Abstract
AbstractThis paper proposes new quasi-periodic orbits around Earth–Moon collinear libration points using solar sails. By including the time-varying sail orientation in the linearized equations of motion for the circular restricted three-body problem (CR3BP), four types of quasi-periodic orbits (two types around L1 and two types around L2) were formulated. Among them, one type of orbit around L2 realizes a considerably small geometry variation while ensuring visibility from the Earth if (and only if) the sail acceleration due to solar radiation pressure is approximately of a certain magnitude, which is much smaller than that assumed in several previous studies. This means that only small solar sails can remain in the vicinity of L2 for a long time without propellant consumption. The orbits designed in the linearized CR3BP can be translated into nonlinear CR3BP and high-fidelity ephemeris models without losing geometrical characteristics. In this study, new quasi-periodic orbits are formulated, and their characteristics are discussed. Furthermore, their extendibility to higher-fidelity dynamic models was verified using numerical examples.
Publisher
Springer Science and Business Media LLC
Reference19 articles.
1. Koon, W. S., Lo, M. W., Marsden, J. E., Ross, S. D. Dynamical Systems, the Three-Body Problem, and Space Mission Design. Marsden Books, 2006.
2. Heiligers, J., MacDonald, M., Parker, J. S. Extension of Earth–Moon libration point orbits with solar sail propulsion. Astrophysics and Space Science, 2016, 361(7): 1–20.
3. Jorba-Cuscó, M., Farrés, A., Jorba, A. Solar sail resonant periodic orbits in the augmented Earth–Moon Quasi-bicircular problem. In: Proceedings of the 67th International Astronautical Congress, Bremen, Germany, 2018: IAC-18 C.
4. Jorba-Cuscó, M., Farrés, A., Jorba, À. On the stabilizing effect of Solar Radiation Pressure in the Earth–Moon system. Advances in Space Research, 2021, 67(9): 2812–2822.
5. Chujo, T., Takao, Y. Synodic resonant halo orbits of solar sails in restricted four-body problem. Journal of Spacecraft and Rockets, 2022, 59(6): 2129–2147.