基于改进正交试验设计的飞行轨道参数优化

采用微分进化算法改进了标准正交设计的均匀性.运用标准正交设计法和改进的正交设计法优化亚轨道飞行器再入段轨道参数.在相同的样本容量下,标准正交设计得到了估计误差满足要求的回归模型,而改进的正交设计得到的回归模型的估计误差有了进一步减小.采用复形调优法对两个回归模型进行寻优计算,两模型所得最优解均满足精度要求,而改进正交设计所得模型的优化效果更好.改进正交设计法进一步增强了抽样效率,是适用于轨道参数优化的重要方法.

Optimization of Flight Entry Trajectory Parameters Based on Improved Orthogonal Design

The Uniformity of standard orthogonal design is improved by differential evolution method . Standard orthogonal design and Improved orthogonal design are used respectively in transition trajectory optimization design of suborbital launch vehicle. In case of the same sampling size, The estimation error of the regressive model based on standard orthogonal design can meet the precision requirement, and the regressive model based on improved orthogonal design can reduce the estimation error more than the premier model. Complex optimization method is used to search the optimization point of the two models, and the result based on the two models are both meet the demand of precision, while the result of the model based on improved orthogonal design has better optimization effect. The improved orthogonal design method increases the sampling efficiency and it is a effective method applying in optimization design of trajectory.