A diffuser may comprise an inlet and an outlet. The inlet may comprise an arcuate shape. The outlet may comprise an annular shape. The diffuser may transition from the arcuate shape at the inlet to the annular shape at the outlet. The diffuser may comprise a radially inner wall and a radially outer wall disposed opposite the radially inner wall. The radially inner wall and the radially outer wall may partially define a duct.

The invention relates to a continuous detonation wave engine and aircraft provided with such an engine. The continuous detonation wave engine (1) operates with a detonation mixture of fuel and oxidant and includes, in particular, a detonation chamber (3) comprising an injection base (10), the length of which is defined along an open line (17), such as to form a detonation chamber (3) having an elongate form in a transverse plane, as well as an injection system (4) arranged such as to inject the fuel/oxidant so mixture into the detonation chamber (3) at at least one segment of the injection base (10).

The invention relates to a continuous detonation wave engine and aircraft provided with such an engine. The continuous detonation wave engine (1) operates with a detonation mixture of fuel and oxidant and includes, in particular, a detonation chamber (3) comprising an injection base (10), the length of which is defined along an open line (17), such as to form a detonation chamber (3) having an elongate form in a transverse plane, as well as an injection system (4) arranged such as to inject the fuel/oxidant so mixture into the detonation chamber (3) at at least one segment of the injection base (10).

A propulsion system defining a longitudinal centerline extended along a longitudinal direction is provided. The propulsion system includes an inlet section configured to provide an oxidizer to a rotating detonation combustion system positioned downstream of the inlet section. The rotating detonation combustion system includes a nozzle assembly positioned to provide a flow mixture of oxidizer and fuel to a combustion chamber, a centerbody forming an inner wall of the combustion chamber, an outer wall at least partially surrounding the centerbody, wherein the inner wall and the outer wall define a volume of the combustion chamber; and an actuation structure coupled to the nozzle assembly. The actuation structure is configured to expand and contract to displace the nozzle assembly along the longitudinal direction to alter the volume of the combustion chamber.

The proposed technology relates to a thrust control apparatus of a propulsion system, and more particularly, to a thrust control apparatus of a solid propulsion system equipped with an aerospike pintle nozzle. The present invention is to simultaneously control the magnitude and direction of thrust by installing a pintle and a thrust vectoring unit at the rear end of a combustion tube of a solid propulsion system.

The proposed technology relates to a thrust control apparatus of a propulsion system, and more particularly, to a thrust control apparatus of a solid propulsion system equipped with an aerospike pintle nozzle. The present invention is to simultaneously control the magnitude and direction of thrust by installing a pintle and a thrust vectoring unit at the rear end of a combustion tube of a solid propulsion system.

A power driver of an unmanned aerial vehicle is disclosed and includes a main body, a fluid actuation system and a controller, wherein the fluid actuation system includes a driving zone, a converging chamber, a plurality of valves and a fluid discharging zone. The driving zone includes a plurality of flow guiding units which arranged in series, parallel or series-parallel, each of the flow guiding unit generates an inside pressure gradient after being actuated, so as to inhale fluid and diverge fluid by guiding channels, and flow into the convergence chamber for storage, wherein the amount of the fluid transported is controlled by the plurality of valves disposed in the connection channels through the controller, and fluid is finally converged to the fluid discharging zone for discharging the specific transportation amount of fluid.

A power driver of an unmanned aerial vehicle is disclosed and includes a main body, a fluid actuation system and a controller, wherein the fluid actuation system includes a driving zone, a converging chamber, a plurality of valves and a fluid discharging zone. The driving zone includes a plurality of flow guiding units which arranged in series, parallel or series-parallel, each of the flow guiding unit generates an inside pressure gradient after being actuated, so as to inhale fluid and diverge fluid by guiding channels, and flow into the convergence chamber for storage, wherein the amount of the fluid transported is controlled by the plurality of valves disposed in the connection channels through the controller, and fluid is finally converged to the fluid discharging zone for discharging the specific transportation amount of fluid.

An optical heat exchanger and an associated system and method are provided to allow a vehicle, such as an unmanned air vehicle, a rocket or the like, to deliver more payload at a lower cost. The optical heat exchanger includes a support surface defining a plurality of tapered openings. Each tapered opening tapers from the first size proximate an outwardly facing end of the opening to a second smaller size proximate an inwardly facing end of the opening. The inwardly facing end of each tapered opening is in communication with the propellant. The optical heat exchanger also includes a plurality of lenses with each lens positioned proximate the outwardly facing end of a respective opening. Each lens is configured to receive an electromagnetic energy beam and concentrate the majority of the electromagnetic energy beam through the inwardly facing end of the respective tapered opening, thereby heating the propellant.

An optical heat exchanger and an associated system and method are provided to allow a vehicle, such as an unmanned air vehicle, a rocket or the like, to deliver more payload at a lower cost. The optical heat exchanger includes a support surface defining a plurality of tapered openings. Each tapered opening tapers from the first size proximate an outwardly facing end of the opening to a second smaller size proximate an inwardly facing end of the opening. The inwardly facing end of each tapered opening is in communication with the propellant. The optical heat exchanger also includes a plurality of lenses with each lens positioned proximate the outwardly facing end of a respective opening. Each lens is configured to receive an electromagnetic energy beam and concentrate the majority of the electromagnetic energy beam through the inwardly facing end of the respective tapered opening, thereby heating the propellant.