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High-fusion aircraft afterbody

A technology of aircraft and trailing edge, which is applied in the field of aircraft exhaust rear body design, can solve the problems of the aircraft's backward, lateral and even forward stealth effects, etc., to reduce the interference of internal and external flow, reduce the structural weight, and reduce the dynamics. The effect of load strength

Pending Publication Date: 2021-03-09
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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AI Technical Summary

Problems solved by technology

[0003] The three generations of fighter jets generally adopt the method of exposing the nozzle of the engine, which leads to a significant decline in the stealth effect of the aircraft in the rear, side and even forward directions.

Method used

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Embodiment Construction

[0024] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the figures are exemplary, and are intended to explain the present application, and should not be construed as limiting the present application. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application. Embodiments of the present application will be described in detail below in conjunction with th...

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Abstract

The invention belongs to the field of design of exhaust afterbodies of airplanes, and particularly relates to a high-fusion aircraft afterbody. The afterbody comprises an afterbody outlet section withthe vertical projection in a D shape, and an inner expansion section is arranged on the rear side of an engine exhaust nozzle; an outlet upper expansion edge is arranged above the rear side of the inner expansion section, the horizontal projection of the outlet upper expansion edge is in an M shape, the outlet upper expansion edge is provided with an outlet upper expansion edge rear edge, and thehorizontal projection of the outlet upper expansion edge rear edge is parallel to the horizontal projection of the fuselage rear edge; an outlet lower expansion edge is arranged below the rear side of the inner expansion section, the length of the outlet lower expansion edge is larger than that of the outlet upper expansion edge, the horizontal projection of the outlet lower expansion edge is W-shaped, and the outlet lower expansion edge is provided with a cusp rear edge; and side wall baffles are arranged on the two sides of the outlet lower expansion edge. According to the high-fusion aircraft afterbody, high stealth and high fusion are both considered, the backward and lateral stealth characteristics of an aircraft are guaranteed, the dynamic load strength of the afterbody is reduced,the structural weight of the aircraft is reduced, and internal and external flow interference is weakened.

Description

technical field [0001] The application belongs to the field of aircraft exhaust rear body design, in particular to a high fusion aircraft rear body. Background technique [0002] Modern unmanned fighter jets have higher and higher requirements for stealth effects, and the infrared radiation of the exhaust system of the aero-engine and the tail jet account for an important part of the infrared radiation of the aircraft, which restricts the stealth index of the aircraft, which is directly related to the survival of combat aircraft force. Therefore, it is essential to obtain a high-integration and high-stealth rear body export in the design of future combat aircraft. [0003] The third-generation fighter jets generally adopt the method of exposing the engine nozzle, which leads to a significant decline in the aircraft's rearward, lateral and even forward stealth effects. The fourth-generation fighter jets use shading technology to reduce infrared radiation. For example, the F...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D33/04
CPCB64D33/04
Inventor 刘方良孙超詹光朱宇刘晓冬
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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