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  • Other Sources  (9)
  • Spacecraft Design, Testing and Performance  (7)
  • Geophysics
  • Man/System Technology and Life Support
  • 2005-2009  (9)
  • 2008  (5)
  • 2005  (4)
  • 1
    Publication Date: 2019-07-27
    Description: In less than two years, the National Aeronautics and Space Administration (NASA) will launch the Ares I-X mission. This will be the first flight of the Ares I crew launch vehicle, which, together with the Ares V cargo launch vehicle, will send humans to the Moon and beyond. Personnel from the Ares I-X Mission Management Office (MMO) are finalizing designs and fabricating vehicle hardware for an April 2009 launch. Ares I-X will be a suborbital development flight test that will gather critical data about the flight dynamics of the integrated launch vehicle stack; understand how to control its roll during flight; better characterize the severe stage separation environments that the upper stage engine will experience during future flights; and demonstrate the first stage recovery system. NASA also will modify the launch infrastructure and ground and mission operations. The Ares I-X Flight Test Vehicle (FTV) will incorporate flight and mockup hardware similar in mass and weight to the operational vehicle. It will be powered by a four-segment Solid Rocket Booster (SRB), which is currently in Shuttle inventory, and will include a fifth spacer segment and new forward structures to make the booster approximately the same size and weight as the five-segment SRB. The Ares I-X flight profile will closely approximate the flight conditions that the Ares I will experience through Mach 4.5, up to approximately130,OOO feet and through maximum dynamic pressure ("Max Q") of approximately 800 pounds per square foot. Data from the Ares I-X flight will support the Ares I Critical Design Review (CDR), scheduled for 2010. Work continues on Ares I-X design and hardware fabrication. All of the individual elements are undergoing CDRs, followed by an integrated vehicle CDR in March 2008. The various hardware elements are on schedule to begin deliveries to Kennedy Space Center (KSC) in early September 2008.
    Keywords: Spacecraft Design, Testing and Performance
    Type: MSFC-2060 , International Astronautical Conference; 29 Sep. 3 Oct. 2008; Glasgow; United Kingdom
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  • 2
    Publication Date: 2019-07-13
    Description: The Construction Resource Utilization Explorer (CRUX) is a technology maturation project for the U.S. National Aeronautics and Space Administration to provide enabling technology for lunar and planetary surface operations (LPSO). The CRUX will have 10 instruments, a data handling function (Mapper - with features of data subscription, fusion, interpretation, and publication through geographical information system [GIs] displays), and a decision support system DSS) to provide information needed to plan and conduct LPSO. Six CRUX instruments are associated with an instrumented drill to directly measure regolith properties (thermal, electrical, mechanical, and textural) and to determine the presence of water and other hydrogen sources to a depth of about 2 m (Prospector). CRUX surface and geophysical instruments (Surveyor) are designed to determine the presence of hydrogen, delineate near subsurface properties, stratigraphy, and buried objects over a broad area through the use of neutron and seismic probes, and ground penetrating radar. Techniques to receive data from existing space qualified stereo pair cameras to determine surface topography will also be part of the CRUX. The Mapper will ingest information from CRUX instruments and other lunar and planetary data sources, and provide data handling and display features for DSS output. CRUX operation will be semi-autonomous and near real-time to allow its use for either planning or operations purposes.
    Keywords: Geophysics
    Type: ILC 2005 - 7th ILEWG International Conference on Exploration and Utilization of the Moon; Sep 18, 2005 - Sep 23, 2005; Toronto; Canada
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  • 3
    Publication Date: 2019-07-13
    Description: Program to Optimize Simulated Trajectories II (POST2) is used as a basis for an end-to-end descent and landing trajectory simulation that is essential in determining design and integration capability and system performance of the lunar descent and landing system and environment models for the Autonomous Landing and Hazard Avoidance Technology (ALHAT) project. The POST2 simulation provides a six degree-of-freedom capability necessary to test, design and operate a descent and landing system for successful lunar landing. This paper presents advances in the development and model-implementation of the POST2 simulation, as well as preliminary system performance analysis, used for the testing and evaluation of ALHAT project system models.
    Keywords: Spacecraft Design, Testing and Performance
    Type: AIAA/AAS Astrodynamics Specialist Conference; Aug 18, 2008 - Aug 21, 2008; Honolulu, HI; United States
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  • 4
    Publication Date: 2019-07-12
    Description: Thermal simulators (highly designed heater elements) developed at the Early Flight Fission Test Facility (EFF-TF) are used to simulate the heat from nuclear fission in a variety of reactor concepts. When inserted into the reactor geometry, the purpose of the thermal simulators is to deliver thermal power to the test article in the same fashion as if nuclear fuel were present. Considerable effort has been expended to mimic heat from fission as closely as possible. To accurately represent the fuel, the simulators should be capable of matching the overall properties of the nuclear fuel rather than simply matching the fuel temperatures. This includes matching thermal stresses in the pin, pin conductivities, total core power, and core power profile (axial and radial). This Technical Memorandum discusses the historical development of the thermal simulators used in nonnuclear testing at the EFF-TF and provides a basis for the development of the current series of thermal simulators. The status of current heater fabrication and testing is assessed, providing data and analyses for both successes and failures experienced in the heater development and testing program.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NASA/TM-2008-215466 , M-1235
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  • 5
    Publication Date: 2019-07-11
    Description: The Space Shuttle Program (SSP) has a zero-fault-tolerant design related to an inadvertent firing of the primary reaction control jets on the Orbiter during mated operations with the International Space Station (ISS). Failure modes identified by the program as a wire-to-wire "smart" short or a Darlington transistor short resulting in a failed-on primary thruster during mated operations with ISS can drive forces that exceed the structural capabilities of the docked Shuttle/ISS structure. The assessment team delivered 17 observations, 6 findings and 15 recommendations to the Space Shuttle Program.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NASA/TM-2005-213750/VERSION1.0 , L-19119/VERSION1.0 , NESC-RP-05-18-Version-1.0
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  • 6
    Publication Date: 2019-07-12
    Description: A document discusses the concept of a demisable motor-drive-and-flywheel assembly [reaction-wheel assembly (RWA)] used in controlling the attitude of a spacecraft. Demisable as used here does not have its traditional legal meaning; instead, it signifies susceptible to melting, vaporizing, and/or otherwise disintegrating during re-entry of the spacecraft into the atmosphere of the Earth so as not to pose a hazard to anyone or anything on the ground. Prior RWAs include parts made of metals (e.g., iron, steel, and titanium) that melt at high temperatures and include structures of generally closed character that shield some parts (e.g., magnets) against re-entry heating. In a demisable RWA, the flywheel would be made of aluminum, which melts at a lower temperature. The flywheel web would not be a solid disk but would have a more open, nearly-spoke-like structure so that it would disintegrate more rapidly; hence, the flywheel rim would separate more rapidly so that parts shielded by the rim would be exposed sooner to re-entry heating. In addition, clearances between the flywheel and other components would be made greater, imparting a more open character and thus increasing the exposure of those components.
    Keywords: Spacecraft Design, Testing and Performance
    Type: GSC-14845-1 , NASA Tech Briefs, December 2008; 25
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  • 7
    Publication Date: 2019-07-12
    Description: High-test hydrogen peroxide (HP) is an energetic liquid with widespread use in a variety of industrial and aerospace applications. In recent years, there has been increased interest in its use as a "green" or environmentally benign propellant in spacecraft and defense propulsion and power systems. HP, however, can be a significant hazard if not properly handled. In addition, hydrogen peroxide is unstable when exposed to trace contaminants, which may catalyze decomposition and result in violent thermal runaway. Many advanced and newly developed alloys, polymers, composites and other construction materials (such as those used in tankage and piping systems) have not been tested for compatibility with hydrogen peroxide. The reliability of extrapolating from short-term compatibility test results to long-term compatibility has not yet been fully assessed. Therefore, the users and designers of HP systems must be aware of these hazards and unknowns and take the appropriate precautions.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NASA/TM-2004-213151 , S-936 , JSC-CN-8960 , JSC-E-DAA-TN63718
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  • 8
    Publication Date: 2019-07-18
    Description: NASA has deemed it necessary to perform the Toxicity Test (offgassing of toxic products) on all non-metallic materials proposed for use in habitable environments onboard the Shuttle and International Space Station flS,!J. This requirement stems from the desire to maintain a healthy, breathable atmosphere for the astronauts. As Shuttle missions have lengthened and with the habitation of the International Space Station, the need for understanding and controlling the contaminants in breathable atmospheres has increased. The increased duration of humans in space present two concerns to the astronauts with regard to their breathing air: 1. Breathing the on-board air. 2. Improved cleaning/filtering of existing air. Trends using existing toxicity data for materials and an understanding of the air cleaning/filtering capabilities in relation to Spacecraft Maximum Allowable Concentrations (SMAC) of offgassed components are explored. Recommendations are made for materials selection practices that should be followed to ensure a safe and healthy breathing environment for astronauts aboard these long term projects. The importance and relevance of Toxicity testing and materials selection in conjunction with the new NASA missions of creating a human presence on the Moon and traveling to Mars are described.
    Keywords: Man/System Technology and Life Support
    Type: National Space and Missile Materials Symposium; Jun 27, 2005 - Jul 01, 2005; Summerlin, NV; United States
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  • 9
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    In:  CASI
    Publication Date: 2019-07-13
    Description: In less than two years, the National Aeronautics and Space Administration (NASA) will launch the Ares I-X mission. This will be the first flight of the Ares I crew launch vehicle, which, together with the Ares V cargo launch vehicle, will eventually send humans to the Moon, Mars, and beyond. As the countdown to this first Ares mission continues, personnel from across the Ares I-X Mission Management Office (MMO) are finalizing designs and fabricating vehicle hardware for an April 2009 launch. This paper will discuss the hardware and programmatic progress of the Ares I-X mission. Like the Apollo program, the Ares launch vehicles will rely upon extensive ground, flight, and orbital testing before sending the Orion crew exploration vehicle into space with humans on board. The first flight of Ares I, designated Ares I-X, will be a suborbital development flight test. Ares I-X gives NASA its first opportunity to gather critical data about the flight dynamics of the integrated launch vehicle stack; understand how to control its roll during flight; better characterize the severe stage separation environments that the upper stage engine will experience during future operational flights; and demonstrate the first stage recovery system. NASA also will begin modifying the launch infrastructure and fine-tuning ground and mission operations, as the agency makes the transition from the Space Shuttle to the Ares/Orion system.
    Keywords: Spacecraft Design, Testing and Performance
    Type: MSFC-2051 , AIAA Space 2008; Sep 09, 2008 - Sep 11, 2008; San Diego, CA; United States
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