Attitude Tracking and Disturbance Rejection of Rigid Spacecraft by Adaptive Control

By Zhiyong Chen, Jie Huang. IEEE Transactions on Automatic Control, 2009

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Attitude Tracking of Rigid Spacecraft With Bounded Disturbances (2011, background): “Proof: It has been proven in [11] that for the kinematic subsystem (14), limt→∞ ev(t) = 0 can be achieved if there exists a control law for (15) satisfying limt→∞ x(t) = 0 with any initial state ‖e(0)‖ = 1.”
Attitude stabilization of rigid spacecraft with finite‐time convergence (2011, background): “In [19], attitude control is converted into a global stabilization problem of a particular type of nonlinear systems involving both disturbance and mass parameter uncertainties.”
Adaptive attitude tracking control for rigid spacecraft with finite-time convergence (2013, background): “Numerical values of tracking control Nominal inertia matrix of the spacecraft system is J0 = [20 1.2 0.9; 1.2 17 1.4; 0.9 1.4 15] kg m2 (Chen & Huang, 2009).”
Adaptive Sliding Mode Control for Attitude Stabilization With Actuator Saturation (2011, background): “1: In spacecraft model equations (1) and (2), the unit-quaternion q and the angular velocity Ω are available in the feedback control design [2], [11].”
Finite-Time Attitude Tracking Control of Spacecraft With Application to Attitude Synchronization (2011, methodology): “Then, the relative kinematic equation is given as in [4] and the relative dynamic equation is given as in [5], [8]”