Presented here is the feasibility of a novel attitude control approach for satellites in high altitude inclined elliptic orbits, in order to compensate for the effect of longitudinal as well as lateral drifts relative to the ground terminal. The approach using tether connecting two satellites is proposed for achieving the fixed apparent orientation of both the satellites with respect to the ground segment of the space mission. A simple control strategy based on tether offset variations is developed so as to ensure controlled changes in the orientation of both the satellites in order to compensate for the effect of their periodic longitudinal and lateral drifts in non-equatorial orbits relative to the ground station. The high degree of line-of-sight pointing of dual satellites possible as well as the simplicity of the proposed control mechanism make the concept particularly viable for future space applications.