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Supercharging device and supercharging method for low-temperature rocket ground redundancy

A technology of pressurization device and rocket, which is applied to projectiles, self-propelled bombs, offensive equipment, etc., can solve problems such as inability to pressurize, and achieve the effect of improving reliability, rapid and high-precision pressurization

Active Publication Date: 2015-07-22
BEIJING INST OF SPACE LAUNCH TECH +1
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AI Technical Summary

Problems solved by technology

[0003] Aiming at the deficiencies in the above-mentioned prior art, the present invention provides a ground redundant pressurization method for low-temperature rockets that solves the problems of inability to pressurize and non-stop pressurization

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  • Supercharging device and supercharging method for low-temperature rocket ground redundancy

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Embodiment Construction

[0040] The present invention is described in detail below with reference to accompanying drawing and embodiment:

[0041] attached figure 1 It can be seen that a ground redundant pressurization device for cryogenic rockets,

[0042] Including pilot-operated two-position two-way normally closed solenoid valve, two-position three-way solenoid valve, manual shut-off valve and throttling orifice arranged on the intake pipeline of the low-temperature propellant pressurized gas source;

[0043] The low-temperature propellant pressurized gas source intake pipeline is connected to the input end of the first throttle orifice 1, the input of the second throttle orifice 2, and the input of the third throttle orifice 3 that are connected in parallel. ;

[0044] The output end of the first throttle orifice 1 is connected with the input end of the first manual stop valve 4;

[0045] The output end of the second throttle orifice 2 is connected with the input end of the third pilot-operate...

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Abstract

The invention relates to a supercharging device and a supercharging method for low-temperature rocket ground redundancy. The device comprises pilot-operated type two-bit two-way normally closed solenoid valves, a two-bit three-way solenoid valve, manual stop valves and restriction orifices arranged on a low-temperature propellent supercharging gas source gas inlet pipeline; the second pilot-operated type two-bit two-way normally closed solenoid valve and the third pilot-operated type two-bit two-way normally closed solenoid valve are started, and tank pressurization is rapidly conducted by gas which passes through the second restriction orifice and the third restriction orifice. According to the supercharging device for the low-temperature rocket ground redundancy, the single-point problem of a low-temperature propellent rocket ground electric supercharging gas circuit is solved, it is guaranteed that a target requirement of narrow window launching is met, four independent solenoid valves are adopted to achieve a series-parallel connection redundant backup, by means of the restriction orifice with different hole diameters, rapid and high-precision supercharging before launching is guaranteed, and the reliability of the rocket launching is improved.

Description

technical field [0001] The invention relates to a low-temperature rocket launch control device, in particular to a low-temperature rocket ground redundant supercharging device. Background technique [0002] At home and abroad, the ground pressurized air supply for low-temperature propellant rockets usually uses a single solenoid valve pressurized air circuit to supply air, which generally lasts until -4 minutes before launch, and is a single point without redundancy, and its reliability is relatively low. Faults will directly affect the progress of the launch process, and even lead to the termination of the launch process, failing to achieve the goal of "narrow window" launch in the mission. Therefore, it is necessary to study a ground redundant pressurization method to deal with possible failures during ground pressurization. Contents of the invention [0003] Aiming at the deficiencies in the above-mentioned prior art, the present invention provides a ground redundant p...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F42B15/01
Inventor 顾乡程帆刘健代春涛谢建明刘茜孙贺刘聪聪罗强周绍志文小平丰裕兵李春林
Owner BEIJING INST OF SPACE LAUNCH TECH
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