Airplane tail beam structure design load screening method

A technology for structural design and screening methods, applied in design optimization/simulation, instrumentation, geometric CAD, etc., to achieve the effect of ensuring safety and reducing the amount of calculation

Active Publication Date: 2021-04-09
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

[0003] At present, there is no complete set of tail beam load screening me

Method used

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  • Airplane tail beam structure design load screening method
  • Airplane tail beam structure design load screening method
  • Airplane tail beam structure design load screening method

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Embodiment Construction

[0027] 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 airplane loading tests, and particularly relates to an airplane tail beam structure design load screening method. The method comprises: 1, establishing a tail beam finite element model, arranging a plurality of loading connectors on the tail beam finite element model based on the actual situation of the aircraft tail beam, and dividing the tail beam finite element model into a plurality of typical areas according to the positions of the loading connectors; 2, applying a load to the tail beam finite element model through each loading joint, and drawing a force flow diagram of the tail beam wallboard; 3, analyzing the loading condition of each typical region according to the wallboard force flow diagram, and calculating the joint load of the corresponding typical region; and 4, calculating the internal force of the typical region according to the joint load of the corresponding typical region, drawing an internal force curve, and selecting the maximum point from the internal force curve as the tail beam design load of the corresponding typical region. The tail beam design load can be rapidly screened out from thousands of load conditions, and design input is provided for tail beam structure design.

Description

technical field [0001] The application belongs to the field of aircraft loading tests, and in particular relates to a method for screening aircraft tail beam structural design loads. Background technique [0002] The tailboom is a typical and very important structure in an aircraft. It is mainly used to transfer the load of the wings, vertical tail and vertical tail to the fuselage. Since it is an important structure, its design load screening is very important. [0003] At present, there is no complete set of tail beam load screening methods, which poses a great challenge to the design of tail beam structures. [0004] Therefore, it is desirable to have a technical solution to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art. Contents of the invention [0005] The purpose of this application is to provide a load screening method for aircraft tail boom structure design to solve at least one problem existing in the prior art. ...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/23G06F119/14
CPCG06F30/15G06F30/23G06F2119/14Y02T90/00
Inventor 田智亮邢华璐吴新悦高维健
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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