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A multi-pulse solid rocket motor

A solid rocket and engine technology, applied in rocket engine devices, machines/engines, mechanical equipment, etc., can solve problems such as small thrust, achieve large thrust, increase initial combustion area, and achieve the effect of repeated starts

Active Publication Date: 2021-03-26
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] Aiming at the technical problem to be solved, the present invention provides a multi-pulse solid rocket motor to solve the problem of small thrust of traditional electronically controlled solid propellant rocket motors

Method used

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  • A multi-pulse solid rocket motor
  • A multi-pulse solid rocket motor
  • A multi-pulse solid rocket motor

Examples

Experimental program
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Effect test

Embodiment 1

[0042] Such as Figure 1-Figure 2 A multi-pulse solid rocket motor shown includes an outer electrode 1, an inner electrode 2, a solid propellant 3, an insulating layer 4, a motor case 5, a front head 6, a nozzle 7, a power supply 8, and a fixed inner electrode Seat 9, lead wire 10 and drug retaining plate 12, the inside of described engine housing 5 is hollow structure, and both ends are respectively detachably connected to front head 6 and nozzle 7 by threads or flanges; The ignition device can realize greater thrust while controlling the thrust of the engine in real time, and has broad application prospects in the field of multi-pulse rocket engines that need to generate high thrust.

[0043] Such as Figure 3-Figure 4 As shown, the external electrode 1 has 19 densely arranged honeycomb-shaped through holes 13, each of which is closely adjacent to each other, and the inner cavity of each of the honeycomb-shaped through-holes 13 serves as a combustion chamber. In this embodi...

Embodiment 2

[0063] as attached Figure 1-Figure 2 Another multi-pulse solid rocket motor shown includes an outer electrode 1, an inner electrode 2, a solid propellant 3, an insulating layer 4, a motor casing 5, a front head 6, a nozzle 7, a power supply 8, and an inner electrode The fixing seat 9, the wire 10 and the medicine retaining plate 12; the difference from the first embodiment is that: in this embodiment, the external electrode 1 has m densely arranged honeycomb through holes (m is greater than 19 and 7 is Integer with increasing arithmetic difference), after increasing the honeycomb through-holes, the thrust of this embodiment can be further improved to meet the greater thrust requirement.

Embodiment 3

[0065] as attached Figure 1-Figure 2 Another multi-pulse solid rocket motor shown includes an outer electrode 1, an inner electrode 2, a solid propellant 3, an insulating layer 4, a motor casing 5, a front head 6, a nozzle 7, a power supply 8, and an inner electrode The fixing seat 9, the wire 10 and the medicine retaining plate 12; the difference from the first embodiment is that in this embodiment, each of the honeycomb-shaped through holes 13 has a regular n-gonal cross-section (n is an integer greater than 6), when When the honeycomb-shaped through holes 13 have more surfaces, the contact area between the internal electrode 2 and the solid propellant 3 can be increased, which further helps to increase the initial combustion area of ​​the solid propellant 3 .

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Abstract

The invention discloses a multi-pulse solid rocket engine. The multi-pulse solid rocket engine comprises an engine shell, a front end socket and a spray pipe, and further comprises an outer electrode,an inner electrode, an electric control solid propellant and a power source, wherein the outer electrode is provided with a plurality of densely-arranged honeycomb-shaped through holes. an inner cavity of each honeycomb-shaped through hole serves as a combustion chamber, and the section of each honeycomb-shaped through hole is in a regular polygon shape; the inner electrode is provided with sections with unequal distances between the centers and the edges, and one end of the inner electrode is connected with an inner electrode fixing base; the space between the outer electrode and the inner electrode is filled with the electric control solid propellant; and one pole of the power source is connected with the outer electrode, and the other pole of the power source is connected with the inner electrode. According to the multi-pulse solid rocket engine, the outer electrode is designed to be of the structure with the multiple densely-arranged honeycomb-shaped through holes, the inner cavity of each honeycomb-shaped through hole serves as the combustion chamber, the honeycomb-shaped combustion chambers serve as the outer electrode to be integrally connected to one pole of the power source, the mass ratio of the engine is not remarkably reduced, meanwhile, large thrust can be obtained, the working characteristics of the electric control solid propellant can be met, and repeated starting and thrust adjustability of the multi-pulse solid rocket engine are achieved.

Description

technical field [0001] The invention relates to the technical field of solid rocket motors, in particular to a multi-pulse solid rocket motor. Background technique [0002] Solid rocket motors have the characteristics of simple structure, good economy, and high reliability. They are widely used in aerospace and national defense fields, and can provide power for missiles, space vehicles and other devices. Solid rocket motor is a rocket motor that uses solid propellant as fuel. Solid propellant is easy to store, has a high mass ratio, is convenient to use, and is easy to transport. However, compared with liquid rocket motor or solid-liquid hybrid rocket motor, solid rocket motor has the largest The disadvantages are: on the one hand, it is difficult to re-ignite the solid propellant after it is extinguished, and it is impossible to achieve repeated start; on the other hand, the solid propellant is not controlled during the combustion process, and it is impossible to use valves...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/08F02K9/95F02K9/34F02K9/26F02K9/80
CPCF02K9/08F02K9/26F02K9/34F02K9/80F02K9/95
Inventor 马立坤冯运超夏智勋段炼李洋何志成
Owner NAT UNIV OF DEFENSE TECH
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