Author:
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Entry Vehicle Heating and thermal protection systems: Space shuttle, solar starprobe, Jupiter Galileo probe
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Entry Vehicle Heating and Thermal Protection Systems, Space Shuttle, Solar Starprobe, Jupiler Galileo Probe
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Entry Vehicle Heating and thermal protection systems: Space shuttle, solar starprobe, Jupiter Galileo probe
Author: Aerospace Sciences Meeting. 20, 1982, Orlando, Fla..
Publisher:
ISBN:
Category :
Languages : en
Pages : 556
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 556
Book Description
An Assessment of Alternate Thermal Protection Systems for the Space Shuttle Orbiter, Volume 1
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 76
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 76
Book Description
Thermal Protection System of the Space Shuttle
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781724691507
Category :
Languages : en
Pages : 314
Book Description
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...
Publisher: Createspace Independent Publishing Platform
ISBN: 9781724691507
Category :
Languages : en
Pages : 314
Book Description
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...
Experimental Assessment of a Computer Program Used in Space Shuttle Orbiter Entry Heating Analyses
Author: William L. Wells
Publisher:
ISBN:
Category : Reusable space vehicles
Languages : en
Pages : 28
Book Description
Publisher:
ISBN:
Category : Reusable space vehicles
Languages : en
Pages : 28
Book Description
Assessment of Alternate Thermal Protection Systems for the Space Shuttle Orbiter
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
Book Description
Thermal Protection System of the Space Shuttle
Author: John Cleland
Publisher:
ISBN:
Category :
Languages : en
Pages : 312
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 312
Book Description
Thermal Protection System of the Space Shuttle
Author: John G. Cleland
Publisher:
ISBN:
Category : Shielding (Heat)
Languages : en
Pages : 404
Book Description
Publisher:
ISBN:
Category : Shielding (Heat)
Languages : en
Pages : 404
Book Description
Static and Aerothermal Tests of a Superalloy Honeycomb Prepackaged Thermal Protection System
Author: National Aeronautics and Space Adm Nasa
Publisher:
ISBN: 9781730709555
Category :
Languages : en
Pages : 54
Book Description
A reusable metallic thermal protection system has been developed for vehicles with maximum surface temperatures of up to 2000 F. An array of two 12- by 12-in. panels was subjected to radiant heating tests that simulated Space Shuttle entry temperature and pressure histories. Results indicate that this thermal protection system, with a mass of 2.201 lbm/ft(exp 2), can successfully prevent typical aluminum primary structure of an entry vehicle like the Space Shuttle from exceeding temperatures greater than 350 F at a location on the vehicle where the maximum surface temperature is 1900 F. A flat array of 20 panels was exposed to aerothermal flow conditions, at a Mach number of 6.75. The panels were installed in a worst-case orientation with the gaps between panels parallel to the flow. Results from the aerothermal tests indicated that convective heating occurred from hot gas flow in the gaps between the panels. Proposed design changes to prevent gap heating occurred from hot gas flow in the gaps between the panels. Proposed design changes to prevent gap heating include orienting panels so that gaps are not parallel to the flow and using a packaged, compressible gap-filler material between panels to block hot gas flow in the gaps. Gorton, Mark P. and Shideler, John L. and Webb, Granville L. Langley Research Center...
Publisher:
ISBN: 9781730709555
Category :
Languages : en
Pages : 54
Book Description
A reusable metallic thermal protection system has been developed for vehicles with maximum surface temperatures of up to 2000 F. An array of two 12- by 12-in. panels was subjected to radiant heating tests that simulated Space Shuttle entry temperature and pressure histories. Results indicate that this thermal protection system, with a mass of 2.201 lbm/ft(exp 2), can successfully prevent typical aluminum primary structure of an entry vehicle like the Space Shuttle from exceeding temperatures greater than 350 F at a location on the vehicle where the maximum surface temperature is 1900 F. A flat array of 20 panels was exposed to aerothermal flow conditions, at a Mach number of 6.75. The panels were installed in a worst-case orientation with the gaps between panels parallel to the flow. Results from the aerothermal tests indicated that convective heating occurred from hot gas flow in the gaps between the panels. Proposed design changes to prevent gap heating occurred from hot gas flow in the gaps between the panels. Proposed design changes to prevent gap heating include orienting panels so that gaps are not parallel to the flow and using a packaged, compressible gap-filler material between panels to block hot gas flow in the gaps. Gorton, Mark P. and Shideler, John L. and Webb, Granville L. Langley Research Center...