Active Bend-Twist PZT Actuator for Centimeter-Scale Flapping Wing Micro-Air Vehicle

2011 ◽  
Author(s):  
Asha J. Hall ◽  
Jaret C. Riddick
Keyword(s):  
Insect Flight ◽  
Leading Edge ◽  
Flapping Wing ◽  
Micro Air Vehicle ◽  
Degree Of Freedom ◽  
Control Surface ◽  
Simultaneous Excitation ◽  
Flexural Response ◽  
Air Vehicle ◽  
Twist Actuation

The present study focuses on development of a flapping wing micro-air vehicle (FWMAV) that employs a piezoelectric actuator to drive the leading edge of the wing. An analysis of insect flight indicates that in addition to the bending excitation (flapping), simultaneous excitation of the twisting degree-of-freedom is required to adequately manipulate the control surface. A functionally-modified piezoelectric bimorph composed of Pb(Zr0.55Ti0.45)O3 (PZT) is being used to produce two degree-of-freedom motion, namely the flapping and twisting facilitated by an off-axis layer of piezoelectric segments affixed to the top surface of a traditional bimorph actuator. The modification of the top surface of a traditional PZT bimorph actuator introduces active bend-twist coupling to the flexural response of the resulting layered PZT. This paper presents analytical and experimental investigation of functionally-modified bimorph designs intended for active bend-twist actuation of cm-scale flapping wing devices.

Numerical Investigation of the Response of Active Bend-Twist PZT Actuator

2012 ◽  
Author(s):  
Jaret C. Riddick ◽  
Asha J. Hall ◽  
Oliver J. Myers
Keyword(s):  
Numerical Investigation ◽  
Insect Flight ◽  
Micro Air Vehicles ◽  
Flapping Wing ◽  
Control Surface ◽  
Finite Element Analyses ◽  
Pzt Actuator ◽  
Simultaneous Excitation ◽  
Flexural Response ◽  
Twist Actuation

Army combat operations have placed a high premium on reconnaissance missions for micro air vehicles (MAVs). An analysis of insect flight indicates that in addition to the bending excitation (flapping), simultaneous excitation of the twisting degree-of-freedom is required to manipulate the control surface adequately. By adding a layer of angled piezoelectric segments to a Pb(Zr,Ti)O3 (also referred to as PZT) bimorph actuator, a bend-twist coupling may be introduced to the flexural response of the layered PZT, thereby creating a biaxial actuator capable of driving wing oscillation in flapping wing MAVs. The present study presents numerical investigation of the response of functionally–modified bimorph designs intended for active bend-twist actuation of cm-scale flapping wing devices. The relationships of geometry and orientation of the angled segments with bimorph bend-twist response will be presented using results of finite-element analyses.

scholarly journals Experimental investigation of wing flexibility on force generation of a hovering flapping wing micro air vehicle with double wing clap-and-fling effects

2017 ◽  
Vol 9 (3) ◽  
pp. 187-197 ◽  
Author(s):  
Quoc V Nguyen ◽  
Woei L Chan ◽  
Marco Debiasi
Keyword(s):  
Experimental Investigation ◽  
Power Consumption ◽  
High Speed ◽  
Electrical Power ◽  
Leading Edge ◽  
Flapping Wing ◽  
Micro Air Vehicle ◽  
Custom Made ◽  
Air Vehicle ◽  
Set Up

Experimental investigation of wing flexibility on vertical thrust generation and power consumption in hovering condition for a hovering Flapping-Wing Micro Air Vehicle, namely FlowerFly, weighing 14.5 g with a 3 g onboard battery and having four wings with double wing clap-and-fling effects, was conducted for several wing configurations with the same shape, area, and weight. A data acquisition system was set up to simultaneously record aerodynamic forces, electrical power consumption, and wing motions at various flapping frequencies. The forces and power consumption were measured with a loadcell and a custom-made shunt circuit, respectively, and the wing motion was captured by high-speed cameras. The results show a phase delay of the wing tip displacement observed for wings with high flexible leading edge at high frequency, resulting in less vertical thrust produced when compared with the wings with less leading edge flexibility at the same flapping frequency. Positive wing camber was observed during wing flapping motion by arranging the wing supporting ribs. Comparison of thrust-to-power ratios between the wing configurations was undertaken to figure out a wing configuration for high vertical thrust production but less power consumption.

scholarly journals Synthesis of a Flapping Wing Mechanism Using a Constrained Spatial RRR Serial Chain

2017 ◽  
Vol 10 (1) ◽  
Author(s):  
Peter L. Wang ◽  
Haithem E. Taha ◽  
J. Michael McCarthy
Keyword(s):  
Flapping Wing ◽  
Micro Air Vehicle ◽  
Degree Of Freedom ◽  
Joint Angles ◽  
Hovering Flight ◽  
Wing Movement ◽  
Serial Chain ◽  
Air Vehicle

This paper designs a one degree-of-freedom (1DOF) spatial flapping wing mechanism for a hovering micro-air vehicle by constraining a spatial RRR serial chain using two SS dyads. The desired wing movement defines the dimensions and joint trajectories of the RRR spatial chain. Seven configurations of the chain are selected to define seven precision points that are used to compute SS chains that control the swing and pitch joint angles. The result is a spatial RRR-2SS flapping wing mechanism that transforms the actuator rotation into control of wing swing and pitch necessary for hovering flight of a micro-air vehicle.

scholarly journals Development of a novel flapping wing micro aerial vehicle with elliptical wingtip trajectory

2019 ◽  
Vol 10 (2) ◽  
pp. 355-362
Author(s):  
Qiang Liu ◽  
Qiang Li ◽  
Xiaoqin Zhou ◽  
Pengzi Xu ◽  
Luquan Ren ◽  
...  
Keyword(s):  
Aerodynamic Force ◽  
Aerodynamic Performance ◽  
Flapping Wing ◽  
Micro Air Vehicle ◽  
Degree Of Freedom ◽  
Motion Trajectory ◽  
Micro Aerial Vehicle ◽  
Air Vehicle ◽  
Aerial Vehicle ◽  
Flapping Mechanism

Abstract. This paper describes a novel flapping wing micro air vehicle (FWMAV),which can achieve two active degree of freedom (DOF) movements of flapping and swing, as well as twisting passively. This aircraft has a special “0” figure wingtip motion trajectory with the 140∘ flapping stroke angle. With these characteristics integrated into the simple flapping mechanism, the aerodynamic force is somewhat improved. The model made a balance between the improved aerodynamic performance induced by complicated movements and the increased weight of the extra components in aircraft. In the driven design, Only one micro-motor is employed to drive the wing flapping and swing motion simultaneously forming the prescribed trajectory. The 23 g aircraft could reach the maximum flapping frequency of 11 Hz with the tip-to-tip wingspan of 29 cm.

Flapping Mechanism Design and Aerodynamic Analysis for the Flapping Wing Micro Air Vehicle

2011 ◽  
Vol 291-294 ◽  
pp. 1543-1546
Author(s):  
Yi Qin ◽  
Wei Ping Zhang ◽  
Wen Yuan Cheng ◽  
Wu Liu ◽  
Hong Yi Li ◽  
...  
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Mechanism Design ◽  
Insect Flight ◽  
Flapping Wing ◽  
Micro Air Vehicle ◽  
Air Vehicle ◽  
Computational Fluid Dynamics Cfd ◽  
The Right ◽  
Flapping Mechanism

This paper introduces a biological flapping micro air vehicle (FMAV) with four wings, instead of two wings, where wing clap-and-fling of real insects has been mimicked. The total weight is 2.236g. A spatial linkage is implemented in the flapping wing system, which is symmetry. This can prevent the flapping wing MAV from tilting toward the left or the right in the course of flight. By using the computational fluid dynamics (CFD), it has been confirmed that the flapping wing system can utilize the clap-and-fling mechanism, which is essential to enhance the lift and thrust in the insect flight.

Design and Fabrication of an SU-8 Biomimetic Flapping-wing Micro Air Vehicle by MEMS Technology

ROBOT ◽  
2011 ◽  
Vol 33 (3) ◽  
pp. 366-370 ◽  
Author(s):  
Pengcheng CHI ◽  
Weiping ZHANG ◽  
Wenyuan CHEN ◽  
Hongyi LI ◽  
Kun MENG ◽  
...  
Keyword(s):  
Flapping Wing ◽  
Micro Air Vehicle ◽  
Air Vehicle ◽  
Mems Technology
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