Abstract
Considering the scenario that the obstinate and difficult-repaired sensor and actuator failure always occurs during the spacecraft rendezvous guidance phase and may cause terrible performance, this paper studies the fault-tolerant guidance method and proposes a velocity-free guidance algorithm. Above guidance law is based on a dual-layer adaptive multi-variable super-twisting-like algorithm, where two waving gains are introduced to autonomously adjust the system trajectory subject to the relative velocity. Hence, the complex parameter selection problem is overcome. Moreover, to overcome the sensor fault in relative-velocity channel, a robust observer which can drive the velocity error converge to zero in a small finite time is presented. To test the effectiveness and stability of the proposed guidance law, considering actuator faults, second-order dynamics and saturation, numerical simulations including comparisons and Monte-Carlo are carried out and the results demonstrate above properties.
Highlights
Spacecrafts reliable autonomous rendezvous guidance is still a hot topic and a key technology in on-orbit docking and servicing missions [1]–[6]
During the process of rendezvous, the chaser spacecraft requires the relative position and its rate between itself and the target in real time, and generates the desired control command and sends it to the actuators, until it arrives in the target with the same velocity
For close-range closing phase, the wellknown Clohessy-Wiltshire (C-W) differential equations [8] and Tschauner-Hempel (T-H) differential equations [9] were proposed at the middle of 20th century (C-W equations in 1959 and T-H equations in 1965) and used to describe relative dynamics for circular target orbit and elliptical target orbit, respectively
Summary
Spacecrafts reliable autonomous rendezvous guidance is still a hot topic and a key technology in on-orbit docking and servicing missions [1]–[6]. Considering the obstacle avoidance, [22] provided a sub-optimal artificial potential function sliding mode control (SMC) based guidance law for safety proximity Other techniques such as backstepping design [23], θ − D method [2], [24], [25], state dependent Riccati equation (SDRE) technique [26] and SMC theory contributed much on rendezvous law design. A dual-layer adaptive super-twisting-like (STL) algorithm for elliptical orbital reliable spacecraft rendezvous is proposed in the presence of external disturbance, actuator failure and input saturation. Considering the actuator faults are difficult to repair during rendezvous phase, a fault-tolerant guidance algorithm which holds a dual-layer STL structure and can autonomously adjust its parameters is proposed in this paper.
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