Self-pressurization supply system based on regenerative cooling

A technology of supply system and regenerative cooling, applied in the field of aerospace propulsion system, can solve the problem of consuming energy resources of missiles/satellites, and achieve the effect of reducing quality and complexity, saving costs and reducing costs

Active Publication Date: 2016-09-28
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The commonly used electric heating method has a simple structure and adjustable heating power, but the disadvantage is that it needs to consume precious electric energy resources on the rocket / satellite

Method used

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  • Self-pressurization supply system based on regenerative cooling
  • Self-pressurization supply system based on regenerative cooling
  • Self-pressurization supply system based on regenerative cooling

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Embodiment Construction

[0025] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, but not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0026] The "self-pressurized supply system based on regenerative cooling" of the present invention includes: a safety valve 1, a storage tank 2, a filling pipeline 3, a filling valve 4, a one-way valve 5, a cooling channel 6, a liquid collection chamber 7, Main supply line 8 , coolant line 8 a , combustion agent line 8 b , main valve 9 , booster line 10 , combustion chamber 11 , propellant 12 .

[0027] In this embodiment, nitrous oxi...

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Abstract

The invention belongs to the technical field of spacecraft systems and is mainly applied to liquid propulsion systems or solid-liquid mixing propulsion systems adopting high-saturated vapor pressure propulsive agents. In order to solve the problems that the temperature of propulsive agents and the pressure in a storage box are seriously reduced in the working process of a self-pressurization supply system, a self-pressurization scheme based on regenerative cooling is provided. The self-pressurization supply system is composed of a safety valve, a storage box, a filling pipeline, a filling valve, a one-way valve, a cooling channel, a liquid accumulating cavity, a main supply pipeline, a coolant pipeline, a burning agent pipeline, a main valve, a pressurization pipeline and the like. Propulsive agents cool the wall of a combustor and acquire heat at the same time. The propulsive agents subjected to heat exchange and vaporization return to the storage box to pressurize the storage box. According to the self-pressurization supply system based on regenerative cooling, the pressure intensity of the storage box can be basically maintained to be stable before the liquid propulsive agents in the storage box are completely discharged, and accordingly the effect that the thrust is basically stable is ensured.

Description

technical field [0001] The invention belongs to the technical field of aerospace propulsion systems, in particular to a self-pressurized supply system based on regenerative cooling. Background technique [0002] The chemical rocket propulsion systems currently in use are: liquid propulsion systems, solid propulsion systems, gas propulsion systems and solid-liquid hybrid propulsion systems. Among the above types of propulsion systems, liquid propulsion systems, solid-liquid propulsion systems and gas propulsion systems all require propellant booster delivery devices. Such booster devices are divided into two categories: pump pressure type and extrusion type. The main advantage of the pumped system is that the propellant tank does not have to withstand high pressure, and a lighter mass tank can be used, but due to the increased complexity and cost of the system due to the use of a turbo pump, it is usually only used for large-scale transport with high thrust and long life. Ro...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/50F02K9/64
CPCF02K9/50F02K9/64
Inventor 胡小平王正凯于萌
Owner NAT UNIV OF DEFENSE TECH
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