A time-fuel hybrid optimal guidance for micro/nano satellite’s glideslope approach

Aimed at the trajectory planning problem of micro/nano satellites’ approaching missions under multiple constraints, this paper proposes a V-bar glideslope maneuver optimization method considering both time and fuel consumption. A dual-objective trajectory optimization model is established based on t...

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Bibliographic Details
Published in:Journal of physics. Conference series Vol. 2764; no. 1; pp. 12046 - 12055
Main Authors: Zeng, Nengwei, Xu, Gen, Chen, Danhe, Liu, Xingchuan, Lu, Zhengliang
Format: Journal Article
Language:English
Published: Bristol IOP Publishing 01.05.2024
Subjects:
Algorithms
Constraints
Energy consumption
Equations of motion
Fuel consumption
Maneuvers
Optimization
Optimization models
Satellites
Trajectory optimization
Trajectory planning
ISSN:1742-6588, 1742-6596
Online Access:Get full text
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Summary:Aimed at the trajectory planning problem of micro/nano satellites’ approaching missions under multiple constraints, this paper proposes a V-bar glideslope maneuver optimization method considering both time and fuel consumption. A dual-objective trajectory optimization model is established based on the CW motion equation, considering the constraints of trajectory and impulse. The optimal solution set of the glideslope point position and maneuvering time is obtained by employing the NSGA2 algorithm. In order to reduce computational complexity, a method for simplifying trajectory optimization is proposed. By solving a constrained dual-impulse optimization problem, the feasible range of distance and transfer time between adjacent glideslope points are obtained, which transforms the constraint equations of the glideslope maneuver optimization into the search space of optimization variables. The problem is simplified to an unconstrained optimization problem. Finally, a simulation is conducted with the approaching mission of a typical micro/nano satellite. The results demonstrate that the proposed method can provide an optimal solution set considering both fuel and time consumption, offering a flexible maneuver planning strategy for on-orbit application.
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ISSN:1742-6588
1742-6596
DOI:10.1088/1742-6596/2764/1/012046