solar pressure and hence the solar torques for controlling the satellite librations. Several typical response results presented here establish the proposed concept. The concept offers a degree of versatility permitting the satellite to attain any general pitching orientation. For the control implementation, sensors are required to measure the attitude angle as well as its rate of variation. Mini-servo units, of course, are needed to rotate the panels. It may be pointed out that even though the proposed attitude control concept has been demonstrated, feasibility of its implementation remains to be established. In particular, the practical problems associated with lining the panels without significantly affecting the solar power, their rotations and the resulting alternating stresses need to be looked into beside the overall cost-effectiveness of the concept.
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