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Pneumatic load processing method based on nacelle cabin structure design

A technology of aerodynamic load and structural design, applied in aircraft parts, ground equipment, transportation and packaging, etc., can solve the problems of difficult determination and implementation of static test plans, complex distribution of aerodynamic loads, and inconvenience in structural strength design of cabins, etc. Shorten the development cycle, facilitate aerodynamic load distribution, determine and implement the effect of simplification

Active Publication Date: 2019-02-15
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] Aircraft external pods bear aerodynamic loads in three directions, and the distribution of aerodynamic loads in each direction is relatively complicated, which is not convenient for the structural strength design of the cabin, and it is difficult to determine and implement the static test plan

Method used

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  • Pneumatic load processing method based on nacelle cabin structure design
  • Pneumatic load processing method based on nacelle cabin structure design

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Embodiment Construction

[0018] 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 discloses a pneumatic load processing method based on a nacelle cabin structure design, which comprises the following steps: judging whether the load peak points of the pneumatic loads under different working conditions are higher than a first preset peak value or not; judging whether the cabin structure at the load peak points of the pneumatic loads higher than the first preset peakvalue is continuous under different working conditions; carrying out leveling treatment of the load peak points of the pneumatic loads higher than the first preset peak value under different workingconditions; judging whether the load peak points of the pneumatic loads under different working conditions are lower than a second preset peak value; carrying out linear straightening treatment of theload peak points of the pneumatic loads lower than the second preset peak value under different working conditions. The pneumatic load processing method based on the nacelle cabin structure design can obtain a pneumatic distribution load which can better facilitate the nacelle cabin structure design, can simplify the determination and implementation of a static scheme, furthermore, can greatly shorten the development period of the nacelle structure .

Description

technical field [0001] The application belongs to the field of aircraft structure design, and in particular relates to an aerodynamic load processing method based on pod cabin structure design. Background technique [0002] Aircraft external pods bear aerodynamic loads in three directions, and the distribution of aerodynamic loads in each direction is relatively complex, which is not convenient for the structural strength design of the cabin, and it is difficult to determine and implement the static test program. Contents of the invention [0003] In order to solve at least one of the above technical problems, the present application provides an aerodynamic load processing method based on the pod cabin structure design. [0004] The application discloses a method for processing aerodynamic loads based on the pod cabin structure design, comprising the following steps: [0005] Step 1. Judging whether the load peak points of aerodynamic loads in different working conditions...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/00B64D47/00
CPCB64D47/00B64F5/00
Inventor 杨方
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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