Finite‐time attitude tracking control and vibration suppression for flexible spacecraft

Abstract

In this paper, an adaptive multivariable continuous terminal sliding mode (CTSM) controller with robust input shaper (RIS) is proposed for flexible spacecraft under model uncertainty and external disturbance. Firstly, for the problem of flexible vibration introduced by flexible appendage, the RIS based on disturbance observer is designed. The proposed input shaper can eliminate the flexible vibration effectively even if there are some disturbances in flight. Then, an adaptive multivariable CTSM controller is proposed for attitude tracking of flexible spacecraft, using only information about the output and its first derivative. The features of the developed methods are that it is continuous multivariable controller which attenuates the chattering effectively and the attitude tracking can be achieved in finite time. The stability and robustness properties of the system are proven using Lyapunov function. Finally, some numerical simulations are performed to validate the efficiency of the developed algorithm.

Fast fixed‐time attitude tracking control of spacecraft with prescribed performance

“…and lim t→0 ̇𝜌i (t)𝜎 ei 𝜌 i (t) ≠ 0. Therefore, the initial value of the controller designed by the new function (7) is smaller than that of the traditional exponential performance function. Meanwhile, the prescribed performance function (7) has the following properties: (I)…”

“…The finite-time controllers were designed mainly by using homogeneous theory 6 or Lyapunov method. 7,8 A homogeneous method-based attitude control scheme was presented to stabilize the attitude control system within finite time even in the presence of the actuator saturation. 6 A velocity-free spacecraft attitude stabilization controller was proposed directly by using Lyapunov stability theory.…”

Anti‐unwinding nonsingular terminal sliding mode control with attitude maneuver planning for flexible spacecraft

“…22 Thus, the terminal manifold was designed to achieve finite-time convergence for flexible spacecraft. [23][24][25] In Reference 23, a finite-time attitude tracking control scheme was presented for rigid spacecraft by constructing a terminal sliding manifold. In Reference 24, by using the homogeneous approach, a global finite-time attitude stabilizing controller was designed for rigid spacecraft.…”

“…The above sliding manifolds can guarantee asymptotic convergence of the system states to equilibrium, but not in finite time 22 . Thus, the terminal manifold was designed to achieve finite‐time convergence for flexible spacecraft 23‐25 . In Reference 23, a finite‐time attitude tracking control scheme was presented for rigid spacecraft by constructing a terminal sliding manifold.…”

“…In Reference 24, by using the homogeneous approach, a global finite‐time attitude stabilizing controller was designed for rigid spacecraft. In Reference 25, a continuous terminal sliding mode controller using a terminal sliding manifold was developed for flexible spacecraft in the presence of external disturbances. In Reference 26, a new fast terminal sliding manifold was developed for multiple spacecraft formation flying, and two novel decentralized finite‐time control laws were proposed to force the spacecraft attitude error dynamics to converge to small regions in finite time.…”