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Normal temperature pressure supplementing system with redundancy function

A pressurization and redundancy technology, which is applied to jet propulsion devices, rocket engine devices, machines/engines, etc., can solve the problem of insufficient redundancy performance of the supplementary pressure system

Active Publication Date: 2014-03-26
BEIJING INST OF ASTRONAUTICAL SYST ENG +1
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AI Technical Summary

Problems solved by technology

[0004] The problem solved by the technology of the present invention is: to overcome the insufficient redundant performance of the existing pressure supplement system, and to provide a redundant technology of the pressure supplement system with high reliability

Method used

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  • Normal temperature pressure supplementing system with redundancy function

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Embodiment Construction

[0018] Specific embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0019] Such as figure 1 As shown, the present invention provides a normal temperature supplementary pressure system with redundant functions, including a gas cylinder group 1, a filter 2, a hydrogen tank supplementary pressure system and an oxygen tank supplementary pressure system; the oxygen tank supplementary pressure system includes a first oxygen tank Supplement pressure solenoid valve 3, second oxygen supplement pressure solenoid valve 4, first oxygen supplement pressure signal device 5, second oxygen supplement pressure signal device 6, first oxygen supplement pressure orifice plate 7, second oxygen supplement pressure hole Plate 8 and oxygen control system 9; the hydrogen tank pressure supplement system includes a first hydrogen supplement pressure solenoid valve 10, a second hydrogen supplement pressure solenoid valve 11, a hy...

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Abstract

A normal temperature pressure supplementing system with the redundancy function comprises a hydrogen box pressure supplementing system and an oxygen box pressure supplementing system. The oxygen box pressure supplementing system is composed of two solenoid valves, pressure signal devices, a hole plate and a corresponding guide pipe. The opening and closing of the solenoid valves are controlled through the pressure signal devices. The redundancy designing of the oxygen box pressure supplementing system is achieved by controlling the opening pressure and the closing pressure of the two pressure signal devices. The hydrogen box pressure supplementing system is composed of two solenoid valves, pressure signal devices, a hole plate, a control system and a corresponding guide pipe, and the redundancy designing of the hydrogen box pressure supplementing system is achieved by controlling the power supply time for the solenoid valves.

Description

technical field [0001] The invention relates to a redundant design scheme for a liquid rocket normal temperature supplementary pressure system. Background technique [0002] Usually, the pressurization system of the liquid rocket tank adopts the self-generated pressurization of the engine or the use of low-temperature helium for pressurization, but before the engine starts, the self-generated pressurized gas of the engine fails to pressurize the tank, and the cold helium pressurized gas fails to pressurize the tank. The pressurization efficiency of the heated low-temperature gas is low, so the liquid rocket is designed with a supplementary pressure system, which is used to pressurize the tank before the engine starts to ensure that the tank has enough pressure before the engine is ignited to ensure that the engine can work normally Ignition, in addition, in the transonic stage of rocket flight, it is necessary to increase the rigidity of the tank by adding pressure to the ta...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/50
Inventor 杜正刚张立强刘文川满满王海洲马方超吴姮李文斌张志广
Owner BEIJING INST OF ASTRONAUTICAL SYST ENG
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