Solid rocket engine

A technology of solid rockets and motors, which is applied in the direction of rocket motor devices, machines/engines, mechanical equipment, etc. It can solve the problems of reducing thrust, reducing charge, reducing volume, etc., and achieves large combustion surface area, short working time and high reliability. Good results

Inactive Publication Date: 2009-09-30
SHENYANG LIGONG UNIV
View PDF0 Cites 30 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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 us

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Solid rocket engine
  • Solid rocket engine
  • Solid rocket engine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0015] refer to figure 1 , the engine layout is to arrange four centrally symmetrical small engines of the same size in a given space, and every two centrally symmetrical engines form a group to realize orbital maneuvering of the satellite. When the first orbit change is required by the ground command, the two centrally symmetrical engines will be ignited to make the satellite enter the transfer orbit from the original orbit; when the satellite moves to the entry point with the target satellite orbit, the other two The engine is ignited to put the satellite into the target satellite orbit. Two centrally symmetrical engines are used to ignite to realize the layout of orbital maneuvering, which requires high machining accuracy of the engines, good ignition reliability, and consistency in timing of the ignition commands issued by the ignition control device for the two engines. better.

[0016] refer to figure 2 , the engine is composed of an igniter 1, a casing 2, a propella...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to view more

PUM

No PUM Login to view more

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...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to view more

Application Information

Patent Timeline
no application Login to view more
IPC IPC(8): F02K9/08F02K9/95F02K9/34F02K9/97
Inventor 侯妮娜张健
Owner SHENYANG LIGONG UNIV
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Try Eureka
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap