Solid rocket engine

Abstract

The invention relates to an orbital-transfer small-sized solid rocket engine, which adopts an arrangement that: four centrosymmetric small-sized engines which are same in size are arranged in a given space; each two centrosymmetric engines form a group to realize the orbital manoeuvre of a satellite; and each small-sized engine comprises igniters, a shell, a propellant and a spray pipe, wherein the igniters adopt three parallelly-connected igniters for ignition, the material of the shell is titanium alloy which is high in strength, temperature-resistance, corrosion-resistance, good in pressure application and processing performance, and high in impact ductility, the propellant is an HTPB propellant which is high in specific thrust, medium in combustion velocity and excellent in energy response, mechanical characteristics and combustion characteristics, and the spray pipe adopts the same material as the shell of a combustion chamber, a grain which is an internal combustion grain adopting a casting installation mode, and a structure of single thrust and single spray pipe. The solid rocket engine can meet the requirements of the orbital transfer engines on large thrust during the start-up, requires short operating time, and is excellent in reliability and high in accuracy.

Description

technical field [0001] The invention relates to a solid rocket motor, in particular to a small solid rocket motor for orbit change. Background technique [0002] The propulsion system is the key subsystem of most spacecraft. It is mainly used for orbital maneuvering and special attitude control of the spacecraft. have a direct impact. The main component of the propulsion system that generates power is the engine. The overall design purpose of the engine is to enable the spacecraft to obtain the best overall performance while ensuring that the engine has as high a quality index as possible. These two purposes are sometimes consistent and sometimes contradictory. When conflicts arise, the overall design requirements of the spacecraft should be met first, and then the quality index requirements of the engine should be properly considered. [0003] At present, the small solid rocket motors used for orbit change have the following disadvantages: [0004] 1. Less powder charg...

AI Technical Summary

Problems solved by technology

Due to the use of a small engine, its volume is reduced, resulting in a reduction in the amount of charge, thus reducing the thrust used for orbit and attitude control

[0006] 3. Low reliability and precision

Because the engine used for orbit change is required to have a short working time and a large thrust, at the same time, the engine works in outer space, where there is almost no air and the external pressure is very small, thus reducing reliability

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