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- W2393465526 abstract "For the rigid spacecraft attitude control problem,a method for designing the finite time controllers is proposed in this paper controllers are analyzed in the absence of disturbance and in the presence of disturbance.For the first case,based on the property of the nonlinear homogeneous system,a continuous and non-singular proportional-derivative(PD) controller is proposed to achieve the finite time convergence of the closed-loop attitude control system,and can be extended to the spacecraft attitude tracking problem.For the second case,we design a new continuous and non-singular controller is design on the basis of Lyapunov finite time theorem,such that the spacecraft attitude and angular velocity converge to a small neighborhood of the equilibrium point.If the disturbance vanishes,all the states will converge to the origin eventually.Last,numerical simulation is conducted to demonstrate the effectiveness of our proposed controller." @default.
- W2393465526 created "2016-06-24" @default.
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- W2393465526 date "2011-01-01" @default.
- W2393465526 modified "2023-09-22" @default.
- W2393465526 title "Finite Time Stabilization Method for the Rigid Spacecraft Attitude Control" @default.
- W2393465526 hasPublicationYear "2011" @default.
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