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Multi-objective optimization design method considering aeroelasticity restraint and for wing made of composite material

A multi-objective optimization and composite material technology, applied in the field of multi-objective optimization design of composite material wings, can solve the problems of not considering the minimum weight and minimum gust response at the same time

Active Publication Date: 2014-03-19
BEIHANG UNIV
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Problems solved by technology

[0006] The purpose of the present invention is to provide a composite material wing multi-objective optimization design method that simultaneously considers weight and gust response in view of the shortcomings of existing design methods that do not simultaneously consider the two objective functions of minimum weight and minimum gust response

Method used

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  • Multi-objective optimization design method considering aeroelasticity restraint and for wing made of composite material
  • Multi-objective optimization design method considering aeroelasticity restraint and for wing made of composite material
  • Multi-objective optimization design method considering aeroelasticity restraint and for wing made of composite material

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Embodiment Construction

[0020] The present invention will be described in detail below in conjunction with the accompanying drawings and embodiments.

[0021] The multi-objective optimization design method of composite material wing based on aeroelastic constraints provided by the present invention, the specific implementation method includes three optimization design stages (weight optimization, gust response optimization and second weight optimization), 4 small steps, combined figure 1 , the specific implementation steps are as follows:

[0022] The first step is to establish the finite element model and analyze the initial model:

[0023] Establish the initial geometric model of the composite material wing: first establish the initial geometric model in 3D software such as CATIA. Set the import unit in Patran, such as mm, and then import the initial geometric model into Patran. On this basis, the redundant lines and surfaces in the imported initial geometric model are removed, and other necessar...

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Abstract

The invention discloses a multi-objective optimization design method considering the aeroelasticity restraint and for a wing made of a composite material. The method includes the following steps that (1) a finite element model is built and analyzed; (2) weight is optimized; (3) gust response is optimized; (4) weight is optimized for the second time. The strength, rigidity and aeroelasticity restraint is considered, multi-objective optimization of structure weight and gust response is achieved, and the problem that the gust response amplitude is increased when structure weight optimization is conducted by using a traditional optimization method for the wing made of the composite material is solved. In the optimization process, in the gust response optimization stage, only the composite material auxiliary layer direction is used as a design variable, and gust response design requirement can be met under the condition that the wing weight is not changed.

Description

technical field [0001] The invention is an optimal design method for a composite material wing, more specifically, a multi-objective optimal design method for a composite material wing considering structural and aeroelastic constraints. Background technique [0002] Aircraft structure weight reduction is an important content of aircraft design. Composite materials are new materials made of two or more materials with different properties through physical or chemical methods. It has the advantages of specific strength, high specific stiffness, small thermal expansion coefficient, fatigue resistance, corrosion resistance, short manufacturing cycle and convenient maintenance. During the processing and forming process, the strength and rigidity of the aircraft can be improved through reasonable layering, thereby reducing the weight of the aircraft. While satisfying the strength and stiffness, aeroelastic tailoring of composite materials can be carried out, that is, the static a...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 李道春向锦武赵仕伟
Owner BEIHANG UNIV
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