It is presented a methodology to actuate trailing edge flap in a wing model using a high performence piezostack device. A composite wing model was built around this piezostack actuator with integrated mechanical amplification. The free displacement and block force of this high voltage actuator were respectively determined as 28 mil and 16 lb at 1000 volts. Tje linear motion of the actuator was converted to rotary motion for flap actuation using a hinge offset mechanism. This model was tested to evaluate the performence of flap actuation without and with aerodynamic forces. The flap deflection was measured using a Hall sensor, and a maximum 8.5 deg flap deflection was achieved. The influence of free stream velocity and angle of attack on flap deflection was examined. A 30 % decrease in flap deflection at free stream velocity at 95 ft/sec was noticed. Angle of attack of 10 deg did not change the flap deflection. Flap deflection was prredicted from force-displacement relation of actuator and calvculated hinge moment and good coorrelation between experiment and predictioon was achieved.
Actuation of trailing edge flap in a wing model using piezostack device
Piezoelektrischer Antrieb für die Flügelhinterkantenklappe eines Hubschrauberrotors
Journal of Intelligent Material Systems and Structures ; 9 , 10 ; 847-853
1998
7 Seiten, 21 Bilder, 1 Tabelle, 8 Quellen
Aufsatz (Zeitschrift)
Englisch