A novel approach to spacecraft re-entry and recovery
Abstract
A deployable radiative heat shield design for spacecraft reentry is discussed. The design would allow the spacecraft to be cylindrical instead of the the traditional conical shape, providing a greater internal volume and thus enhancing mission capabilities. The heat shield uses a flexible thermal blanket material which is deployed in a manner similar to an umbrella. Based on the radiative properties of this blanket material, heating constraints have been established which allow a descent trajectory to be designed. The heat shield and capsule configuration are analyzed for resistance to heat flux and aerodynamic stability based on reentry trajectory. Experimental tests are proposed.
- Publication:
-
AIAA, Aerospace Sciences Meeting
- Pub Date:
- January 1990
- Bibcode:
- 1990aiaa.meetR....P
- Keywords:
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- Reentry Physics;
- Spacecraft Design;
- Spacecraft Recovery;
- Spacecraft Reentry;
- Thermal Protection;
- Manned Space Flight;
- Radiative Heat Transfer;
- Reentry Trajectories;
- Reusable Spacecraft;
- Launch Vehicles and Space Vehicles