A shut-off valve, engine and rocket vehicle

A technology of stop valve and spool, applied in the field of aircraft, can solve problems such as difficult flow control effectively, and achieve the effects of improving reliability, facilitating auxiliary adjustment, and simple structure

Active Publication Date: 2021-07-09
BEIJING XINGJI RONGYAO SPACE TECH CO LTD +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Therefore, the technical problem to be solved by the present invention is to overcome the defect that the common cut-off valve in the prior art is difficult to effectively control the flow in different working stages, thereby providing a cut-off valve and engine and rocket system

Method used

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  • A shut-off valve, engine and rocket vehicle

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Embodiment Construction

[0050] The technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Apparently, the described embodiments are some of the embodiments of the present invention, but not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0051] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" etc. The indicated orientation or positional relationship is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, ...

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Abstract

The shut-off valve, the engine and the rocket vehicle provided by the present invention include: a material passage, which is suitable for conveying feed liquid; The valve core and the second valve core; the first valve core has a built-in first elastic member, which abuts against the inner wall of the feeding passage under the action of the first elastic member, and at least partially closes the flow limiting state of the feeding passage, and is connected with the The inner wall of the feeding channel is arranged at intervals, and the communication state of the feeding channel is opened; the second valve core is arranged adjacent to the first valve core, and a second elastic member is arranged on it, and the second valve core has a function under the action of the second elastic member. It abuts against the first spool and completely closes the closed state of the material passage, and the open state of partially opening the material passage; the control assembly connects the first spool and the second spool, and is suitable for adjusting the first spool and the second spool. The state of the second spool changes.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to a shut-off valve, an engine and a rocket system. Background technique [0002] A liquid rocket is a rocket powered by a liquid rocket engine. The chemical propellant used by the liquid rocket engine is composed of fuel and oxidant, which need to be fed into the thrust chamber at the same time during work. [0003] Nowadays, the opening and closing of fuel and oxidant into the thrust chamber is usually controlled by a cut-off valve, but liquid rocket engines have high requirements for valve response time and action sensitivity, and need to control the flow of fuel and oxidant according to different stages. Conventional shut-off valves in the prior art are difficult to implement. Contents of the invention [0004] Therefore, the technical problem to be solved by the present invention is to overcome the defect that the common cut-off valve in the prior art is difficult to effect...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F16K1/44F16K1/52F16K31/122F02K9/58
CPCF02K9/58F16K1/443F16K1/52F16K31/122
Inventor 刘兴睿张玺唐文熊宴斌
Owner BEIJING XINGJI RONGYAO SPACE TECH CO LTD
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