Abstract
This paper presents the conceptual design of a re–entry vehicle suitable for the emergency return of personnel from the International Space Station. For injured occupants, or those with emergency medical conditions, a re–entry environment with a maximum g loading of less than 1.1 would be necessary. This has been met by using a relatively conventional design employing leading–edge bluntness and a passive thermal–protection system. The paper addresses the guidance and control required to meet these conditions and thermal modelling is used to determine the cabin temperature rise during re–entry. In comparison with vehicles employing greater aerodynamic sophistication, such as wave–riders, the cross–range is inferior, but in other respects it is shown that the requirements of the re–entry environment can be met.
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Schedule a callMore From: Philosophical Transactions of the Royal Society of London. Series A: Mathematical, Physical and Engineering Sciences
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