Solar Array Drive Assembly Disturbance Modeling, Jitter Analysis and Validation Tests for Precision Space-Based Operations

Background Vibrations in space operations, induced by disturbance torque of solar array drive assembly (SADA), is one of the major setbacks, as these reduce performance precision of satellite. Purpose Aiming to simulate behavior of solar panel, this work provides an analytical modeling and analysis method to calculate the disruption response of SADA rotating flexible loading. Methodology The discussed SADA is 64 subdivisions bi-phase hybrid step drive with variably toothed rotor. Initially, vibration equation of step motor is obtained by linearization and simplification of electromagnetic torque. For precise ground testing, a measurement system comprising of piezoelectric test platform is designed to measure and validate no load SADA disturbance. Based on SADA dynamic equation and employing the force/moment analysis, disturbance torque produced by drive is approximated when it is operating rigid load. The results, validated through simulations to provide amplitude of coupled vibrations, imply that the suggested model for disturbance torque possesses the aptitude to demonstrate the vibrations generated by drive motor with high accuracy. Results and Conclusion Analytical and simulation studies, used to examine the effect of increasing the number of rotor teeth on the vibration behavior of subdivided SADA, show an increase in frequency and a decrease in amplitude of produced vibrations. All of the analysis approaches provide a foundation for analyzing SADA vibrations and their impact on actual solar arrays.