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Pneumatic cutting optimization design method for flexible inflatable wing structure

A technology of optimized design and wing structure, applied in the field of aircraft, can solve problems such as aero-elastic failure, achieve the effect of effectively improving aerodynamic lift-drag ratio, improving aero-elastic characteristics, extending working time and effective range

Active Publication Date: 2022-07-08
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to solve the aeroelastic failure problem including fold-buckling existing in the existing flexible inflatable wing structure, the main purpose of the present invention is to provide an aerodynamic tailoring optimization design method for the flexible inflatable wing structure, by fully considering the idea of ​​aerodynamic tailoring Essentially, for the flexible inflatable wing structure, the air beam slope angle is optimized under the premise of considering the inflation internal pressure and the thickness of the membrane material, and the allowable stress of the membrane material is used as the constraint condition, and the maximum lift-to-drag ratio of the aerodynamic subject and the structure subject are selected. The minimum wrinkle area is the optimization goal, considering the aerodynamic / structural multidisciplinary strong coupling effect of the flexible inflatable wing, improving the aeroelastic characteristics of the flexible inflatable wing structure from the underlying design level of changing the stiffness distribution of the system, and making up for the underlying optimization of the inflatable wing configuration by the existing technology lack of design
The invention helps to improve the mechanical properties of the flexible inflatable wing structure, solves the aeroelastic failure problem including fold-buckling existing in the flexible inflatable wing structure, and can improve optimization efficiency and precision

Method used

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  • Pneumatic cutting optimization design method for flexible inflatable wing structure
  • Pneumatic cutting optimization design method for flexible inflatable wing structure
  • Pneumatic cutting optimization design method for flexible inflatable wing structure

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0102] Optimal design of joint objective functions for aerodynamic tailoring of flexible inflatable wing structures

[0103]

[0104] Take the weight coefficient , that is, to pursue the optimal performance of the aerodynamic discipline, temporarily ignoring the influence of the parameters of the structural discipline.

[0105] The optimization result is as Figure 4 As shown, the simulation results of aerodynamics and structural disciplines under the condition of global optimal design variables are as follows: Figure 5 and Image 6 shown.

[0106] For the optimization results of Example 1, the optimal slope angle of the air beam of the flexible inflatable wing structure for , because this example pursues the optimal aerodynamic discipline, the inflation internal pressure and the thickness of the membrane material have little influence on the aerodynamic results, and are kept at the initial value of 30KPa and [0.200, 0.200, 0.200] mm. From the aerodynamic simulati...

Embodiment 2

[0109] Optimal design of joint objective functions for aerodynamic tailoring of flexible inflatable wing structures

[0110]

[0111] Take the weight coefficient , that is, to pursue the optimal performance of the structural discipline, temporarily ignoring the influence of the parameters of the aerodynamic discipline.

[0112] The optimization result is as Figure 4 As shown, the simulation results of aerodynamics and structural disciplines under the condition of global optimal design variables are as follows: Figure 5 and Image 6 shown.

[0113] For the optimization results of Example 2, the optimal slope angle of the air beam of the flexible inflatable wing structure for , because this embodiment pursues the optimal structural discipline and the optimal inflatable internal pressure It is 56.8KPa, and the film thickness of the skin, the end face of the wing tip and the pulling tape is [0.542, 1.150, 1.336] mm. The aerodynamic simulation results show that the ...

Embodiment 3

[0116] Optimal design of joint objective functions for aerodynamic tailoring of flexible inflatable wing structures

[0117]

[0118] Take the weight coefficient , that is, on the basis of considering the optimal carrying capacity of structural disciplines, at the same time pursuing the optimal lift-to-drag ratio of aerodynamic disciplines.

[0119] The optimization result is as Figure 4 As shown, the simulation results of aerodynamics and structural disciplines under the condition of global optimal design variables are as follows: Figure 5 and Image 6 shown.

[0120] For the optimization results of Example 3, the optimal slope angle of the air beam of the flexible inflatable wing structure for , this embodiment pursues the optimal lift-to-drag ratio and optimal inflatable internal pressure of the aerodynamic discipline on the basis of considering the optimal bearing capacity of the structural discipline. It is 52.9KPa, and the film thickness of the skin, the en...

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Abstract

The invention discloses a pneumatic tailoring optimization design method for a flexible inflatable wing structure, and belongs to the field of aircrafts. The implementation method comprises the following steps of: aiming at a flexible inflatable wing structure, optimizing the oblique sweep angle of an air beam on the premise of considering the inflatable internal pressure and the thickness of a membrane material, and selecting the maximum lift-drag ratio of a pneumatic subject and the minimum wrinkle area of a structural subject as optimization targets by taking the allowable stress of the membrane material as a constraint condition; the aerodynamic / structure multidisciplinary strong coupling effect of the flexible inflatable wing is considered, and the aeroelastic characteristic of the flexible inflatable wing structure is improved from the bottom layer design level of changing system rigidity distribution. In the optimization process, an adaptive strategy and an agent model are adopted, a sample point set can be driven to be concentrated near an optimal solution on the basis of reducing the operation cost, the calculation precision of the agent model in the region of interest is further improved, and the optimization convergence difficulty is reduced. For pneumatic cutting optimization of the flexible inflatable wing structure, a high-precision global optimization algorithm is selected, the calculation efficiency is ensured, and falling into a local optimal solution is avoided.

Description

technical field [0001] The invention relates to an aerodynamic tailoring optimization design method for a flexible inflatable wing structure, and belongs to the field of aircraft. Background technique [0002] The inflatable wing is a multi-cavity inflatable structure made of high-strength composite flexible materials and filled with high-pressure gas to maintain the pressure and shape. Significant advantages such as lower cost. With the refinement of combat requirements and the diversified development of aircraft uses, inflatable wing technology organically combines rigid body and flexible wings. The characteristics of rigid-flexible coupling have attracted extensive attention from scholars at home and abroad. It has shown great application value on aircraft such as missiles. [0003] Since the inflatable film is prone to large deformation under the action of air pressure, the existing inflatable wing designs usually use multiple inscribed circles to approach the airfoil,...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/20G06F119/14
CPCG06F30/15G06F30/20G06F2119/14Y02T90/00
Inventor 孟军辉孟繁敏马诺李文光刘莉
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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