The Active Vertical Tail (ATV) successfully reduced the buffet response of the structure by utilizing integrated piezoelectric actuators, strain gage sensors and simple control techniques. The AVT is a 5%-scale aeroelastically-tailored structure that exhibits vibration response similar to a full-scale aircraft structure, and was designed such that piezoelectric actuators mounted on the AVT's spar could provide control authority in the first two bending and two torsion modes. The AVT was tested in a low speed wind tunnel on a generic twin-tailed double-delta fighter model at angles of attack and dynamic pressures representative of actual aircraft flight envelopes. At high angles of attack, the leading edge vortices generate severe random buffet pressures on the vertical tails, causing excitation of the first few natural modes of the flexible tail. Simple control algorithms were used with piezoelectric actuators and collocated strain gage sensors to either minimize the acceleration at the AVT's tip or the strain at the root of the tail. Control gains were verified to be a nonlinear function of angle of attack, dynamic pressure and location of the actuator/sensor pair. Spectral analysis showed that the peak response of the controlled AVT was up to 65 % lower than the uncontrolled response. This represents approximately an order of magnitude improvement in the fatigue life of the structure. The root mean squard response below 200 Hz was reduced by over 20 %.
Reduction of vertical tail buffet response using active control
Verringerung der Schwingungen des Leitwerks von Flugzeugen mit Hilfe von aktiver Regelung
1995
8 Seiten, 11 Bilder, 15 Quellen
Aufsatz (Konferenz)
Englisch
Reduction of Vertical Tail Buffet Response Using Active Control
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