| Abstract | Frequency domain system identification of higher order models for the Bell 412 helicopter was performed. First, a frequency response database was derived from flight test data. For hover, a combination of sweep and 2311- multistep maneuvers had to be used to achieve good results. The identified hover model includes besides the classical 6-DoF rigid body states, as extension inflow and coning dynamics and uses a Padé approximation for the influence of engine dynamics, to improve the response in the vertical axis. The forward flight (60 kt) model includes as extension first order flapping dynamics, mainly to improve the roll and pitch response. Besides the simple Padé approach used in the hover model, two different engine model structures were investigated but they provided no significant improvement compared to the Padé solution when coupled to the rigid-body model. Finally a method derived from feedforward principles of model following control is shown, to use the identified hover model to analytically derive an "input filter" correction that improves the fidelity of a linearized FLIGHLAB simulation model. |
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