A Combined Piezoelectric and Composite Actuator

A novel composite-piezoelectric actuator
configuration is proposed and analytically modeled
in this book. The actuator is a low complexity,
active compliant mechanism obtained by coupling a
modified star cross sectional configuration
composite beam with a helicoidal bimorph
piezoelectric actuator coiled around it. The
modified star beam is tailored and optimized to
achieve increased torsional compliance and bending
stiffness at constant axial stiffness. The coiled
piezoelectric actuator is designed to directly
generate finite rotation output without need for
mechanisms to amplify the piezoelectric displacement
output and/or to convert linear output to rotational
output. The proposed cylindrical actuator
configuration is compact and is a good candidate for
use as a hinge tension-torsion bar actuator for a
helicopter rotor blade flap or blade tip. For such
cases the modified star composite beam also carries
the centrifugal loads of the flap or blade tip, and
those of the coiled actuator, thereby eliminating
the need for a thrust bearing.

Autorentext

Kwangtae Ha was born in Jinju, Korea. He received Doctor of
Philosophy degree in Aerospace Engineering from Georgia
Institute of Technology in Atlanta, Georgia in December 2005. He
worked for Groen Brothers Aviation and currently working
for Caterpillar. He married Simbackhwa Lee in 2004, and has
a son, Ethan Ha, and a daughter, Iyan Ha.

Klappentext

A novel composite-piezoelectric actuator
configuration is proposed and analytically modeled
in this book. The actuator is a low complexity,
active compliant mechanism obtained by coupling a
modified star cross sectional configuration
composite beam with a helicoidal bimorph
piezoelectric actuator coiled around it. The
modified star beam is tailored and optimized to
achieve increased torsional compliance and bending
stiffness at constant axial stiffness. The coiled
piezoelectric actuator is designed to directly
generate finite rotation output without need for
mechanisms to amplify the piezoelectric displacement
output and/or to convert linear output to rotational
output. The proposed cylindrical actuator
configuration is compact and is a good candidate for
use as a hinge tension-torsion bar actuator for a
helicopter rotor blade flap or blade tip. For such
cases the modified star composite beam also carries
the centrifugal loads of the flap or blade tip, and
those of the coiled actuator, thereby eliminating
the need for a thrust bearing.