Design and static testing of a trailing-edge flap actuator with piezostacks for a rotor blade

Taeoh Lee; Inderjit Chopra

doi:10.1117/12.316903

27 July 1998 Design and static testing of a trailing-edge flap actuator with piezostacks for a rotor blade

Taeoh Lee, Inderjit Chopra

Proceedings Volume 3329, Smart Structures and Materials 1998: Smart Structures and Integrated Systems; (1998) https://doi.org/10.1117/12.316903
Event: 5th Annual International Symposium on Smart Structures and Materials, 1998, San Diego, CA, United States

Abstract

This paper presents the development of an actuator for a trailing edge flap on a full-scale helicopter rotor blade using a high performance piezoelectric stack device. The actuator was designed and constructed using two identical piezostacks that were selected among commercially available actuators through a systematic testing. To calculate the aerodynamic requirement of the flap actuator, an analytical model was formulated using quasi-steady aerodynamics. A new amplification device utilizing double-lever mechanism was designed and fabricated. An amplification factor of 19.4 and the constant response covering up to 8/rev were obtained experimentally under non-rotating condition. It was shown that the present flap actuator is capable of achieving the required flap deflection to actively control rotor vibration.

Citation Download Citation

Taeoh Lee and Inderjit Chopra "Design and static testing of a trailing-edge flap actuator with piezostacks for a rotor blade", Proc. SPIE 3329, Smart Structures and Materials 1998: Smart Structures and Integrated Systems, (27 July 1998); https://doi.org/10.1117/12.316903

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