Self-pressurization double-component pulse working rocket engine

Abstract

The invention discloses a self-pressurization double-component pulse working rocket engine, and belongs to the technical field of aerospace propulsion. A double-cylinder pneumatic plunger pump and a thrust chamber are organically combined into a whole, gas in a combustion chamber is used for driving the double-cylinder plunger pump, the sum of the action areas of the pressure, borne by an annularpiston of the plunger pump, of a propellant is smaller than the action area of the pressure of the gas of the combustion chamber, and therefore the pressure difference is generated. After an oxidizingagent pressurized by the plunger pump is catalytically decomposed, hot gas is generated to enter the combustion chamber to be combusted with fuel, the pressure of the combustion chamber is increased,a positive feedback effect is formed, the combustion chamber works at high-voltage pulses at low inlet pressure, the performance of the engine can be greatly improved, the size, the structure weightand the manufacturing cost of the engine can be reduced, meanwhile, as it is required that the inlet pressure of the propellant is low, the amount of gas pressurized by a propellant storage box is small, the pressure of the storage box is low, the structure weights of the storage box and a pressurization system can be effectively reduced, and therefore the loading capacity and the use performanceof a spacecraft are effectively improved.

Description

technical field [0001] The invention relates to the field of aerospace propulsion technology, in particular to a dual-component engine for the upper stage of a launch vehicle or orbit control, which can also be used as a propulsion system for space vehicles and high-speed unmanned aerial vehicles. Background technique [0002] The two-component propulsion system of the upper stage of the launch vehicle and the orbit control engine or the space vehicle generally adopts the squeeze type or pump type propulsion system scheme. The extrusion system needs to be equipped with a high-pressure gas source, a pressure reducing valve or a pressure regulator to maintain a high supply pressure of the propellant tank, and the system is relatively complicated; and the higher the tank pressure, the larger the volume of the gas source required , The greater the weight of the system structure, the chamber pressure of these engines is generally relatively low, only 1-2Mpa, and the engine perfor...

AI Technical Summary

Problems solved by technology

This single-component propulsion system can avoid the use of high-pressure gas cylinders and realize the lightweight of the propulsion system, but there are disadvantages in that: because the gas driving the plunger pump is directly discharged to the outside, there is a certain energy loss, and the system pressure The higher the energy loss, the greater the energy loss; the second is that it is necessary to set up a flow regulator that works in high-temperature and high-pressure gas media, and it is difficult to achieve high reliability and safety, which is a major factor that restricts the pressure level that the propulsion system can achieve. The published test maximum pressure does not exceed 5Mpa

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