US 12,421,920 B1
Multi-mode rocket-based combined cycle
Ben Saletta, Houston, TX (US); and Andrew Thomas Duggleby, Houston, TX (US)
Assigned to VENUS AEROSPACE CORP, Houston, TX (US)
Filed by VENUS AEROSPACE CORP, Houston, TX (US)
Filed on Jul. 26, 2024, as Appl. No. 18/786,333.
Int. Cl. F02K 7/18 (2006.01); F02K 7/12 (2006.01); F02K 9/78 (2006.01)
CPC F02K 7/18 (2013.01) [F02K 7/12 (2013.01); F02K 9/78 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A combined cycle propulsion system comprising:
a jet engine and a rocket engine;
an air inlet configured to receive a flow of air;
a combustor in fluid communication with the air inlet; and
a rocket ejector comprising the rocket engine positioned between the air inlet and combustor, the rocket ejector connected to the combustor with a mixing tube, wherein the rocket ejector is configured to adjustably output high-temperature gas into air in the mixing tube, wherein the high-temperature gas changes a pressure and thermal energy of the air within the mixing tube; and
a rotating detonation rocket engine (RDRE) positioned exterior to an exhaust bell of the combustor and in fluid communication with the exhaust bell.