Using differential solar radiation pressure (DSRP) for satellite formation keeping is not a new idea. However, there is no existing design methodology of DSRP-based controllers for lunar satellite formation keeping. Lunar orbits are different from low Earth orbits, because the third-body effects are dominant. This paper develops a DSRP-based formation keeping controller, using mean orbital element feedback, for regulating relative distances between satellites in lunar orbits. It is shown that the most effective way to mitigate the intersatellite drift is to adjust the semimajor axes. This is achieved by modifying the cross-sectional areas of the satellites. The stability of the closed-loop system is proven based on the finite time stability theory. Numerical simulation results illustrate that the new DSRP-based controller is able to arrest the relative distance drift in lunar orbits for several years.
Lunar Satellite Formation Keeping Using Differential Solar Radiation Pressure
Journal of Guidance, Control, and Dynamics ; 43 , 4 ; 754-766
2019-12-27
13 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Multiple Satellite Formation Flying Using Differential Solar Radiation Pressure
British Library Conference Proceedings | 2010
|Satellite formation keeping using differential lift and drag under J2 perturbation
Emerald Group Publishing | 2017
|AIAA-2002-4431 Solar Radiation Pressure and Formation-Keeping in Highly Elliptical Orbits
British Library Conference Proceedings | 2002
|