Abstract
The release and retrieval of a CubeSat from a big spacecraft is useful for the external inspection and monitoring of the big spacecraft. However, docking maneuvers during the retrieval are challenging since safety constraints and high performance must be achieved, considering the small dimensions and the actual small satellites technology. The trajectory control is crucial to have a soft, accurate, quick, and propellant saving docking. The present paper deals with the design of a tracking model predictive controller (TMPC) tuned to achieve the stringent docking requirements for the retrieval of a CubeSat within the cargo bay of a large cooperative vehicle. The performance of the TMPC is verified using a complex model that includes non-linearities, uncertainties of the CubeSat parameters, and environmental disturbances. Moreover, 300 Monte Carlo runs demonstrate the robustness of the TMPC solution.
Highlights
CubeSats and nanosatellites missions have gained the attention of the main actors in the space field [1]
One of the most interesting and challenging types of missions is the inspection and monitoring of orbiting spacecraft/targets, such as the International Space Station [2], the Lunar Gateway [3], as well as operative [4] and not operative [5] big satellites. These missions for inspection require a set of maneuvers for rendezvous, proximity operations and, in case, docking with the Target, as shown in [6]
Severe safety constraints and high-performance requirements are the main drivers of a retrieval phase
Summary
CubeSats and nanosatellites missions have gained the attention of the main actors in the space field [1]. One of the most interesting and challenging types of missions is the inspection and monitoring of orbiting spacecraft/targets, such as the International Space Station [2], the Lunar Gateway [3], as well as operative [4] and not operative [5] big satellites. These missions for inspection require a set of maneuvers for rendezvous, proximity operations and, in case, docking with the Target, as shown in [6]. The spacecraft shall avoid any possible collision with the Target, i.e., (1) maintaining its trajectory out of a safety ellipse during the inspection phase [6], (2) guaranteeing passive safe trajectories in case of misbehaviors or off-nominal conditions, and (3) moving away from the Target in case of risk of collision with quick maneuvers
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