Abstract
This article focuses on the validation of a classical PID controller scheme for flexible spacecraft with regards to the effect of parameter uncertainty on system stability and pointing precision. A high-fidelity simulation environment with external disturbances was built in Simulink using a control-oriented model of an Earth-observing satellite with a flexible appendage and on-board microvibration sources in orbit around the planet. Then, a PID control loop was designed with sensor dynamics, time delay behaviour, and a smooth trajectory generator. After declaring the natural frequencies, damping ratio, and rotation angle of the appendage, as well as the propellant tank mass to be uncertain, two worst-case scenarios were identified. Comparing the response of worst-case systems with nominal settings, only a minor drop has been found in the phase margins, with little to no difference in the pointing errors (smaller than ±2 arcsec for both roll and pitch).
Original language | English |
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Pages (from-to) | 241-246 |
Number of pages | 6 |
Journal | IFAC-PapersOnline |
Volume | 55 |
Issue number | 20 |
DOIs | |
Publication status | Published - 2022 |
Event | 10th Vienna International Conference on Mathematical Modelling, MATHMOD 2022 - Vienna, Austria Duration: 27 Jul 2022 → 29 Jul 2022 |
Keywords
- attitude tracking
- flexible spacecraft
- nonlinear dynamics
- parameter uncertainty
- PID control
- precise pointing control