Abstract
More sophisticated space vehicles will carry telescopes to be aimed at the stars, solar converters to be aimed at the sun, propulsion jets to be aimed along the velocity vector, and perhaps several antennas to be aimed in several directions. Orientation control systems will be required for these appendages. The purpose of this paper is to present the analysis of a biaxial control system to be used with such appendages. The analysis is performed with Lagrangian mechanics and sufficient mathematical details are given so that this paper can serve to introduce Lagrangian mechanics to control engineers. Preliminary design criteria for achieving stability are discussed. Adaptation of the system to a solar converter is covered in detail.
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