Aircraft Aerodynamic Shape Design Method and System Based on Simulation and Optimization Coupling

Abstract

The invention discloses an aircraft aerodynamic shape design method and system based on simulation and optimization coupling, including determining an aircraft shape parameterization method according to a given aircraft shape model to obtain design variables; using a constrained domain experimental design method to generate initial sampling points; Use a high-precision aerodynamic simulation model to perform flow field simulation calculations, obtain simulated flow field distribution, build a training set and generate a full flow field approximate model; predict the optimal point in the design space for the full flow field approximate model, and use it as a new sampling point ; Use the high-precision aerodynamic simulation model to perform simulation calculations on the new sampling point, and obtain the simulated flow field approximation model of the new sampling point; output the new sampling point when the convergence judgment condition is reached. Through the deep coupling of the optimization algorithm and the simulation model, the present invention realizes the dual acceleration of accelerating the convergence of the optimization algorithm by the simulation solution information and accelerating the aerodynamic simulation solution by the optimization algorithm, thereby greatly reducing the total time consumption of the optimization process and improving the efficiency of the aerodynamic optimization.

Description

technical field [0001] The invention belongs to the field of aircraft aerodynamic shape design, in particular to an aircraft aerodynamic shape design method and system based on simulation and optimization coupling. Background technique [0002] Aerodynamic shape design is an important part of aircraft design and has a great impact on the overall performance of the aircraft. With the improvement of aircraft performance requirements, the design of aircraft becomes more complex, which puts forward higher requirements for the fine design of aerodynamic layout. [0003] Currently commonly used aerodynamic design methods are: 1. Inverse design method, such as literature 1 "CARLSON L. A direct-inverse method for the prediction of transonic and separated flows about airfoils at high angles of attack [A]. 24th Aerospace Sciences Meeting [C ]. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986." and literature 2 "Greff E, Mantel J. An engineering approach to t...

AI Technical Summary

Problems solved by technology

However, the disadvantages of the existing start-up optimization design method are: the determination of the target flow field distribution in the inverse design method requires the designer to have a deep understanding of the design target and rich design experience, and the design quality depends heavily on the selection of the target aerodynamic characteristics; On the other hand, it is difficult to deal with aerodynamic, geometrical constraints, and non-design point performance constraints

In this process, the simulation model is regarded as a "black box", and the approximate model only predicts the input-output relationship of the "black box", which cannot make full use of the large amount of data information generated by the time-consuming simulation model, which seriously weakens the ability of the proxy model to capture the real The ability of the essential characteristics of the model greatly limits the further improvement of the efficiency of the approximate optimization method

In the patent document CN111079228A "A Method for Optimizing Aerodynamic Shape Based on Flow Field Prediction", although the surrogate model is also used to predict the aerodynamic shape parameters, it can be seen from the specific embodiments and drawings that it solves the simple two 3D aircraft shape design problems, such as airfoil and fairing 2D cross-sectional shape parameter design, the optimization process only performs approximate modeling of the aerodynamic shape parameters for the local flow field, and the mesh does not deform during the optimization process, so it cannot be applied to complex 3D aircraft shape optimization design problem, that is, it is impossible to model the full flow field of the aircraft shape to achieve accurate prediction of the aerodynamic shape parameters of the 3D aircraft

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