To use launchpad based laser beam generators to stream 50+ kilowatt laser beams up through clear fused quartz discs located in the base of the rocket to super heat the steam in the rocket's pressure chamber for the purpose of increasing the thrusting power of the rocket. This rocket does not use fossil fuel, but rather it uses 99% pure hydrogen peroxide fuel, (H.sub.2O.sub.2) which flashes into steam without the use of combustion.

A method, which uses real pressure, temperature and mass data obtained from real telemetry, to control the mixture ratio based on the change of the temperature set in its tanks, where the mixture ratio is defined by the ratio between the oxidant mass consumption by the fuel mass consumption. To achieve this, the space system in question must have a bipropellant propulsion system operating in blow-down mode containing independent temperature control systems for each tank. The method is related to the aerospace field, the application of this method is of interest to the areas of manufacturing and operation of space systems.

A catalyst bed includes a structure defining a plurality of channels configured to receive flow of fluid to be chemically catalyzed. The plurality of channels are oriented at least partially non-parallel to an overall flow direction of the flow from inputs of the plurality of channels to outputs of the plurality of channels. A catalyst is exposed at an exterior of the structure.

Closed-loop refrigeration cycles for liquid oxygen densification are disclosed. The disclosed refrigeration cycles may be turbine-based refrigeration cycles or a Joule-Thompson (JT) expansion valve based refrigeration cycles and include a refrigerant or working fluid comprising a mixture of neon or helium together with nitrogen and/or oxygen.

Carbide-based fuel assembly includes outer structural member of ceramic matrix composite material, the interior surface of which is lined in higher temperature regions with an insulation layer of porous refractory ceramic material. A continuous insulation layer extends the length of the fuel assembly or separate insulation layer sections have a thickness increasing step-wise along the length of the fuel assembly from upper (inlet) section towards bottom (outlet) section. A fuel element positioned inward of the insulation layer and between support meshes has a fuel composition including HALEU and has the form of a plurality of individual elongated fuel bodies or one or more fuel monolith bodies containing coolant flow channels. Fuel assemblies are distributively arranged in a moderator block, with upper end of the outer structural member attached to an inlet for propellant and lower end of the outer structural member operatively interfaced with a nozzle forming a NTP reactor.

A rocket propulsion system comprises a combustion chamber, a hydrogen-oxygen supply system connected to the combustion chamber, which hydrogen-oxygen supply system is configured to conduct hydrogen and oxygen into the combustion chamber, and a coolant supply system connected to the combustion chamber, which coolant supply system is configured to conduct a combustible coolant into the combustion chamber. An ignition system of the rocket propulsion system is configured to initiate combustion of the hydrogen-oxygen-coolant mixture in the combustion chamber.

A hybrid airbreathing rocket engine module (70) comprises an air intake arrangement (62) configured to receive air and a heat exchanger arrangement (63) configured to cool air from the air intake arrangement (62); a compressor (64) configured to compress air from the heat exchanger arrangement (63); and one or more thrust chambers (65). The air intake arrangement (62), the compressor (64), the heat exchanger arrangement (63), and the one or more thrust chambers (65) are arranged generally along an axis (69) of the engine module (70). The heat exchanger arrangement (63) is arranged between the compressor (64) and the one or more thrust chambers (65).

A high density, generally recognized as safe hybrid rocket motor is described which has a density-specific impulse similar to a solid rocket motor, with good performance approaching or equal to a liquid rocket motor. These high density hybrid motors resolve the packaging efficiency/effectiveness problems limiting the application of safe, low cost hybrid motor technology.

A system and methods are disclosed for an upper stage space launch vehicle that uses gases from the propellant tanks to power an internal combustion engine that produces mechanical power for driving other components including a generator for generation of electrical current for operating compressors and fluid pumps and for charging batteries. These components and others comprise a thermodynamic system from which system enthalpy may be leveraged by extracting and moving heat to increase the efficient use of propellant and the longevity and performance of the launch vehicle.

A rocket propulsion system comprises a combustion chamber, an oxygen supply system, comprising an oxygen supply duct and being configured to supply oxygen to the combustion chamber, and a hydrogen supply system, comprising a hydrogen supply duct and being configured to supply hydrogen to the combustion chamber. An ignition unit of the propulsion system, to which at least portions of the oxygen and the hydrogen supplied to the combustion chamber can be supplied, is configured to initiate combustion of the oxygen-hydrogen mixture in the combustion chamber. The propulsion system further comprises a cooling duct extending along an inner surface of a combustion chamber wall and through which at least a portion of the oxygen supplied to the combustion chamber, at least a portion of the hydrogen supplied to the combustion chamber or a combustion gas mixture emerging from the ignition unit flows.