A high-efficiency spacecraft propulsion system, including includes electric pumps inserted in the oxidizer and fuel lines that increase liquid apogee engine ("LAE") operating pressure and reduce tank-operating pressure. An on-board computer generates pump drive signals, in response to measured oxidizer and fuel line pressures, that are input to the pump controller electronics. The controller electronics provides current drives to the pump motors. The system uses an LAE that can operate at higher thrust chamber pressures (e.g., 500 psia) than standard LAEs, where pump-fed rocket motors have integrated turbopumps that are fuel operated. The turbopump increases LAE complexity and cost, reduces fuel efficiency, and is not compatible with active thrust and mixture ratio control.
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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