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Solenoid pilot air control two position three way valve

A two-position three-way valve and pilot technology, applied in multi-way valves, valve details, valve devices, etc., can solve the problems of lack of discharge function, slow response, heavy weight, etc., and achieve the elimination of tumbling phenomenon, fast response, and high pressure Effect

Active Publication Date: 2017-10-13
XIAN AEROSPACE PROPULSION INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Existing valves have the disadvantages of large size, heavy weight, slow response and lack of discharge function

Method used

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  • Solenoid pilot air control two position three way valve
  • Solenoid pilot air control two position three way valve
  • Solenoid pilot air control two position three way valve

Examples

Experimental program
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Embodiment Construction

[0034] In order to realize multiple start and shutdown of the engine, reduce the mass of the engine, and improve the response speed of the engine, a new control valve with shutdown discharge function must be designed. The valve needs to have the main performance of being able to work repeatedly, with a working pressure range of 0-11MPa, a working flow range of 0-1.5kg / s, a flow resistance of less than 0.3MPa, a control air pressure of 7-12MPa, and a response time of less than 50ms.

[0035] like figure 1 The electromagnetic pilot air-controlled two-position three-way valve structure shown is a preferred embodiment of the present invention. It consists of a plug 1, a main spring 2, a main valve body 3, a main valve core 4, a discharge valve core 5, a dynamic sealing ring 6, Inflator 7, auxiliary valve seat 8, auxiliary valve core 9, auxiliary valve spring 10, electromagnetic assembly 11 and sealing ring 12 etc. are composed.

[0036] The implementation example of applying the ...

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Abstract

The invention discloses an electromagnetic pilot pneumatic-control two-position three-way valve. The valve comprises a secondary valve, an air cylinder (7) and a main valve, wherein the secondary valve is a two-position three-way electromagnetic valve and comprises a secondary valve body, a secondary valve seat (8), a secondary valve core (9), an electromagnetic component (11) and a secondary valve spring (10), wherein the secondary valve spring (10), the secondary valve core (9) and the secondary valve seat (8) are sequentially arranged from top to bottom in the secondary valve body; the secondary valve spring (10) is in a compression state; one end of the air cylinder (7) is an air inlet (16); the main valve is a two-position three-way valve and comprises a main valve body (3), a main valve rod and a chamber, wherein the main valve rod and the chamber are arranged in the main valve body; a piston (31), an exhausting valve core (5) and a main valve core (5) sequentially sleeves from right to left on the main valve rod; the piston can perform reciprocating motion in the chamber. The electromagnetic pilot pneumatic-control two-position three-way valve disclosed by the invention has the advantages of high pressure, large flow rate, small size, rapid response and the like, and has the effects of realizing rapid start and stop of an engine and reducing the after-working impulse of the engine when the engine is shut down.

Description

technical field [0001] The invention relates to an electromagnetic pilot air-controlled two-position three-way valve structure, which is suitable for an upper-stage engine propulsion system with large flow, high pressure, fast response and multiple starts. The valve can be used in the propulsion system of the multi-satellite launching common upper stage and strategic missile multi-warhead guided upper stage. Background technique [0002] In order to enable our country's rockets to have multi-satellite launch capabilities, meet the multi-satellite deployment in different orbits, and adapt to launch missions in various orbits, it is necessary to develop a low-cost, high-performance multiple-start upper stage. [0003] The XX-XX engine is an upper-stage propulsion system used in the second-generation navigation project for one-rocket multi-satellite launch. Existing valves suffer from the disadvantages of bulkiness, weight, slow response, and lack of discharge function. Cont...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F16K11/044F16K31/06
CPCF16K11/044F16K31/0675
Inventor 赵文华袁洪滨胡攀董万峰吴晓东李海
Owner XIAN AEROSPACE PROPULSION INST
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