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Introduction
Published in Yaguang Yang, Spacecraft Modeling, Attitude Determination, and Control Quaternion-based Approach, 2019
Chapter 15 considers coupled orbit and attitude control that is the key technology for spacecraft rendezvous and soft docking. Coupled orbit and attitude control is an extensively studied problem with renewed interest because of installations of powerful on-board computers, availability of advanced theoretical results, and requirements for better performance in future missions. The method considered in this chapter addresses a fundamental requirements for soft docking, i.e., there is no oscillation crossing the horizontal line for relative position and relative attitude between chaser and target spacecraft to avoid collision during the docking process.
Aerial Cranes
Published in Jie Huang, Nonlinear Dynamics and Vibration Control of Flexible Systems, 2023
Dynamics and control of multiple quadrotors slung a liquid tank have been reported in the previous literature. However, the quadrotor attitude was ignored, and the complex sloshing dynamics were simplified as the equivalent mass-spring model. The dynamics of vehicle attitude is critical for safe flight. Moreover, the equivalent mass-spring model of sloshing dynamics cannot describe the complex attitude-pendulum-sloshing dynamics. Therefore, no attention has been directed at the coupled dynamics among the vehicle attitude, container swing, and liquid sloshing because of complex dynamics in the quadrotor slung liquid tank.
Aerospace Controls
Published in William S. Levine, Control System Applications, 2018
M. Pachter, C. H. Houpis, Vincent T. Coppola, N. Harris McClamroch, S. M. Joshi, A. G. Kelkar, David Haessig
Another important class of actuators used for attitude control are reaction wheel devices. Typically, balanced reaction wheels are mounted on the spacecraft so that their rotational axes are rigidly attached to the spacecraft. As a reaction wheel is spun up by an electric motor rigidly attached to the spacecraft, there is a reaction moment on the spacecraft. These three reaction moments provide the control moments on the spacecraft. In some cases, the effects of the electric motor dynamics are significant; these dynamics are ignored in this chapter.
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.
H ∞ inverse optimal attitude tracking on the special orthogonal group SO(3)
Published in International Journal of Control, 2022
Farooq Aslam, M. Farooq Haydar
Rigid-body attitude control is an extensively studied control problem with numerous applications in aircraft, spacecraft, robotics, and marinesystems. Different attitude parametrizations, or coordinates, have been used to develop a wide array of attitude control methods. Among these, the rotation matrix or direction cosine matrix (DCM), an element of the Special Orthogonal Group , is the only attitude representation which is both globally defined and unique (Chaturvedi et al., 2011). Other attitude representations either contain singularities (e.g. Euler angles, exponential coordinates, Rodrigues parameters) due to which they are not globally defined, or provide a non-unique attitude representation (e.g. quaternions, axis-angle representation) where two different coordinates describe the same attitude. In the case of quaternions, the resulting ambiguity in attitude representation can lead to unwinding (Chaturvedi et al., 2011). This is when a rigid-body is initially close to the desired orientation and yet rotates through a large angle before returning to the desired orientation.
Extended state observer-based attitude fault-tolerant control of rigid spacecraft
Published in International Journal of Systems Science, 2018
Lijian Yin, Yuanqing Xia, Zhihong Deng, Baoyu Huo
Aerospace technology, which is the integration of mechanics, thermodynamics, automatic control, jet propulsion and other disciplines, is one of the most conspicuous projects in modern society. Attitude control, as one of the most important part, has attracted more and more scholars' attention in recent years. The attitude control of spacecraft includes attitude stabilisation and attitude tracking problems (Li, Ding, & Li, 2009; Tsiotras, 1996; Wen & Kreutz-Delgado, 1991). In this paper, we focus on the attitude tracking control. Many methods were proposed to solve these problems, such as sliding mode control (SMC) (Pukdeboon, Zinober, & Thein, 2010), nonlinear feedback control (Xing & Parvez, 2001), optimal control (Luo, Chu, & Ling, 2005), adaptive control (Chen & Huang, 2009; Chen, Shi, Na, Ren & Nan 2018), robust control (Li & Wang, 2007; Chen, Ren, Na & Zheng, 2016) and so on.