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Force-System Resultants and Equilibrium
Published in Richard C. Dorf, The Engineering Handbook, 2018
Most spacecraft require attitude stabilization to point antennas, properly orient solar arrays, point sensors, and orient thrusters. Attitude control consists of sensing the current attitude of the spacecraft and applying torques to reorient the spacecraft to a desired attitude.
Output feedback model predictive control of spacecrafts based on proportional-integral observer
Published in Systems Science & Control Engineering, 2022
Attitude control system plays a very important role in the space missions, providing spacecrafts with capabilities of maneuvering, tracking and pointing. As we know, the motion equation of a spacecraft is highly nonlinear, and there is coupling between the channels. Especially, the nonlinearity and coupling are more serious in the case of large attitude angles, which makes it very difficult to apply the linear control theory to controller design directly. Up to now, various nonlinear control algorithms have been applied to spacecrafts, such as sliding mode control (Pukdeboon, 2016; Pukdeboon & Kumam, 2015), finite time control (Du et al., 2011; Zou et al., 2017), robust control (Wang & Xue, 2017) and backstepping control (Sun et al., 2017). Generally, the nonlinear design is more complicated than the linear design. In order to make the linear design for spacecrafts, a feasible way is to apply the feedback linearization technique to the nonlinear dynamics (Liu et al., 2016; Yin et al., 2016). However, the linearization procedure involves a lot of calculations, such as the Lie derivative operation.
Continuous precise predefined-time attitude tracking control for a rigid spacecraft
Published in International Journal of Control, 2023
Wencong Wang, Mingshan Hou, Yikai Fu, Bojun Liu
Spacecraft attitude control plays important role in many aerospace missions, such as weather forecast, satellite navigation, deep-space operation and spacecraft formation flying (Du et al., 2020). Thus, much attention has been paid by academic and industrial communities in past decades, and numerous advanced control approaches have been developed, such as PID control method (Su & Cai, 2011), control methods (Kang, 1995; Luo et al., 2005), optimal control method (Carrington & Junkins, 1986), adaptive control method (Lee, 2017), sliding mode control method (Zou, 2016) and backstepping control method (Guo et al., 2017), etc.
An effective approach to identify the mass properties of a satellite attitude dynamics simulator
Published in Australian Journal of Mechanical Engineering, 2020
Ghasem Sharifi, Ehsan Zabihian
Difficulties in changing the structure and reconfiguration of the satellite in space lead to ground simulation and testing in order to increase the probability of mission success. During the three past decades satellite attitude control simulators have been markedly used to test and validate the system performance in a circumstances similar to their real work conditions. This procedure has remarkably impact on the elimination of devices errors and improvement the control algorithms. It’s undeniable fact that Rigorous ground testing of satellite dynamics will significantly reduce various risks of the mission.