On the orbital eccentricity control of synchronous satellites

Two strategies for the control of the mean orbital eccentricity of synchronous satellites within a specified tolerance have been examined. The first strategy consists of biasing the mean eccentricity vector relative to the sun such that its magnitude reduces to zero at the middle of the east-west drift cycle. The second strategy consists of biasing the mean eccentricity vector relative to the sun such that its magnitude at the beginning and at the end of the east-west drift cycle is equal to the maximum tolerance. The second strategy is shown to cost less in terms of velocity change than the first strategy in connection with east-west stationkeeping operations.