An Optimal Design Method for Large Aspect Ratio Wing Based on Model Fusion Method

Abstract

The invention discloses a high-aspect-ratio wing optimization design method based on a model merging method, and belongs to the technical field of overall optimization design of aircraft. The method comprises the steps that a penalty function method is used for processing complex constraints for an optimization model and a system-level optimization model which are optimally divided into structure subjects as needed; a high precision pneumatic structure coupling analysis model and a low precision pneumatic structure coupling analysis model are built through a pneumatic structure coupling modeling technology; high precision sample points and low precision sample points are generated through an experiment design method; high precision sample information and low precision sample information are obtained by calling the high precision pneumatic structure coupling analysis model and the low precision pneumatic structure coupling analysis model respectively and stored; by using the model merging method, the high precision sample information and the low precision sample information are merged to build a surrogate model; optimization solution is conducted based on an optimization method for a current surrogate model, whether the optimization result is credible or not is judged according to a difference value of a true response value of the optimal solution and a surrogate model value based on the model merging method, if not, the step is executed again to rebuild a merging model for optimization solution, if yes, the optimal design result is output, and optimization design is completed.

Description

technical field [0001] The invention relates to a large-aspect-ratio wing optimization design method based on a model fusion method, and belongs to the technical field of aircraft overall optimization design. Background technique [0002] High-aspect-ratio wings have the characteristics of large lift-to-drag ratio and large wing volume, and are widely used in high-altitude drones, solar-powered aircraft, and large intercontinental airliners. During the flight of this type of aircraft, the wing with a large aspect ratio is affected by the aerodynamic load, and the structural deformation occurs, and the deformation amplitude has a significant impact on the aerodynamic performance. Therefore, the aerodynamic structure coupling problem needs to be considered in the analysis and design of a large aspect ratio wing. For the coupling problem of aerodynamic structure, fluid mechanics and structural mechanics can be solved independently as a single discipline, and interdisciplinary ...

AI Technical Summary

Problems solved by technology

[0013] Aiming at the problem of high computational cost when considering aerodynamic structure coupling in the process of optimizing the design of wings with large aspect ratios, the invention discloses a method for optimizing the design of wings with large aspect ratios based on the model fusion method. The technical problem to be solved In the case of ensuring the accuracy, considering the aerodynamic structure coupling problem to realize the efficient optimal design of the wing with a large aspect ratio, it has the following advantages: use the model fusion method to effectively fuse the high and low precision analysis model information, make full use of the low precision model The information guarantees the accuracy of the fusion model, reduces the number of high-precision analysis model calls, thereby reducing computing costs and improving the optimization design efficiency of large aspect ratio wings

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