Composite material structural design verification method for airworthiness certification

A composite material and structural design technology, applied in computing, special data processing applications, instruments, etc., to achieve the effects of reducing design costs and sea trial review costs, saving review time, and high confidence

Inactive Publication Date: 2016-03-23
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

[0003] The purpose of the present invention is to provide a composite material structural design verification method for airworthiness certification, to solve or at least alleviate at least one problem in the background technology

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  • Composite material structural design verification method for airworthiness certification

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[0011] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. 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 invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

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Abstract

The invention discloses a composite material structural design verification method for airworthiness certification. The composite material structural design verification method for airworthiness certification comprises the following steps that 1, the application positions of composite materials are determined, and airworthiness verification of the composite materials is performed; 2, the preliminary dimension of the typic structure is determined, the needed composite material is selected from the composite material system determined in the first step, and airworthiness verification is performed on design allowable values of the composite material in the structural state; 3, according to the design allowable values obtained in the second step, assembly-level detailed design and airworthiness verification of the composite material structure are performed; 4, according to the structural design of the assembly-level composite material in the third step, the detailed design and trial trip verification of the composite material of full-scale-level of an airplane are determined. The composite material structural design verification method has the advantages that the confidence coefficient of a result obtained through the experimental verification method is high, the requirement for experience of designers is low, different persons can follow the same verification method, the certification time is shortened, and the product development period is shortened.

Description

technical field [0001] The invention relates to the technical field of aviation airworthiness certification, in particular to a composite material structure design verification method for airworthiness certification. Background technique [0002] Due to the commercial needs of increasingly fierce market competition and the essential requirements of aircraft performance, the amount of composite materials used in modern advanced civil aircraft body structures is increasing, and it has realized from non-load bearing, secondary load bearing components, to empennage level main load, Then to the application of the main load-bearing components of the wing and fuselage. The application of composite material structures has become an important symbol to measure the technological advancement of the new generation of civil aircraft, and it is also one of the important factors to reduce costs, improve performance and market competitiveness. At present, the design and verification of com...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/13
Inventor 段敏鸽刘存喜周景锋何思邱朝群孙世东
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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