A Depth Variable Thrust Multiple Start Liquid Rocket Power System

Abstract

The invention relates to a liquid rocket engine, in particular to a liquid rocket power system with depth-variable thrust and multiple starts; it solves the technical problems of low performance of the existing moon-landing rocket engine, poisonous propellant and complicated parts of the pressurization system, and The propellants of the orbit control and attitude control power systems of the existing liquid oxygen kerosene-based propellants for lunar landing and ascent aircraft are not uniform, and additional propellants and high-pressure storage tanks are required, resulting in an increase in volume and mass, and a reduction in liquid rockets. The payload of the engine, a technical problem that increases the cost of the launch. A liquid rocket power system with variable thrust and multiple starts, including a liquid rocket engine, a propellant supply system and a gas-oxygen gas generator; the gas-oxygen gas generator is used to burn liquid oxygen and kerosene provided by the propellant supply system to generate high-fuel Oxygen gas is used and stored; the liquid rocket engine is a liquid rocket engine that starts the liquid rocket engine multiple times based on the depth variable thrust of the liquid oxygen 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

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