Rocket thrust chamber with fuel switching function and supply system of rocket thrust chamber

Abstract

The invention relates to a rocket thrust chamber with the fuel switching function and a supply system of the rocket thrust chamber and belongs to an afterburning type rocket engine capable of switching hydrogen peroxide/kerosene into liquid hydrogen. The rocket thrust chamber aims at integrating a hydrogen peroxide/liquid hydrogen engine with a hydrogen peroxide/kerosene engine and achieving the fuel switching function. The technical schemes of a head four-bottom three-cavity structure suitable for switching fuel, a combined fuel nozzle shared by hydrogen rich gas, hydrogen ultra-rich gas and kerosene, a straight-hole type oxidizing agent nozzle continuously injecting oxygen rich gas before and after fuel is switched, a body where an oxidizing agent flows through uninterruptedly for cooling, a hydrogen peroxide system used before and after fuel is switched, a kerosene system used before fuel is switched, a liquid hydrogen system used after fuel is switched and the like are adopted. The rocket thrust chamber with the fuel switching function is suitable for engines of a single-stage-to-orbit rocket, a core-stage rocket and a reusable aerospace craft and the rocket thrust chamber also can be applied to an engine of a hydrogen peroxide/liquid hydrogen upper-stage rocket when fuel is not switched.

Description

technical field [0001] The invention relates to a fuel switching rocket thrust chamber (combustion chamber) and its supply system, belonging to hydrogen peroxide / kerosene switching to liquid hydrogen supplementary combustion rocket engine. Background technique [0002] Liquid rocket engines have a history of 70 years of application, and all countries use one kind of propellant for one rocket stage. For boosters and first stage rockets, propellants with higher density than impulse represented by liquid oxygen / kerosene are mainly used. For upper-stage rockets, propellants with high specific impulse represented by liquid oxygen / liquid hydrogen are mainly used. [0003] For new single-stage rockets, such as liquid oxygen / kerosene engines, the first stage from take-off to mid-flight has high propulsion performance, but the second stage from mid-flight to high-altitude shutdown has poor propulsion performance. If a liquid oxygen / hydrogen engine is used, although the second-stage...

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Problems solved by technology

[0006] Aiming at the need for a new single-stage orbit rocket that needs reasonable propulsion and a better-performing fuel-switching rocket engine, in order to solve the problem of combining the hydrogen peroxide / liquid hydrogen engine and the hydrogen peroxide / kerosene engine to achieve fuel switching, this paper Invention According to the characteristics of fuel switching and the requirements of optimal design, necessary modifications and arrangements are made, and a rocket thrust chamber and its supply system for switching fuel are proposed

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