MODULAR ARCHITECTURE FOR THERMAL CONTROL OF SPACECRAFT

摘要

PROBLEM TO BE SOLVED: To provide an architecture of an automatic control system for electricity, a machine and heat allowing use of a standard modular interface provided with electronic equipment for payload and platforms of a spacecraft. SOLUTION: The equipment 20 is constituted to be supported by a structure 24 of a satellite and includes at least one electronic module 21 for payload or platforms of the satellite. The structure 24 of the satellite includes a heat carrying device for carrying radiated heat to a radiator. The equipment 20 includes a heat carrying means for heat radiated by the electronic module 21 and a means for connecting the heat carrying means to the heat carrying device of the structure 24. Cooling liquid can be supplied to the carrying means and heat radiated by the electronic module 21 can be carried to the radiator. Layout of the structure 24 of the satellite and the equipment 20 and a communication system for the satellite are provided. COPYRIGHT: (C)2004,JPO