A Combined Piezoelectric and Composite Actuator
A Novel Piezoelectric-Composite-Actuator and Its Application to Wing/Blade Tip
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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 piezoelec...
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.
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.
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