Our news editors obtained a quote from the research, "Numerical simulations as well as flight-test data for the hingeless EC145 helicopter with trailing-edge flaps were used for this purpose. Initially, a numerical model was validated against flight-test data in order to match accurately the phase and gain of the dynamic behavior of the helicopter system actuated by the trailing-edge flaps. The validated model was then used to design a model-based controller for rotor blade lead-lag damping enhancement. The performances of the closed-loop concept were then assessed in simulations and flown during flight tests for the first time for rotor stability enhancement. The presented results show a significant improvement in the transfer behavior of the system at the frequency of the rotor's first regressive lagging mode as well as a strong increase in its damping."
According to the news editors, the research concluded: "It is shown that this is true without the necessity of gain scheduling and interaction with other dynamics."
For more information on this research see: Helicopter Rotor In-Plane Stability Enhancement Using Trailing-Edge Flaps.
The news editors report that additional information may be obtained by contacting
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