4 edition of Surface catalysis and characterization of proposed candidate TPS for access-to-space vehicles found in the catalog.
Surface catalysis and characterization of proposed candidate TPS for access-to-space vehicles
David A. Stewart
by National Aeronautics and Space Administration, Ames Research Center, National Technical Information Service, distributor in Moffett Field, Calif, [Springfield, Va
Written in English
|Statement||David A. Stewart.|
|Series||NASA technical memorandum -- 112206.|
|Contributions||Ames Research Center.|
|The Physical Object|
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Surface Catalysis and Characterization of Candidate TPS for Access-to-Space Vehicles DAVID A. STEWART Antes Research Center Summary Surface properties have been obtained on several classes of thermal protection systems (TPS) using data from both side-arm-reactor and arc-jet facilities.
Thermochemical stability, optical properties, and File Size: 1MB. Get this from a library. Surface catalysis and characterization of proposed candidate TPS for access-to-space vehicles. [David A Stewart; Ames Research Center.]. Surface Catalysis and Characterization of Proposed Candidate TPS for Access-to-Space Vehicles.
atom recombination were determined for candidate TPS proposed for single-stage-to-orbit vehicles. Challenge in the aerospace university classroom.
Characterization of Proposed Candidate TPS for. Access-To-Space Vehicles,” NASA TMAuthor: Vladimir Riabov. Full text of "NASA Technical Reports Server (NTRS) Computational Aerothermodynamic Design Issues for Hypersonic Vehicles" See other formats. This banner text can have markup.
web; books; video; audio; software; images; Toggle navigation. TPS Environment Modeling for Aerospace Flight Vehicles and Planetary Probes (Sub Task A) Response to Experimental and computational Investigations of Enthalpy Facilities (Sub Task B) Response to Thermal Protection Materials Development and Characterization (Sub Task C) References 2 Management Plan The proposed project leverages NASA EPCSoR RA investment by 1) using the modeling codes developed through these investments to design and size the.
Low-cost access to space is one of the greatest challenges for today's aerospace sector. Prohibitive costs of current systems motivate the search for unconventional approaches and emphasize the importance of reusability.
Notable examples of Reusable Launch Vehicles (RLV) are the NASA Space Shuttle and the Boeing XB. Cynthia L. Lach, Effect of Temperature and Gap Opening Rate on the Resiliency of Candidate Solid Rocket Booster O-Ring Materials, NASA TP, Junepp.
Lyle C. Schroeder, M. Bailey and John L. Mitchell, Deployable Reflector Antenna Performance Optimization Using Automated Surface Correction and Array-Feed Compensation, NASA TP.  Stewart D.
et al., Surface characterization of Candidate Metallic TPS for RLV, AIAA Paper  Stewart D. et al., Surface Catalytic Efficiency of Advanced Carbon Carbon Candidate Thermal Protection Materials for SSTO Vehicles, NASA TM .
Non-dependent access to space is a prerequisite for Europe to achieve its strategic space objectives. In technical terms, access to space encompasses launch, propulsion and transport technologies to enable a cost, energy and mass efficient voyage of space assets to their operational position, whether in Earth orbit, planetary or lunar orbit, or.
The combination of large integrated heat loads, large surface heat fluxes, and long duration flights (time > seconds) for emerging DoD, National Aeronautics and Space Administration, and commercial vehicles; requires new TPS designs and materials to accommodate quantum leaps in demands exerted by new missions.
This includes single-stage to orbit (SSTO), two-stage to orbit (TSTO) accelerators, access to space vehicles, and hypersonic cruise vehicles. This paper will start out with a brief discussion of aerodynamic heating and thermal management techniques to address the high heating, followed by an overview of TPS for rocket-launched and air-breathing.
Such was the case for a study of a proposed Assured Crew Return Vehicle (ACRV) documented in Ref. In Figs. 12(a) and 12(b), oil-flow and heating data show nonuniform flow at fairly low angle of attack emanating from the change in planform contour. A., Surface Catalysis and Characterization of Proposed Candidate TPS for Access-to.
Phase II deliverables include a working prototype of the proposed product and/or software, along with documentation and tools necessary for NASA to use the product and/or modify and use the software. In order to enable mission deployment, proposed prototypes should include a path, preferably demonstrated, for fault tolerance and mission tolerance.
 Stewart D. et al., “Surface characterization of Candidate Metallic TPS for RLV”, AIAA Paper  Stewart D. et al., “Surface Catalytic Efficiency of Advanced Carbon Carbon Candidate Thermal Protection Materials for SSTO Vehicles”, NASA TM .
(7) Characterization of the broad spectrum of surface radiation, including galactic cosmic radiation, solar proton events, and secondary neutrons.
(8) Characterization of the local environment, including basic meteorology, the state and cycling of water and C02, and the near-surface.
Notes on Numerical Fluid Mechanics, vol. NNFM Springer, Heidelberg () The NNFM Series E.H. Hirschel Herzog-Heinrich-Weg 6 Zorneding, Germany [email protected] Summary The book series "Notes on Numerical Fluid Mechanics and Multidisciplinary Design" is portrayed.
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