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Fairing design method

A design method and fairing technology, applied in the field of fairing design and aircraft fairing design, can solve problems such as aircraft stealth performance damage

Active Publication Date: 2021-04-16
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Therefore, when the arresting hook protrudes from the fuselage, it will cause serious damage to the stealth performance of the aircraft, and it must be designed with a fairing

Method used

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Embodiment Construction

[0038] In order to make the objectives, technical solutions and advantages of the implementation of the application clearer, the technical solutions in the implementation modes of the application will be described in more detail below with reference to the drawings in the implementation modes 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 present 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 implementation manners in this application, all other implementation manners obtained by persons of ordinary skill in the art without creative efforts fall within the scope of protection of this application. Embodiments of the pr...

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Abstract

The invention belongs to the technical field of aircraft fairing design, and particularly relates to a fairing design method. The method comprises the following steps: S1, determining an integral frame of a fairing of equipment extending out of a machine body, setting a plurality of transition points on the fairing to divide the fairing into a plurality of areas, and determining a transition curved surface transition mode between the areas and a curved surface transition mode between the areas on the two sides and the machine body; s2, taking the transition point coordinate as a variable, taking the condition that the fairing can accommodate the equipment as a constraint condition, taking the curved surface smoothness of the fairing as an optimization target, and carrying out variable calculation to obtain a transition point coordinate value; and S3, generating a fairing according to the transition point coordinate value and a preset curved surface transition mode. Fusion of the fairing and the peripheral curved surface can be well achieved, and on the premise that the space requirement of the device is met, pneumatic and invisible appearance integrated design is conducted on the appearance of the fairing.

Description

technical field [0001] The application belongs to the technical field of aircraft fairing design, and in particular relates to a method for designing a fairing. Background technique [0002] In the process of stealth aircraft design, not only the shape of the strong scattering source parts of the whole aircraft must be strictly controlled, but also the outer surface of the aircraft should be as smooth and "clean" as possible to minimize the scattering sources of the aircraft. Therefore, when the arresting hook protrudes from the fuselage, it will cause serious damage to the stealth performance of the aircraft, and it must be designed with a fairing. The shape design of the fairing needs to solve the following four problems: [0003] 1) The RCS scattering of the fairing itself is controllable; [0004] 2) The RCS coupling scattering between the fairing and surrounding components is controllable; [0005] 3) The fairing needs to comprehensively consider the requirements of ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/17G06F111/04
CPCY02T90/00
Inventor 李君哲解引花赵洪波
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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