Abstract The relative hovering of satellites in highly elliptic orbits (HEO), as one of the most crucial space operations, is modeled and analyzed in this paper. The proposed modeling is based on the new perturbed relative dynamics equations, uses the time-varied parameters depending on the motion of the target satellite. This proposed model considered the dynamic air drag, oblateness of Earth (including all zonal harmonics coefficients) and the Lunar perturbation as an inclined third-body disturbing effect on both follower and target orbits. The non-simplified relative motion model has been obtained by employing the Lagrangian mechanics principals and completed along with the target satellite’s motion characteristic. Then the required thrust for relative hovering mission has been obtained without any simplifications to ensure the accuracy of long-duration flight analyses. To validate the presented model, another model has been built as an ECI based Relative Motion (ERM) model. Then, according to effective parameters on hovering mission design around HEOs such as the eccentricity and inclination of the target obit, the fuel consumption, optimal positioning of the follower, maximum required thrust, and the appropriate time to perform the operation, several examples are provided. Furthermore, the hybrid IWO/PSO algorithm has been used to find the location and the minimum/maximum amounts of thrust force.
Perturbed HEO Satellite Hovering Investigation in the Earth-Moon System
2019
Aufsatz (Zeitschrift)
Englisch
Perturbed HEO Satellite Hovering Investigation in the Earth-Moon System
Springer Verlag | 2019
|Sun-Perturbed Earth-to-Moon Transfers with Ballistic Capture
Online Contents | 1993
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