This paper presents the wind tunnel testing of a smart rotor model with piezoelectric bender actuated trailing-edge flaps for active vibration control. First, open-loop tests were performed at different rotor speeds, advance ratios, and collective pitch settings. Flap deflections of +/-4 to +/-6 deg. were recorded in the 1-5/rev frequency range at 1800 rpm. The rotor collective pitch and advance ratio were found to have negligible impact on actuator performance. For in-phase 3/rev actuator excitation, oscillatory thrust levels of up to +/-36 lbs (60% steady rotor thrust at 6 deg. collective) were recorded. Next, closed-loop vibration suppression tests were conducted in conjunction with a neural network controller. These tests demonstrated between 70% and 90% reduction in the 4/rev thrust, pitching moment, and rolling moment levels for 2 to 4 deg. collective. The trailing-edge flap was also used to suppress a rotating frame load (blade root flat-wise bending moment) with equally good success.
Wind tunnel testing of a smart rotor model with trailing-edge flaps
Windtunneluntersuchung an einem intelligenten Rotormodell mit Hinterkantenklappen
Journal of the American Helicopter Society ; 47 , 4 ; 263-272
2002
10 Seiten, 14 Bilder, 6 Tabellen, 16 Quellen
Article (Journal)
English
Drehzahlsteuerung und -regelung , Flügelblatt , intelligente Regelung , Lernalgorithmus , Lernprozess , neuronaler Regler , neuronales Netzwerk , piezoelektrischer Aktor , Rechnerprogramm , Regelbereich , Rotor (Drehflügel) , Schubkraft , Schwingungsfrequenz , Schwingungsverhalten , Stellantrieb , Test (Prüfung) , Hubschrauber , Umdrehungsgeschwindigkeit , Versuchsmodell , Windkanal
Wind Tunnel Testing of a Smart Rotor Model with Trailing-Edge Flaps
Online Contents | 2002
|Design and Testing of a Helicopter Rotor Model with Smart Trailing Edge Flaps
British Library Conference Proceedings | 1994
|