High-precision shape approximation low-thrust trajectory optimization method satisfying bi-objective index

作     者：Ruiye JIANG Ming YANG Songyan WANG Tao CHAO Rajan SHANKARAN Ruiye JIANG;Ming YANG;Songyan WANG;Tao CHAO;Rajan SHANKARAN

作者机构：Control and Simulation CenterHarbin Institute of TechnologyHarbin 150080China Department of ComputingMacquarie UniversitySydneyNSW 2109Australia 

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

年 卷 期：2022年第35卷第1期

页      面：436-457页

核心收录：

学科分类：08[工学] 0825[工学-航空宇航科学与技术] 

基　　金：supported by the National Natural Science Foundation of China(Nos.61627810 61790562 61403096) 

主　　题：Constrained optimization Intelligent optimization Low-thrust trajectory Multi-objective optimization Shape approximation method 

摘      要：The shape approximation method has been proven to be rapid and practicable in resolving low-thrust trajectory;however,it still faces the challenges of large deviation from the optimal solution and inability to satisfy the specific flight time and fuel mass *** this paper,a modified shape approximation low-thrust model is presented,and a novel constrained optimization algorithm is developed to solve this *** proposed method aims at settling the bi-objective optimization orbit involving the twin objectives of minimum flight time and low fuel consumption and enhancing the accuracy of optimized *** particular,a transformed high-order polynomial model based on finite Fourier series is proposed,which can be characterized as a multi-constraint optimization ***,a novel optimization algorithm is specifically developed to optimize the large-scale multi-constraint dynamical equations of shape *** key performance indicators of the index include minimum flight time,low fuel consumption and bi-objective optimization of the *** results prove that this approach possesses both the high precision achievable by numerical methods and low computational complexity offered by shape approximation ***,the Pareto front of the fuel-time bi-objective optimization orbit is firstly introduced to analyze an intact optimal solution ***,we have demonstrated that our proposed approach is appropriate to generate the preliminary orbit for pseudo-spectral method.