The dynamic equations for the simulation of Space Station Freedom configured with solar dynamic (SD) power modules are developed. The formulation permits the structure to be subjected to shuttle docking disturbances while being controlled with a “natural” vibration and tracking control approach. Multiple control cases can be performed for the purpose of investigating the relationship between actuator effort, SD pointing, and thermal loading on the receiver aperture plate. Transient, one-dimensional heat transfer equations are formulated to conservatively predict temperatures of the multilayered receiver aperture plate assembly and thermal stresses in its shield layer. Numerical results from these analyses are presented in a companion paper (Part II).

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