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151 results about "Propellant tank" patented technology

A propellant tank is a container which is part of a vehicle, where propellant is stored prior to use. Propellant tanks vary in construction, and may be a fuel tank in the case of many aircraft. In rocket vehicles, propellant tanks are fairly sophisticated since weight is on a premium.

Remotely located cryocooler

A cryocooler is located on a spacecraft bus, such as a bus box, separate from the cryogenic propellant tanks disposed on a separable and distinct propellant cartridge system spacecraft docked to the spacecraft bus. In operation, propellant may be continuously pumped from the tanks through the cryocooler cold heat exchanger and then back to the tanks on the separable propellant cartridge system spacecraft through temporarily couplable lines. After the propellant tanks are depleted, the propellant cartridge system is then undocked from the bus and typically discarded. A new propellant cartridge system spacecraft comprising a full set of tanks may then be docked to the bus and the cryocooler supply / return lines coupled. The remote cryocooler may function as part of a larger space depot for spacecraft resupply, although it is not limited to such applications.
Owner:THE BOEING CO

System and method for cooling rocket engines

A propulsion system for a rocket engine and a method of cooling a rocket engine includes a propellant tank fluidically coupled to the rocket engine to hold a pressurized propellant, a coolant tank to hold a coolant, a first heat exchanger thermally coupled to the rocket engine and fluidically coupled to the coolant tank, a second heat exchanger thermally coupled to the propellant tank and fluidically coupled to the first heat exchanger, and a third heat exchanger disposed inside the propellant tank to thermally couple a propellant withdrawn from the tank for combustion to a propellant disposed inside the tank. The coolant flows from the coolant tank to the first heat exchanger and through the first heat exchanger to cool the rocket engine. The propellant withdrawn from the propellant tank receives heat from the propellant disposed inside the tank through the third heat exchanger to convert to a gaseous propellant when withdrawn from the propellant tank as a liquid propellant. The coolant flows from the first heat exchanger to the second heat exchanger and through the second heat exchanger to heat the propellant disposed inside the propellant tank.
Owner:XCOR AEROSPACE

Power system for carrier rocket upper stage and orbit transfer vehicle

InactiveCN109630316AEnsure safetyTo achieve non-toxicRocket engine plantsAttitude controlKerosene
The invention discloses a power system for a carrier rocket upper stage and an orbit transfer vehicle. The power system for the carrier rocket upper stage and the orbit transfer vehicle solves the existing problems that a main engine and an attitude control engine are relatively independent, the carrying burden is relatively heavy,a propellant used in the attitude control engine is rather toxic,and the environment and safety of a human body are seriously threatened. The power system for the carrier rocket upper stage and the orbit transfer vehicle comprises the main engine and the attitude control engine; a propellant tank of the main engine can simultaneously deliver a propellant to a thrust chamber of the main engine and a thrust chamber of the attitude control engine under the action ofa propellant supply system of the propellant tank, and liquid oxygen is used as an oxidant of the propellant; kerosene, or liquid hydrogen or liquid methane is used as an incendiary agent; the detoxication of the attitude control engine is achieved, and integration of the homologous propellant of the main engine and the attitude control engine is achieved; a propellant tank of the attitude control engine can be supplemented after operation through the main engine; and the propellant dosage carried by the attitude control engine during flight can be reduced, thus the weight of the overall system is lowered, and the payload of a carrier is greatly increased.
Owner:XIAN AEROSPACE PROPULSION INST

Hydraulic accumulator for propellant tank in spacecraft

The invention discloses a hydraulic accumulator for a propellant tank in a spacecraft. The hydraulic accumulator comprises an air guide tube, a cover plate, an outer shell, blades, a support column, a base, channel window pressing plates, a channel window meshes, hydraulic accumulator meshes, a fixing block and hydraulic accumulator mesh pressing plates, wherein the blades are uniformly distributed on and fixed to the support column in the radial direction to form a whole structure, and the whole structure is mounted on and fixed to a circular partition plate in the base; the hydraulic accumulator meshes are pressed on the circular partition plate in the base through the hydraulic accumulator mesh pressing plates and then fixed; the channel window meshes are pressed on the outer side of a cylinder wall of the base through the channel window pressing plates and then fixed; the outer shell is fixed at the top end of the base, the cover plate is fixed on the outer shell, and the air guide tube is fixed on the cover plate through the fixing block. The hydraulic accumulator disclosed by the invention is simple in structure, high in strength and reliability, large in liquid storage quantity and wide in work application range, has the function of repeatedly and circularly filling liquids to the hydraulic accumulator and discharging the liquids from the hydraulic accumulator, is large in liquid filling and discharging rate, and meanwhile has the capacity of realizing ground repeated filling.
Owner:BEIJING INST OF CONTROL ENG
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