Robust control of a spin-stabilized spacecraft via a 1DoF gimbaled-thruster and two reaction wheels.
In impulsive orbital maneuvers, thrust vector misalignment from the center of mass (C.M) results in a large disturbance torque. In this paper a thrusting maneuver system is proposed and studied which is based on the combination of a one degree of freedom (1DoF) gimbaled-thruster, two reaction wheels (RWs) and spin-stabilization. The main goals are disturbance rejection and thrust vector stabilization without using reaction control systems (RCS). The nonlinear two-body dynamics of the proposed system is formulated. The controller design is formulated as a multi-objective optimization problem where the peak-value of the control input and H∞performance are the cost functions. Based on the peak-to-peak gain minimization, the accuracy of the linearized model can be guaranteed. The optimization results give many optimal controllers which are acceptable for a thrusting maneuver. The simulation results illustrate the applicability of the proposed method in presence of the sampling effects of the control inputs.
Department of Mechanical Engineering, Amirkabir University of Technology, 424 Hafez Ave, Tehran 15875-4413, Iran. Electronic address: h_kouhi@aut.ac.ir.
Hamed
H
Kouhi
Department of Mechanical Engineering, Amirkabir University of Technology, 424 Hafez Ave, Tehran 15875-4413, Iran. Electronic address: kabgan@aut.ac.ir.
Mansour
M
Kabganian
Space Science and Technology Institute, Amirkabir University of Technology, 424 Hafez Ave, Tehran 15875-4413, Iran. Electronic address: f.sabery@aut.ac.ir.
Farhad Fani
FF
Saberi
Space Research Institute, Tehran 15875-1774, Iran. Electronic address: shahravim@yahoo.com.
Morteza
M
Shahravi
Disturbance rejection; Gimbaled-thruster; Impulsive orbital maneuver; Reaction wheel; Spin-stabilization; Thrust vector stabilization; Worst-case output magnitude