US 12,351,344 B2
Nuclear thermal propulsion system with reactor direct drive of cryocooler turbine
Zachary Reid Tolley, Kent, WA (US)
Assigned to Blue Origin Manufacturing, LLC, Huntsville, AL (US)
Filed by Blue Origin Manufacturing, LLC, Huntsville, AL (US)
Filed on Nov. 15, 2024, as Appl. No. 18/949,069.
Application 18/949,069 is a continuation of application No. 18/632,124, filed on Apr. 10, 2024, granted, now 12,234,042.
Application 18/632,124 is a continuation of application No. 17/808,256, filed on Jun. 22, 2022, granted, now 11,975,870, issued on May 7, 2024.
Prior Publication US 2025/0066045 A1, Feb. 27, 2025
Int. Cl. B64G 1/40 (2006.01); F02K 9/42 (2006.01); F02K 9/44 (2006.01); F02K 9/50 (2006.01); F02K 9/64 (2006.01); G21D 5/02 (2006.01); F02K 9/46 (2006.01)
CPC B64G 1/408 (2013.01) [F02K 9/42 (2013.01); F02K 9/425 (2013.01); F02K 9/44 (2013.01); F02K 9/50 (2013.01); F02K 9/64 (2013.01); G21D 5/02 (2013.01); F02K 9/46 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A method of operating a spacecraft having a cryogenic fluid management (CFM) system, the method comprising:
driving a cryocooler turbine of the CFM system using a heated first thermal working fluid;
maintaining a cryogenic temperature of propellant using the cryocooler turbine;
pumping the propellant along a nuclear reactor core of the spacecraft, thereby heating the propellant; and
expelling the propellant to provide thrust to the spacecraft.