Method for applying landing gear load to full-aircraft finite element model of aircraft structure

A technology of aircraft structure and landing gear, applied to aircraft parts, ground equipment, transportation and packaging, etc., can solve problems such as deviations in the analysis of force transmission routes of aircraft structures, unfavorable fine design of aircraft structures, and weight gain of aircraft structures, etc.

Active Publication Date: 2021-11-26
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

This method ignores the force transmission process of landing gear, aircraft inertial loads and other concentrated force balance, resulting in deviations in the analysis of the force transmission route of the aircraft structure, which is not conducive to the refined design of the aircraft structure and may increase the weight of the aircraft structure

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  • Method for applying landing gear load to full-aircraft finite element model of aircraft structure

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Embodiment Construction

[0036] 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 structure design, and particularly relates to a method for applying a landing gear load to a full-aircraft finite element model of an aircraft structure. The method includes the steps: 1, carrying out full-aircraft load balancing under the load of a landing gear; 2, adding a landing gear finite element model in a landing gear load state in the aircraft structure full-aircraft finite element model, and adjusting the attitude of the aircraft structure full-aircraft finite element model to the corresponding landing gear load state; 3, applying an aircraft distributed load in the aircraft structure whole-aircraft finite element model; 4, applying an aircraft concentrated force load in the aircraft structure full-aircraft finite element model; 5, applying displacement constraint in the whole-aircraft finite element model of the aircraft structure; and 6, checking a loading result of the whole-aircraft finite element model of the aircraft structure. According to the invention, the real loading condition of the aircraft structure under the load of the landing gear can be simulated more accurately, and the fine design of the loading of the aircraft structure can be realized, thereby reducing the weight of the structure.

Description

technical field [0001] The application belongs to the field of aircraft structure design, and in particular relates to a method for applying landing gear loads to the whole aircraft structure finite element model of the aircraft structure. Background technique [0002] In aircraft structure design, the impact of landing gear loads on aircraft structures is generally considered to be limited to the aircraft structure near the corresponding landing gear, and the force analysis and structural design of the aircraft structure are carried out by applying concentrated loads on the landing gear and restraining at the far end. This method ignores the force transmission process of landing gear, aircraft inertial load and other concentrated force balance, resulting in deviations in the analysis of the force transmission route of the aircraft structure, which is not conducive to the refined design of the aircraft structure and may increase the weight of the aircraft structure. [0003]...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/23B64F5/00G06F119/14
CPCG06F30/15G06F30/23B64F5/00G06F2119/14
Inventor 蔡永明刘思远戴亚光靳诚忠李伟
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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