The present invention relates to throttleable propulsion launch escape systems and devices. In one embodiment, the system includes a tower and at least one throttleable motor secured to the tower. The throttleable motor is able to throttle to a reduced power setting during flight. In another embodiment, the system includes at least one throttleable motor and a space vehicle unit that includes a containing structure. In a further embodiment, the throttleable motor may be secured about a boost escape system of a space vehicle unit. In an additional embodiment, the present invention is a three-dimensional nozzle.

An ignition system (10) includes a fuel injection opening (30), a fuel reforming device (70), an ignition gas injection opening (50) and an ignition gas supply passage (52). The fuel injection opening (30) injects the hydrocarbon fuel into the combustion chamber (20). The fuel reforming device (70) reforms the hydrocarbon fuel to the ignition gas which ignites automatically through contact with the oxidizing agent. The ignition gas injection opening (50) injects the ignition gas into the combustion chamber (20). The ignition gas supply passage (52) supplies the ignition gas to the ignition gas injection opening (50) from the fuel reforming device (70).

Systems and methods for a multimode propulsion system (MMPS) are presented. The MMPS includes a chemical thruster, an electric thruster, and a shared propellant tank. The MMPS further includes a propellant decomposition chamber that transforms, via a catalytic and/or electrolytic process, the propellant from the tank into vapor form for use as gas propellant by the electric thruster. The electric thruster can be configured for targeted ionization of one or more constituent species present in the vapor form of the propellant. Flow activation/control from the tank to the chemical and electric thrusters is provided by a fluidic feed system. The branches include a check valve and a pressure regulator in series connection. A normally closed squib valve prevents propellant flows/leaks from the tank to either the chemical or the electric thrusters when the MMPS is not in operation.

A spacecraft-borne propulsion device includes a propellant storage mechanism including a propellant storage container that stores a propellant in a vapor-liquid equilibrium state or a liquid phase, the propellant being ethanol or an aqueous ethanol solution; a propellant transport mechanism configured to supply, with an electric pump, the propellant under pressurization to a pressure exceeding 1 atm at room temperature; a gas heating mechanism including a heater including a separate heater for heating up connected via a check valve; a thruster head mechanism having a nozzle that generates a thrust with a heated gas; and a power supply mechanism including a storage battery for driving the electric pump and the heater for heating up. The propellant storage mechanism, the propellant transport mechanism, the gas heating mechanism, and the thruster head mechanism are connected in series.

Method and apparatus for controlling pressure in a pressure vessel. A plurality of valves between a pressure source and a pressure vessel can be selectively opened or turned off, singularly or in combinations, to control pressure in the pressure vessel. A maximum pressure threshold and a minimum pressure threshold can be established based on operating considerations of the pressure vessel. One or more of the valves can be turned on when the pressure in the pressure vessel reaches the minimum pressure threshold. One or more of the valves can be turned off when the pressure in the pressure vessel reaches the maximum pressure threshold.

The present invention relates to improved rocket engine systems. In one embodiment, an improved rocket engine system includes a propellant source, at least one power source, at least one power source motor, a rocket engine, and at least one pump. The improved rocket engine system may further include at least one of the following: at least one controller, at least one propellant valve, and a propellant pressurizing source.

Method and apparatus for controlling pressure in a pressure vessel. A plurality of valves between a pressure source and a pressure vessel can be selectively opened or turned off, singularly or in combinations, to control pressure in the pressure vessel. A maximum pressure threshold and a minimum pressure threshold can be established based on operating considerations of the pressure vessel. One or more of the valves can be turned on when the pressure in the pressure vessel reaches the minimum pressure threshold. One or more of the valves can be turned off when the pressure in the pressure vessel reaches the maximum pressure threshold.

A hybrid-like liquid fuel motor (the motor) may include a port surrounded by a wall. Surrounding the wall are a plurality of chambers and segmented walls to separate the chambers. In some instances, a single helix chamber may surround the wall, and may operate similar to that of a segmental chamber. During operation of the motor, gas flows from one end of the port to another end of the port. As the walls surrounding the port begin to disintegrate, liquid fuel within chambers begins to begin to mix with the flow of gas. As the segmented walls between the chambers begin to disintegrate, liquid from the other chambers begin to mix with the flow of gas, creating a metering of the liquid fuel.

A liquid storage device for a propellant tank in a spacecraft includes a gas-guide tube, a cover plate, a housing, blades, a supporting column, a base, a passage-window pressing plate, a passage-window mesh piece, a liquid-storage-device mesh piece, a fixing block, and a pressing plate for the liquid-storage-device mesh piece. The blades are uniformly distributed on and fixed to the support column in a radial direction to form an integral structure, and the integral structure is mounted on and fixed to a circular partition plate in the base. The liquid-storage-device mesh piece is pressed on the circular partition plate in the base by the pressing plate for the liquid-storage-device mesh piece and then is fixed. The passage-window mesh piece is pressed on the outer side of a cylinder wall of the base by the passage-window pressing plate and then is fixed.

A vapor jet system to continuously jet vapors while suppressing cavitation. One vapor jet system includes a liquid storage part for separately storing two or more kinds of mutually insoluble liquids; a jet orifice; and a jet control part. Jetting the vapors is from a state where pressure in the space storing the vapors in the liquid storage part is higher than the saturated vapor pressure in any of the two or more kinds of liquids. Alternatively, a vapor jet system can include a fluid storage part storing one kind of liquid and at least one kind of inactive gas having a composition different from the liquid; a similar jet orifice; and a similar jet control part. Jetting the vapors and inactive gas(es) is (are) from a state where pressure in a vapor storing space in the fluid storage part is higher than the saturated vapor pressure in the liquid.