A Fast Analytical Prediction Method for Orbit-Attitude Performance of Solar Sails in LEO Including Air Drag and Eclipses

Abstract

Low Earth orbit (LEO) has become a proving ground for advanced solar sailing missions. The combination of solar radiation pressure thrust and active attitude control enables various fuel-free orbital maneuvers. However, it is challenging to accurately predict the orbit of a LEO solar sail during early-stage mission design. The sail is highly sensitive to solar radiation pressure and air drag, both of which are strongly time-dependent in LEO due to eclipses and space weather respectively. In addition, the impact of active attitude control on the orbit should be accounted for. Analytical orbit-attitude modelling offers one attractive, but usually simplistic option, ignoring eclipses and air drag. In response, this paper develops a new analytical orbit-attitude model with a more realistic LEO environment, via the variation of parameters method. As a case study, the model is used to design a LEO space science mission with solar sailing and active attitude control. The orbital predictions are verified against a high-fidelity coupled simulator. Good accuracy is obtained, with a four to six order of magnitude reduction in computation time. The model offers a fast, accurate tool for early-stage mission design of next-generation LEO solar sails.