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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 problems such as inappropriateness, difficulty in calculating explicit or implicit function functions, and complex wing structure, so as to avoid Sampling process, omitting structural relationship calculations, easy-to-achieve effects

Active Publication Date: 2022-07-12
HARBIN ENG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • 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 assessment system and method based on the response surface method, the wing finite element simulation system is verified and corrected by the real data of the wing structure test system, and then the wing finite element simulation system is used to sample and establish the response The surface equations are used to solve various coefficients, and finally the structural reliability of this type of airfoil is calculated.

[0031] First, a wing structure test system is established, a 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 of the wing structure, the elastic modulus E and Poisson's ratio μ, and the geometric parameters, a finite element simulation system of the wing structure is established. The finite element method is currently the method with high ...

Embodiment 2

[0035] The invention includes the hardware system design of the wing reliability evaluation system and the method design of the computer 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 is used to simulate the loading of the aerodynamic load and the measurement of the displacement response.

[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 action point of the force and moment genera...

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Abstract

The invention discloses a wing reliability evaluation system and method based on a response surface method, which belongs to the field of reliability research in fixed-wing aircraft wings. The invention includes a wing structure test module, a wing structure finite element simulation module, and a reliability calculation module. Module, data storage and display module, firstly build the wing structure test module, then build the wing structure finite element simulation module, then verify and modify the wing structure finite element simulation module through the wing structure test module, and then pass the reliability The calculation module calculates the reliability, and finally performs data storage and display through the data storage and display module. The invention omits the complex structure calculation inside the wing through the response surface method; uses the real test data of the structure and the structure simulation system for comparison and verification, and supports the simulation sampling of the simulation system through the real data; uses the finite element simulation system to randomly sample, avoids the need for Sampling process for 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] Aircraft has special functionality, and its structural reliability is also an important issue in aircraft design. The structure of the aircraft wing is complex and the load is changeable, so the reliability analysis of the wing is the top priority of the reliability design of the aircraft structure. The characteristic that the structure completes the specified function under the specified conditions and within the specified time is called the structural reliability. Due to the particularity of the wing, it is impossible to carry out the reliability evaluation test for each wing, so it is necessary to calculate the reliability of this type of wing according to a special case of the wing with the same structure. ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15G06F30/23G06F119/02G06F119/14
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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