Abstract
A multipayload spacecraft modeling approach that combines constituent subassemblies (plant and controllers) into a combined system (model synthesis) is presented. This technique was used to model the Upper Atmosphere Research Satellite. The simulation was developed to determine the amount of controls-structure interaction, and the satellite flight results verified simulation predictions during payload tracking and scan modes and solar-array sun-tracking modes. The simulation was developed using the Dynamics Analysis Design System program. The program was modified to include a multirate sampling capability, a robust analog delay element, a stepper-motor kinematic driver, and a modified flexible body formulation. The simulation includes the structural models of the satellite components, the dominant flexible modes, the vehicle attitude control system and orbit adjust capability, and all instrument elevation and azimuth control systems. The model includes the flexible modes below 16 Hz and the instrument control systems. This study presented simulation results using the synthesized modeling approach and the in-flight data to validate the approach
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