Research Of The Parameters Effects On The Dynamic Characteristics Of Smart Rotor With Trailing-edge Flaps

Helicopter in forward flight is subjected to periodic vibration loads, wherein the rotor vibrationload plays a major role. Excessive vibration load will reduce the structural fatigue life of thehelicopter body, the level of occupant and driver comfort and work efficiency, so the helicoptervibration and control has been the important contents in the design of helicopter. Active trailing edgeflaps is a new kind of smart rotor vibration technology, which can effectively reduce rotor vibrationlevel. Therefore, in this paper, comprehensive aeroelastic analysis model of the smart rotor withtrailing edge flaps has been formulated, and the vibration reduction capability of trailing edge flapsand the power required to drive the trailing edge flaps have been analyzed.Comprehensive analysis model smart rotor with trailing edge flaps has been formulated in thispaper, which includes the rotor dynamics model based on the moderate deflection beam theory,Theodorsen quasi-steady aerodynamic model and uniform linear inflow, and the aerodynamic loads ofthe trailing edge flaps are obtained by Theodorsen flapping airfoil theory. In order to verify the bladedynamics model, the deflections of the model under static and dynamic load has been calculated, aswell as the inherent characteristics, with results of Patran simulation, the validity of the model hasbeen verified.Based on the comprehensive aeroelastic analysis model, the effect of the design parameters oftrailing edge flaps on the hub loads has been studied. The results show that, the flap deflection adjuststhe distribution of the high order aerodynamic lift of the blade, counterbalance the main harmoniccomponent of the excitation force, which can effectively reduce the hub vibratory loads, and vibratoryloads is very sensitive to the change of design parameters on the trailing edge flaps.