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Abstract
This paper investigates the robust finite-time rendezvous maneuver control for spacecraft via sliding mode control technology. Two control architectures are devised for realizing the control objective, where a novel-developed sliding mode surface (SMS) is designed by resorting to the hyperbolic tangent function. Without considering the chattering problem inherent in sliding mode control, a basis control scheme is constructed to force the tracking errors entering a compact set in finite time. To reduce the effect of the chattering phenomenon, a modified controller is established by resorting to the well-designed adaptive laws. Both of these two controllers can ensure finite-time convergence for the entire system. Theoretical analysis and numerical simulations have shown the effectiveness and superiorities of the proposed methods.
Highlights
For the indispensable role in numerous space activities, including docking, removing space debris, Mars exploration, etc., spacecraft rendezvous maneuver control has gained popularity during the last decades
Fruitful research achievement for spacecraft control has emerged recently, such as adaptive control [1]–[4], [32], backstepping control [5]–[8], neural network-based control [9]–[12], sliding mode control (SMC) [13]–[16], model predictive control [31] as well as control based on hybrid actuators [35]
A basic control scheme is presented to guarantee that the sliding mode surface (SMS) could be stabilized in finite time. Though it is effective for the rendezvous task, chattering problem is a threat to the safety of the actuators
Summary
For the indispensable role in numerous space activities, including docking, removing space debris, Mars exploration, etc., spacecraft rendezvous maneuver control has gained popularity during the last decades. Considering that the mass and initial matrix of the pursuer spacecraft are unknown for designers, Zhang et al have proposed output feedback controllers for relative pose control problem during rendezvous maneuver [20]. Z. Shi et al.: Hyperbolic Tangent Function-Based Finite-Time SMC for Spacecraft Rendezvous Maneuver Without Chattering artificial potential function-based SMC and backstepping control has been presented in [21] and [22], respectively. In [24], nonsingular terminal sliding mode control technology (NTSMCT) was utilized to solve the control issue for spacecraft rendezvous maneuver by incorporation with a finite-time disturbance observer. The finite-time rendezvous control for spacecraft will be investigated with the consideration of chattering problem in sliding mode control.
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