A system receives a signal from a sensor indicative of a condition of a pump, decomposes the signal into a wavelet, and analyzes the wavelet to detect a likelihood of cavitation in the pump.

Method and system for detecting cavitation in a pump

An oxygen-hydrogen pressurization system includes a cryogenic oxygen tank, cryogenic hydrogen tank, thermal switch, supercritical oxygen bottle, supercritical hydrogen bottle, and pressure management system and a thermodynamic vent system. The thermal switch permits heat to flow between hot and cool areas within the space vehicle to help facilitate pressure management within the cryogenic liquid oxygen tank and the cryogenic liquid hydrogen tank in conjunction with the higher pressure fluid from the supercritical oxygen tank and the fluid from the supercritical hydrogen tank and the added cooling from the pressure management system.

Thermally-integrated fluid storage and pressurization system

A gas generator or rocket engine includes: a first storage tank configured to contain a high-pressure liquid propellant; a nozzle connected to the first storage tank; a heat source connected between the first storage tank and the nozzle and configured to add heat to the high-pressure liquid propellant at a heat transfer rate to substantially gasify the high-pressure liquid propellant, where the nozzle is configured to expel and expand the substantially gasified high-pressure liquid propellant, and where the gas generator is configured so that an expanded temperature of the substantially gasified high-pressure liquid propellant after being expanded by the nozzle is in the range −50° C. to 100° C., preferably 0° C. to 50° C.; and a controller connected to the heat source and configured to adjust the heat transfer rate.

Cool gas generator and ultra-safe rocket engine

The invention relates to the field of rocket engines, and more particularly to a system for feeding a rocket engine ( 2 ) with propellant, the system comprising a first tank ( 3 ), a second tank ( 4 ), a first feed circuit ( 6 ) connected to the first tank ( 3 ), and a second feed circuit ( 7 ) connected to the second tank ( 4 ). In order to cool the propellant contained in the second tank ( 4 ), the first circuit ( 6 ) includes a branch ( 12 ) passing through a first heat exchanger ( 14 ) incorporated in the second tank ( 4 ). The invention also provides a method of feeding the rocket engine ( 2 ).

System and a method for feeding a rocket engine

[Problem] A heat exchanger generally employs a method for supplying liquid having a critical pressure or more or a high pressure in order to suppress a boil. However, because gas obtained in a carburetor behind the heat exchanger has a relatively low pressure, supplying the liquid to the heat exchanger requires a system such that the energy form of the obtained gas is converted to kinetic energy or electrical energy, and a pressure increase is achieved with a mechanical pump. Thus, the complicated system involving efficiency loss was the only solution, and it has been difficult to achieve a weight reduction or system simplification of a propellant supply apparatus in a moving body, specifically, a flying object. [Solution] A device according to the present invention uses relatively low-pressure gas itself, obtained by vaporizing liquid, in pressurizing and supplying a raw fluid as a material of the gas without requiring the conversion of energy form of the gas into kinetic energy or electrical energy. Also provided are a system and a method that use the device to supply a propellant in a moving body, specifically, a flying object.

Device, system, and method for pressurizing and supplying fluid

Cavitation is reduced in a rotary pump while the pump performance is maintained by utilizing a low-temperature fluid source already present in the pump system. The fluid from the low-temperature fluid source receives heat from the fluid flowing to the pump, thereby lowering its temperature and the saturated vapor pressure, which increases the allowable margin for a decrease in fluid pressure and reduces the occurrence of cavitation. The pump system may be used for a liquid rocket engine. The fluid velocity of the fluid directed to the pump is low before releasing heat, so there is only a slight pressure loss at the pump. Accordingly, the temperature is lowered and the occurrence of cavitation is reduced within the pump.

System for reducing pump cavitation

We reduce the appearance of cavitation in a rotary pump while maintaining the performance of the pump, by using a low temperature source present in the pump system for heat exchange with the fluid flowing in the pump, thereby lowering its temperature and also the saturation vapor pressure of the fluid. In the case of a liquid fuel rocket engine, a refrigerant or other propellant B whose temperature is lower than that of the primary propellant A, can be used for this source at low temperature. The propellant B passes through a heat exchanger 2 by means of a pump 4, and exchanges its heat with the propellant A coming from a reservoir 3, to lower the temperature of the fluid. At low fluid speed of the propellant A, there is only a slight pressure drop inside the heat exchanger 2 and the appearance of cavitation is reduced inside the pump 1.

Reduction system for pump cavitation, cools fluid flowing into rotary pump in order to reduce cavitation in rotary pump

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System for reducing pump cavitation

Reduction system for pump cavitation, cools fluid flowing into rotary pump in order to reduce cavitation in rotary pump