Unlock instant, AI-driven research and patent intelligence for your innovation.

Method for Improving the Shock Resistance of the Orbital Control Engine of the Planetary Lander Propulsion System

An orbit-controlled engine and propulsion system technology, which is applied to the system of the spacecraft returning to the earth's atmosphere, the landing device of the spacecraft, and the aircraft, etc. Risk of insufficient impact capability, effect of preventing accidental discharge

Active Publication Date: 2021-08-06
SHANGHAI INST OF SPACE PROPULSION
View PDF3 Cites 0 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] For the valve with this structure, if the pilot electromagnetic self-locking valve of the driving air path is flushed open under the environment of large impact, the driving gas will be supplied to the front of the main valve spool, pushing the main valve spool open, which will cause the rail control engine propellant emissions, and even misfire failures

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
  • Method for Improving the Shock Resistance of the Orbital Control Engine of the Planetary Lander Propulsion System

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0057] (1) The planetary lander does not work at this stage, the launch stage is completed by the launch vehicle, and the orbit transfer process is completed by the transfer aircraft. The impact resistance of the orbital control engine is mainly guaranteed by the double guarantee of isolating propellant and isolating driving gas;

[0058] (2) The method of isolating the propellant of the oxidizer path: the primary electric explosion valve PV1 downstream of the oxidant storage tank 3 and the backup electric explosion valve PV2 downstream of the oxidant storage tank 3 are not detonated, and the propellant is guaranteed by the parallel normally closed electric explosion valve. Effective isolation in the oxidizer propellant tank;

[0059] (3) The method of isolating the propellant of the fuel path: the main portion electric explosion valve PV3 downstream of the fuel storage tank 4 and the backup electric explosion valve PV4 downstream of the fuel storage tank 4 are not detonated, a...

Embodiment 2

[0062] (1) At this stage, the planetary lander is preparing for the landing and descent mission, the filling of the propellant pipeline has been completed, and the oxidizer and fuel have been filled to the front end of the orbital control engine 5 valve. Step 2 and step 3 in the above-mentioned example 1 are now invalid, and only rely on the method of isolating the driving gas to improve the impact resistance of the orbital control engine 5;

[0063] (2) Method of isolating driving gas: as shown in step 4 in Example 1.

Embodiment 3

[0065] (1) At this stage, the planetary lander is performing landing and descending tasks, and the connection of the gas supply circuit has been completed, that is, the detonation of the main electric explosion valve PV5 downstream of the pressure reducing valve 2 and the backup electric explosion valve PV6 downstream of the pressure reducing valve 2 have been completed. . The landing process needs to face a large impact environment where the parachute and the heat-insulated cabin are separated. At this time, the propellant has been filled into the front-end pipeline of the 5-valve of the orbital control engine, and the driving gas is filled to the front-end of the 5-valve pilot valve of the orbital control engine. At this time, as described above Step 2, step 3 and step 4 in the above-mentioned example 1 are all invalid, and only rely on the pilot valve energization maintenance method to the electric gas valve to improve the impact resistance of the rail control engine 5;

[...

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

The invention provides a method for improving the anti-shock capability of the orbit control engine of the planetary lander propulsion system, comprising: dividing the flight process of the planetary lander propulsion system into three stages: launch and orbit transfer stage, pre-landing preparation stage and landing descent stage; launch and orbit transfer phases adopt dual measures of isolating propellant and isolating driving gas; the pre-landing preparation stage adopts the measure of isolating driving gas; landing and descending phase adopts the measure of powering up the pneumatic pilot valve of the orbit control engine and keeping it open or closed. The method for improving the impact resistance of the orbital control engine of the propulsion system in the present invention solves the problem that the aerodynamic pilot valve of the orbital control engine may be flushed open in the large impact environment of the entire flight mission in the propulsion system of extraterrestrial space landers such as Mars and asteroids. The long-term and reliable operation of the propulsion system is guaranteed.

Description

technical field [0001] The present invention relates to a method for improving the anti-shock ability of an orbital control engine, in particular, to a method for improving the anti-shock ability of an orbital control engine for a propulsion system of a planetary lander, and more specifically, for an orbital control engine used for a propulsion system of a planetary lander A method for improving the impact resistance of valves. Background technique [0002] The Earth's long-distance planetary exploration mission has become a hot spot in the deep space exploration of international aerospace powers. In recent decades, European and American aerospace powers represented by the United States have achieved multiple soft landings on Mars. The mission scope of subsequent long-distance planetary landing probes will gradually expand from Mars to Jupiter and asteroid detection, which has scientific value. to the planet. Taking Mars as an example, the international soft landing proces...

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): B64G1/24B64G1/62
CPCB64G1/24B64G1/62B64G1/245
Inventor 潘一力韩泉东王浩钟雪莹赵正井建方朱鹏程何壮睿曹伟刘锋李和军叶青
Owner SHANGHAI INST OF SPACE PROPULSION