Space propulsion system with propellant and pressurized gas discharge

A technology of pressurized gas and exhaust device, which is applied to the propulsion system device of space navigation vehicle, etc., can solve the problems of rupture of ruptured diaphragm, inability to completely ensure that the residual propellant does not leak, and low reliability, etc., and achieve the effect of reliable isolation.

Active Publication Date: 2016-12-14
SHANGHAI INST OF SPACE PROPULSION
View PDF0 Cites 2 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The current method is to use two electric explosion valves to realize the opening of the propellant and pressurized gas discharge system, without the design of the closing function, it is impossible to completely ensure that the residual propellant does not leak when the aircraft lands
At the same time, the reliability of the currently adopted rupture diaphragm isolation gas-liquid circuit scheme is not high, and the rupture diaphragm may rupture early due to the influence of the system working process

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
  • Space propulsion system with propellant and pressurized gas discharge

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0013] The invention will be described in more detail hereinafter with reference to the accompanying drawings showing embodiments of the invention. However, this invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In these drawings, the size and relative sizes of layers and regions may be exaggerated for clarity.

[0014] Now, the present invention will be further explained by describing preferred specific embodiments according to the present invention in detail.

[0015] Such as figure 1 As shown, the space propulsion system with pressurized gas and propellant discharge device of the embodiment of the present invention includes a high-pressure gas cylinder 1, a gas circuit electric explosion valve 2, a pressure reducing valve 3, a g...

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

A space propulsion system with a propellant and a pressurized gas discharge device of the present invention includes a high-pressure gas cylinder, a gas circuit electric explosion valve, a pressure reducing valve, a gas circuit self-locking valve, a liquid circuit electric explosion valve, and a propellant storage tank. , Liquid circuit self-locking valve, discharge port; two high-pressure gas cylinders and propellant storage tanks are connected by pipelines, and gas circuit gas circuit electric explosion valves and pressure reducing valves are arranged in sequence on the pipelines; On the pipeline between the pressure reducing valve and the propellant storage tank; the two liquid circuit electric explosion valves are respectively connected to the two propellant storage tanks, which play the role of pipeline blowing and pressurized gas discharge; The lock valve is connected to the outlet of the two storage tanks. After the first operation, the propellant and pressurized gas are discharged, and the second operation closes the discharge system. The invention realizes that the discharge process can be controlled, and the self-locking valve is closed to stop or restart the discharge process after the discharge process is started; and the system is closed after the discharge process is completed.

Description

technical field [0001] The invention relates to the technical field of spacecraft propulsion, in particular to a space propulsion system with a propellant and pressurized gas discharge device. Background technique [0002] In order to achieve a safe landing at the end of the aircraft's life, it is required that pressurized gas and propellant be exhausted from the inside of the system at a specific time and altitude before landing. [0003] The method currently adopted is to use two electric explosion valves to realize the opening of the propellant and pressurized gas discharge system. There is no closing function design, and it is impossible to completely ensure that the residual propellant does not leak when the aircraft lands. At the same time, the reliability of the currently adopted solution for isolating the gas-liquid circuit by the rupture diaphragm is not high, and the rupture diaphragm may rupture in advance due to the influence of the working process of the system....

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
Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/40
Inventor 宣晓萍刘建盈郭鸿华赵京顾帅华
Owner SHANGHAI INST OF SPACE PROPULSION
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