Effect of Attitude Control on a Periodic Orbit Maintenance of Solar Sail in Earth-Moon Circular Restricted 3-Body Problem

摘要

This paper aims to study how the transient process of attitude control affect the orbit dynamics for solar sail, and investigate the method to design specification for attitude control to maintain the periodic orbit in Earth-Moon Circular Restricted 3-Body problem. An asymmetric periodic orbit around L1 Lagrange point is designed as the nominal orbital trajectory by solving a two-point boundary value problem. To describe the transient process of attitude control for solar sail, a first-order reference model is proposed considering the initial angular error and time-delay behavior of the attitude control system. A series of numerical experiments are designed based on the proposed model, where the effects of two model parameters are investigated respectively. The orbital deviations due to the cone angle and clock angle are also compared in detail to study the different effects from two attitude angles. The simulation results show that the effect of maximum attitude angular rate is much more significant than that of the initial angular errors and the cone angle has a dominant impact compared to the clock angle. At last, the specification design method for attitude control system is given based on the simulation results.