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Thermal-protection requirements for near-earth aero-assisted 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. 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 to 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 trade-offs with aeromaneuvering vehicles in volumetric efficiency, retrothrust plane-change capability, and heat-protection requirements. In addition, the results of this study indicate that the aero-assist technique produces small 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
19830051532
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Menees, G. P.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 11, 2013
Publication Date
June 1, 1983
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 83-1513
Accession Number
83A32750
Distribution Limits
Public
Copyright
Other

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