Abstract Separation and reconfiguration of stacked satellites in orbit is an effective method for constructing large space structures. This paper investigates the dynamics of a stacked satellite system (SSS) during the separation and reconfiguration process. Firstly, the dynamic model of the SSS is established via the natural coordinate formulation (NCF) to conveniently handle the time-varying constraints between satellites. Then, the separation and reconfiguration strategies are proposed for the SSS including the reconstruction step between two configurations. To ensure collision-free satellite assembly, a proportional differential (PD) controller combined with a potential function is introduced. Additionally, a docking mechanism is designed, considering collision force constraints during satellite docking assembly. Finally, several numerical simulations are conducted to demonstrate the effectiveness of the separation and assembly strategies.
Highlights An orbital dynamic model of a stacked satellite system (SSS) is established. A collision detection algorithm for the docking mechanism is introduced. A PD controller law for the collision-free assembly of satellites is designed. The dynamics for reconfiguration and assembly of the SSS is studied.
Dynamics of reconfiguration and assembly of a stacked satellite system
Acta Astronautica ; 218 ; 367-382
2024-02-28
16 pages
Article (Journal)
Electronic Resource
English
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