An analytical method for thermal buckling critical temperature of aircraft panels

An aircraft panel and critical temperature technology, applied in the field of aircraft manufacturing, can solve the problems of increasing complexity of thermal buckling behavior, destroying structural stability, complex thermal physical properties and mechanical properties, etc., and achieves the effect of simplifying the model and simple processing method.

Active Publication Date: 2022-07-19
CHINA AIRPLANT STRENGTH RES INST
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Problems solved by technology

[0005] On the one hand, the thermal buckling behavior is sudden, which seriously damages the stability of the structure; on the other hand, in the high temperature / low temperature environment, the thermal physical properties and mechanical properties of the material itself become complex and have obvious nonlinearity, which makes the thermal buckling behavior the increased complexity of

Method used

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  • An analytical method for thermal buckling critical temperature of aircraft panels
  • An analytical method for thermal buckling critical temperature of aircraft panels
  • An analytical method for thermal buckling critical temperature of aircraft panels

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Embodiment 1

[0052] This embodiment is a method for analyzing the thermal buckling critical temperature of an aircraft panel, such as figure 1 shown, including the following steps:

[0053] S1. Overall modeling and numerical analysis of aircraft wall panels, including the following steps:

[0054] S1-1. Select the mixed-structure aircraft wall panel including composite material laminate and aluminum alloy plate reinforcing rib as the test piece, and establish the geometric model of the test piece, such as figure 2 As shown, the composite material laminate is 2520mm long, 300mm wide, and 3mm thick, which is used to simulate the skin of the aircraft panel. The laminate plate and the aluminum alloy plate reinforcing rib are connected by rivets.

[0055] S1-2. In the calculation process, the material properties of composite material laminates and aluminum alloy plate reinforcing ribs are assigned. The material properties of composite material laminates include: elastic modulus, Poisson's ra...

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Abstract

The invention provides a method for analyzing the thermal buckling critical temperature of an aircraft wall plate, which relates to the technical field of aircraft manufacturing. It includes the following steps: S1, the overall modeling and numerical analysis of the aircraft panel; S2, the thermal buckling deformation test of the aircraft panel; S3, the analysis of the thermal buckling deformation test result of the aircraft panel; S4, the analysis of the thermal buckling of the aircraft panel by the south-well method Buckling critical temperature; S5, verification of the results of thermal buckling critical temperature of aircraft panel. The present invention solves the problem that the thermal buckling behavior weakens the bearing capacity of the aircraft structure and poses a serious threat to the structural integrity and even the safety of the aircraft. The results can be obtained after data processing and analysis, and the method has the advantages of simple method and high reliability.

Description

technical field [0001] The invention relates to the technical field of aircraft manufacturing, in particular to a method for analyzing the thermal buckling critical temperature of an aircraft wall plate. Background technique [0002] In order to improve market share and model competitiveness, domestic and foreign civil aircraft manufacturers have been working on research on reducing structural weight, improving structural efficiency and extending aircraft life. Composite materials have been successfully used in civil aircraft with their excellent mechanical properties of specific strength and specific stiffness. The most representative new generation of large civil aircraft Boeing 787 and Airbus A350, the amount of composite materials accounted for 50% of the weight of the body structure. % and 52%, so that the airframe life of advanced civil aircraft such as A350 and B787 can reach more than 90,000 flight hours, which is much higher than that of domestic regional airliners ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G16C60/00G16C20/30G06F30/15G06F30/23G01N25/12G06F111/04G06F111/10G06F113/24G06F113/26G06F113/28G06F119/08
CPCG16C60/00G16C20/30G06F30/15G06F30/23G01N25/12G06F2111/04G06F2111/10G06F2113/24G06F2113/26G06F2113/28G06F2119/08
Inventor 邓文亮刘海燕李闯勤雷凯田培强任战鹏吴敬涛
Owner CHINA AIRPLANT STRENGTH RES INST
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