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Optimization design method based on self-adaptive radial basis function surrogate model for aircraft

A proxy model and optimization design technology, applied in electrical digital data processing, instruments, calculations, etc., to achieve the effect of improving approximation accuracy, optimization efficiency, and global approximation accuracy

Inactive Publication Date: 2012-09-19
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0015] 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 analysis model of the aircraft by the traditional global optimization method, and proposes an efficient, accurate and versatile method based on adaptive radial basis function Aircraft Optimization Design Method Based on Proxy Model

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  • Optimization design method based on self-adaptive radial basis function surrogate model for aircraft
  • Optimization design method based on self-adaptive radial basis function surrogate model for aircraft
  • Optimization design method based on self-adaptive radial basis function surrogate model for aircraft

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Embodiment 1

[0037] Embodiment 1: Wing Airfoil Optimal Design

[0038] 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. The description methods of the airfoil shape mainly include the linear perturbation method and the parameter method. In this embodiment, the shape function method is used to describe the geometric shape of the airfoil. In this example, NACA0012 is selected as the initial airfoil, and the flight speed is Ma=0.6. The lift-to-drag ratio of the wing is improved by optimizing the airfoil. The mathematical description of the problem is as follows:

[0039] max ( Cl / Cd ) s . t . t max * ≥ ...

Embodiment 2

[0054] Embodiment 2: multidisciplinary optimal design of supersonic commercial aircraft

[0055] The multidisciplinary optimization design of a supersonic commercial aircraft involves four subsystems: structure, aerodynamics, propulsion, and range. The optimization goal is to obtain the maximum cruising range. The design structure matrix of this multidisciplinary optimization design problem is as follows: figure 2 shown. figure 2 The elements on the diagonal of the design structure matrix in are each subsystem, the vertical elements of each subsystem are the input parameters of the subsystem, and the horizontal elements are the output parameters of the system. The input of the structural subsystem is: relative thickness (t / c), wing sweep angle (Λ), wing x-section (x), root-slip ratio (λ), aspect ratio (AR), wing surface area (S REF ), lift (L), engine weight (W E ), fuel gross weight (W FO ), gross weight (W O ) and maximum load (N z ); the output of the structural su...

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Abstract

The invention provides an optimization design method based on a self-adaptive radial basis function surrogate model for an aircraft. The optimization design method comprises the following steps of: first, sampling an experimental design sample in a design space by adopting a latin square experimental design method and acquiring an aircraft high-precision analytical model response value corresponding to the experimental design sample; constructing an approximate aircraft high-precision analytic model of the radial basis function surrogate model; acquiring the global optimal solution of a current radial basis function surrogate model by utilizing a genetic algorithm; constructing an aircraft optimization design major sampling space according to current optimization flow information, increasing a few experimental design samples, and updating the radial basis function surrogate model; and acquiring the global optimal solution of the updated radial basis function surrogate model by utilizing the genetic algorithm again, judging whether an optimization flow is converged or not, stopping optimization if the optimization flow is converged, and reconstructing the aircraft optimization design major sampling space until the optimization is converged if the optimization flow is not converged. By using the optimization design method provided by the invention, the optimization efficiency is improved, and the optimization design cost of the aircraft is saved.

Description

technical field [0001] The invention relates to an aircraft optimization design method based on an adaptive radial basis function proxy model, and belongs to the technical field of multidisciplinary optimization in aircraft design. Background technique [0002] Today's aircraft systems are becoming more and more complex. In order to solve the huge difficulties faced by the optimization design of modern complex aircraft systems, multidisciplinary design optimization (MDO) is widely used. In order to improve the accuracy and credibility of the design results, high-precision analysis models are commonly used in the multidisciplinary design optimization of aircraft, such as the finite element analysis (Finite element analysis, FEA) model used in structural analysis, and the computational fluid dynamics (CFD) model used in aerodynamic analysis. Computational fluid dynamic, CFD) analysis model, etc. However, the high-precision aircraft analysis model also brings the problem of ti...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 龙腾刘莉彭磊王正平王律
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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