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研究了航空发动机部件特性修正技术,提出了一种基于变适应度函数的模型优化算法,以达到减小总体建模误差,提高模型精度的目的.在稳态模型的基础上,对引气系数、总压恢复系数和各部件的特性进行了修正,使修正后的模型输出与实验数据相一致.采用改进遗传算法,对交叉率和变异率进行了非线性自适应调整,并根据误差大小调整适应度加权系数,避免算法陷入局部最优,同时减小最大建模误差.仿真结果表明,修正后各实验参数平均误差从2.4208%减小到0.3217%,模型满足稳态误差小于2%的要求.
Aeroengine component characteristics correction technology is studied and a model optimization algorithm based on variable fitness function is proposed to reduce the overall modeling error and improve the precision of the model.Based on the steady state model, , The total pressure recovery coefficient and the characteristics of each component were modified, so that the revised model output and experimental data are consistent.Adopting improved genetic algorithm, the crossover rate and mutation rate were nonlinearly adjusted adaptively, and adjusted according to the error size Fitness weighting coefficient to avoid the algorithm falling into the local optimum and reduce the maximum modeling error.The simulation results show that the average error of each experimental parameter is reduced from 2.4208% to 0.3217% and the model satisfies the requirement of less than 2% steady-state error .