This paper presents the design of model predictive control (MPC) for a linear time-variant model of a CubeSat nanosatellite. The MPC controller is derived from the formulation of a linear-quadratic regulator (LQR) problem for finding a periodic gain evaluated at each sampling instant. The obtained parameters are subsequently used to formulate the MPC problem. The control law is implemented within a complex simulation environment for attitude determination and control system, which combines spacecraft dynamics and environmental models. We also use the extended Kalman filter to address the sensor fusion problem and to eliminate state estimation errors. Objective of the controller is to track a set of state references corresponding to a predefined observation trajectory. Finally, control performance is numerically demonstrated and compared with LQR.
Design of an MPC based attitude control system for a CubeSat nanosatellite
2021-06-01
1134079 byte
Conference paper
Electronic Resource
English
Design of Attitude Control Systems for CubeSat-Class Nanosatellite
Tema Archive | 2013
|CubeSat Attitude Control Simulator Design
AIAA | 2018
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