. In this manner the effects of both the geometry on the flow distribution and the flow distribution on losses are accounted for. The flow may be subsonic or shock-free transonic. The blade row may be fixed or rotating, and the blades may be twisted and leaned. This program has been applied to axial and radial turbines, and is helpful in the analysis of mixed flow machines. This program is a combination of the flow analysis programs MERIDL and TSONIC coupled to the boundary layer program BLAYER. The subsonic flow solution is obtained by a finite difference, stream function analysis. Transonic blade-to-blade solutions are obtained using information from the finite difference, stream function solution with a reduced flow factor. Upstream and downstream flow variables may vary from hub to shroud and provision is made to correct for loss of stagnation pressure. Boundary layer analyses are made to determine profile and end-wall friction losses. Empirical loss models are used to account for incidence, secondary flow, disc windage, and clearance losses. The total losses are then used to calculate stator, rotor, and stage efficiency. This program is written in FORTRAN IV for batch execution and has been implemented on an IBM 370/3033 under TSS with a central memory requirement of approximately 4.5 Megs of 8 bit bytes. This program was developed in 1985.

  15. Cascade thermoacoustic engine

    NASA Astrophysics Data System (ADS)

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

    2003-04-01

    Over the past several years, Los Alamos has successfully fabricated and tested traveling wave thermoacoustic heat engines having efficiencies much greater than those of traditional standing wave thermoacoustic engines. Unfortunately, Gedeon streaming effects present in these traveling wave engines has required using fluid flow ``diodes'' having greater complexity than desired. The cascade thermoacoustic engine recently fabricated and tested at Los Alamos uses three stages in series, one standing wave and two traveling wave, yielding a configuration in which Gedeon streaming is eliminated and efficiency can still be high. The cascade engine will be described and experimental data will be presented. [Work supported by the U.S. DOE Office of Science and Praxair, Inc.

  16. Satellite Upper Air Network (SUAN)

    NASA Astrophysics Data System (ADS)

    Reale, Tony L.; Thorne, Peter

    2004-10-01

    During the past 20 years of NOAA operational polar satellites, it has become evident that a growing problem concerning their utilization in Climate and also Numerical Weather Prediction (NWP) applications are the systematic errors and uncertainties inherent in the satellite measurements. Similar arguments can be made for global radiosonde observations. These uncertainties are often larger than the sensitive signals and processes, that satellite and radiosonde measurements are designed to reveal, particularly in the realm of climate. Possible strategies to quantify and compensate for these problems include the analysis of satellite overlap data and/or available collocations of satellite and ground truth (radiosonde) observations. However, overlap observations are typically not available except in extreme polar regions and current sampling strategies for compiling collocated radiosonde and satellite observations are insufficient, further compounding the inherent uncertainties in the ground-truth radiosonde data. A Satellite Upper Air Network is proposed to provide reference radiosonde launches coincident with operational polar satellite(s) overpass. The SUAN consist of 36 global radiosonde stations sub-sampled from the Global Upper Air Network (GUAN), and is designed to provide a robust, global sample of collocated radiosonde and satellite observations conducive to the monitoring and validation of satellite and radiosonde observations. The routine operation of such a network in conjunction with operational polar satellites would provide a long-term of performance for critical observations of particular importance for climate. The following report presents a candidate network of 36 upper-air sites that could comprise a SUAN. Their selection along with the mutual benefit across the satellite, radiosonde, climate, numerical weather prediction (NWP) and radiative transfer (RT) model areas are discussed.

  17. Physiological Mechanisms of Upper Airway Hypotonia during REM Sleep

    PubMed Central

    McSharry, David G.; Saboisky, Julian P.; DeYoung, Pam; Jordan, Amy S.; Trinder, John; Smales, Erik; Hess, Lauren; Chamberlin, Nancy L.; Malhotra, Atul

    2014-01-01

    Study Objectives: Rapid eye movement (REM)-induced hypotonia of the major upper airway dilating muscle (genioglossus) potentially contributes to the worsening of obstructive sleep apnea that occurs during this stage. No prior human single motor unit (SMU) study of genioglossus has examined this possibility to our knowledge. We hypothesized that genioglossus SMUs would reduce their activity during stable breathing in both tonic and phasic REM compared to stage N2 sleep. Further, we hypothesized that hypopneas occurring in REM would be associated with coincident reductions in genioglossus SMU activity. Design: The activity of genioglossus SMUs was studied in (1) neighboring epochs of stage N2, and tonic and phasic REM; and (2) during hypopneas occurring in REM. Setting: Sleep laboratory. Participants: 29 subjects (38 ± 13 y) (17 male). Intervention: Natural sleep, including REM sleep and REM hypopneas. Measurement and Results: Subjects slept overnight with genioglossus fine-wire intramuscular electrodes and full polysomnography. Forty-two SMUs firing during one or more of stage N2, tonic REM, or phasic REM were sorted. Twenty inspiratory phasic (IP), 17 inspiratory tonic (IT), and five expiratory tonic (ET) SMUs were characterized. Fewer units were active during phasic REM (23) compared to tonic REM (30) and stage N2 (33). During phasic REM sleep, genioglossus IP and IT SMUs discharged at slower rates and for shorter durations than during stage N2. For example, the SMU peak frequency during phasic REM 5.7 ± 6.6 Hz (mean ± standard deviation) was less than both tonic REM 12.3 ± 9.7 Hz and stage N2 16.1 ± 10.0 Hz (P < 0.001). The peak firing frequencies of IP/IT SMUs decreased from the last breath before to the first breath of a REM hypopnea (11.8 ± 10.9 Hz versus 5.7 ± 9.4 Hz; P = 0.001) Conclusion: Genioglossus single motor unit activity is significantly reduced in REM sleep, particularly phasic REM. Single motor unit activity decreases abruptly at the onset of REM hypopneas. Citation: McSharry DG; Saboisky JP; DeYoung P; Jordan AS; Trinder J; Smales E; Hess L; Chamberlin NL; Malhotra A. Physiological mechanisms of upper airway hypotonia during REM sleep. SLEEP 2014;37(3):561-569. PMID:24587579

  18. Pediatric feline upper respiratory disease.

    PubMed

    Sykes, Jane E

    2014-03-01

    Infectious feline upper respiratory tract disease (URTD) continues to be a widespread and important cause of morbidity and mortality in kittens. Multiple pathogens can contribute to URTD in kittens, and coinfections are common in overcrowded environments and contribute to increased disease severity. Worldwide, the most prevalent pathogens are feline herpesvirus-1 and feline calicivirus. Primary bacterial causes of URTD in cats include Bordetella bronchiseptica, Chlamydia felis, and Mycoplasma species. Streptococcus canis and Streptococcus equi subspecies zooepidemicus occasionally play a role as primary pathogens in shelter situations and catteries. This article reviews the major causes of disease in kittens, and provides an update on treatment and prevention strategies. PMID:24580994

  19. A Hybrid Sport Education-Games for Understanding Striking/Fielding Unit for Upper Elementary Pupils

    ERIC Educational Resources Information Center

    Curtner-Smith, Matthew

    2004-01-01

    This article describes a hybrid Sport Education-Games for Understanding unit through which upper elementary pupils can learn to play basic striking/fielding games. The unit is written for a class of 30 pupils. The twenty-five lesson unit is described in detail within 10 stages: (1) Getting started and early skill, strategy, rule, and role work…

  20. Progressive Pulmonary Fibrocystic Changes of Both Upper Lungs in a Patient with Ankylosing Spondylitis

    PubMed Central

    Kim, Do Youn; Lee, Seok Jeong; Lee, Jin Hwa; Chang, Jung Hyun; Kim, Yookyung

    2015-01-01

    Ankylosing spondylitis is a chronic inflammatory multisystem disease that primarily affects the axial joints. Pleuropulmonary involvement is an uncommon extra-articular manifestation of ankylosing spondylitis. There is a wide spectrum of pulmonary parenchymal changes in ankylosing spondylitis, beginning in the early stages of the disease and increasing over time. The lesions are usually asymptomatic, and not visible on chest radiographs in early stages. We reported a case of advanced ankylosing spondylitis in a 56-year-old man with progressive pulmonary bullous fibrocystic changes on both upper lobes that were misdiagnosed as tuberculosis in the early stages of the disease. PMID:26508946

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

    NASA Technical Reports Server (NTRS)

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

    2010-01-01

    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.

  2. College of Engineering College of Engineering

    E-print Network

    Connors, Daniel A.

    College of Engineering _______________ 2.7 Page 1 College of Engineering Office in Engineering Siller, Associate Dean UNDERGRADUATE MAJORS Biomedical Engineering Chemical and Biological Engineering Civil Engineering Computer Engineering Electrical Engineering Engineering Science Environmental

  3. 40 CFR 89.915 - Staged-assembly exemption.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... 40 Protection of Environment 20 2010-07-01 2010-07-01 false Staged-assembly exemption. 89.915 Section 89.915 Protection of Environment ENVIRONMENTAL PROTECTION AGENCY (CONTINUED) AIR PROGRAMS (CONTINUED) CONTROL OF EMISSIONS FROM NEW AND IN-USE NONROAD COMPRESSION-IGNITION ENGINES...

  4. Advanced two-stage compressor program design of inlet stage

    NASA Technical Reports Server (NTRS)

    Bryce, C. A.; Paine, C. J.; Mccutcheon, A. R. S.; Tu, R. K.; Perrone, G. L.

    1973-01-01

    The aerodynamic design of an inlet stage for a two-stage, 10/1 pressure ratio, 2 lb/sec flow rate compressor is discussed. Initially a performance comparison was conducted for an axial, mixed flow and centrifugal second stage. A modified mixed flow configuration with tandem rotors and tandem stators was selected for the inlet stage. The term conical flow compressor was coined to describe a particular type of mixed flow compressor configuration which utilizes axial flow type blading and an increase in radius to increase the work input potential. Design details of the conical flow compressor are described.

  5. Carboplatin and Paclitaxel With or Without Cisplatin and Radiation Therapy in Treating Patients With Stage I, Stage II, Stage III, or Stage IVA Endometrial Cancer

    ClinicalTrials.gov

    2014-12-23

    Endometrial Clear Cell Adenocarcinoma; Endometrial Serous Adenocarcinoma; Stage IA Uterine Corpus Cancer; Stage IB Uterine Corpus Cancer; Stage II Uterine Corpus Cancer; Stage IIIA Uterine Corpus Cancer; Stage IIIB Uterine Corpus Cancer; Stage IIIC Uterine Corpus Cancer; Stage IVA Uterine Corpus Cancer

  6. 114 MECHANICAL ENGINEERING Department of Mechanical Engineering (MEE)

    E-print Network

    Kostic, Milivoje M.

    education credit. The Department of Mechanical Engineering offers an upper- division curriculum which leads and laboratory courses. Computers are used extensively throughout the curriculum, with emphasis on interactive computer design/ computer aided manufacturing. The department also has a significant amount of equipment

  7. MECHANICAL ENGINEERING 121 Department of Mechanical Engineering (MEE)

    E-print Network

    Kostic, Milivoje M.

    education credit. The Department of Mechanical Engineering offers an upper- division curriculum which leads and laboratory courses. Computers are used extensively throughout the curriculum, with emphasis on interactive computer design/ computer aided manufacturing. The department also has a significant amount of equipment

  8. Effects of upper-surface blowing and thrust vectoring on low-speed aerodynamic characteristics of a large-scale supersonic transport model

    NASA Technical Reports Server (NTRS)

    Coe, P. L., Jr.; Mclemore, H. C.; Shivers, J. P.

    1975-01-01

    Tests were conducted in the Langley full-scale tunnel to determine the low-speed aerodynamic characteristics of a large-scale arrow-wing supersonic transport configured with engines mounted above the wing for upper surface blowing, and conventional lower surface engines with provisions for thrust vectoring. A limited number of tests were conducted for the upper surface engine configuration in the high lift condition for beta = 10 in order to evaluate lateral directional characteristics, and with the right engine inoperative to evaluate the engine out condition.

  9. 115. Stage Level floor structure. Detail of the ends of ...

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

    115. Stage Level floor structure. Detail of the ends of three movable stage floor sections. An inclined steel angle track attached to the web of the floor beam allows the sections to roll under the fixed floor. The upper section of the inclined track is hinged so it can be moved upward by a cam mechanism to raise the end of the movable section level with the stage floor. A similar mechanism was used to open and close the floor sections for the star lifts (see sheet 4 of 9, note 6; sheet 8 of 9, details 5, 6A and 6B; sheet 6 of 9, notes 2A, 2B, and 3; and photo IL-1007-120). The pulley, and tongue extending out from the end of the movable section, were used to move the sections back and forth. - Auditorium Building, 430 South Michigan Avenue, Chicago, Cook County, IL

  10. Electrical, Engineering

    E-print Network

    Environment (Paul Westerhoff) Civil and Environmental Engineering Construction Management EnvironmentalSchool of Electrical, Computer and Energy Engineering 2009-2010 Annual Report #12;Organizational Structure for Ira A. Fulton Schools of Engineering Schools (Director) Lead These Engineering Undergraduate

  11. Engineering Prestigious

    E-print Network

    Saskatchewan, University of

    Engineering Studious Prestigious Adventurous Curious Ambitious Ingenious #12;TheCollegeof Engineering We are committed to innovation in all aspects of engineering education and research. We deliver an accredited professional education program that effectively prepares our students to become engineering

  12. Alternate vehicles for engine/vehicle optimization

    NASA Technical Reports Server (NTRS)

    Venkatasubramanyam, G.; Martin, James A.

    1993-01-01

    The space shuttle main engine, full flow staged combustion, integrated modular engine concept, split expander, and expander bleed rocket engine cycles were studied for use on Single-Stage-to-Orbit fully reusable vehicles. The vehicle uses vertical take-off and horizontal landing and liquid hydrogen rockets for propulsion. The PROPSIZE computer code was modified for use on the available computers. Vehicle sizing was done after trajectory optimization for various engine designs. The various rocket engine cycles were compared and it was found that the full flow staged combustion cycle had the lowest vehicle dry mass. The split expander cycle could have advantages in safety and cooling which could make it the preferred choice in some cases. Comparison to previous work with two-stage heavy-lift vehicles showed that the same ranking of the cycles was found for both vehicle concepts.

  13. Alternate vehicles for engine/vehicle optimization

    NASA Astrophysics Data System (ADS)

    Venkatasubramanyam, G.; Martin, James A.

    1993-06-01

    The space shuttle main engine, full flow staged combustion, integrated modular engine concept, split expander, and expander bleed rocket engine cycles were studied for use on Single-Stage-to-Orbit fully reusable vehicles. The vehicle uses vertical take-off and horizontal landing and liquid hydrogen rockets for propulsion. The PROPSIZE computer code was modified for use on the available computers. Vehicle sizing was done after trajectory optimization for various engine designs. The various rocket engine cycles were compared and it was found that the full flow staged combustion cycle had the lowest vehicle dry mass. The split expander cycle could have advantages in safety and cooling which could make it the preferred choice in some cases. Comparison to previous work with two-stage heavy-lift vehicles showed that the same ranking of the cycles was found for both vehicle concepts.

  14. Staged membrane oxidation reactor system

    DOEpatents

    Repasky, John Michael; Carolan, Michael Francis; Stein, VanEric Edward; Chen, Christopher Ming-Poh

    2012-09-11

    Ion transport membrane oxidation system comprising (a) two or more membrane oxidation stages, each stage comprising a reactant zone, an oxidant zone, one or more ion transport membranes separating the reactant zone from the oxidant zone, a reactant gas inlet region, a reactant gas outlet region, an oxidant gas inlet region, and an oxidant gas outlet region; (b) an interstage reactant gas flow path disposed between each pair of membrane oxidation stages and adapted to place the reactant gas outlet region of a first stage of the pair in flow communication with the reactant gas inlet region of a second stage of the pair; and (c) one or more reactant interstage feed gas lines, each line being in flow communication with any interstage reactant gas flow path or with the reactant zone of any membrane oxidation stage receiving interstage reactant gas.

  15. Staged membrane oxidation reactor system

    DOEpatents

    Repasky, John Michael; Carolan, Michael Francis; Stein, VanEric Edward; Chen, Christopher Ming-Poh

    2013-04-16

    Ion transport membrane oxidation system comprising (a) two or more membrane oxidation stages, each stage comprising a reactant zone, an oxidant zone, one or more ion transport membranes separating the reactant zone from the oxidant zone, a reactant gas inlet region, a reactant gas outlet region, an oxidant gas inlet region, and an oxidant gas outlet region; (b) an interstage reactant gas flow path disposed between each pair of membrane oxidation stages and adapted to place the reactant gas outlet region of a first stage of the pair in flow communication with the reactant gas inlet region of a second stage of the pair; and (c) one or more reactant interstage feed gas lines, each line being in flow communication with any interstage reactant gas flow path or with the reactant zone of any membrane oxidation stage receiving interstage reactant gas.

  16. Staged membrane oxidation reactor system

    DOEpatents

    Repasky, John Michael; Carolan, Michael Francis; Stein, VanEric Edward; Chen, Christopher Ming-Poh

    2014-05-20

    Ion transport membrane oxidation system comprising (a) two or more membrane oxidation stages, each stage comprising a reactant zone, an oxidant zone, one or more ion transport membranes separating the reactant zone from the oxidant zone, a reactant gas inlet region, a reactant gas outlet region, an oxidant gas inlet region, and an oxidant gas outlet region; (b) an interstage reactant gas flow path disposed between each pair of membrane oxidation stages and adapted to place the reactant gas outlet region of a first stage of the pair in flow communication with the reactant gas inlet region of a second stage of the pair; and (c) one or more reactant interstage feed gas lines, each line being in flow communication with any interstage reactant gas flow path or with the reactant zone of any membrane oxidation stage receiving interstage reactant gas.

  17. A preliminary stage configuration for a low pressure nuclear thermal rocket (LPNTR)

    SciTech Connect

    Leyse, C.F.; Madsen, W.W.; Neuman, J.E.; Ramsthaler, J.H.; Schnitzler, B.G.

    1990-01-01

    A low pressure nuclear thermal rocket (LPNTR) is configured to meet the requirements of a nuclear stage for manned Mars exploration. Safety, reliability and performance are given equal consideration in selecting the stage configuration. Preliminary trade studies are conducted to size the engine thrust and determine the thrust chamber pressure. A weight breakdown and mechanical configuration for the selected LPNTR concept are defined. A seven engine stage configuration is selected which gives a two engine out capability and eliminates the need for engine gimbaling. The stage can be ground assembled and launched as a unit including tankage for trans Earth injection and Earth orbital capture. The tankage is configured to eliminate the need for an inert shield. The small engine will be cheaper to develop than a single engine providing full thrust, and will be compatible with stages for Earth orbital, Lunar and deep space missions. Mission analyses are presented with engine operation in a high thrust mode and in a dual range high thrust-low thrust mode. Mass savings over a reference NERVA stage are projected to be 45--55% for the high thrust operating mode and 50--60% for the dual range mode. Potential exists for further increases in performance by optimizing the thrust chamber/nozzle design. 6 refs., 10 figs., 5 tabs.

  18. 55. Photocopy of Fcsle & Upper Deck, Booklet of General ...

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

    55. Photocopy of Fcsle & Upper Deck, Booklet of General Plans, U.S.C.G.C. White Heath, WLM-545. U.S. Coast Guard Naval Engineering Department, U.S.C.G. Headquarters, Washington, D.C. Coast Guard Headquarters Drawing No. 540-WAGL-0103-019 C. sheet 5 of 7, dated May 1967; revised June 1971, December 1976, and April 1989. Original drawing property of the U.S. Coast Guard. - U.S. Coast Guard Cutter WHITE HEATH, USGS Integrated Support Command Boston, 427 Commercial Street, Boston, Suffolk County, MA

  19. Catalyst Development for Hydrogen Peroxide Rocket Engines

    NASA Technical Reports Server (NTRS)

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

    1999-01-01

    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.

  20. AJ26 Rocket Engine Test - Duration: 85 seconds.

    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...

  1. Undergraduate environmental engineering education in China

    SciTech Connect

    Yang, C.; Bero, B.N.

    1999-07-01

    In this paper, the development process, present situations, causes of improvement, and trends of higher education of environmental engineering in China are discussed. Several education modes in environmental engineering in China are also presented. The development process can be divided into three stages: the beginning stage, the expansion stage, and the modification stage. The 1970's and early 1980's wake of environmental consciousness and serious pollution situation in China resulted in about 20 universities setting up an environmental engineering specialty. The late 1980's and middle 1990's job opportunities for undergraduates in China resulted in many universities' creation of the environmental engineering specialty from specialties such as geography, geology, hydrology, mining engineering, and mineral separation engineering where job opportunities were stagnant. At present, adjustment and improvement of environmental engineering education are urgently required because of the excessive increase of undergraduate number, change of job opportunities and implementation of five-work-day system in China. Other problems include how to determine the ratio of social science courses to engineering science courses, how to determine the relationship of fundamental and applied courses, and how to determine the specialized direction. Hunan University, as a typical university conferring an accredited Bachelor degree in Environmental Engineering in four academic years in China, has been improving the instruction schedule for undergraduate education in environmental engineering. The curricula of the three phases for undergraduates of environmental engineering specialty at Hunan University are presented as a case study.

  2. Characterization of the 2012-044C Briz-M Upper Stage Breakup

    NASA Technical Reports Server (NTRS)

    Hamilton, Joseph A.; Matney, Mark

    2013-01-01

    The NASA breakup model prediction was close to the observed population for catalog objects. The NASA breakup model predicted a larger population than was observed for objects under 10 cm. The stare technique produces low observation counts, but is readily comparable to model predictions. Customized stare parameters (Az, El, Range) were effective to increase the opportunities for HAX to observe the debris cloud. Other techniques to increase observation count will be considered for future breakup events.

  3. Testing of a Spray-Bar Zero Gravity Cryogenic Vent System for Upper Stages

    NASA Technical Reports Server (NTRS)

    Lak, Tibor; Flachbart, Robin; Nguyen, Han; Martin, James

    1999-01-01

    The capability to vent in zero gravity without resettling is a fundamental technology need that involves practically all uses of subcritical 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 then-nal energy from the propellant. In a cooperative effort, Marshall Space Flight Center's (MSFC's) Multipurpose Hydrogen Test Bed (N4HTB) was used to test a unique "spray bar" TVS system developed by Boeing. A schematic of this system is included in Figure 1. The 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. In the mixing mode, the recirculation pump withdraws liquid from the tank and sprays it radially 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 spray bar heat exchanger element, and is vented overboard. The vented vapor cools the circulated bulk fluid, thereby removing thermal energy and reducing tank pressure. Figure 2 is a plot of ullage pressure (P4) and liquid vapor pressure (PSAI) versus time. 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. The primary advantage of the spray bar configuration is that pressure reduction is achieved independent of liquid and vapor location, thereby enhancing the applicability of normal gravity test data to zero gravity conditions. The in-tank components are minimized with the proposed TVS design. Because the recirculation pump is external to the tank, no electrical power penetration of the tank is required for pump or valve operation. This is especially desirable for L02 tanks since the presence of an electrical ignition source in oxygen represents a critical failure mode. Also, since the critical components (pump, motor, valve, orifice) are external to the tank, system checkout and ground servicing/replacement are easier. For zero-g operation, component replacement external to the tank may be a significant benefit. In addition to satisfying the zero g TVS design objectives, the TVS concept tested offers additional benefits to the integrated subcritical cryogenic storage and launch system.

  4. Ares Upper Stage Processes to Implement Model Based Design - Going Paperless

    NASA Technical Reports Server (NTRS)

    Gregory, Melanie

    2012-01-01

    Computer-Aided Design (CAD) has all but replaced the drafting board for design work. Increased productivity and accuracy should be natural outcomes of using CAD. Going from paper drawings only to paper drawings based on CAD models to CAD models and no drawings, or Model Based Design (MBD), is a natural progression in today?s world. There are many advantages to MBD over traditional design methods. To make the most of those advantages, standards should be in place and the proper foundation should be laid prior to transitioning to MBD. However, without a full understanding of the implications of MBD and the proper control of the data, the advantages are greatly diminished. Transitioning from a paper design world to an electronic design world means re-thinking how information gets controlled at its origin and distributed from one point to another. It means design methodology is critical, especially for large projects. It means preparation of standardized parts and processes as well as strong communication between all parties in order to maximize the benefits of MBD.

  5. "Setting the Stage" *Stages of preparation for a student

    E-print Network

    Peak, Derek

    "Setting the Stage" *Stages of preparation for a student placement Clinical Education Video Series and evidence of professional development #12;Additional Resources for CI Clinical education videos on website School of Physical Therapy Master of Physical Therapy (MPT) #12;Pre-Reading (on School of PT website

  6. Second stage gasifier in staged gasification and integrated process

    DOEpatents

    Liu, Guohai; Vimalchand, Pannalal; Peng, Wan Wang

    2015-10-06

    A second stage gasification unit in a staged gasification integrated process flow scheme and operating methods are disclosed to gasify a wide range of low reactivity fuels. The inclusion of second stage gasification unit operating at high temperatures closer to ash fusion temperatures in the bed provides sufficient flexibility in unit configurations, operating conditions and methods to achieve an overall carbon conversion of over 95% for low reactivity materials such as bituminous and anthracite coals, petroleum residues and coke. The second stage gasification unit includes a stationary fluidized bed gasifier operating with a sufficiently turbulent bed of predefined inert bed material with lean char carbon content. The second stage gasifier fluidized bed is operated at relatively high temperatures up to 1400.degree. C. Steam and oxidant mixture can be injected to further increase the freeboard region operating temperature in the range of approximately from 50 to 100.degree. C. above the bed temperature.

  7. Brief Communications Stress Potentiates Early and Attenuates Late Stages of Visual

    E-print Network

    Wisconsin at Madison, University of

    Brief Communications Stress Potentiates Early and Attenuates Late Stages of Visual Processing Minds, University of Wisconsin­Madison, Madison, Wisconsin 53705, 7Human Research & Engineering 55455 Stress can fundamentally alter neural responses to incoming information. Recent research suggests

  8. Project design criteria manual: Upper Mechanicville Hydroelectric Redevelopment Project

    SciTech Connect

    1980-12-01

    The design criteria presented in this manual are to be used as the bases for the detailed design for the Upper Mechanicville (NY) Hydroelectric Redevelopment Project. The manual refers to codes and standards which are to be used in the design of the project. Design approaches not covered by existing codes and standards are also given for all phases of the project. The manual is divided into six sections: civil design, hydraulic design, geotechnical design, electrical systems, mechanical systems, and major equipment. These design criteria are to be used as a guide for design. When changes become necessary, these shall be documented by the engineer responsible for the design. This documentation shall be sent to the Project Engineer and Project Manager for submission to the client for reference. The documentation shall specify the reason for the change and shall be routed to all Department Coordinators.

  9. An Analytic Framework to Develop Policies for Testing, Prevention and Treatment of Two-stage Contagious Diseases

    E-print Network

    Gautam, Natarajan

    -stage Contagious Diseases Hoda Parvin, Department of Industrial and Operations Engineering University of Michigan in testing, preven- tion and cure of two-stage contagious diseases. An individual that has contracted the two-stage contagious disease will initially show no symptoms of the disease but is capable of spreading it

  10. V/STOL model fan stage rig design report

    NASA Technical Reports Server (NTRS)

    Cheatham, J. G.; Creason, T. L.

    1983-01-01

    A model single-stage fan with variable inlet guide vanes (VIGV) was designed to demonstrate efficient point operation while providing flow and pressure ratio modulation capability required for a V/STOL propulsion system. The fan stage incorporates a split-flap VIGV with an independently actuated ID flap to permit independent modulation of fan and core engine airstreams, a flow splitter integrally designed into the blade and vanes to completely segregate fan and core airstreams in order to maximize core stream supercharging for V/STOL operation, and an EGV with a variable leading edge fan flap for rig performance optimization. The stage was designed for a maximum flow size of 37.4 kg/s (82.3 lb/s) for compatibility with LeRC test facility requirements. Design values at maximum flow for blade tip velocity and stage pressure ratio are 472 m/s (1550 ft/s) and 1.68, respectively.

  11. Rheology of the upper mantle: a synthesis.

    PubMed

    Karato, S; Wu, P

    1993-05-01

    Rheological properties of the upper mantle of the Earth play an important role in the dynamics of the lithosphere and asthenosphere. However, such fundamental issues as the dominant mechanisms of flow have not been well resolved. A synthesis of laboratory studies and geophysical and geological observations shows that transitions between diffusion and dislocation creep likely occur in the Earth's upper mantle. The hot and shallow upper mantle flows by dislocation creep, whereas cold and shallow or deep upper mantle may flow by diffusion creep. When the stress increases, grain size is reduced and the upper mantle near the transition between these two regimes is weakened. Consequently, deformation is localized and the upper mantle is decoupled mechanically near these depths. PMID:17746109

  12. Second Stage Separation - Duration: 17 seconds.

    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 ...

  13. A Three Stage Model for Gifted Education.

    ERIC Educational Resources Information Center

    Feldhusen, John F.; Kolloff, Margaret B.

    1978-01-01

    The article describes a three-stage enrichment model for gifted children (at the elementary and secondary levels) which involves divergent and convergent thinking (stage 1), creative thinking and problem solving (stage 2), and independent learning abilities (stage 3). (SBH)

  14. Treatment Options by Stage (Esophageal Cancer)

    MedlinePLUS

    ... cancer cells. The following stages are used for squamous cell carcinoma of the esophagus: Stage 0 (High-grade Dysplasia) ... is also called high-grade dysplasia . Stage I squamous cell carcinoma of the esophagus Stage I is divided into ...

  15. Collaborative Stage Manual Part II

    Cancer.gov

    SEER Program Coding and Staging Manual 2004, Revision 1 Appendix C Site-Specific Coding Modules C-299 Collaborative Staging Codes Nasal Cavity C30.0 C30.0 Nasal cavity (excludes nose, NOS C76.0) Note: Laterality must be coded for this site,

  16. A Model of Moral Stages

    ERIC Educational Resources Information Center

    Reed, Don Collins

    2008-01-01

    The argument of this paper focuses on the relationship between cognitive structures and structures of interaction. It contends that there is still a place in moral development theory and research for a concept of moral stages. The thesis, in short, is that moral stages are not structures of thought. They are structures of action encoded in…

  17. Microsoft Word - stages.doc

    Cancer.gov

    Stages of Change Readiness and Treatment Eagerness Scale (SOCRATES). Psychology of Addictive Behaviors, 10, 81-89. Petry, N. M. (2005). Stages of change in treatment-seeking pathological gamblers. Journal of Consulting and Clinical Psychology, 73, 312-322. Prochaska, J.

  18. 23. Photocopy of engineering drawing, April 10, 1958 (original drawing ...

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

    23. Photocopy of engineering drawing, April 10, 1958 (original drawing located at Fairchild Air Force Base, Civil Engineering Building, Civil Engineering Vault). READINESS CREW BUILDING, UPPER FLOOR PLANS - Fairchild Air Force Base, Bomber Alert Facility, 803G South Taxi Way, Spokane, Spokane County, WA

  19. American Institute of Aeronautics and Astronautics Deformation of the Upper and Lower Surfaces of an Airfoil

    E-print Network

    Debiasi, Marco

    of an Airfoil by Macro Fiber Composite Actuators Marco Debiasi1,§ , Yann Bouremel2 , and Zhenbo Lu3 Temasek fiber composite actuators were used to change the shape of the upper and lower surfaces of an airfoil & Aerospace Engineering, Nanyang Technological University, Singapore, 639798 In this follow-on study, macro

  20. American Institute of Aeronautics and Astronautics Deformation of the Upper Surface of an Airfoil by Macro

    E-print Network

    Debiasi, Marco

    by Macro Fiber Composite Actuators Marco Debiasi1 and Yann Bouremel2 Temasek Laboratories, National Engineering, National University of Singapore, Singapore, 117576 In this follow-on study, macro fiber composite actuators are used to change the shape of the upper surface of an airfoil model with geometry

  1. TRANSPORT AND DEPOSITION OF NANO-SIZE PARTICLES IN THE UPPER HUMAN RESPIRATORY AIRWAYS

    EPA Science Inventory

    TRANSPORT AND DEPOSITION OF NANO-SIZE PARTICLES IN THE UPPER HUMAN RESPIRATORY AIRWAYS. Zhe Zhang*, Huawei Shi, Clement Kleinstreuer, Department of Mechanical and Aerospace Engineering, North Carolina State University, Raleigh, NC 27695-7910; Chong S. Kim, National Health and En...

  2. 78 FR 35747 - Special Conditions: Cirrus Design Corporation, Model SF50; Fire Extinguishing for Upper Aft...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-06-14

    ... Corporation. DATES: This special condition published on April 20, 2010 at 75 FR 20518 is withdrawn, effective... model SF50 certification project was granted an extension on September 19, 2011. Amendment 23-62 (76 FR...; Fire Extinguishing for Upper Aft Fuselage Mounted Engine; Withdrawal AGENCY: Federal...

  3. Subminiature infrared detector translation stage

    NASA Technical Reports Server (NTRS)

    Bell, Alan D.

    1989-01-01

    This paper describes a precision subminiature three-axis translation stage used in the GOES Sounder to provide positional adjustment of 12 cooled infrared detectors. Four separate translation stages and detectors are packaged into a detector mechanism which has an overall size of 0.850 x 1.230 x 0.600 inches. Each translation stage is capable of + or - 0.015 inch motion in the X and Y axes and +0.050/-0.025 inch motion in the Z axis with a sensitivity of 0.0002 inches. The function of the detector translation stage allows real time detector signal peaking during Sounder alignment. The translation stage operates in a cryogenic environment under a 10 to the -6th torr vacuum.

  4. Upper Gastrointestinal Hemorrhage—Diagnosis and Management

    PubMed Central

    Midgley, Robert C.; Cantor, David

    1977-01-01

    The current management of a patient with upper gastrointestinal hemorrhage involves three steps: initial correction of unstable hemodynamics, obtaining the specific diagnosis of the lesion responsible for gastrointestinal blood loss, and therapy directed at the specific bleeding lesion. The current approach to upper gastrointestinal hemorrhage is carrying out upper gastrointestinal endoscopy following stabilization of the patient. Although improved morbidity and mortality statistics have been slow to appear, the use of endoscopy permits appropriate therapy directed at the specific lesion. Specific therapeutic measures have been outlined for seven common causes of upper gastrointestinal hemorrhage. The advent of therapeutic endoscopy promises to bring further advances in therapy in the near future. PMID:335664

  5. Overview of Transonic to Hypersonic Stage Separation Tool Development for Multi-Stage-to-Orbit Concepts

    NASA Technical Reports Server (NTRS)

    Murphy, Kelly J.; Bunning, Pieter G.; Pamadi, Bandu N.; Scallion, William I.; Jones, Kenneth M.

    2004-01-01

    An overview of research efforts at NASA in support of the stage separation and ascent aerothermodynamics research program is presented. The objective of this work is to develop a synergistic suite of experimental, computational, and engineering tools and methods to apply to vehicle separation across the transonic to hypersonic speed regimes. Proximity testing of a generic bimese wing-body configuration is on-going in the transonic (Mach numbers 0.6, 1.05, and 1.1), supersonic (Mach numbers 2.3, 3.0, and 4.5) and hypersonic (Mach numbers 6 and 10) speed regimes in four wind tunnel facilities at the NASA Langley Research Center. An overset grid, Navier-Stokes flow solver has been enhanced and demonstrated on a matrix of proximity cases and on a dynamic separation simulation of the bimese configuration. Steady-state predictions with this solver were in excellent agreement with wind tunnel data at Mach 3 as were predictions via a Cartesian-grid Euler solver. Experimental and computational data have been used to evaluate multi-body enhancements to the widely-used Aerodynamic Preliminary Analysis System, an engineering methodology, and to develop a new software package, SepSim, for the simulation and visualization of vehicle motions in a stage separation scenario. Web-based software will be used for archiving information generated from this research program into a database accessible to the user community. Thus, a framework has been established to study stage separation problems using coordinated experimental, computational, and engineering tools.

  6. Non-Toxic Reaction Control System for the Reusable First Stage Vehicle

    NASA Technical Reports Server (NTRS)

    Keith, E. L.; Rothschild, W. J.

    1999-01-01

    This paper presents the Boeing Reusable Space Systems vision of a Reaction Control System (RCS) for the Reusable First Stage (RFS) being considered as a replacement for the Solid Rocket Booster for the Space Shuttle. The requirement is to,achieve reliable vehicle control during the upper atmospheric portion of the RFS trajectory while enabling more efficient ground operations, unhindered by constraints caused by operating with highly toxic RCS propellants. Boeing's objective for this effort is to develop a safer, more efficient and environmentally friendly RCS design approach that is suitable for the RFS concept of operations, including a low cost, efficient turnaround cycle. The Boeing RCS concept utilizes ethanol and liquid oxygen in place of the highly toxic, suspected carcinogen, ozone- depleting mono-methyl-hydrazine and highly toxic nitrogen tetroxide. The Space Shuttle Upgrade program, under the leadership of the NASA Johnson Space Flight Center, is currently developing liquid oxygen and ethanol (ethyl alcohol) technology for use as non-toxic orbital maneuvering system (OMS) and RCS. The development of this liquid oxygen and ethanol technology for the Space Shuffle offers a significant leverage to select much of the same technology for the RFS program. There are significant design and development issues involved with bringing this liquid oxygen and ethanol technology to a state of maturity suitable for an operational RCS, The risks associated with a new LOX and Ethanol RCS are mitigated by maintaining kerosene and hydrogen peroxide RCS technology as an alternative. These issues, presented within this paper, include managing the oxygen supply and achieving reliable ignition in the short pulse mode of engine operation. Performance, reliability and operations requirements are presented along with a specific RCS design concept to satisfying these requirements. The work reported in this paper was performed under NASA Marshall Space Flight Center Contract to define Reusable First Stage design concepts for the Space Shuttle.

  7. Non-Toxic Reaction Control System for the Reusable First Stage Vehicle

    NASA Technical Reports Server (NTRS)

    Keith, E. L.; Rothschild, W. J.

    1999-01-01

    This paper presents the Boeing Reusable Space Systems vision of a Reaction Control System (RCS) for the Reusable First Stage (RFS) being considered as a replacement for the Solid Rocket Booster for the Space Shuttle. The requirement is to achieve reliable vehicle control during the upper atmospheric portion of the RFS trajectory while enabling more efficient ground operations, unhindered by constraints caused by operating with highly toxic RCS propellants. Boeing's objective for this effort is to develop a safer, more efficient and environmentally friendly RCS design approach that is suitable for the RFS concept of operations, including a low cost, efficient turnaround cycle. The Boeing RCS concept utilizes ethanol and liquid oxygen in place of the highly toxic, suspected carcinogen, ozone-depleting mono-methyl-hydrazine and highly toxic nitrogen tetroxide. The Space Shuttle Upgrade program, under the leadership of the NASA Johnson Space Flight Center, is currently developing liquid oxygen and ethanol (ethyl alcohol) technology for use as non-toxic orbital maneuvering system (OMS) and RCS. The development of this liquid oxygen and ethanol technology for the Space Shuttle offers a significant leverage to select much of the same technology for the RFS program. There are significant design and development issues involved with bringing this liquid oxygen and ethanol technology to a state of maturity suitable for an operational RCS. The risks associated with a new LOX and Ethanol RCS are mitigated by maintaining kerosene and hydrogen peroxide RCS technology as an alternative. These issues, presented within this paper, include managing the oxygen supply and achieving reliable ignition in the short pulse mode of engine operation. Performance, reliability and operations requirements are presented along with a specific RCS design concept to satisfying these requirements. The work reported in this paper was performed under NASA Marshall Space Flight Center Contract Number NAS8-97272 to define Reusable First Stage design concepts for the Space Shuttle.

  8. NASA Ares I Launch Vehicle First Stage Roll Control System Cold Flow Development Test Program Overview

    NASA Technical Reports Server (NTRS)

    Butt, Adam; Popp, Christopher G.; Holt, Kimberly A.; Pitts, Hank M.

    2010-01-01

    The Ares I launch vehicle is the selected design, chosen to return humans to the moon, Mars, and beyond. It is configured in two inline stages: the First Stage is a Space Shuttle derived five-segment Solid Rocket Booster and the Upper Stage is powered by a Saturn V derived J-2X engine. During launch, roll control for the First Stage (FS) is handled by a dedicated Roll Control System (RoCS) located on the connecting Interstage. That system will provide the Ares I with the ability to counteract induced roll torque while any induced yaw or pitch moments are handled by vectoring of the booster nozzle. This paper provides an overview of NASA s Ares I FS RoCS cold flow development test program including detailed test objectives, types of tests run to meet those objectives, an overview of the results, and applicable lessons learned. The test article was built and tested at the NASA Marshall Space Flight Center in Huntsville, AL. The FS RoCS System Development Test Article (SDTA) is a full scale, flight representative water flow test article whose primary objective was to obtain fluid system performance data to evaluate integrated system level performance characteristics and verify analytical models. Development testing and model correlation was deemed necessary as there is little historical precedent for similar large flow, pulsing systems such as the FS RoCS. The cold flow development test program consisted of flight-similar tanks, pressure regulators, and thruster valves, as well as plumbing simulating flight geometries, combined with other facility grade components and structure. Orifices downstream of the thruster valves were used to simulate the pressure drop through the thrusters. Additional primary objectives of this test program were to: evaluate system surge pressure (waterhammer) characteristics due to thruster valve operation over a range of mission duty cycles at various feed system pressures, evaluate temperature transients and heat transfer in the pressurization system, including regulator blowdown and propellant ullage performance, measure system pressure drops for comparison to analysis of tubing and components, and validate system activation and re-activation procedures for the helium pressurant system. Secondary objectives included: validating system processes for loading, unloading, and purging, validating procedures and system response for multiple failure scenarios, including relief valve operation, and evaluating system performance for contingency scenarios. The test results of the cold flow development test program are essential in validating the performance and interaction of the Roll Control System and anchoring analysis tools and results to a Critical Design Review level of fidelity.

  9. Stage measurement at gaging stations

    USGS Publications Warehouse

    Sauer, Vernon B.; Turnipseed, D. Phil

    2010-01-01

    Stream and reservoir stage are critical parameters in the computation of stream discharge and reservoir volume, respectively. In addition, a record of stream stage is useful in the design of structures that may be affected by stream elevation, as well as for the planning for various uses of flood plains. This report describes equipment and methodology for the observation, sensing, and recording of stage in streams and reservoirs. Although the U.S. Geological Survey (USGS) still uses the traditional, basic stilling-well float system as a predominant gaging station, modern electronic stage sensors and water-level recorders are now commonly used. Bubble gages coupled with nonsubmersible pressure transducers eliminate the need for stilling wells. Submersible pressure transducers have become common in use for the measurement of stage in both rivers and lakes. Furthermore, noncontact methods, such as radar, acoustic, and laser methods of sensing water levels, are being developed and tested, and in the case of radar, are commonly used for the measurement of stage. This report describes commonly used gaging-station structures, as well as the design and operation of gaging stations. Almost all of the equipment and instruments described in this report will meet the accuracy standard set by the USGS Office of Surface Water (OSW) for the measurement of stage for most applications, which is ?0.01 foot (ft) or 0.2 percent of the effective stage. Several telemetry systems are used to transmit stage data from the gaging station to the office, although satellite telemetry has become the standard. These telemetry systems provide near real-time stage data, as well as other information that alerts the hydrographer to extreme or abnormal events, and instrument malfunctions.

  10. Lower Oligocene bivalves of Ramanian Stage from Kachchh, Gujarat, India

    NASA Astrophysics Data System (ADS)

    Kachhara, R. P.; Jodhawat, R. L.; Devi, K. Bigyapati

    2012-04-01

    Marine Oligocene sequences in India outcrop only in western part of Kachchh. Earlier researchers have recognized the Oligocene strata under the Nari Series (Nagappa 1959; Chatterji and Mathur 1966). The Nari Series has a type area in Pakistan. It has two subdivisions - the Lower Nari (Lower Oligocene) and the Upper Nari (Upper Oligocene). It seems that there is no valid proof about the age of the Lower Nari due to lack of proper fauna (Eames 1975), and according to Pascoe (1962), the Upper Nari slightly transgress into Aquitanian (Lower Miocene), therefore, one has to be very cautious. Biswas and Raju (1971) reclassified the Oligocene strata of Kachchh and lithostratigraphically clubbed them as the Maniyara Fort Formation with type section along the Bermoti stream. This Formation has four members. The lower three members correspond to the Ramanian Stage (Lower Oligocene, Biswas 1971, 1973) while the uppermost to the Waiorian Stage (Upper Oligocene, Biswas 1965, 1971, 1973). The Ramanian Stage is characterized by large forams especially Nummulites fichteli, Nummulites fichteli intermedius, Lepidocyclina ( Eulepidina) dialata and Operculina sp. Several ostracods are also known to occur. Megafauna include bivalves, gastropods, echinoids, corals, mammals and reptiles. Concerning bivalves earlier researchers have recorded a few taxa namely Trisidos semitorta (Lamarck), Cubitostrea angulata (J de C Sowerby), Pecten ( Amussiopecten) labadyei d'Archiac and Haime, Periglypta puerpera (Linne') var. aglaurae Brongniart, Ostrea fraasi Mayer Eymer and listed Pecten laevicostatus J de C Sowerby, Callista pseudoumbonella Vredenburg and Clementia papyracea (Gray) from Kachchh as against overall 42 forms from the Nari Series as a whole (Vredenburg 1928). This tempted us to make an attempt to collect bivalve fauna systematically which are occurring prolifically in the Ramanian Stage. In the present work, for this purpose, sections are worked out around Lakhpat (23°50'N; 68°47'E), Maniyara Fort (23°28'05?N; 68°37'E) Rakhdi Dam (23°27'26?N; 68°40'10?E) and Waior (23°25'05?N; 68°41'37?E) with a view to highlight the entombed bivalve taxa. Authors have encountered 53 species of which 23 are restricted to the Ramanian Stage.

  11. Dynamic Modeling of Starting Aerodynamics and Stage Matching in an Axi-Centrifugal Compressor

    NASA Technical Reports Server (NTRS)

    Wilkes, Kevin; OBrien, Walter F.; Owen, A. Karl

    1996-01-01

    A DYNamic Turbine Engine Compressor Code (DYNTECC) has been modified to model speed transients from 0-100% of compressor design speed. The impetus for this enhancement was to investigate stage matching and stalling behavior during a start sequence as compared to rotating stall events above ground idle. The model can simulate speed and throttle excursions simultaneously as well as time varying bleed flow schedules. Results of a start simulation are presented and compared to experimental data obtained from an axi-centrifugal turboshaft engine and companion compressor rig. Stage by stage comparisons reveal the front stages to be operating in or near rotating stall through most of the start sequence. The model matches the starting operating line quite well in the forward stages with deviations appearing in the rearward stages near the start bleed. Overall, the performance of the model is very promising and adds significantly to the dynamic simulation capabilities of DYNTECC.

  12. Layered Systems Engineering Engines

    NASA Technical Reports Server (NTRS)

    Breidenthal, Julian C.; Overman, Marvin J.

    2009-01-01

    A notation is described for depicting the relationships between multiple, contemporaneous systems engineering efforts undertaken within a multi-layer system-of-systems hierarchy. We combined the concepts of remoteness of activity from the end customer, depiction of activity on a timeline, and data flow to create a new kind of diagram which we call a "Layered Vee Diagram." This notation is an advance over previous notations because it is able to be simultaneously precise about activity, level of granularity, product exchanges, and timing; these advances provide systems engineering managers a significantly improved ability to express and understand the relationships between many systems engineering efforts. Using the new notation, we obtain a key insight into the relationship between project duration and the strategy selected for chaining the systems engineering effort between layers, as well as insights into the costs, opportunities, and risks associated with alternate chaining strategies.

  13. Portable engine-pump assembly

    SciTech Connect

    Eberhardt, H.A.

    1987-02-17

    This patent describes a portable engine-pump assembly that is compact and light in weight comprising: an internal combustion engine mounted with its crankshaft extending vertically, a centrifugal pump having an impeller mounted for rotation on a pump shaft within a volute chamber, means mounting the pump on and immediately beneath the engine with the pump shaft extending vertically in accurate alignment and concentricity with the engine crankshaft, means coupling the engine crankshaft and the pump shaft together so that the engine crankshaft drives the pump shaft, the pump comprising a pump body defining the volute chamber and providing a pump inlet passage and a pump discharge passage oriented in generally horizontal directions, the pump body defining an inlet chamber providing passages for the flow of liquid from the pump inlet passage into the impeller from both above and below same and including an upper body portion and a lower body portion, and an exhaust system for the engine including an exhaust passage contained in the upper body portion, a muffler having an inlet, and means providing flow communication between the exhaust passage and the inlet of the muffler.

  14. Saturn IB S-IB Stages at Michoud Assembly Facility (MAF)

    NASA Technical Reports Server (NTRS)

    1967-01-01

    Three S-IB stages near completion at the NASA's Michoud Assembly Facility (MAF) near New Orleans, Louisiana, in November 1967. Developed by the Marshall Space Flight Center and built by the Chrysler Corporation at MAF, the 90,000-pound booster utilized eight H-1 engines and each produced 200,000 pounds of thrust for the Saturn IB launch vehicle's first stage.

  15. A novel voice coil motor-driven compliant micropositioning stage based on flexure mechanism.

    PubMed

    Shang, Jiangkun; Tian, Yanling; Li, Zheng; Wang, Fujun; Cai, Kunhai

    2015-09-01

    This paper presents a 2-degrees of freedom flexure-based micropositioning stage with a flexible decoupling mechanism. The stage is composed of an upper planar stage and four vertical support links to improve the out-of-plane stiffness. The moving platform is driven by two voice coil motors, and thus it has the capability of large working stroke. The upper stage is connected with the base through six double parallel four-bar linkages mechanisms, which are orthogonally arranged to implement the motion decoupling in the x and y directions. The vertical support links with serially connected hook joints are utilized to guarantee good planar motion with heavy-loads. The static stiffness and the dynamic resonant frequencies are obtained based on the theoretical analyses. Finite element analysis is used to investigate the characteristics of the developed stage. Experiments are carried out to validate the established models and the performance of the developed stage. It is noted that the developed stage has the capability of translational motion stroke of 1.8 mm and 1.78 mm in working axes. The maximum coupling errors in the x and y directions are 0.65% and 0.82%, respectively, and the motion resolution is less than 200 nm. The experimental results show that the developed stage has good capability for trajectory tracking. PMID:26429469

  16. A novel voice coil motor-driven compliant micropositioning stage based on flexure mechanism

    NASA Astrophysics Data System (ADS)

    Shang, Jiangkun; Tian, Yanling; Li, Zheng; Wang, Fujun; Cai, Kunhai

    2015-09-01

    This paper presents a 2-degrees of freedom flexure-based micropositioning stage with a flexible decoupling mechanism. The stage is composed of an upper planar stage and four vertical support links to improve the out-of-plane stiffness. The moving platform is driven by two voice coil motors, and thus it has the capability of large working stroke. The upper stage is connected with the base through six double parallel four-bar linkages mechanisms, which are orthogonally arranged to implement the motion decoupling in the x and y directions. The vertical support links with serially connected hook joints are utilized to guarantee good planar motion with heavy-loads. The static stiffness and the dynamic resonant frequencies are obtained based on the theoretical analyses. Finite element analysis is used to investigate the characteristics of the developed stage. Experiments are carried out to validate the established models and the performance of the developed stage. It is noted that the developed stage has the capability of translational motion stroke of 1.8 mm and 1.78 mm in working axes. The maximum coupling errors in the x and y directions are 0.65% and 0.82%, respectively, and the motion resolution is less than 200 nm. The experimental results show that the developed stage has good capability for trajectory tracking.

  17. The upper airway resistance syndrome.

    PubMed

    Pépin, J L; Guillot, M; Tamisier, R; Lévy, P

    2012-01-01

    Obstructive sleep apnea syndrome has been recognized as a major public health problem. Both its cardiovascular and metabolic comorbidities and symptoms motivate for an accurate diagnosis and appropriate treatment. The main stimulus associated with obstructive sleep apnea (OSA) and explaining deleterious consequences is intermittent hypoxia. The upper airway resistance syndrome (UARS) has been described based on the hypothesis that snoring and repetitive occurrence of respiratory effort-related arousals (RERAs) but not oxygen desaturation might produce a significant disease with symptoms, altered quality of life and cardiovascular morbidity. Diurnal sleepiness remains the main diagnostic criteria, which is often confounded with tiredness in women. UARS patients may also report insomnia and symptoms that closely resemble those of the functional somatic syndromes. Currently, the International Classification of Sleep Disorders does not individualize UARS as a specific entity and reports UARS patients as a subgroup of OSA. However, RERAs are described as unambiguous abnormal respiratory events occurring during sleep and requiring a specific scoring. In this review, the authors attempt to describe the specific characteristics of UARS that are relevant for both clinicians and researchers. PMID:22377755

  18. NASA's J-2X Engine Builds on the Apollo Program for Lunar Return Missions

    NASA Technical Reports Server (NTRS)

    Snoddy, Jimmy R.

    2006-01-01

    In January 2006, NASA streamlined its U.S. Vision for Space Exploration hardware development approach for replacing the Space Shuttle after it is retired in 2010. The revised CLV upper stage will use the J-2X engine, a derivative of NASA s Apollo Program Saturn V s S-II and S-IVB main propulsion, which will also serve as the Earth Departure Stage (EDS) engine. This paper gives details of how the J- 2X engine effort mitigates risk 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. It is well documented that propulsion is historically a high-risk area. NASA s risk reduction strategy for the J-2X engine design, development, test, and evaluation is to build upon heritage hardware and apply valuable experience gained from past development efforts. In addition, NASA and its industry partner, Rocketdyne, which originally built the J-2, have tapped into their extensive databases and are applying lessons conveyed firsthand by Apollo-era veterans of America s first round of Moon missions in the 1960s and 1970s. NASA s development approach for the J-2X engine includes early requirements definition and management; designing-in lessons learned from the 5-2 heritage programs; initiating long-lead procurement items before Preliminary Desi& Review; incorporating design features for anticipated EDS requirements; identifying facilities for sea-level and altitude testing; and starting ground support equipment and logistics planning at an early stage. Other risk reduction strategies include utilizing a proven gas generator cycle with recent development experience; utilizing existing turbomachinery ; applying current and recent main combustion chamber (Integrated Powerhead Demonstrator) and channel wall nozzle (COBRA) advances; and performing rigorous development, qualification, and certification testing of the engine system, with a philosophy of "test what you fly, and fly what you test". These and other active risk management strategies are in place to deliver the J-2X engine for LEO and lunar return missions as outlined in the U.S. Vision for Space Exploration.

  19. AJ26 engine test

    NASA Technical Reports Server (NTRS)

    2010-01-01

    John C. Stennis Space Center engineers conduct a 55-second test fire of Aerojet's liquid-fuel AJ26 rocket engine that will power the first stage of Orbital Sciences Corporation's Taurus II space launch vehicle. The Dec. 17, 2010 test was conducted on the E-1 Test Stand at Stennis in support of NASA's Commercial Transportation Services partnerships to enable commercial cargo flights to the International Space Station. Orbital is under contract with NASA to provide eight cargo missions to the space station through 2015.

  20. X Y parallel compliant stage with compact configuration.

    PubMed

    Choi, Kee-Bong; Lee, Jae Jong; Kim, Gee Hong; Lim, Hyung Jun

    2012-07-01

    This paper presents a piezo-driven compliant stage for nano positioning with two degree-of-freedom parallel linear motions. Nano positioning is one of the most important factors in completion of nanotechnologies. It can be accomplished by flexure-based compliant stages driven by piezo-actuators. For compact configuration, the compliant stage is stacked by two-layered compliant mechanisms. The upper layer contains a motion guide mechanism, and the lower layer two displacement amplification mechanisms. The motion guide mechanism consists of four prismatic-prismatic parallel compliant joint chains for two translational motion guides. The displacement amplification mechanism is adopted by a flexure-based flextensional amplification mechanism driven by a stack-type piezo actuator. Due to the parallel compliant joint chains, the stage has the same dynamics in the x and y axes. In this study, through design and analysis, the mechanisms were machined via wire electro-discharge machining and are were then integrated with two stack-type piezoelectric elements for actuation, and two capacitive sensors for ultra-precision displacement measurement. Finally, experiments were carried out to demonstrate the performance of the compliant stage. PMID:22966553