An LQ Approach to Active Control of Vibrations in Helicopters
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Published:1996-09-01
Issue:3
Volume:118
Page:482-488
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ISSN:0022-0434
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Container-title:Journal of Dynamic Systems, Measurement, and Control
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language:en
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Short-container-title:
Author:
Bittanti Sergio1, Lorito Fabrizio1, Strada Silvia1
Affiliation:
1. Dipartimento di Elettronica e Informazione, Politecnico di Milano, Piazza Leonardo da Vinci, 32, 20133 Milano, Italy
Abstract
In this paper, Linear Quadratic (LQ) optimal control concepts are applied for the active control of vibrations in helicopters. The study is based on an identified dynamic model of the rotor. The vibration effect is captured by suitably augmenting the state vector of the rotor model. Then, Kalman filtering concepts can be used to obtain a real-time estimate of the vibration, which is then fed back to form a suitable compensation signal. This design rationale is derived here starting from a rigorous problem position in an optimal control context. Among other things, this calls for a suitable definition of the performance index, of nonstandard type. The application of these ideas to a test helicopter, by means of computer simulations, shows good performances both in terms of disturbance rejection effectiveness and control effort limitation. The performance of the obtained controller is compared with the one achievable by the so called Higher Harmonic Control (HHC) approach, well known within the helicopter community.
Publisher
ASME International
Subject
Computer Science Applications,Mechanical Engineering,Instrumentation,Information Systems,Control and Systems Engineering
Reference19 articles.
1. Achache, M., and Gauvrit, M., 1986, “Control actif des vibrations sur helicopters par commandes multicycliques autoadaptatifs.” 2. Anderson, B. D. O., and Moore, J. B., 1990, Optimal Control—Linear Quadratic Methods, Prentice-Hall, Englewood Cliffs, N.J. 3. Bittanti, S., Lorito, F., Moiraghi, L., and Strada, S., 1992, “Active Control of Vibrations in Helicopters: from HHC to OBC,” Proc. of the 18th European Rotorcraft Forum, Avignone, France. 4. Bittanti, S., Bolzern, P., Colaneri, P., Delrio, P., De Nicolao, G., Lorito, F., Russo, A., and Strada, S., 1991, “Identification of a Helicopter Dynamic Model for Active Control of Vibrations,” Proc. of the IFAC/IFORS Symposium on Identification and System Parameter Estimation, Budapest, Hungary. 5. Bittanti, S., Laub, A. J., and Willems, J. C., 1991, The Riccati Equation, Springer-Verlag, Berlin.
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