Abstract
The helicopter’s main source of propulsion is provided by the main and tail rotor. The aerodynamic forces and moments are nonlinear functions of motion characteristics and controls. Due to the complexity and the uncertainty associated with the aerodynamic phenomena, a detailed model of the forces and moments produced by the main rotor would be of high order and completely impractical for any controller design. In this Chapter, the modeling approach presented in (Koo and Sastry in Proceedings of the 37th IEEE Conference on Decision and Control, vol. 4, 1998, pp. 3635–3640; Lee et al. in Proceedings of Society of Instrument and Control Engineers, 1993, pp. 1385–1390; Mettler in Identification Modeling and Characteristics of Miniature Rotorcraft, Kluwer Academic Publishers, Norwell, 2003; Mettler et al. in Presented at the American Helicopter Society 55th Forum, May 1999 ) is followed to arrive at a simplified derivation of the main rotor dynamics and the produced thrust force vector that are considered sufficient for controller design purposes.
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Raptis, I.A., Valavanis, K.P. (2011). Simplified Rotor Dynamics. In: Linear and Nonlinear Control of Small-Scale Unmanned Helicopters. Intelligent Systems, Control and Automation: Science and Engineering, vol 45. Springer, Dordrecht. https://doi.org/10.1007/978-94-007-0023-9_4
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DOI: https://doi.org/10.1007/978-94-007-0023-9_4
Publisher Name: Springer, Dordrecht
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