Sliding mode maneuvering control and active vibration damping of three-axis stabilized flexible spacecraft with actuator dynamics

Abstract

This paper presents a dual-stage control system design method for the three-axis-rotational maneuver control and vibration stabilization of a spacecraft with flexible appendages embedded with piezoceramics as sensor and actuator. In this design approach, the attitude control system and vibration suppression were designed separately using a lower order model. Based on the sliding mode control (SMC) theory, a discontinuous attitude control law in the form of the input voltage of the reaction wheel is derived to control the orientation of the spacecraft actuated by the reaction wheel, in which the reaction wheel dynamics is also considered from the real applications point of view. The asymptotic stability is shown using Lyapunov analysis. Furthermore, an adaptive version of the proposed attitude control law is also designed for adapting the unknown upper bounds of the lumped disturbance so that the limitation of knowing the bound of the disturbance in advance is released. In addition, the concept of varying the width of boundary layer instead of a fixed one is also employed to eliminate the chattering and improve the pointing precision as well. For actively suppressing the induced vibration, modal velocity feedback and strain rate feedback control methods are presented Q. Hu ( ) and compared by using piezoelectric materials as additional sensors and actuators bonded on the surface of the flexible appendages. Numerical simulations are performed to show that rotational maneuver and vibration suppression are accomplished in spite of the presence of disturbance torque and parameter uncertainty.

Dynamics and control of a smart flexible satellite moving in an orbit

“…They also used another technique for active vibration suppression utilizing piezoelectric materials to design a controller in the inner feedback loop and a variable structure output feedback control scheme in the outer feedback loop that was applied to control the single axis rotational maneuver of a spacecraft [20]. In 2008, a dual stage control method was presented by Hu [21] for the three-axis rotational maneuver control and vibration reduction of a flexible spacecraft with attached piezoelectric layers as sensor and actuator. The effects of orbiting were neglected in his study.…”

Sliding mode attitude control for flexible spacecraft

“…As one of the variable structure control method, sliding variable structure control is insensitive to the external disturbance which satisfied the match condition and the uncertainty of parameters, due to good robustness and other advantages, it gets a widespread application on the spacecraft attitude control [1][2][3] . However, the system chattering is an obvious weak point of the various structure control, if this chattering cannot be eliminated or weaken, then the chattering of the flexible accessory may endure for long time which greatly reduced the meaning of various structure control.…”

On attitude maneuver control of flexible spacecraft without angular velocity sensors

“…Singhose designed a robust input shaping method for limiting deflection during the attitude maneuver to reduce residual vibrations [3]. Hu proposed a control strategy based on active vibration control and sliding mode control for the large angle attitude maneuver control approach, in which the sliding mode control is applied on the central rigid body and the active vibration control is applied in an independent flexible control system by using piezoceramics as actuators and sensors [4]. Lei proposed an active disturbance rejection controller for spacecraft attitude control system was designed to estimate and compensate external disturbance [7].…”