Uncertainty analysis and design optimization of hybrid rocket motor powered vehicle for suborbital flight

作     者：Zhu Hao Tian Hui Cai Guobiao Bao Weimin 

作者机构：School of Astronautics Beihang University China Aerospace Science and Technology Corporation 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2015年第28卷第3期

页      面：676-686页

核心收录：

学科分类：080703[工学-动力机械及工程] 082502[工学-航空宇航推进理论与工程] 08[工学] 0807[工学-动力工程及工程热物理] 0825[工学-航空宇航科学与技术] 

基　　金：supported by the National Natural Science Foundation of China(No.51305014) China Postdoctoral Science Foundation(No.2013M540842) 

主　　题：Design optimization Hybrid rocket motor Kriging model Uncertainty analysis Uncertainty-based designoptimization 

摘      要：Abstract In this paper, we propose an uncertainty analysis and design optimization method and its applications on a hybrid rocket motor （HRM） powered vehicle. The multidisciplinary design model of the rocket system is established and the design uncertainties are quantified. The sensitivity anal- ysis of the uncertainties shows that the uncertainty generated from the error of fuel regression rate model has the most significant effect on the system performances. Then the differences between deterministic design optimization （DDO） and uncertainty-based design optimization （UDO） are discussed. Two newly formed uncertainty analysis methods, including the Kriging-based Monte Carlo simulation （KMCS） and Kriging-based Taylor series approximation （KTSA）, are carried out using a global approximation Kriging modeling method. Based on the system design model and the results of design uncertainty analysis, the design optimization of an HRM powered vehicle for suborbital flight is implemented using three design optimization methods： DDO, KMCS and KTSA. The comparisons indicate that the two UDO methods can enhance the design reliability and robustness. The researches and methods proposed in this paper can provide a better way for the general design of HRM powered vehicles.