A Study of the Thermal Effects in a Smart Structure Helicopter Rotor
Final rept. Mar-Sep 1998
INSTITUTE FOR DEFENSE ANALYSES ALEXANDRIA VA
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One concept being considered for active noise and vibration control of helicopter rotors is a trailing edge flap design driven by a high-displacement piezoelectric actuator device. The proposed device requires an 800-V power supply and draws a current on the order of .3 A. Thus, depending on the duty cycle and efficiency of the mechanism, some portion of the 240 W of electrical input energy will be converted to heat. This study provides an initial estimate of the temperatures that may be encountered if no provisions are made for cooling the actuator. Also included are a discussion of the heat transfer calculation, assuming conduction and radiation as the dominant modes, and a description of HEAT 8, the computer code used.