Abstract
A novel finite-time control scheme is investigated for a rigid spacecraft in present of parameter uncertainties and external disturbances. Firstly, the spacecraft mathematical model is transformed into a cascading system by introducing an adaptive variable. Then a novel finite-time attitude stabilization control scheme for a rigid spacecraft is proposed based on the homogeneous method. Lyapunov stability analysis shows that the resulting closed-loop attitude system is proven to be stable in finite time without parameter uncertainties and asymptotically stable with parameter uncertainties. Finally, numerical simulation examples are also presented to demonstrate that the control strategy developed is feasible and effective for spacecraft attitude stabilization mission.
Highlights
With the development of aerospace science and technology faster and faster, for its higher technical requirements the spacecraft’s attitude control and stability got close attention and extensive research
In view of the presence of parameter uncertainty spacecraft attitude stability control system, it puts forward the category of odd theory based on the finite time control
By introducing new adaptive state variables, the spacecraft attitude control system is converted to a cascade system; a novel finite-time attitude stabilization control scheme for a rigid spacecraft is proposed based on the homogeneous method
Summary
With the development of aerospace science and technology faster and faster, for its higher technical requirements the spacecraft’s attitude control and stability got close attention and extensive research. Many scholars in this field at home and abroad have made a lot of research results, such as optimal control [1], feedback control [2], input-output approach [3], adaptive control [4], T-S fuzzy theory [5–7], sliding mode control [8, 9], data driven [10], and all this integrated control methods [11, 12] These nonlinear control methods have certain advantages and are widely used in spacecraft control, they can guarantee the stability of the closed-loop control system, and only for the equilibrium point, and the stable time is infinite. The literature [18] according to rigid satellite attitude control problem, design the existence and there is no outside interference torque under the condition of two kinds of finite time state feedback control law, Which in view of the situation without disturbances, based on the nature of nonlinear homogeneous systems, designs a kind of PD control feedback control algorithm, the position closed-loop control system of finite time convergences to equilibrium, and the method has simple structure and is convenient for application in the engineering practice. Design in this paper, finite time controller structure is simple, is easy to adjust, and has the very high practical engineering practical value
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