Deep variable-thrust multi-start liquid rocket power system

Abstract

The invention relates to a liquid rocket engine, in particular to a deep variable-thrust multi-start liquid rocket power system. The technical problems that the performance of an existing moon landingrocket engine is low, propellants are toxic, and supercharging system components are complex and the technical problems that propellants of an existing moon landing and rising aircraft rail control and attitude control power system with liquid oxygen kerosene as a main propellant are not uniform, and the propellants and high-pressure storage boxes thereof need to be additionally arranged, so thatthe size and the mass of the system are increased, effective loads of the liquid rocket engine are reduced, and the launching cost is increased are solved. The deep variable-thrust multi-start liquidrocket power system comprises a liquid rocket engine, a propellant supply system and a gas oxygen gas generator. The gas oxygen gas generator is used for burning liquid oxygen and kerosene provided by the propellant supply system to generate high-oxygen-rich gas and store the high-oxygen-rich gas. The liquid rocket engine is a deep variable-thrust multi-start liquid rocket engine based on liquidoxygen expansion cycle.

Description

technical field [0001] The invention relates to a liquid rocket power system, in particular to a depth-variable-thrust multiple-start liquid rocket power system. Background technique [0002] In the mission process of lunar exploration and (manned) lunar surface landing, in order to realize lunar surface orbit transfer and lunar surface soft landing, the engine is required to have multiple starts, working condition depth adjustment (10%-100%), long-term Work (1000s) and reliable work performance. [0003] The U.S. "Apollo" lunar landing downgrade engine uses a squeeze system with mixed hydrazine and nitrogen tetroxide. This type of engine has a simple structure and high reliability, but its performance is low and the propellant is poisonous. [0004] The former Soviet Union proposed the "L-3" lunar module power system, which adopted the integrated form of the descending engine and the ascending engine, in which the main engine used a gas generator cycle of unsymmetrical dim...

AI Technical Summary

Problems solved by technology

[0008] In order to solve the technical problems of the low performance of the existing lunar landing rocket engines, toxic propellant and complex parts of the pressurization system, as well as the inconsistency of the propellants in the orbit control and attitude control power systems of the existing lunar landing and ascent aircraft, additional propulsion is required agent and its high-pressure storage tank, resulting in an increase in its volume and mass, reducing the payload of the liquid rocket engine and increasing the technical problem of launch costs. The invention provides a liquid rocket power system with depth variable thrust and multiple starts

Images