Relative Orbital Motion Control of Spacecraft Based on Multi-Objective Optimization

Abstract

In this paper, we consider the relative motion of a follower spacecraft orbiting the Earth in a near circular orbit with respect to a leader spacecraft. The relative orbital motion-control problem of the follower spacecraft is studied here. In order to allow the follower spacecraft to succeed in its target orbital motion maneuver, we proposed a multi-objective optimization method to solve the relative orbital motion-control problem. Firstly, a Hill–Clohessy–Wiltshire equation was used to describe the continuous relative orbital motion-control system. Then, the system was discretized into a discrete system using numerical methods. Next, a multi-objective optimization model of the relative orbital motion-control problem was formulated. In the model, two objectives, i.e., the orbital motion error and the energy consumption, were minimized simultaneously. Furthermore, the ε-constraint method was used to solve the multi-objective optimization problem and the Pareto front, which demonstrates that the trade-off between the two objectives can be achieved. Finally, numerical experiments were carried out to validate the effectiveness of the proposed multi-objective optimization approach.

Anomaly detection method for space payload parameters under telemetry command changes

“…However, the detection accuracy of this traditional approach is significantly lower. To solve this problem, researchers have proposed a series of higher accuracy anomaly detection methods [9][10][11][12][13][14] . However, these methods generally ignore the property that the values of space payload telemetry parameters vary with the CMDs given.…”