Method for aeroelastic tailoring of composite wing and genetic/sensitivity-based hybrid optimization method of composite wing

An aeroelastic, composite material technology, applied in the field of genetic/sensitivity hybrid optimization, can solve problems such as increased bending and torsional deformation, reduced aileron efficiency, and significant aeroelastic effect.

Inactive Publication Date: 2014-03-26
BEIHANG UNIV +1
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  • Abstract
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Problems solved by technology

[0003] At the same time, the prominent bending-torsion coupling characteristics of the swept wing with a large aspect ratio increase the bending and torsion deformation of the wing

Method used

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  • Method for aeroelastic tailoring of composite wing and genetic/sensitivity-based hybrid optimization method of composite wing
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  • Method for aeroelastic tailoring of composite wing and genetic/sensitivity-based hybrid optimization method of composite wing

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Embodiment Construction

[0012] A key to the aeroelastic tailoring of composite wings is to choose a reasonable and effective aeroelastic optimization method.

[0013] According to one aspect of the present invention, a genetic / sensitivity hybrid optimization method is provided, and an aeroelastic tailoring method of a composite material wing based on the optimization method is provided.

[0014] In the aeroelastic tailoring method of a composite wing according to an embodiment of the present invention, the aeroelastic tailoring of the wing is achieved through aeroelastic optimization, and aeroelastic optimization is one of the optimization problems, which is through genetic / Sensitivity hybrid optimization method to solve. In the present invention, the optimization problem can be expressed as searching for a set of design variables that minimizes the objective function F(v) in the ndv-dimensional space, namely:

[0015] Min. F(v) (1)

[0016] S.T. g j (v)≤0 j=1,2,...,n c (2)

[0017] v il ≤v i ≤v...

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Abstract

The invention provides a method for aeroelastic tailoring of a composite wing. The method for aeroelastic tailoring of the composite wing comprises the steps that aeroelastic tailoring of the composite wing is achieved by means of aeroelasticity optimization, and solution of aeroelasticity optimization is conducted according to a genetic/sensitivity-based hybrid optimization method. The genetic/sensitivity-based hybrid optimization method comprises the steps that (A) a group of individuals are generated randomly according to a genetic algorithm; (B) performance evaluation is conducted on the individuals in the group one by one; (C) according to a user definition, whether sensitivity-based optimization is applied or not is judged; (D) whether the end condition is met or not is judged; (E) if the end condition is not met, a new generation of excellent individuals are generated; if the end condition is met, operation is ended. By the adoption of the method for aeroelastic tailoring of the composite wing and the genetic/sensitivity-based hybrid optimization method, under the condition that multiple requirements for flutter, diffusion, inherent frequency, deformation, aileron efficiency, strength, the flight load, weight and the like are met, tailoring design of the structure is achieved and optimized.

Description

Technical field [0001] The invention relates to a genetic / sensitivity hybrid optimization method, and a civil aircraft composite material wing aeroelastic tailoring method based on the method, and belongs to the field of aerospace vehicle calculation methods and structural design. Background technique [0002] With the development of aircraft structural design technology, the use of advanced composite materials in the structural design of large and medium-sized aircraft has become an inevitable mainstream trend. Composite materials have a series of advantages such as high specific strength, high specific modulus, good fatigue resistance, corrosion resistance, and strong designability. Large aspect ratio wings are mostly used in large and medium-sized transport aircraft, and their structural flexibility is relatively large. In order to meet the stiffness design requirements, the aeroelastic design of composite wings with obvious weight advantages has become a hot spot in the desig...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 万志强王斌团刘超肖飞孙晓红杨超
Owner BEIHANG UNIV
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