Thrusting maneuver control of a small spacecraft via only gimbaled-thruster scheme |
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Authors: | Mansour Kabganian Hamed Kouhi Morteza Shahravi Farhad Fani Saberi |
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Affiliation: | 1. Department of Mechanical Engineering, Amirkabir University of Technology, 424 Hafez Ave, Tehran 15875-4413, Iran;2. Space Research Institute, Tehran 15875-1774, Iran;3. Space Science and Technology Institute, Amirkabir University of Technology, 424 Hafez Ave, Tehran 15875-4413, Iran |
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Abstract: | The thrust vector control (TVC) scheme is a powerful method in spacecraft attitude control. Since the control of a small spacecraft is being studied here, a solid rocket motor (SRM) should be used instead of a liquid propellant motor. Among the TVC methods, gimbaled-TVC as an efficient method is employed in this paper. The spacecraft structure is composed of a body and a gimbaled-SRM where common attitude control systems such as reaction control system (RCS) and spin-stabilization are not presented. A nonlinear two-body model is considered for the characterization of the gimbaled-thruster spacecraft where, the only control input is provided by a gimbal actuator. The attitude of the spacecraft is affected by a large exogenous disturbance torque which is generated by a thrust vector misalignment from the center of mass (C.M). A linear control law is designed to stabilize the spacecraft attitude while rejecting the mentioned disturbance torque. A semi-analytical formulation of the region of attraction (RoA) is developed to ensure the local stability and fast convergence of the nonlinear closed-loop system. Simulation results of the 3D maneuvers are included to show the applicability of this method for use in a small spacecraft. |
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Keywords: | Orbital maneuver Small spacecraft Gimbaled-SRM Two-body dynamics Thrust vector misalignment Region of attraction |
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