Active spacecraft thermal control system and method

Details Active spacecraft thermal control system and method Active spacecraft thermal control system and method

B - Operations, Transporting

64

G

B64G 1/58 (2006.01) B64G 1/40 (2006.01) B64G 1/50 (2006.01)

Patent

CA 2229716

A spacecraft (10) has combined propulsion and active thermal control systems. A propellant storage tank (20) couples to a pressurant storage tank (18). A working fluid (52) resides in the pressurant storage tank (18) and propels propellant when needed while concurrently acting as a thermal working fluid. The working fluid (52) is expanded then routed to selected cooled components (64). After passing by the cooled components (64), the working fluid (52) is compressed and passed by selected heated components (82). A controller (36) monitors temperature sensors (88) and controls valve assemblies (60, 78) to determine the components (64, 82) to which the working fluid (52) is routed.

Aéronef (10) comprenant des systèmes combinés de propulsion et de contrôle thermique actif. Un réservoir (20) de stockage des ergols est raccordé à un réservoir de stockage de gaz sous pression (18). Un fluide actif (52) est entreposé dans le réservoir de stockage (18) de gaz sous pression et pousse les ergols, au besoin, tout en servant en même temps de fluide caloporteur. Le fluide actif (52) est expansé puis transféré à des composants sélectionnés refroidis (64). Après son passage dans ces composants refroidis (64), le fluide actif (52) est comprimé et passe dans des composants chauffés sélectionnés (82). Un contrôleur (36) surveille les capteurs de température (88) et commande les ensembles de robinets (60,78), afin de déterminer vers quels composants (64, 82) le fluide actif doit être acheminé.

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