Abstract
In this paper, a bounded finite-time control strategy is developed for the final proximity maneuver of spacecraft rendezvous and docking exposed to external disturbance and input quantization. To realize the integrated control for spacecraft final proximity operation, the coupling kinematics and dynamics of attitude and position are modeled by feat of Lie group SE 3 . With a view to improving the convergence rate and reducing the chattering, an adaptive finite-time controller is proposed for the error tracking system with one-step theoretical proof of stability. Meanwhile, the hysteresis logarithmic quantizer is implemented to effectively reduce the frequency of data transmission and the quantization errors are reduced under the proposed controller. The algorithms outlined above are based on an integrated model expressed by SE 3 and denoted by uniform motion states, which can simplify the design progress and improve control precision. Finally, simulations are provided to exhibit the effectiveness and advantages of the designed strategy.
Highlights
Spacecraft rendezvous and docking (RVD) technology has been successfully applied in many space missions, including space station installation and operation and deep space exploration [1,2,3]
In this paper, we denote to designing a finite-time terminal SMC (TSMC) scheme for spacecraft RVD subject to external disturbance and input quantization
An hysteretic logarithmic quantizer (HLQ) is adopted in this paper to validate the feasibility of the proposed quantized TSMC scheme
Summary
Spacecraft rendezvous and docking (RVD) technology has been successfully applied in many space missions, including space station installation and operation and deep space exploration [1,2,3]. (iii) The quantized control is first applied to the final proximity maneuver of spacecraft RVD modeled by Lie group SEð3Þ. We present the kinematics and dynamics models of a spacecraft’s motion around the earth and obtains the relative motion model of attitude and position tracking systems denoted by Lie group SEð3Þ. In order to tackle the problem of an integrated description of relative translation and rotation, the configuration space of rigid spacecraft motions can be denoted by the special Euclidean group SEð3Þ. Relative Dynamical Model for Spacecraft Proximity Operation It defines the relative configuration and desired relative configuration between the chaser and the target to be h ∈ SEð3Þ and hf ∈ SEð3Þ. By combining the relative kinematics expressed by exponential coordinate in (20) and the relative acceleration equation in Equation (23), the coupled error tracking system of spacecraft final proximity maneuvers is established
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