Effects Analysis of Frozen Conditions for Spacecraft Relative Motion Dynamics

The purpose of this rersearch is to analyze the effective application of particular earth orbits in dynamical modeling of relative motion problem between two spacecraft. One challenge inimplementing these motions is maintaining the relations as it experiences orbital perturbations (zonalharmonics J2 and J3), notably due to the Earth’s oblateness. Certain aspects of the orbital geometry canremain virtually fixed over extended periods of time due to a natural phenomenon called a frozen orbit.Specifically, the elements of the orbital geometry that can remain fixed are the argument of perigee (ω) and eccentricity (e). Simulation results show that, using frozen orbits phenomenon results in considerable propellant saving and performance duration a relative orbital mission is preferable. In thisregard, an method is developed that determines if the relative orbit conditions will be met given theinitial differences in frozen orbit elements (argument of perigee and eccentricity) for each of two spacecraft. Using the frozen conditions in relative motion dynamics can be reduced the amount of required propellant for orbit correction manoeuvres due to the harmonic perturbations over the course of a year.

Keywords:

Frozen Orbits , Relative Motion , Argument of Perigee , Dynamical Modeling , Eccentricity Rate , Propellant Saving , Simulation Results , Zonal Harmonic Perturbation