Aeroelastic
Control of Flutter using Trailing-Edge Control Surfaces Powered by
Piezoelectric Actuators
The primary focus of
this research is the development of a trailing edge control
surface (flap)actuation system, suited for aeroelastic flutter
control of HAR wings. In order to be effective for aeroelastic
control of flutter, the deflection of the flaps should be up to ±
5-6°
with frequencies up to 25-30 Hz. As classical solutions for flap
actuation do not have the capabilities required for this task,
actuation systems using active materials were investigated. A new
piezoelectric actuator (V-Stack Piezoelectric Actuator) was
developed. Although the actuator was designed for flap actuation,
other applications could benefit from its capabilities.
SolidWorks
Model of the actuator
Click
here to watch a video of the actuator being tested (2.2 MB mpeg)
This
actuator meets the requirements for trailing edge flap actuation
in both stroke and force. It is compact, simple, sturdy, and
leverages stroke geometrically with minimum force penalties while
displaying linearity over a wide range of stroke.
Actuator
frequency response (experimental)
Force-displacement
characteristics for different electric fields
Integration
of the actuator inside a structure requires minimal modifications.
The shape of the actuator makes it extremely suitable for trailing
edge flap actuation eliminating the need of a push rod. It leads
to smaller number of parts, less added mass, less compliance and
simplicity of the actuation mechanism.
Actuator
integration into
a typical-section model
In
order to validate the concept a typical section prototype was
constructed and tested experimentally in the wind tunnel at
Duke
University
. Operating in closed-loop, the flutter was suppressed at the
speed at which the flutter occurred open-loop, and the flutter
speed was increased by over 26%.
Typical-section
in the wind tunnel
Click
here to watch a video showing flutter suppression. (661KB)
Flutter
suppression at various flow speeds
This
work was generously supported by DARPA through AFOSR Grant
#F49620-99-1-00253.
Research
performed by Emil Ardelean and Robert
L. Clark.
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