A wing reliability evaluation system and method based on response surface method

A technology of response surface method and evaluation system, which is applied in the field of reliability calculation in fixed-wing aircraft wings, which can solve the problems of difficulty in calculating explicit or implicit function functions, inappropriateness, and complex wing structure, and achieves omitting Structural relationship calculation, avoid sampling process, easy to achieve effect

Active Publication Date: 2018-12-11
HARBIN ENG UNIV
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  • Application Information

AI Technical Summary

Problems solved by technology

Among them, the first-order second-order moment method needs to calculate the function function, and the wing structure is relatively complicated, so it is difficult to calculate its explicit or implicit function function
However, the Monte Carlo method requires a large amount of data experiments, and the cost of the aircraft is relatively high, so this method is obviously not suitable

Method used

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  • A wing reliability evaluation system and method based on response surface method
  • A wing reliability evaluation system and method based on response surface method
  • A wing reliability evaluation system and method based on response surface method

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Embodiment 1

[0030] A wing reliability evaluation system and method based on the response surface method, which verifies and corrects the wing finite element simulation system through the real data of the wing structure test system, and then uses the wing finite element simulation system to sample and establish a response Surface equations are used to solve various coefficients, and finally the structural reliability of this type of wing is calculated.

[0031] Firstly, the wing structure test system is established, the distributed aerodynamic simulation load is applied to the wing, and the displacement at the wing tip is selected as the structural response for the wing structure, and the structural response value is measured. According to the material parameters elastic modulus E and Poisson's ratio μ of the wing structure, as well as the geometric parameters, the finite element simulation system of the wing structure is established. The finite element method is currently a method with hi...

Embodiment 2

[0035] The invention includes the hardware system design of the wing reliability evaluation system and the method design of calculating the wing reliability. figure 1 Schematic diagram of the wing reliability evaluation system.

[0036]The wing reliability evaluation system mainly includes wing structure test module, wing structure finite element simulation module, response surface method calculation unit, data storage and display module and other parts.

[0037] 1) Wing structure test module

[0038] The wing structure test system mainly includes a simulated load loading module, a support module and a displacement response measurement module, which are used to simulate the aerodynamic load loading and displacement response measurement of the wing.

[0039] The load on the wing is a non-uniformly distributed aerodynamic load, which can be replaced by an equivalent concentrated load in the test, so that the magnitude, direction and point of action of the force and moment it pr...

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Abstract

The invention discloses a wing reliability evaluation system and method based on a response surface method, belonging to the reliability research field of a fixed-wing aircraft wing. The system includes a wing structure test module, a wing structure finite element simulation module, a reliability calculation module, a data storage and a display module. Firstly, the wing structure test module is constructed, and then the wing structure finite element simulation module is constructed. Secondly, the wing structure finite element simulation module is verified and modified through the wing structure test module, and then the reliability is calculated through the reliability calculation module. Finally, the data are stored and displayed through the data storage and display module. The inventionomits the complicated structure calculation inside the wing through the response surface method. Comparison and verification are conducted through the real test data and the simulation system, and thesimulation sampling is supported by the real data. The finite element simulation system is used to simulate the random sampling process of multiple wings, which avoids the sampling process of multiple wings.

Description

technical field [0001] The invention relates to the field of reliability calculation in the wing of a fixed-wing aircraft, in particular to a system and method for evaluating the reliability of a wing based on a response surface method. Background technique [0002] The aircraft has special functions, and its structural reliability is also an important issue in aircraft design. The structure of the aircraft wing is complex and the load is variable, so the reliability analysis of the wing is the most important thing in the reliability design of the aircraft structure. The characteristic that a structure completes a specified function under specified conditions and within a specified time is called structural reliability. However, due to the particularity of the wings, it is impossible to conduct reliability evaluation tests for each wing, so it is necessary to calculate the reliability of this type of wing based on a special case of wings with the same structure. [0003] T...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F2119/06G06F30/23Y02T90/00
Inventor 邰荐吴限德白文彬陈卫东陈柯帆谢亚恩陶文舰赵晗李世龙李世一
Owner HARBIN ENG UNIV
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