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Entry Vehicle Heating And Thermal Protection Systems Space Shuttle Solar Starprobe Jupiler Galileo Probe
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Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781724691507 Total Pages :314 pages Book Rating :4.6/5 (915 download)
Book Synopsis Thermal Protection System of the Space Shuttle by : National Aeronautics and Space Administration (NASA)
Download or read book Thermal Protection System of the Space Shuttle written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-04 with total page 314 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Thermal Protection System (TPS), introduced by NASA, continues to incorporate many of the advances in materials over the past two decades. A comprehensive, single-volume summary of the TPS, including system design rationales, key design features, and broad descriptions of the subsystems of TPS (E.g., reusable surface insulation, leading edge structural, and penetration subsystems) is provided. Details of all elements of TPS development and application are covered (materials properties, manufacturing, modeling, testing, installation, and inspection). Disclosures and inventions are listed and potential commercial application of TPS-related technology is discussed. Cleland, John and Iannetti, Francesco Unspecified Center NASA-CR-4227, NAS 1.26:4227 NASW-3841...
Book Synopsis Performance Analysis of Advanced Spacecraft Tps by : National Aeronaut Administration (Nasa)
Download or read book Performance Analysis of Advanced Spacecraft Tps written by National Aeronaut Administration (Nasa) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-10 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt: Spacecraft entering a planetary atmosphere require a very sophisticated thermal protection system. The materials used must be tailored to each specific vehicle based on its planned mission profiles. Starting with the Space Shuttle, many types of ceramic insulation with various combinations of thermal properties have been developed by others. The development of two new materials is described: A Composite Flexible Blanket Insulation which has a significantly lower effective thermal conductivity than other ceramic blankets; and a Silicon Matrix Composite which has applications at high temperature locations such as wing leading edges. Also, a systematic study is described that considers the application of these materials for a proposed Personnel Launch System. The study shows how most of these available ceramic materials would perform during atmospheric entry of this vehicle. Other specific applications of these thermal protection materials are discussed. Pitts, William C. Unspecified Center...
Book Synopsis An Assessment of Alternate Thermal Protection Systems for the Space Shuttle Orbiter by : Drew Hays
Download or read book An Assessment of Alternate Thermal Protection Systems for the Space Shuttle Orbiter written by Drew Hays and published by . This book was released on 1982 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781724681683 Total Pages :30 pages Book Rating :4.6/5 (816 download)
Book Synopsis Preliminary Analysis of Remote Infrared Imagery of Shuttle During Entry by : National Aeronautics and Space Administration (NASA)
Download or read book Preliminary Analysis of Remote Infrared Imagery of Shuttle During Entry written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-06 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: The preliminary feasibility of remote high-resolution infrared imagery of the space shuttle orbiter lower surface during entry to obtain accurate measurements of aerodynamic heat transfer to that vehicle was examined. In general, it was determined that such such images can be taken from an existing aircraft/telescope system (the C-141 AIRO) with a minimum modification or addition of systems using available technology. These images will have a spatial resolution of about 0.3 m and a temperature resolution much better than 2.5 percent. The data from these images will be at conditions and at a scale not reproducible in ground based facilities and should aid in the reduction of the prudent factors of safety required to account for phenomenological uncertainties on the thermal protection system design. Principal phenomena to be observed include laminar heating, boundary-layer transition, turbulent heating, surface catalysis, and flow separation and reattachment. Swenson, B. L. and Edsinger, L. E. Ames Research Center NASA-TM-73251, A-6995 RTOP 750-01-20-05-00-21
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721503872 Total Pages :36 pages Book Rating :4.5/5 (38 download)
Book Synopsis Thermal Vacuum Facility for Testing Thermal Protection Systems by : National Aeronautics and Space Administration (NASA)
Download or read book Thermal Vacuum Facility for Testing Thermal Protection Systems written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-19 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: A thermal vacuum facility for testing launch vehicle thermal protection systems by subjecting them to transient thermal conditions simulating re-entry aerodynamic heating is described. Re-entry heating is simulated by controlling the test specimen surface temperature and the environmental pressure in the chamber. Design requirements for simulating re-entry conditions are briefly described. A description of the thermal vacuum facility, the quartz lamp array and the control system is provided. The facility was evaluated by subjecting an 18 by 36 in. Inconel honeycomb panel to a typical re-entry pressure and surface temperature profile. For most of the test duration, the average difference between the measured and desired pressures was 1.6% of reading with a standard deviation of +/- 7.4%, while the average difference between measured and desired temperatures was 7.6% of reading with a standard deviation of +/- 6.5%. The temperature non-uniformity across the panel was 12% during the initial heating phase (t less than 500 sec.), and less than 2% during the remainder of the test. Daryabeigi, Kamran and Knutson, Jeffrey R. and Sikora, Joseph G. Langley Research Center NASA/TM-2002-211734, NAS 1.15:211734, L-18163
