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Engine jet pipe with throat diameter adjustable

A technology of engine nozzles and nozzles, which can be applied to machines/engines, rocket engine devices, mechanical equipment, etc., and can solve problems such as complex device structures.

Active Publication Date: 2015-03-25
江西洪都航空工业股份有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Some people have proposed a sliding disk plugging device or a pintle type structure, but this type of device has a complex structure and requires a servo mechanism to actuate

Method used

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  • Engine jet pipe with throat diameter adjustable
  • Engine jet pipe with throat diameter adjustable
  • Engine jet pipe with throat diameter adjustable

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Embodiment Construction

[0017] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments. The following examples are only used to illustrate the present invention, and are not intended to limit the protection scope of the present invention.

[0018] An engine nozzle with adjustable throat diameter of the present invention comprises a nozzle housing 1, a plug cone 4, a nozzle convergence section 2, a nozzle diffusion section 3, an energy storage mechanism 5 and a mechanical locking device 6, The plug cone 4 is fixed on the nozzle convergent section 2, the nozzle diffuser section 3 is movable at the throat of the nozzle, the energy storage mechanism 5 and the mechanical locking device 6 are installed on the nozzle housing 1, and the nozzle convergent section 2 During the working process of the engine, it can move along the axial direction of the engine under the action of the energy storage mechanism, thereby realizing the change of the...

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Abstract

The invention discloses an engine jet pipe with the throat diameter adjustable. The engine jet pipe comprises a jet pipe casing, a plug cone, a jet pipe convergence section, a jet pipe diffusion section, an energy storage mechanism and a mechanical locking device. The plug cone is fixed to the jet pipe convergence section, the jet pipe divergence section is movably arranged at the throat portion of the jet pipe, the energy storage mechanism and the mechanical locking device are arranged on the jet pipe casing, and the jet pipe convergence section can move in the axial direction of an engine under the effect of the energy storage mechanism in the working process of the engine, so that the relative position change of the plug cone and the throat portion of the jet pipe is achieved, and one-time change of the throat diameter of the jet pipe is finally achieved. The relative position change of the plug cone and the throat portion of the jet pipe is achieved through the energy storage mechanism in the engine jet pipe with the throat diameter adjustable, the diameter of the throat portion during work of the engine can be changed, and the high thrust ratio of the engine can be achieved.

Description

technical field [0001] The invention relates to an engine nozzle, in particular to an engine nozzle with an adjustable throat diameter. Background technique [0002] The throat diameter of the conventional single-chamber dual-thrust solid rocket motor cannot be adjusted, and the high thrust ratio of the two-stage motor cannot be realized. In order to achieve the requirement of high thrust ratio, the throat diameter needs to be adjusted. Someone proposes a sliding plate throat blocking device or a pintle type structure, but this type of device has a complicated structure and needs a servo mechanism to actuate. [0003] Therefore, it is necessary to provide a new technical solution to solve the above problems. Contents of the invention [0004] The technical problem to be solved by the present invention is to provide an engine nozzle with adjustable throat diameter, so that the thrust ratio of the two stages of the single-chamber double-thrust engine can be increased to me...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/97
Inventor 王武张效义尹志龙赵胜海王啸雄张林邓波袁晓昱江海涛孙子杰马少杰余文锋
Owner 江西洪都航空工业股份有限公司
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