The combustor for a rocket engine includes a combustion room configured to cause a combustion reaction between a fuel and an oxidant, an injector configured to inject the fuel and the oxidant into the combustion room, and a nozzle skirt configured to inject combustion gas generated by the combustion reaction to an outside, and an inertance increasing portion configured to increase an equivalent inertance in a vibration equivalent circuit of the combustor for the rocket engine.

The present disclosure relates to a rocket engine, and more particularly, a rocket engine with an integrated combustor head and turbopump in which a turbopump of the rocket engine is formed integrally with a combustor head.

According to one embodiment, there is provided a propulsion apparatus of liquid propellant rocket engine. The propulsion apparatus of liquid propellant rocket engine, the propulsion apparatus including: a body in which liquid propellant flows; an injector core located inside the body; at least one outlet connected to the injector core to discharge combustion gas; and an injector for discharging the liquid propellant flowing into the body, wherein the injector is located in an area adjacent to the outlet, wherein the liquid propellant moves between a frame of the body and a frame of the injector core.

According to one embodiment, there is provided a propulsion apparatus of liquid propellant rocket engine. The propulsion apparatus of liquid propellant rocket engine, the propulsion apparatus including: a body in which liquid propellant flows; an injector core located inside the body; at least one outlet connected to the injector core to discharge combustion gas; and an injector for discharging the liquid propellant flowing into the body, wherein the injector is located in an area adjacent to the outlet, wherein the liquid propellant moves between a frame of the body and a frame of the injector core.

A motor and fuel-powered hybrid system of a rocket thruster is disclosed, which mainly provides power through a motor and a fluid fuel injector. In particular, at the beginning stage of the rocket lift-off, the motor drives the compressor to provide power to send the rocket into air. When the speed and height of the rocket gradually increase, the fuel is ignited to give power to keep propelling the rocket, thereby reducing the fluid fuel that needs to be carried on the rocket, increasing the rocket's loading space and enhancing the carrying capacity.

A motor and fuel-powered hybrid system of a rocket thruster is disclosed, which mainly provides power through a motor and a fluid fuel injector. In particular, at the beginning stage of the rocket lift-off, the motor drives the compressor to provide power to send the rocket into air. When the speed and height of the rocket gradually increase, the fuel is ignited to give power to keep propelling the rocket, thereby reducing the fluid fuel that needs to be carried on the rocket, increasing the rocket's loading space and enhancing the carrying capacity.

Embodiments are directed toward a monopropellant continuous detonation engine. In some embodiments, the continuous detonation engine includes an engine body, a monopropellant feed assembly, and a detonation initiator. The engine body defines a detonation wave channel. The monopropellant feed assembly delivers monopropellant from a monopropellant storage tank into the detonation wave channel. The detonation initiator initiates continuous detonation of the monopropellant in the detonation wave channel, preferably without a catalyst to promote decomposition of the monopropellant. Accordingly, specific impulse is increased compared to constant-pressure reaction thrusters that catalytically decompose the monopropellant with deflagration combustion.

Embodiments are directed toward a monopropellant continuous detonation engine. In some embodiments, the continuous detonation engine includes an engine body, a monopropellant feed assembly, and a detonation initiator. The engine body defines a detonation wave channel. The monopropellant feed assembly delivers monopropellant from a monopropellant storage tank into the detonation wave channel. The detonation initiator initiates continuous detonation of the monopropellant in the detonation wave channel, preferably without a catalyst to promote decomposition of the monopropellant. Accordingly, specific impulse is increased compared to constant-pressure reaction thrusters that catalytically decompose the monopropellant with deflagration combustion.

An injector element for a liquid propellant rocket engine includes an oxidizer conduit, a central cavity that is fluidly coupled with the oxidizer conduit downstream of the oxidizer conduit, a first annulus that at least partially surrounds the oxidizer conduit and is fluidly coupled with an ignition fluid supply downstream of the ignition fluid supply, and a second annulus that at least partially surrounds the oxidizer conduit and is fluidly coupled with a fuel supply downstream of the fuel supply. The second annulus is fluidly coupled between the first annulus and the central cavity.

An injector element for a liquid propellant rocket engine includes an oxidizer conduit, a central cavity that is fluidly coupled with the oxidizer conduit downstream of the oxidizer conduit, a first annulus that at least partially surrounds the oxidizer conduit and is fluidly coupled with an ignition fluid supply downstream of the ignition fluid supply, and a second annulus that at least partially surrounds the oxidizer conduit and is fluidly coupled with a fuel supply downstream of the fuel supply. The second annulus is fluidly coupled between the first annulus and the central cavity.