Optimization design method for air vehicle lifting surface structure

An optimized design and lift surface technology, applied in the fields of instruments, calculations, special data processing applications, etc.

Active Publication Date: 2012-11-21
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0034] The purpose of the present invention is to solve the shortcomings of time-consuming calculation and analysis in the process of optimizing the high-precision

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  • Optimization design method for air vehicle lifting surface structure
  • Optimization design method for air vehicle lifting surface structure
  • Optimization design method for air vehicle lifting surface structure

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Embodiment Construction

[0076] In order to better illustrate the technical solution of the present invention, the present invention will be further described below in conjunction with the accompanying drawings and specific embodiments, and by comparing with the results of traditional aircraft lifting surface structure optimization design methods, the comprehensive performance of the present invention is verified and analyzed.

[0077] The objective of the optimal design in this embodiment is to minimize the mass of the aircraft's lifting surface under the condition of satisfying the flutter velocity constraints. For high-speed aircraft, flutter speed is a very important nonlinear index. When the flying speed of the aircraft reaches the critical speed of flutter, nonlinear self-excited vibration will be caused, and the aircraft will be damaged.

[0078] A method for optimizing the design of the lift surface structure of an aircraft, the operation process of which is as follows figure 1 As shown, speci...

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Abstract

Disclosed is an optimization design method for an air vehicle lifting surface structure. The method includes utilizing a Latin hypercube design (LHD) method to extract experiment design samples and obtain a high-accuracy analysis model response value of an air vehicle lifting surface; constructing a radial basis function (RBF) broker model; generating a certain amount of grid points randomly by using the LHD method in design space, and calculating a corresponding response value of the RBF broker model; setting a global space reduction rate M1% and a local space reduction rate M2%, and performing two times of pseudo reduction; optimizing the RBF broker model by using a genetic algorithm in each clustering space; obtaining the space distance between an optimal point and a last-time space global approximate optimal point, and deleting the current space to obtain novel space if reduction criteria are met; and obtaining an actual response value of a current global approximate optimal solution, determining whether the value is convergent, and stopping optimizing if the value is convergent, otherwise, performing iteration repeatedly till the optimal solution is found. According to the optimization design method for the air vehicle lifting surface structure, the optimization efficiency is improved, and the optimization design cost of the air vehicle lifting surface structures saved.

Description

technical field [0001] The invention relates to an optimization design method for a lift surface structure of an aircraft, and belongs to the technical field of multidisciplinary coupling optimization design in the optimization design of aircraft. Background technique [0002] Since the 1980s, Sobieski of the NASA Langley Research Center in the United States and other scientists and engineering designers in the aerospace field proposed a new aircraft design method: Multidisciplinary Design Optimization (MDO). The proposal of MDO has been widely valued by research institutions, universities and industries in various countries (such as NASA, Stanford University, Massachusetts Institute of Technology, Airbus and Boeing, etc.), which has set off a wave of MDO research. On the one hand, in order to improve the analysis accuracy and reliability, high-precision analysis models are widely used in aircraft design, such as the finite element analysis (FEA) model used in structural ana...

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Application Information

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IPC IPC(8): G06F19/00
Inventor 刘莉李昱霖龙腾彭磊陈鑫
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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