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在旋翼气弹动力学模型基础上进行了多目标优化问题的描述和分类,定义了多目标优化问题及其解,讨论了多目标优化问题的解法,提出了直升机旋翼气弹动力学多目标优化问题的解法。使用改进的遗传模拟退火算法、加权系数法、全局准则法相结合的混合式解法进行旋翼气弹动力学多目标优化问题的求解。算例结果表明:使用混合法的多目标优化解法设计变量变化平缓;同时设计目标函数的3次/转、4次/转、5次/转谐波振动载荷和桨叶总质量分别比初始设计减少13.4%、31.5%、20.9%和7.36%,优化效果明显。由本文的研究可知,在直升机旋翼气弹动力学多目标优化问题中,使用混合式多目标优化问题解法能使旋翼气弹动力学多目标优化收敛到Pareto最优解,同时可提高多目标优化问题解质量和结果的鲁棒性。
The description and classification of multi-objective optimization problems are described on the basis of rotor-aeroelastic dynamics model. Multi-objective optimization problems and their solutions are defined. The solution of multi-objective optimization problems is discussed. The multi-objective optimization of helicopter rotor aeroelastic dynamics is proposed Solution of the problem. The solution of multi-objective optimization problem of rotor aeroelastic dynamics is solved by a hybrid method combining improved genetic simulated annealing algorithm, weighted coefficient method and global rule method. The results of the example show that the design variables are changed smoothly with the multi-objective optimization method of hybrid method. At the same time, the design parameters of the objective function such as 3 times per revolution, 4 times per revolution, 5 times per revolution, Reduce 13.4%, 31.5%, 20.9% and 7.36%, the optimization effect is obvious. From the research in this paper, we can see that the hybrid multi-objective optimization problem method can make the multi-objective optimization of rotor aeroelastic dynamics converge to the Pareto optimal solution and improve the multi-objective optimization in helicopter rotor aeroelastic dynamics multi-objective optimization problem Problem solving quality and the robustness of the results.