A rotating detonation engine comprising: an outer cylinder that extends in an axial direction; a base that is connected to the outer cylinder, and comprises a plurality of fuel injection ports positioned in a circular ring shape and injecting a fuel, and a plurality of oxidizing agent injection ports positioned in a circular ring shape and injecting an oxidizing agent; an inner cylinder that is positioned in the outer cylinder, and is positioned in the axial direction relative to the base; and a mechanism that switches a combustion space, wherein the combustion space is switched in accordance with a combustion mode.

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.

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.

An engine in which thrust is achieved by converting electrical energy into high temperature plasma discharges that, in turn, apply thermal, pressure, and/or kinetic energy to a stream of passing air. The engine comprises a plasma region that includes a pair of gapped electrodes, such that the plasma discharges occur in the electrode gap. An energy storage device generates voltage pulses between the electrodes that electrically break down the air as the operating medium within the electrode gap and create plasma discharges.

An engine in which thrust is achieved by converting electrical energy into high temperature plasma discharges that, in turn, apply thermal, pressure, and/or kinetic energy to a stream of passing air. The engine comprises a plasma region that includes a pair of gapped electrodes, such that the plasma discharges occur in the electrode gap. An energy storage device generates voltage pulses between the electrodes that electrically break down the air as the operating medium within the electrode gap and create plasma discharges.