Abstract
Swing usually occurs in the maneuver process of a tethered combination, which is constituted of a platform, a tether and a target (i.e., space debris) for capture. Therefore, a dynamical model of the space tethered combination was established, based on the maneuver of the mission platform in a short time. The conditions for the three swing formations of the tethered combination were obtained according to the analysis of the dynamical model. In order to solve the swing problem, anti-swing control strategies, based on linear feedback control, approximate linearization control and variable structure control, were proposed, respectively. Furthermore, simulation results verified the correctness and effectiveness of the above strategies. To test the validity of the control strategies, a ground experiment setup was built according to the similarity of dynamics. The experimental results show that linear feedback control and approximate linearization control can suppress the in-plane and out-of-plane swing of the combination rapidly.
Highlights
With the increase of human aerospace activities, space debris problems become more and more pronounced
In order to meet the requirements of non-cooperative target capture tasks, the concept of flexible capture has gradually entered human vision, which covers the target with flexible structures, and forms a reliable combination with the mission spacecraft through a flexible tether
L = − m − ax cos φ sin θ − a y sin φ − az cos φ cos θ + lθ cos φ + lφ According to Equation (1), the in-plane swing angle θ and the out-of-plane swing angle φ are coupled with each other, and the motion of the space tethered combination in the maneuver process is
Summary
With the increase of human aerospace activities, space debris problems become more and more pronounced. The severity and frequency of the disintegration events will increase with the mass and cross section area of the orbiting objects Based on this situation, the active removal technology of non-cooperative targets, such as space debris, has become one of the hotspots in the field of space research [2,3,4]. Whatever the flexible capture system, in the maneuver process for the space tethered combination after target capture, the physical phenomena of collision, swing, tumbling and recombination between. Some research on the swing analysis and control of the space tethered combination has been conducted. A dynamical model of the space tethered combination, based on the maneuver of the mission platform, was established. The ground experiment setup was built to test the control strategies
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