The scope of this work is to present and discuss a Simulink model aimed at estimating the amount of jitter caused by the solar array drive mechanism, starting from the early design phases of a space mission. This model was required in the toolbox used by the European Space Agency (ESA) GNC/AOCS division during concurrent design facility sessions and preliminary design phases. In such feasibility studies, one of the main constraints is the simulation time. To improve this specific point, three simulation models are presented in this paper. Each of them is conceived with the same general architecture: rigid hub inverse dynamic model and flexible appendage direct dynamic model in feedback, coupled through a stepper motor and a gearbox. The perturbations due to the gearbox were modeled as a positional transmission error, to represent results of experimental tests performed on the mechanism in later design phases. Simulation results are compared to reference data coming from an ESA simulator, to validate the models. They have proven to be able to estimate the jitter in a very limited times, making the feasibility study possible and reliable at the same time.
Solar Array Drive Mechanism Disturbance Simulation
Aerotec. Missili Spaz.
Aerotecnica Missili & Spazio ; 100 , 1 ; 57-67
2021-03-01
11 pages
Article (Journal)
Electronic Resource
English
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