Modeling method for airplane composite material wall plate weight analysis

A modeling method and weight analysis technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve the problem of large error in weight estimation of axial compression-resistant composite wall panels

Inactive Publication Date: 2016-02-17
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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Problems solved by technology

[0007] The technical solution provided by the invention solves the problem that the weight estimation error of the anti-ax

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  • Modeling method for airplane composite material wall plate weight analysis
  • Modeling method for airplane composite material wall plate weight analysis
  • Modeling method for airplane composite material wall plate weight analysis

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Embodiment Construction

[0027] In order to better understand the aircraft composite panel weight analysis modeling method according to the solution of the present invention, a preferred embodiment of the aircraft composite panel weight analysis modeling method of the present invention will be further described below in conjunction with the accompanying drawings.

[0028] Such as Figure 1-4 As shown, the aircraft composite wall panel weight analysis modeling method provided by the present invention is used for weight control in the production process of aircraft composite material structural parts, including the following steps:

[0029] S1, defining structural parameters, said structural parameters including panels and ribs;

[0030] S2, constructing the finite element model of the composite panel structure;

[0031] S3, defining loads and boundary constraints on the finite element model of the composite panel structure;

[0032] S4, Static strength and stiffness analysis of composite panel struct...

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Abstract

The invention discloses a modeling method for airplane composite material wall plate weight analysis and relates to the airplane weight research direction in the airplane overall design technical field. The modeling method is used for weight control in the airplane composite material structural component production process and includes the steps that S1, structural parameters are defined and comprise parameters of panels and ribs; S2, a composite material wall plate structure finite element model is constructed; S3, loads and boundary constraint of the composite material wall plate structure finite element model are defined; S4, the structural strength and the rigidity of the composite material wall plate structure finite element model are analyzed; S5, structural stability is analyzed; S6, a laying layer of a composite material structure is optimized; S7, the composite material wall plate structure weight is calculated. According to the modeling method for airplane composite material wall plate weight analysis, finite element modeling is fast and accurately performed on an anti-axial-compression composite material wall plate structure at the early stage of airplane design, and therefore the weight, the gravity center and the rotating inertia of the anti-axial-compression composite material wall plate structure can be accurately and fast calculated through numerical simulation.

Description

technical field [0001] The invention relates to the research direction of aircraft weight in the technical field of aircraft overall design, in particular to a method for analyzing and modeling the weight of aircraft composite wall panels. Background technique [0002] The mass characteristics of the aircraft as a whole and each sub-component need to be estimated in the aircraft conceptual design stage and preliminary design stage. The estimation of aircraft mass characteristics has two purposes: one is that the weight, center of gravity, and moment of inertia of the aircraft are used as the basic input parameters for flight control, performance, and stability analysis, which determine the safety, maneuverability, and stability of the aircraft; The multi-scheme evaluation carried out in the aircraft design and selection stage provides a reference basis. [0003] Accurate mass characteristic estimation in the aircraft scheme design stage is the premise and basis for aircraft...

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Application Information

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IPC IPC(8): G06F17/50
Inventor 汤春尧李海泉潘若刚戴浩
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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