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Two-dimensional thrust vectoring nozzle outer cover structure and design method thereof

A technology of vectoring nozzles and housings, which is applied to jet propulsion devices, machines/engines, etc.

Active Publication Date: 2021-07-13
AECC SHENYANG ENGINE RES INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] Existing binary vector nozzle housings cannot meet the above requirements well

Method used

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  • Two-dimensional thrust vectoring nozzle outer cover structure and design method thereof
  • Two-dimensional thrust vectoring nozzle outer cover structure and design method thereof

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Embodiment Construction

[0042] In order to make the technical solutions and advantages of the present application, the technical solutions of the present application will be further clarified, and the specific embodiments described herein will be appreciated that the specific embodiments described herein are only part of the present application. EXAMPLES, which is intended to explain the present application, not the limitation of the present application. It should be noted that in order to facilitate the description, only the portion related to the present application is shown, and other related portions can be referred to usual design, in the case of unlafred, the techniques in the present application and the embodiments Features can be combined with each other to obtain a new embodiment.

[0043] Moreover, unless otherwise defined, the technical terms or scientific terms used in this application description should be generally meanings that the art will appreciate the general artper of the present appl...

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Abstract

The invention belongs to the technical field of two-dimensional thrust vectoring nozzle outer cover design, and particularly relates to a two-dimensional thrust vectoring nozzle outer cover structure. The two-dimensional thrust vectoring nozzle outer cover structure comprises a rear-section annular cover, a middle-section annular cover and a front-section annular cover, wherein the rear-section annular cover sleeves the periphery of a two-dimensional thrust vectoring nozzle, the tail end is connected with the outlet end of the expanding section of the two-dimensional thrust vectoring nozzle, and a set angle alpha is formed between the tail end and the expanding section. The middle-section annular cover sleeves the periphery of the two-dimensional thrust vectoring nozzle, the tail end of the middle-section annular cover is rotationally connected with the front end of the rear-section annular cover, and the inner side of the middle-section annular cover is rotationally connected with the expanding section. The front-section annular cover sleeves the periphery of the two-dimensional thrust vectoring nozzle, the tail end of the front-section annular cover is partially overlapped with the front end of the middle-section annular cover and is in sliding connection with the middle-section annular cover, and the inner side of the front-section annular cover is rotationally connected with the round-to-square section of the two-dimensional thrust vectoring nozzle. In addition, the invention relates to a design method of the two-dimensional thrust vectoring nozzle outer cover structure.

Description

Technical field [0001] The present application belongs to the field of binary vector nozzle cover design technology, and specific to a binary vector nozzle cover structure and its design method thereof. Background technique [0002] Avio engine binary vector nozzle can provide vector thrust, and has good stealth performance, which is more and more widely used. [0003] The engine binary vector nozzle mainly includes a circular transcription section, the convergence segment hinged with the rounded square outlet end, and the expansion segment of the outlet end of the convergence segment, wherein the convergence segment, the expansion segment can be expanded in three-dimensional space. Its deflection movement. [0004] In order to protect the binary vector nozzle and its engine internal components do not directly suffer from external force, rectification of the outside, reduce the aircraft rear body resistance, ensure stealth performance, need to design the corresponding outer cover...

Claims

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Application Information

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IPC IPC(8): F02K1/82F02K1/78
CPCF02K1/82F02K1/78
Inventor 马宏宇程荣辉任利锋曹茂国叶留增杜寅威牛春岩王伟王瑞祥
Owner AECC SHENYANG ENGINE RES INST
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