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Method for analyzing design sensitivity of aerostatic elastic energy of wing with high aspect ratio

A technology with a large aspect ratio and an analysis method, applied in the direction of geometric CAD, etc., can solve the problems of destroying the original characteristics, storage structure, and computational complexity, and achieve the effect of avoiding damage and solving the fluctuation problem of the deformed surface

Active Publication Date: 2020-01-17
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

The technical flaws of this algorithm are: the stiffness matrix is ​​a large-scale symmetric and sparse positive definite matrix, modifying the stiffness matrix in the calculation will destroy its original characteristics and storage structure, and updating the storage structure of the stiffness matrix is ​​of great importance to large-scale structural optimization design. Unfavorable, it will cause computational complexity

Method used

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  • Method for analyzing design sensitivity of aerostatic elastic energy of wing with high aspect ratio
  • Method for analyzing design sensitivity of aerostatic elastic energy of wing with high aspect ratio
  • Method for analyzing design sensitivity of aerostatic elastic energy of wing with high aspect ratio

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Embodiment

[0108] The schematic diagram of the algorithm flow of the present invention is as figure 1 As shown, the correctness and effectiveness of the algorithm of the present invention will be further described below for specific embodiments.

[0109] This embodiment is a swept wing with a large aspect ratio. The half-span length of the wing is 8.90m, the wing root chord length is 2.14m, the wingtip chord length is 0.44m, the leading edge sweep angle is 9°, and the reference area is 8.92 m 2 . Taking the lift efficiency and its design sensitivity as an example, the basic ability of the algorithm of the present invention is tested. The concrete steps of this embodiment are:

[0110] Step 1. Establish the structural model and aerodynamic model of the large aspect ratio wing.

[0111] HYPERMESH is used to establish the finite element structural model of the wing structure. The main structures include skin, beams, ribs, beam rafters, and rib rafters, including 990 shell elements, 400 ...

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Abstract

According to the method, the least square fitting surface function is established by utilizing the linear function and the consistent tight support radial basis function, so that the simulation of theelastic deformation of the wing is realized, and the problem of deformation surface volatility during displacement transmission of a traditional interpolation method is solved. On the basis of staticaeroelastic calculation, a model analysis solving method for aerodynamic load design sensitivity based on an iteration mode is provided and comprises a direct method and an accompanying method, the algorithm avoids damage to an original rigidity matrix, meanwhile, calculation efficiency is high, and the requirement of engineering practice is met.

Description

technical field [0001] The invention is applicable to the field of static aeroelastic optimization design of aircraft structure, and in particular relates to an analysis method for design sensitivity of static aeroelastic energy of a wing with a large aspect ratio. Background technique [0002] The light weight and great flexibility of the structure of modern aircraft make the static aeroelastic effect more prominent. With the refinement of aircraft structure optimization design, the influence of static air bombs must be considered in the optimization process. The static aeroelastic energy design sensitivity refers to the change degree of the static aeroelastic performance index caused by the change of the structural size or parameters, which will provide the necessary information for the gradient optimization algorithm and guide the optimization process. The static aeroelastic energy design sensitivity The calculation of is an important work link in the optimization design...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15
Inventor 程云鹤孙秦
Owner NORTHWESTERN POLYTECHNICAL UNIV
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