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A Fast Approximate Optimization Method for Aircraft Aiming at High Time-consuming Constraints

An optimization method and aircraft technology, applied in the field of multi-disciplinary optimization, can solve problems such as inability to solve constraints and time-consuming calculation, and achieve the effect of shortening engineering optimization cycle, reducing calculation cost, and overcoming calculation time-consuming

Active Publication Date: 2019-09-13
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Description
  • Claims
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Problems solved by technology

[0039] Aiming at the defects that the traditional global optimization algorithm is time-consuming in the process of optimizing the high-precision analysis model, and the standard efficient global optimization method cannot solve the constraint problem
The technical problem to be solved by the rapid approximate optimization method for aircraft with high time-consuming constraints disclosed by the present invention is to improve the calculation of the optimization process of high-precision analysis models in the global optimization algorithm of the rapid approximate optimization method for aircraft with high time-consuming constraints. Efficiency, and can solve the defect that standard efficient global optimization methods cannot solve constrained problems

Method used

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  • A Fast Approximate Optimization Method for Aircraft Aiming at High Time-consuming Constraints
  • A Fast Approximate Optimization Method for Aircraft Aiming at High Time-consuming Constraints
  • A Fast Approximate Optimization Method for Aircraft Aiming at High Time-consuming Constraints

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Embodiment 1

[0091] Embodiment 1: Take the application of reducing the design cost of a pressure vessel as an example under the constraint condition.

[0092] The purpose of the pressure vessel design problem is to reduce the cost including welding, materials and molding under the premise of satisfying certain constraints. Assuming that the pressure vessel model is a time-consuming high-precision analysis model in engineering design, by solving the corresponding function in the design space The minimum value in , to verify the performance of C-EGO. The purpose of this embodiment is to improve the optimization design efficiency, that is, to reduce the times of solving the function.

[0093] The given pressure vessel design problem is as follows:

[0094]

[0095] In order to obtain the global optimal solution, an optimization method with global optimization capability is used. Here, the design problem is optimized by using the aircraft rapid approximate optimal design method for high t...

Embodiment 2

[0136] Embodiment 2: The optimization application of reducing the quality of the earth observation satellite under the constraint condition is taken as an example.

[0137] The design goal of the earth observation satellite is to obtain as many ground remote sensing images as possible and to achieve the coverage of the earth's surface area while ensuring the resolution and distortion, while reducing the cost of the satellite as much as possible. The design structure matrix (Design Structure Matrix, DSM) of the multidisciplinary design optimization model in this paper is as follows: Figure 4 As shown in , where the horizontal line represents the subject output, the vertical line represents the subject input, and the symbols at the nodes indicate the coupling parameters between subjects. The multi-disciplinary analysis (Multi-Disciplinary Analysis, MDA) process consists of five disciplines: orbit, control, payload, power supply and structure, and also includes the coupling rela...

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Abstract

The invention relates to a high time consumption constraint-oriented rapid approximate optimization method for aircrafts, and belongs to the technical field of multidisciplinary optimization. The method comprises the following steps of: in the process of optimizing an engineering design problem with constraints, constructing an agent model according to known sample point information, a constraint corresponding to a sample point and a penalty coefficient updated at each time in each iteration process; optimizing the agent model and adding a sample point; calling a real analysis model to obtain a corresponding function value and a corresponding constraint value; if the optimized sample point satisfies the constraint, decreasing the penalty coefficient to ensure that the next optimization iteration places emphasis on improving the optimality; if the optimized sample point does not satisfy the constraint, increasing the penalty coefficient to ensure that the next optimization iteration places emphasis on improving the feasibility; and carrying out repeated iteration until a termination criterion is satisfied. The method can consider the local approximate accuracy and the global approximate accuracy, has an ability of processing constraints and is capable of effectively improving the optimization efficiency and saving the aircraft optimization design cost.

Description

[0001] The invention relates to an aircraft fast approximate optimization method aimed at high time-consuming constraints, and belongs to the technical field of multidisciplinary optimization in aircraft design. Background technique [0002] With the advancement of science and technology, engineering optimization problems are becoming more and more complex. Many analysis and simulation software are used in design and research, but most of these analysis and simulation problems are high-precision analysis models, such as the finite element used in structural analysis Analysis (FEA) models, computational fluid dynamics (CFD) analysis models used in aerodynamic analysis, etc. While improving the accuracy and reliability of the analysis, the high-precision analysis model also brings about the problem of time-consuming calculation. Although today's computer hardware and software technology has made great progress, it is still extremely consuming to call the high-precision analysis m...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20G06F2111/04
Inventor 龙腾史人赫刘莉刘建
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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