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Optimum design method for aircraft system based on sequence radial basis function surrogate model

A proxy model and design method technology, applied in electrical digital data processing, special data processing applications, instruments, etc., can solve the problems of time-consuming and computationally time-consuming high-precision analysis models, and achieve reduced design costs, strong versatility, The effect of improving the efficiency of optimized design

Active Publication Date: 2013-12-25
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

In order to improve the accuracy and reliability of design results, high-precision analysis models are commonly used in multidisciplinary design optimization of aircraft systems, such as finite element analysis (Finite element analysis, FEA) models, computational fluid dynamics (Computational fluid dynamic, CFD) models, etc. However, the high-precision analysis model also brings the problem of time-consuming calculation while improving the analysis accuracy and reliability.
Even with the rapid development of high-performance computers, parallel computing, distributed computing and database technology, it is still time-consuming to use high-precision analysis models in optimization design

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  • Optimum design method for aircraft system based on sequence radial basis function surrogate model
  • Optimum design method for aircraft system based on sequence radial basis function surrogate model
  • Optimum design method for aircraft system based on sequence radial basis function surrogate model

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Embodiment Construction

[0060] In order to better illustrate the purpose and advantages of the present invention, below, the present invention will be further described in conjunction with the accompanying drawings and tables through the wing airfoil optimization design example and the general-purpose aircraft overall parameter optimization design example, and by comparing with the traditional optimization method results, the present invention The comprehensive performance of the invention is verified and analyzed.

[0061] (1) Optimal design of wing airfoil

[0062] The optimal design of airfoil is of great significance to improve the overall performance of aircraft. With the development of computer technology, Computational Fluid Dynamics (CFD) technology is widely used in airfoil optimization design. In this optimal design example, the CST method is selected to describe the coordinate points of the upper and lower surfaces of the airfoil. In this example, NACA0012 is selected as the initial airf...

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Abstract

The invention relates to an optimum design method for an aircraft system based on a sequence radial basis function surrogate model and belongs to the technical field of optimum design of the aircraft system. According to the optimum design method, the thought of searching step range of trust domain solving high-dimensional optimization problem is applied to a supervisory sequence surrogate model, the sample space is gradually updated and the approximate precision of the surrogate model is promoted, so that the optimizing strategy convergence is guided to the globally optimal solution and the optimum design method provided by the invention has better global optimization capacity and optimization efficiency. The method is strong in universality. According to the method, the program development is conveniently realized, the optimum design means for the aircraft system is improved, the design cost is lowered and the requirement for multidisciplinary optimum design of the present aircraft system is met.

Description

technical field [0001] The invention relates to an aircraft system optimization design method based on a sequential radial basis function surrogate model, and belongs to the technical field of aircraft system optimization design. Background technique [0002] Today, Multidisciplinary Design Optimization (MDO) has been widely used in the design of aircraft systems. In order to improve the accuracy and reliability of the design results, high-precision analysis models are commonly used in multidisciplinary design optimization of aircraft systems, such as finite element analysis (Finite element analysis, FEA) models, computational fluid dynamics (Computational fluid dynamic, CFD) models, etc. However, the high-precision analysis model also brings the problem of time-consuming calculation while improving the analysis accuracy and reliability. Even with the rapid development of high-performance computers, parallel computing, distributed computing, and database technologies, using...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 龙腾郭晓松刘莉彭磊黄波
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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