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Thermal Protection Requirements for Near-Earth Aeroassisted Orbital Transfer Vehicle MissionsThe thermal protection required for decelerating and maneuvering spacecraft by aerodynamic forces is determined for return missions from geosynchronous to low Earth orbits. The effect of vehicle configuration on surface heating rates and selection of heat shield materials is analyzed. The effects of the current widespread estimates in the structure of atmospheric density are also evaluated. It is shown that nonequilibrium radiation can be a major source of surface heating during atmospheric entry and a significant factor for heat shielding requirements. It is also demonstrated that drag-brake concepts have application to a broad range of orbital transfer missions because of the favorable tradeoffs with aeromaneuvering vehicles in volumetric efficiency, retrothrust plane-change capability, and heat protection requirements. In addition, the results of this study indicate that the aeroassist technique produces acceptable penalties in vehicle payload capacity for drag-brake concepts, because of the system's heat protection requirements, and is highly attractive relative to all-propulsive orbital change maneuvers.
Document ID
19990066630
Acquisition Source
Ames Research Center
Document Type
Reprint (Version printed in journal)
Authors
Menees, Gene P.
(NASA Ames Research Center Moffett Field, CA United States)
Date Acquired
August 19, 2013
Publication Date
January 1, 1985
Publication Information
Publication: Progress in Astronautics and Aeronautics: Thermal Design of Aeroassisted Orbital Transfer Vehicles
Volume: 96
Subject Category
Thermodynamics And Statistical Physics
Report/Patent Number
AIAA Paper 83-1513
Meeting Information
Meeting: Thermophysics
Location: Montreal
Country: Canada
Start Date: June 1, 1983
End Date: June 3, 1983
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Other

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