A flight test system uses a flight termination destruct charge that is configured to overpressurize a pressure vessel in a rocket motor to terminate thrust. The flight termination destruct charge is an electroexplosive detonator arranged on a final burn surface of a propellant contained in the pressure chamber. In a multi-pulse rocket motor, one of the pulses is ignited by the activation of the detonator. The activated detonator is configured to ignite the propellant grain without venting of the gas resulting from the burning of the propellant. Due to the burning of the propellant, the surface area in the pressure vessel is increased which causes increased pressure in the pressure vessel until a critical pressure is reached. When the critical pressure is reached, the rocket motor casing structural capabilities are exceeded. The overpressurized rocket motor casing then ruptures and thrust of the rocket motor is terminated.

A flight test system uses a flight termination destruct charge that is configured to overpressurize a pressure vessel in a rocket motor to terminate thrust. The flight termination destruct charge is an electroexplosive detonator arranged on a final burn surface of a propellant contained in the pressure chamber. In a multi-pulse rocket motor, one of the pulses is ignited by the activation of the detonator. The activated detonator is configured to ignite the propellant grain without venting of the gas resulting from the burning of the propellant. Due to the burning of the propellant, the surface area in the pressure vessel is increased which causes increased pressure in the pressure vessel until a critical pressure is reached. When the critical pressure is reached, the rocket motor casing structural capabilities are exceeded. The overpressurized rocket motor casing then ruptures and thrust of the rocket motor is terminated.

An igniter system and method for igniting a propellant by an optical energy source. The igniter system including an igniter composite and a propellant. The igniter composite including a reactive component and a fluoropolymer. The propellant is coupled to the igniter composite. The igniter composite has a composition including nano-aluminum at ideal stoichiometry in polyvinylidene fluoride. The igniter composite is configured to achieve a sustained ignition from a wavelength emitted from the optical energy source. The wavelength is between around 250 nanometers to around 1100 nanometers.

An igniter system and method for igniting a propellant by an optical energy source. The igniter system including an igniter composite and a propellant. The igniter composite including a reactive component and a fluoropolymer. The propellant is coupled to the igniter composite. The igniter composite has a composition including nano-aluminum at ideal stoichiometry in polyvinylidene fluoride. The igniter composite is configured to achieve a sustained ignition from a wavelength emitted from the optical energy source. The wavelength is between around 250 nanometers to around 1100 nanometers.

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.

Self-ignited burns can be increased by stimulation. External ignition must often be carried out in the combustion chamber. Often an ignition nucleus is formed electrically. This has energetic disadvantages. Required internals can be disadvantageous. Ignitions with plasma torches also need fixed internals. Electromagnetically, however, the ignition field can be widened, the combustion rate increased and the temperature changed. Due to high electrical consumption, this effective ignition has not yet been advantageous for aerospace applications. This concept should be feasible with low electrical energy requirements.

Sufficient electrical energy can be provided by turbopump, generator or thermocouple. For better coupling of electromagnetism, catalytic absorbers and possibly other particles are used. These lower the activation energy. Contactless ignition can be achieved using ceramics or metallic antennas. Ignition in the center of the combustion chamber at the highest pressures is particularly promising. The aim is to achieve combustion that is as directional as possible.

Self-ignited burns can be increased by stimulation. External ignition must often be carried out in the combustion chamber. Often an ignition nucleus is formed electrically. This has energetic disadvantages. Required internals can be disadvantageous. Ignitions with plasma torches also need fixed internals. Electromagnetically, however, the ignition field can be widened, the combustion rate increased and the temperature changed. Due to high electrical consumption, this effective ignition has not yet been advantageous for aerospace applications. This concept should be feasible with low electrical energy requirements.

Sufficient electrical energy can be provided by turbopump, generator or thermocouple. For better coupling of electromagnetism, catalytic absorbers and possibly other particles are used. These lower the activation energy. Contactless ignition can be achieved using ceramics or metallic antennas. Ignition in the center of the combustion chamber at the highest pressures is particularly promising. The aim is to achieve combustion that is as directional as possible.

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.