Indirect optimal control techniques for multimode propulsion mission design

被引:0
作者
Cline, Bryan C. [1 ]
Pascarella, Alex [1 ]
Woollands, Robyn M. [1 ]
Rovey, Joshua L. [1 ]
机构
[1] Univ Illinois, Dept Aerosp Engn, Talbot Lab, 104 S Wright St, Urbana, IL 61801 USA
关键词
Multimode propulsion; Optimal control; Trajectory design; Trajectory optimization; Mission design; OPTIMAL TRAJECTORY DESIGN; MULTIPLE OPERATION MODES; ORBIT TRANSFERS; OPTIMIZATION; SYSTEM;
D O I
10.1016/j.actaastro.2024.07.020
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
Multimode spacecraft propulsion has the potential to greatly increase the maneuvering capability of spacecraft in comparison to traditional architectures. This technology combines two or more propulsive modes (e.g., chemical and electric) into a single system with a single propellant. Trajectory design techniques for spacecraft with this capability, however, are presently limited and typically require manual selection of the burn sequence. In this study, indirect optimal control formulations with automatic mode selection are developed and applied for the first time to multimode spacecraft with two modes of propulsion. Minimum-fuel transfers are solved using polar coordinates as well as using Modified Equinoctial Elements with perturbations. Propellant- constrained minimum-time problems are also solved for the first time using a penalty function approach. An interior-point constraint formulation is also provided. Sample transfers are developed for each coordinate choice and optimization objective and are compared to trajectories that use a single mode of propulsion. The results demonstrate viability of the proposed techniques and show that the multimode approach can reduce the time-of-flight in comparison to a low-thrust only trajectory while providing mass savings over high-thrust only solutions.
引用
收藏
页码:759 / 776
页数:18
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