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Air control pilot type magnetic self-locking bi-stable engine control valve structure

A technology for controlling valves and bistable states, applied to engine components, valve details, multi-way valves, etc., can solve problems such as high flow resistance, large power load, and low power consumption, and achieve obvious energy-saving advantages and reduce power consumption. power consumption, the effect of low power design goals

Active Publication Date: 2016-04-06
XIAN AEROSPACE PROPULSION INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The structure of the existing engine control solenoid valve is heavy and has high flow resistance. It needs continuous power supply during steady-state operation, and the power load is relatively large, which does not meet the design requirements of low power consumption.

Method used

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  • Air control pilot type magnetic self-locking bi-stable engine control valve structure
  • Air control pilot type magnetic self-locking bi-stable engine control valve structure

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Experimental program
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Embodiment Construction

[0028] of the present invention figure 1 It is an air-controlled pilot magnetic self-locking bistable engine control valve structure, which is the basic form of the present invention. It mainly consists of a nozzle 1, a main valve core 2, a main valve body 3, an air cylinder 4, a spring 5, a piston 6, and a retaining ring. 7. Nut 8, sealing ring 9, auxiliary valve body 10, magnetically conductive housing 15, coil 14, auxiliary valve core 11, auxiliary valve seat 12, permanent magnet 13, etc.

[0029] Pneumatic pilot structure is adopted, the main valve part is driven by a piston, and the piston control chamber communicates with the first annular groove of the auxiliary valve. The auxiliary valve adopts a two-position three-way solenoid valve with permanent magnet self-locking. By rationally designing parameters such as the specification of the permanent magnet, the gap between the magnetic poles, the stroke, and the area, the auxiliary valve can realize magnetic self-locking a...

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PUM

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Abstract

The invention discloses an air control pilot type magnetic self-locking bi-stable engine control valve structure. The air control pilot type magnetic self-locking bi-stable engine control valve structure comprises a main valve, an air cylinder and an auxiliary valve; the auxiliary valve is of a two-position three-way permanent magnet self-locking structure and can be self-locked through electromagnetic force generated by a permanent magnet, the opening movement and the closing movement can be carried out when pulse currents are guided into coils, the auxiliary valve controls gas to fill a piston cavity of the main valve or to be exhausted from the piston cavity of the main valve, and therefore a main valve core can be opened or closed under the effect of aerodynamic force of a piston and spring force. According to the air control pilot type magnetic self-locking bi-stable engine control valve structure, an engine control valve is light in weight and low in power consumption.

Description

technical field [0001] The invention relates to an air-controlled pilot magnetic self-locking bistable engine control valve structure, which can be used in liquid rocket engines with large thrust and long-range steady-state work requirements. The air-controlled pilot structure can effectively reduce the weight and flow resistance of the product , Bistable design can effectively reduce system power consumption. Background technique [0002] The 3000N engine is used as the main engine of a probe orbiter and ascender, providing thrust for the probe to complete tasks such as flight. According to the task characteristics of the 3000N engine, its control valve needs to meet the requirements of small pressure drop, low power consumption, light weight, single working time not less than 3000s, and be able to adapt to the space environment. [0003] The existing engine control solenoid valve has a heavy structure and high flow resistance. It needs continuous power supply in steady st...

Claims

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Application Information

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IPC IPC(8): F16K11/02F16K31/122F16K31/08
CPCF16K11/02F16K31/08F16K31/122
Inventor 王可立赫伟涛袁洪滨祁增强陈展蔡德慧
Owner XIAN AEROSPACE PROPULSION INST
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