دانلود رایگان مقاله نفوذ انعطاف پذیری بر ثبات منفعل بادبان خورشیدی در حال چرخش

Abstract

The attitude passive stability design during inclination cranking is developed using a rigid solar sail model. The criterion shows that the solar sail can be stabilized by designing the structure parameters and the spin rate. An oscillation–attitude–orbit dynamical model by hybrid method is employed to quantify the flexibility effect on the passive station keeping. The simulation results indicate that the oscillation has an obvious impact on the attitude and orbit. The oscillation effect is reduced as the spin rate increases, which means a larger spin rate is required to stable the attitude for a flexible solar sail than the rigid one. For some certain spin rates, the passive stability criterion obtained from the rigid model may become invalid. The comparative simulations are implemented to explain this phenomenon by noting the fact that the flexible structural parameter and the solar radiation pressure torque due to sail vibration are different from the rigid one.

4. Conclusion

In this paper, the general passive stability design criterion of a flexible solar sail is investigated. As a design model, the passive station keeping during the inclination cranking of a spinning solar sail is developed using a rigid model. The design criterion shows that the required stable attitude of solar sail can be obtained passively by adjusting the cm/cp offset and the spin rate. A modal reduced oscillation–attitude–orbit model for spinning solar sail is developed to analyze the impacts of sail oscillation and the attitude–orbit coupling. The total time-varying SRP force experienced by the deformed sail is considered using the FE based method. The study indicates that the attitude–orbit coupling effect referred in this paper during the inclination cranking is tiny, whereas the oscillation has an obvious impact on the attitude and orbit of the solar sail under a certain spin rate. In the case of considering the oscillation, the original passive stability criterion by the rigid model may become invalid. The reasons of the oscillation influence are investigated via comparative simulations. The results indicate that the SRP torque due to the sail deformation and the variation of structural parameter of a flexible solar sail are the two main causes to influence the attitude and orbit. Attempt to stabilize the flexible solar sail is proposed, which is increasing the spin rate and the cm/cp offset.