The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Nov. 11, 2025

Filed:

Jun. 20, 2024
Applicant:

Trans Astronautica Corporation, Lake View Terrace, CA (US);

Inventors:

Joel C. Sercel, Lake View Terrace, CA (US);

Philip J. Wahl, Altadena, CA (US);

Conrad T. Jensen, Altadena, CA (US);

James G. Small, Sonoita, AZ (US);

Benjamin G. Workinger, Chattanooga, TN (US);

Samuel Daugherty-Saunders, Claremont, CA (US);

Assignee:

Trans Astronautica Corporation, Lake View Terrace, CA (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F02K 9/64 (2006.01); B64G 1/40 (2006.01); B64G 1/44 (2006.01); F02K 9/42 (2006.01); F02K 9/44 (2006.01); F02K 9/60 (2006.01); F03H 99/00 (2009.01); F24S 20/20 (2018.01); F24S 23/30 (2018.01); F24S 23/70 (2018.01); F24S 70/16 (2018.01);
U.S. Cl.
CPC ...
F02K 9/64 (2013.01); B64G 1/401 (2013.01); B64G 1/402 (2013.01); B64G 1/446 (2013.01); F02K 9/42 (2013.01); F02K 9/44 (2013.01); F02K 9/60 (2013.01); F03H 99/00 (2013.01); F24S 20/20 (2018.05); F24S 23/30 (2018.05); F24S 23/70 (2018.05); F24S 70/16 (2018.05); F24S 2023/832 (2018.05);
Abstract

Omnivorous solar thermal thrusters and adjustable cooling structures are disclosed. In one aspect, a solar thermal rocket engine includes a solar thermal thruster configured to receive solar energy and one or more propellants, and heat the one or more propellants using the solar energy to generate thrust. The solar thermal thruster is further configured to use a plurality of different propellant types, either singly or in combination simultaneously. The solar thermal thruster is further configured to use the one or more propellants in both liquid and gaseous states. Related structures can include valves and variable-geometry cooling channels in thermal contact with a thruster wall.


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