Optimal multi-segment trajectory of solar sail with analytical approximation

被引:0
|
作者
Qi, Ji [1 ]
Jin, Ruhao [1 ]
Zhao, Ce [1 ]
Gao, Zhibo [1 ]
Feng, Wenyu [1 ]
Fan, Zichen [1 ]
Huo, Mingying [1 ]
机构
[1] Harbin Inst Technol, Harbin 150001, Peoples R China
基金
美国国家科学基金会; 中国国家自然科学基金;
关键词
Solar sail; Analytical approximation; Multi-target exploration; Fixed pitch angle; LOW-THRUST; PRELIMINARY DESIGN; ELECTRIC SAIL;
D O I
10.1016/j.ast.2024.109384
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
This paper focuses on the optimization of two-dimensional transfer trajectories for solar sails using analytical approximation and modified analytical approximation methods. Instead of assuming circular orbits [29-31,37], the proposed approach allows for the analysis of solar sails launched from general heliocentric elliptical orbits. By employing linear perturbation theory, analytical propelled trajectories with fixed pitch angles are derived, where the perturbation coefficient serves as the reference lightness coefficient. To obtain the optimal transfer orbit between general heliocentric elliptical orbits, the analytical segments corresponding to different pitch angles are spliced together. A nonlinear optimization algorithm is then utilized to optimize the multi-segment trajectory, aiming to achieve the optimal performance index while satisfying boundary and intermediate constraints. Remarkably, this method requires the optimization of only the pitch angle for each segment, resulting in a small number of optimization variables and significantly improved efficiency in transfer orbit optimization. Additionally, the analytical approximation approach offers substantial time savings compared to numerical integration, particularly when repeated calculations are involved. Furthermore, the modified approximate trajectory exhibits high accuracy, with the optimal analytical transfer trajectory closely approximating the optimal actual trajectory acquired through the shooting method. This paper extensively validates and analyzes the precision of the proposed analytical transfer orbit through numerical verification. Additionally, when contrasted with actual transfer orbit, the suggested analytical approach can significantly decrease the computation time for multi-object challenges by a minimum of 80%. This makes the proposed method highly suitable for rapid design of optimal transfer orbits in multi-target mission scenarios for solar sail-based probes.
引用
收藏
页数:10
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