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.
[1]
J. Anderson,et al.
Hypersonic and High-Temperature Gas Dynamics
,
2019
.
[2]
Howard W. Stone,et al.
21st century space transportation system design approach - HL-20 personnel launch system
,
1993
.
[3]
Ping Lu,et al.
Entry Guidance for the X-33 Vehicle
,
1998
.
[4]
Wilbur L. Hankey,et al.
Re-entry aerodynamics
,
1988
.
[5]
J. C. Harpold,et al.
Shuttle entry guidance
,
1978
.
[6]
Barnes W. McCormick,et al.
Aerodynamics, Aeronautics and Flight Mechanics
,
1979
.
[7]
Daniel P. Raymer,et al.
Aircraft Design: A Conceptual Approach
,
1989
.