A hybrid design method, focused on reducing vibration while minimizing control effort, is developed. In this integrated active-passive approach, trailing edge flap controller design is combined with blade structural optimisation. An aeroelastic model is developed for a helicopter rotor with a trailing edge flap. The objective function, which includes vibratory hub loads and active flap control inputs, is minimised by an integrated optimal control/structural optimisation process. It is demonstrated that both the hub vibratory loads and active flap control effort can be reduced. The study shows that retrofitting an active flap to a baseline blade or to an optimal passive blade configuration might not be an effective design approach. The active-passive hybrid method can outperform these configurations by achieving more vibration reduction with less control effort. The hybrid design procedure can reduce the required active flap deflections by about 30-60 % in the whole flight range. An analysis and parametric study of the hybrid design of rotor blades with trailing edge flaps is conducted. The off-design condition for hybrid approaches is examined and the robustness of the hybrid design is addressed. The physical understandings of the hybrid design are explored.
Active-passive hybrid optimization of rotor blades with trailing edge flaps
Aktiv-Passiv Hybrid-Optimierung von Rotorblättern mit Hinterkantenklappen
Journal of the American Helicopter Society ; 49 , 1 ; 54-65
2004
12 Seiten, 19 Bilder, 7 Tabellen, 36 Quellen
Aufsatz (Zeitschrift)
Englisch
Active-Passive Hybrid Optimization of Rotor Blades with Trailing Edge Flaps
Online Contents | 2004
|An Active-Passive Hybrid Method for Optimization of Rotor Blades with Trailing Edge Flaps
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|Swashplateless Helicopter Rotor with Trailing-Edge Flaps
AIAA | 2004
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