Conventional control surfaces have been used in most carbon fiber composite, membrane-wing autonomous
micro air vehicles (MAV). In some cases, vehicle morphing is achieved using servo actuators to articulate vehicle
kinematic joints, or to deform crucial wing / tail surfaces. However, articulated lifting surfaces and articulated
wing sections are difficult to instrument and fabricate in a repeatable fashion. Assembly is complex and time
consuming. The goal of this paper is to establish the feasibility of morphing wings on autonomous MAVs that
are actuated via active materials. Active actuation is achieved via a type of piezoceramic composite called Macro
Fiber Composite (MFC). This paper investigates the structural dynamics of morphing wings on MAVs that are
actuated via active composites. This paper continues the work presented in1 by considering structural dynamic
characteristics of the morphing vehicle determined through Scanning Laser Doppler Vibrometry (SLDV).
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