We present a helicopter flight dynamics nonlinear model for a flybarless, articulated, pitch–lag–flap (P–L–F) main rotor (MR) with rigid blades, particularly suited for small-scale unmanned aerial vehicles (UAVs). The model incorporates the MR, tail rotor (TR), fuselage, and tails. This model is further applicable for high bandwidth control specifications and is valid for a range of flight conditions, including the vortex-ring-state (VRS) and autorotation. Additionally, the paper reviews all assumptions made in deriving the model, i.e., structural, aerodynamics, and dynamical simplifications. Simulation results show that this nonlinear model is in good agreement with an equivalent flightlab model, for both static (trim) and dynamic conditions.
A Flight Dynamics Model for a Small-Scale Flybarless Helicopter
Contributed by the Dynamic Systems Division of ASME for publication in the JOURNAL OF DYNAMIC SYSTEMS, MEASUREMENT, AND CONTROL. Manuscript received March 18, 2015; final manuscript received September 10, 2015; published online November 18, 2015. Assoc. Editor: Yongchun Fang.
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Taamallah, S. (November 18, 2015). "A Flight Dynamics Model for a Small-Scale Flybarless Helicopter." ASME. J. Dyn. Sys., Meas., Control. January 2016; 138(1): 011010. https://doi.org/10.1115/1.4031738
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