Inlet bleed diversion through rotating detonation rocket engine
AssigneeVenus Aerospace Corp.
InventorsWilliam Thomas Ross, Sibylle Frederike Walter
Life of this patent
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Abstract
A rocket-based combined cycle propulsion system comprising an air inlet and a centerbody extending along a center axis. The centerbody at least partially defines the air inlet. The system further includes a first propulsion system (e.g., a rotating detonation rocket engine, RDRE) and a second propulsion system (e.g., a scramjet) coupled with the first propulsion system. The system further includes an air bleed assembly including an inlet aperture formed in the centerbody, an outlet aperture positioned in the first propulsion system, and a duct fluidly connecting the inlet aperture and the outlet aperture.
Claims27
A rocket-based combined cycle propulsion system comprising:
- an air inlet;
- a centerbody extending along a center axis, wherein the centerbody at least partially defines the air inlet;
- a first propulsion system;
- a second propulsion system coupled with the first propulsion system;
- and
- an air bleed assembly including an inlet aperture formed in the centerbody, an outlet aperture positioned in the first propulsion system, and a duct fluidly connecting the inlet aperture and the outlet aperture;
- and
- wherein the first propulsion system includes a rotating detonation rocket engine (RDRE);
- and wherein the RDRE is positioned between the air inlet and a flameholder of the second propulsion system.
Dependencies are inferred from the claim text.