Aeroelastic structure coupling optimization method based on self-adaptive point adding proxy model

A proxy model and self-adaptive technology, applied in constraint-based CAD, electrical digital data processing, design optimization/simulation, etc., can solve problems such as inability to realize self-adaptive point addition, improve optimization efficiency, reduce total times, and reduce calculation volume effect

Pending Publication Date: 2022-04-05
BEIHANG UNIV
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Problems solved by technology

[0006] The technical problem to be solved by the present invention is: to overcome the deficiency that the existing proxy model method cannot realize adaptive point addition, and to provide an aeroelastic structure coupling optimization method based on the adaptive point plus proxy model, which fully considers the practical engineering problems Ubiquitous parameter uncertainty and model uncert

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  • Aeroelastic structure coupling optimization method based on self-adaptive point adding proxy model
  • Aeroelastic structure coupling optimization method based on self-adaptive point adding proxy model
  • Aeroelastic structure coupling optimization method based on self-adaptive point adding proxy model

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Embodiment

[0066] Such as Figure 8 Shown, the present invention a kind of aeroelastic structure coupling optimization method based on self-adaptive adding agent model, comprises the following steps:

[0067] Step (1) to figure 1 The aircraft wing structure shown is taken as the optimization object, and the uncertain variable interval is α I =[0,1], the material used in the structure is 2A12 aluminum alloy, and the relationship between the elastic modulus E of the structure and the uncertain variable α is:

[0068]

[0069] The structure consists of three parts: skin, spar, and rib. The finite element grids of the three parts are all shell elements. The thickness of the skin is 5.7mm, and the thickness of the spar is taken as the first design variable x 1 , taking the element thickness of the rib as the second design variable x 2 , and the initial value of the design variable is The root of the aircraft wing structure is a fixed end, which bears a distributed aerodynamic load on ...

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Abstract

The invention discloses an aeroelastic structure coupling optimization method based on a self-adaptive point adding proxy model, and the method comprises the steps: firstly considering the parameter uncertainty and the model uncertainty, carrying out the quantification of the uncertainty, and providing a self-adaptive intelligent point adding criterion based on a Kriging proxy model, the maximum stress of the aircraft structure and the upper and lower boundaries of the flutter speed are obtained, and then the aircraft structure is optimally designed by considering the structural strength constraint condition and the aeroelasticity constraint condition based on the self-adaptive point adding agent model. According to the method, the number of times of finite element analysis and aeroelasticity analysis in the aircraft structure optimization process is reduced, the calculation amount is reduced, the optimization efficiency is improved, and a new thought is provided for aircraft structure optimization design.

Description

technical field [0001] The invention relates to the field of aeroelastic structure coupling optimization, in particular to an aeroelastic structure coupling optimization method based on an adaptive point addition agent model. Background technique [0002] Aeroelastic problems widely exist in the process of aircraft design. Under the action of aerodynamic load, the structure of the aircraft will deform and vibrate, and the deformation and vibration of the structure will in turn affect the size and distribution of the aerodynamic load on the aircraft. the same aeroelastic problem. Aeroelastic problems are mainly divided into two categories. One is to study the displacement and deformation of elastic bodies under aerodynamic loads, which is called static aeroelastic problems; the other is to study the dynamic response of elastic bodies under aerodynamic loads, which is called dynamic aeroelastic problems. Resilience issues. [0003] The flutter phenomenon belongs to the prob...

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Application Information

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IPC IPC(8): G06F30/15G06F30/23G06F119/14G06F111/04
Inventor 邱志平刘晨浩祝博李云龙
Owner BEIHANG UNIV
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