A thermal control system may transfer energy (directly or after a delay) to a thrusting device that can be used to slow a reentry vehicle entering a gaseous atmosphere from orbit. The thermal control system may mitigate the heating of the vehicle by transferring heat generated by the viscous interaction between the vehicle and high-altitude portions of a planetary atmosphere to a working fluid. This working fluid may then be routed through and/or ejected through one or more nozzles aligned to produce thrust in a direction that opposes the forward motion of this vehicle. This counter thrust may help to slow the reentry vehicle and reduce the amount of kinetic energy that can be converted into thermal energy. The working fluid may also be stored to use for propulsion after the reentry vehicle slows below hypersonic velocities.
THERMAL CONTROL SYSTEM FOR REENTRY VEHICLES
2023-06-01
Patent
Electronic Resource
English
IPC: | B64G Raumfahrt , COSMONAUTICS / F03H PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR , Erzeugung von Vortriebskraft [Schub] nach dem Prinzip des Rückstoßes, soweit nicht anderweitig vorgesehen / F24V COLLECTION, PRODUCTION OR USE OF HEAT NOT OTHERWISE PROVIDED FOR , Sammeln, Erzeugen oder Verwenden von Wärme, soweit nicht anderweitig vorgesehen |
Online Contents | 1994
|Online Contents | 2004
|British Library Conference Proceedings | 2004
|Thermal sensor design for glide reentry vehicles
NTRS | 1965
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