基于试验设计的无人机火箭助推起飞参数敏感性分析与优化  

Sensitivity analysis and optimization of UAV rocket booster launch parameters based on DOE

作　　者：赵志俊 拜莉莎 孟祥喆 ZHAO Zhijun;BAI Lisha;MENG Xiangzhe(Chinese Flight Test Establishment,Xi’an 710089,China)

机构地区：[1]中国飞行试验研究院,陕西西安710089

出　　处：《飞行力学》2024年第1期89-94,共6页Flight Dynamics

摘　　要：针对火箭助推起飞参数敏感性分析和优化问题,提出了田口法结合响应曲面法的试验设计(DOE)分析方法。首先,基于田口法生成正交试验表,仿真计算各试验样本下助推火箭脱落时无人机的离地高度、速度、俯仰角和俯仰角速度等响应变量,通过极差分析确定各起飞参数敏感性和重要度排序。然后,基于响应曲面法建立回归数学模型,给出起飞参数多目标组合优化和允许误差边界预测结果。最后,通过试飞验证了该方法的合理性和可行性。所提方法可为无人机火箭助推起飞参数敏感性分析和优化提供参考。Aiming at the problem of sensitivity analysis and optimization of UAV rocket booster launch parameters,design of experiment(DOE)based on Taguchi method and response surface method(RSM)was proposed.Firstly,based on Taguchi method,the orthogonal test table was generated,and the response variables such as altitude,velocity,pitch angle and pitch angle velocity when the test booster rocket falling off were simulated and calculated.The sensitivity and importance of each launch parameters were determined through range analysis.Secondly,the regression mathematical model was established based on RSM,and the results of multi-objective combination optimization and allowable error boundary prediction of launch parameters were given.Finally,the rationality and feasibility of this method was verified by flight test.The proposed method provides some reference for the sensitivity analysis and optimization of UAV rocket booster launch parameters.

关 键 词：无人机火箭助推发射 试验设计 田口法 响应曲面法 

分 类 号：V271.4[航空宇航科学与技术—飞行器设计]