A spacecraft instrument thermal control method and system providing scalable thermal control of on-board instrument temperature. Adapted for a spacecraft with bus supporting instrumentation and thermal radiator panels, cooling is carried out by one or more active coolers, such as cryocoolers, each mounted to the spacecraft at a radiator spatially separated from the instrument, with cold side of the cooler being thermally coupled to an instrument focal plane or other instrument location requiring cryogenic cooling and the warm side coupled to the radiator. A closed loop temperature control system measures the temperature of the controlled portion of the instrument, and adjusts active cooler drive signals to maintain a specified set point temperature.
This information is part of a study by Oasis Global, Inc. of all space inventions filed at the United States Patent and Trademark Office, and is provided for informational purposes only. It is not an endorsement of any particular assignee, inventor or invention. Although Peter A. Koziol represents inventors and assignees of space inventions he does not represent all of the inventors and assignees listed. The prosecuting attorney agent or firm for each patent is identified by the United States Patent and Trademark Office in the patent specfication, which can be viewed by clicking on the patent image or downloading the patent document. For more information regarding Mr. Koziol's background and experience, or to learn more about space inventions, please contact Mr. Koziol.
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