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Solid-propellant rocket engine

A rocket engine and solid fuel technology, which is applied to rocket engine devices, machines/engines, mechanical equipment, etc., can solve problems such as low efficiency, easy nozzle blockage, insufficient fuel combustion, etc., to improve efficiency, improve combustion efficiency, To ensure that the effect of not being blocked

Inactive Publication Date: 2013-05-22
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] However, the currently commonly used solid rocket motors have defects such as insufficient fuel combustion, easy nozzle clogging, and low efficiency.

Method used

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  • Solid-propellant rocket engine

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Embodiment Construction

[0026] The present invention will be further described in detail below in conjunction with the accompanying drawings, so that those skilled in the art can implement it with reference to the description.

[0027] Such as figure 1 As shown, the solid fuel rocket motor of the present invention includes: a casing 3; propellant, which is placed in the casing, and includes a plurality of fuel pellets; the propellant is interposed between the casing 3 and the pellets In the area between the supports 2 , in other words, between the casing 3 and the pellet supports 2 , a plurality of fuel pellets are placed. The nozzle group 1 is combined with the housing 3 and includes several independent nozzles distributed in a ring around an axially symmetrical central body with a central axis. The gas produced by the burning of the pellets is ejected through the nozzle.

[0028] a pellet support 2, which is a hollow structure, and is disposed in the middle of the casing so as to confine the comb...

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Abstract

The invention relates to a solid-propellant rocket engine, which comprises a shell, a propellant arranged in the shell and comprising a plurality of fuel pellets, an injector set combined with the shell and comprising a plurality of independent nozzles, and a hollow fuel pellet supporting body arranged in the center of the shell to limit the fuel pellets in a combustion chamber between the fuel pellet supporting body and the shell, wherein the nozzles are distributed circularly around an axially symmetrical center body with a center axis, and the surface of the fuel pellet supporting body is provided with spray orifice bodies penetrating through the hollow inside of the fuel pellet supporting body to allow gas generated by combusting the fuel pellets to pass through the spray orifice bodies to flow to the nozzles and prevent the fuel pellets from being discharged through the nozzle set or blocking the nozzle set.

Description

technical field [0001] The invention relates to a rocket motor, in particular to a solid fuel rocket motor. Background technique [0002] The propulsion system is a key subsystem of the aerospace system, and the main component of the propulsion system to generate power is the engine. The overall design purpose of the engine is to enable the spacecraft to obtain the best overall performance while ensuring the highest possible quality indicators. [0003] However, the currently commonly used solid rocket motors have defects such as insufficient fuel combustion, easy nozzle blockage, and low efficiency. Contents of the invention [0004] In order to overcome the defects of the prior art, according to one embodiment of the invention, the invention provides a solid fuel rocket motor, comprising: [0005] case; [0006] a propellant disposed within the casing and comprising a plurality of fuel pellets; [0007] a group of nozzles combined with the housing and comprising a pl...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/32
Inventor 张建华
Owner BEIHANG UNIV