Sability analysis method for composite integral air inlet channel

A technology of composite materials and analysis methods, which is applied in the field of overall air inlet stability analysis of composite materials, can solve the problems of large errors in air inlet stability analysis and design risks, and achieves the effect of small errors and large improvement errors.

Pending Publication Date: 2021-11-26
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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Problems solved by technology

Therefore, using the existing engineering calculation method to analyze the stability of the intake port has a large error, and there is a design risk

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  • Sability analysis method for composite integral air inlet channel
  • Sability analysis method for composite integral air inlet channel
  • Sability analysis method for composite integral air inlet channel

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Embodiment Construction

[0028] 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 aircraft design strength, and particularly relates to a stability analysis method for a composite integral air inlet channel. The method comprises: 1, constructing a finite element model of the composite material integral air inlet channel, wherein the finite element model comprises an air inlet channel model and a force bearing component model connected with the air inlet channel; 2, determining analysis parameters of the finite element model; 3, determining a concerned part of the stability analysis of the composite material integral air inlet channel through linear buckling analysis; and 4, determining the instability critical load of the concerned part according to the load-strain relation obtained by the nonlinear analysis. According to the method, the defect that a traditional engineering method based on the linear theory is large in error can be effectively overcome, the nonlinear mechanical behavior of structural instability of the composite material integral air inlet channel is truly simulated, the structural instability part and the structural instability critical load are accurately determined, the error is small, and the requirement of engineering application can be met.

Description

technical field [0001] The application belongs to the field of aircraft design strength, and in particular relates to a method for analyzing the stability of a composite material integral air inlet. Background technique [0002] In order to meet the high stealth requirements and reduce the radar scattering area of ​​the new generation of military aircraft, the air intake is usually embedded in the fuselage, and the profile is relatively complicated; in order to reduce the connection relationship, the overall thick skin and thin reinforcement structure of composite materials is usually used. As a complex curvature surface structure, the stability of the intake duct under the action of out-of-plane loads (pressure or suction) is very prominent. It is one of the most important basic research directions in the field of modern mechanics research, and no satisfactory results have been obtained so far. . [0003] At present, the engineering calculation methods for the stability of...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/17G06F30/23B64F5/00G06F113/14G06F113/26G06F119/14
CPCG06F30/15G06F30/17G06F30/23B64F5/00G06F2113/14G06F2113/26G06F2119/14
Inventor 杜玉梅于鹏周翌勋何刚尚晋
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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