A gas distribution system is provided for use in an enclosed volume. This system includes a distribution duct and a first inflatable duct portion in fluid communication with the distribution duct. A passageway is provided defining an opening which extends through the passageway wherein the opening is in fluid communication with the first inflatable duct portion and wherein a cross-sectional area of the opening is less than a cross-sectional area of the first inflatable duct portion. Additionally, an inflatable enclosure is provided which is in fluid communication with the opening of the passageway wherein the inflatable enclosure is configured to form a volume within and separated from the enclosed volume.

Systems and methods for launching space vehicles into outer space are disclosed. Method include powering a thrust augmentation stage of a launch vehicle during an initial portion of a launch trajectory to provide thrust to the launch vehicle; following the initial portion of the launch trajectory, separating a first stage of the launch vehicle from the thrust augmentation stage; powering the first stage of the launch vehicle during the initial portion and during a second portion of the launch trajectory following the initial portion of the launch trajectory to provide thrust to the launch vehicle; and controlling a controlled descent of the thrust augmentation stage to Earth following separation of the thrust augmentation stage from the first stage.

A fuel depot in space is provided. The fuel depot has a collapsible housing with a guidance, navigation, and control (GNC) system, a power management system, and a reaction control system (RNC). Connected to the housing are a plurality of fuel tanks that are connected via collapsible rods. The fuel tanks have pipe systems that are in communication with a plurality of pumps to transfer fuel from the tanks through a refueling arm and into a spacecraft during refueling.

The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, and an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided.

Systems and methods for launching space vehicles into outer space are disclosed. Method include powering a thrust augmentation stage of a launch vehicle during an initial portion of a launch trajectory to provide thrust to the launch vehicle; following the initial portion of the launch trajectory, separating a first stage of the launch vehicle from the thrust augmentation stage; powering the first stage of the launch vehicle during the initial portion and during a second portion of the launch trajectory following the initial portion of the launch trajectory to provide thrust to the launch vehicle; and controlling a controlled descent of the thrust augmentation stage to Earth following separation of the thrust augmentation stage from the first stage.

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.

Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example method includes deploying a space vehicle including an electric propulsion system; and using the electric propulsion system for attitude control and orbit control, no other propulsion system provided to enable the attitude control and the orbit control.

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.

The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, and an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided.

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.