This article describes a general framework to generate linearized models of satellites with large flexible appendages. The obtained model is parameterized according to the tilt of flexible appendages and can be used to validate an attitude control system over a complete revolution of the appendage. Uncertainties on the characteristic parameters of each substructure can be easily considered by the proposed generic and systematic multibody modeling technique, leading to a minimal linear fractional transformation (LFT) model. The uncertainty block has a direct link with the physical parameters avoiding nonphysical parametric configurations. This approach is illustrated to analyze the attitude control system of a spacecraft fitted with a tiltable flexible solar panel. A very simple root locus allows the stability of the closed-loop system to be characterized for a complete revolution of the solar panel.
Dynamic Modeling and Analysis of Spacecraft With Variable Tilt of Flexible Appendages
Contributed by the Dynamic Systems Division of ASME for publication in the JOURNAL OF DYNAMIC SYSTEMS, MEASUREMENT, AND CONTROL. Manuscript received June 26, 2012; final manuscript received November 7, 2013; published online January 9, 2014. Assoc. Editor: Evangelos Papadopoulos.
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Guy, N., Alazard, D., Cumer, C., and Charbonnel, C. (January 9, 2014). "Dynamic Modeling and Analysis of Spacecraft With Variable Tilt of Flexible Appendages." ASME. J. Dyn. Sys., Meas., Control. March 2014; 136(2): 021020. https://doi.org/10.1115/1.4025998
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