Affiliation:
1. University Politehnica of Bucharest
Abstract
This paper presents a new design methodology for the control system of a launch vehicle. The method is based on the $H_\infty$ minimisation of the closed loop configuration obtained with a state feedback control law. Necessary and sufficient conditions for the existence of a state feedback control law minimising the effects of wind disturbances on the angle of attack and the control effort are derived. These conditions are expressed in terms of feasibility of a specific system of linear matrix inequalities. The theoretical developments are illustrated by numerical comparative results indicating that the proposed optimal design approach provides improved stability robustness, disturbances attenuation and tracking performances with respect to non-optimal design methods.
Publisher
Trans Tech Publications, Ltd.
Reference15 articles.
1. D. Arzelier and D. Peaucelle: Multiobjective H2/H∞ impulse-to-peak synthesis: Application to the control of an aerospace launcherProceedings of the 16th IFAC Symposium on Automatic Control in Aerospace, St-Petersburg, Russia (2004).
2. S. Mauffrey, P. Meunier, G. Pigni, A. Biard and I. Rougier: H∞ control for the ARIANE 5 plus Launcher, 52nd International Astronautics Congress, Toulouse, France (2001).
3. M.A. Creagh and R. Lind: H-infinity Control for Attitude Manoeuvres of a Spinning Asymmetric Vehicle, Proceedings of Guidance, Navigation and Control Conference, Chicago, USA (2009).
4. O. Voinot, D. Alazard and A. Piquereau: A Robust Multiobjective Synthesis applied to Launcher Attitude Control, Proceedings of 15th IFAC Symposium on Automatic Control in Aerospace, Bologne, Italy (2001).
5. O. Voinot, P. Apkarian and D. Alazard: Gain-scheduluing H∞ control of the launcher in atmospheric flight via linear parameter varying technique, AIAAA Guidance, Navigation and Control Conference, Monterey, USA (2002).
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