This paper outlines the design, fabrication and testing of a new, high performance piezoelectrically driven aircraft flutter
test vane. This flutter test vane utilizes low-net passive stiffness (LNPS) actuator configurations to produce deflection
amplification ratios on the order of 5:1 while maintaining full blocked moment generation capability. With an order of
magnitude lower weight than conventional vanes, the LNPS flight flutter test vane is capable of producing larger
amplitude structural deflections with smaller force levels because vane forcing waveforms, frequencies and phasing can
be very exactingly controlled with respect to each other. The paper covers the fundamental driving theories behind the
device, actuator geometry, test article layout, fabrication and testing. This device was wind tunnel tested at airspeeds up
to 110 ft/s with excellent correlation between theory and experiment. Experimental tests show an improvement in
angular deflection and delta lift forces from approximately ±1.8 deg. and 0.45 lbf to ±8.5 deg. and 1.45 lbf, respectively.
The flutter test vane consumes only 1W of peak power at max. actuation frequency, drastically reducing the impact of
electrical power supply lines on the modal mass of the wing. This paper describes the modeling, testing and evaluation
of the adaptive flutter test vane and quantifies the implications on the current state of flight flutter testing.