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A Nozzleless Solid Rocket Motor

A solid rocket and engine technology, which is applied in rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of limited exit velocity of combustion products, avoid a large amount of energy loss, reduce structural quality, and improve specific impulse performance Effect

Active Publication Date: 2021-11-05
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to provide a nozzleless solid rocket motor to solve the problem that the outlet velocity of the combustion product of the existing solid rocket motor is limited

Method used

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  • A Nozzleless Solid Rocket Motor
  • A Nozzleless Solid Rocket Motor
  • A Nozzleless Solid Rocket Motor

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Embodiment Construction

[0034] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0035] The invention discloses a nozzleless solid rocket motor, such as figure 1 and 2 As shown, it includes a shell 1, a propellant grain 3, a support tube 2, and an inner cavity electromagnetic field mechanism 6 and an inner cavity high-voltage thermoelectric mechanism 5 located on the inner wall of the support tube 2. The shell 1 is columnar, and the propellant grain 3 Filled in the inner cavity of the shell 1, a gas channel 4 is opened along the centerline of the propellant grain 3, the support tube 2 is cylindrical, the support tube 2 is sleeved in the gas channel 4, and is close to the outlet of the gas flow, the support tube 2 A plurality of inner cavity electromagnetic field mechanisms 6 and a plurality of inner cavity high-voltage thermoelectric mechanisms 5 are arranged at intervals in sequence on the inner wall, and the plurality ...

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Abstract

The invention discloses a nozzleless solid rocket motor, comprising: a shell, which is in the shape of a column, propellant grains filled in the inner cavity of the shell, a gas channel is opened along the central line, a support tube, which is in the shape of a tube, and is sleeved on the In the gas channel and close to the outlet of the gas flow, a plurality of inner cavity electromagnetic field mechanisms and a plurality of inner cavity high-voltage thermoelectric mechanisms are sequentially arranged on the inner wall, and the inner cavity electromagnetic field mechanisms and the inner cavity high-voltage thermoelectric mechanisms cooperate with each other for the gas to pass through. When supporting the gas channel in the inner cavity of the tube, a millivolt-level thermoelectric potential is generated due to the thermoelectric effect, and then a high-voltage thermoelectric potential is formed. The thermoelectric potential greatly accelerates the gas containing a large number of ionized products, and is discharged through the inner cavity of the supporting tube to propel the rocket. Operation; the invention cancels the nozzle structure of the conventional solid rocket motor, greatly reduces the structural quality of the motor, and reduces the probability of failure.

Description

technical field [0001] The invention belongs to the field of aerospace power, in particular to a nozzleless solid rocket motor. Background technique [0002] Solid Rocket Motor: A chemical rocket motor that uses solid propellants. Also known as solid propellant rocket motor. After the solid propellant is ignited, it burns in the combustion chamber, and the chemical energy is converted into heat energy to produce high temperature and high pressure combustion products. Combustion products flow through the nozzle, where they expand and accelerate, heat energy is converted into kinetic energy, and are discharged from the nozzle at high speed to generate thrust. [0003] Since the birth of the solid rocket motor, its basic structural form has always been "combustion chamber + Laval nozzle". The gas generated by the combustion of solid propellant is continuously accelerated in the nozzle and discharged from the engine, thereby generating thrust. In order to ensure high energy c...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/08F02K9/10F02K9/34F02K9/32F02K9/95
CPCF02K9/08F02K9/10F02K9/32F02K9/34F02K9/95
Inventor 吕翔刘佩进何国强陈剑
Owner NORTHWESTERN POLYTECHNICAL UNIV
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