US 12,263,964 B2
Propulsion system for a vehicle using heat energy absorbed in an active cooling system
Mikhail Kokorich, Payerne (CH)
Assigned to DESTINUS SA, Payerne (CH)
Appl. No. 18/558,800
Filed by DESTINUS SA, Payerne (CH)
PCT Filed May 11, 2021, PCT No. PCT/EP2021/062415
§ 371(c)(1), (2) Date Nov. 3, 2023,
PCT Pub. No. WO2022/237965, PCT Pub. Date Nov. 17, 2022.
Prior Publication US 2024/0229746 A1, Jul. 11, 2024
Int. Cl. B64G 1/58 (2006.01); B64G 1/14 (2006.01); B64G 1/40 (2006.01); B64G 1/50 (2006.01); B64G 1/62 (2006.01); F02K 9/42 (2006.01); F02K 9/64 (2006.01); F02K 9/74 (2006.01)
CPC B64G 1/58 (2013.01) [B64G 1/14 (2013.01); B64G 1/401 (2013.01); B64G 1/402 (2013.01); B64G 1/4026 (2023.08); B64G 1/50 (2013.01); B64G 1/623 (2023.08); F02K 9/42 (2013.01); F02K 9/64 (2013.01); F02K 9/74 (2013.01)] 22 Claims
OG exemplary drawing
 
1. A vehicle for a supersonic or hypersonic flight, comprising:
at least one thermal rocket engine with at least one nozzle,
an active cooling system having cooling channels for cooling a heat shield to protect leading edges of the vehicle,
a reaction control system with at least one nozzle, and
wherein the thermal rocket engine and the active cooling system comprise:
a working fluid absorbing heat in the active cooling system, and
the heated working fluid expanding through the at least one nozzle to create thrust,
wherein the thermal rocket engine is configured for main propulsion of the vehicle in order to propel the vehicle to high rocket velocity or to sustain an existing velocity of the vehicle.