Dynamic modeling and analysis of spacecraft with variable tilt of flexible appendages

Nicolas Guy (1) , Daniel Alazard (2) , Christelle Cumer (1) , Catherine Charbonnel (3)

1 ONERA - The French Aerospace Lab [Toulouse]
2 DMIA - Département de Mathématiques, Informatique, Automatique
3 THALES [France]

This article describes a general framework to generate linearized models of satellites with large flexible appendages. The obtained model is parametrized 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 LFT model. The uncertainty block has a direct link with the physical parameters avoiding non-physical 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.

Mots clés: Space vehicles; Dynamic models; Satellites; Uncertainty; Dynamic modeling; Control equipment; Control systems

Domaines: Mécanique des structures [physics.class-ph]

Nicolas Guy, Daniel Alazard, Christelle Cumer, Catherine Charbonnel. Dynamic modeling and analysis of spacecraft with variable tilt of flexible appendages. Journal of Dynamic Systems, Measurement, and Control, 2014, 136 (2), pp.0. ⟨10.1115/1.4025998⟩. ⟨hal-01920562⟩