Theoretical and experimental study of a piezoelectric flapping wing rotor for micro aerial vehicle

Guo, Shijun; Li, Daochun; Wu, Jianghao

doi:10.1016/j.ast.2011.10.002

Cited by 72 publications

(43 citation statements)

References 19 publications

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“…10 Several direct measurements of the units and fixtures of the assembled test model are shown in Figure 3. Data collection and processing are shown in Figure 4.…”

Section: Experimental Apparatus and Validationmentioning

confidence: 99%

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Experimental study on the lift generated by a flapping rotary wing applied in a micro air vehicle

Zhou

Guo

et al. 2013

Proceedings of the Institution of Mechanical Engineers, Part G:

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An experimental study was conducted to further validate whether the newly proposed flapping rotary wing is suitable for micro air vehicle design. First, the effects of two main kinematical parameters (flapping frequency and initial angle of attack) of flapping rotary wing on lift generation were discussed. It was found that a higher lift can be generated by flapping rotary wing through increasing flapping frequency at a proper initial angle of attack. Second, effect of coupled flapping motion with rotating motion on lift generation was analyzed. It is important that a larger lift was generated by flapping rotary wing than the superposition lifts from purely flapping and purely rotating motions when the initial angle of attack was less than a critical value. Finally, the comparison of the capability of lift generation from the flapping rotary wing and conventional rotary wing was given. It was indicated that the lift from flapping rotary wing was larger than that from conventional rotary wing in the range of Reynolds number from 2600 to 5000 as long as Strouhal number was determined appropriately. The present work suggests that flapping rotary wing may be a feasible and promising wing layout used in the design of micro air vehicle in terms of lift generation.

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“…10 Several direct measurements of the units and fixtures of the assembled test model are shown in Figure 3. Data collection and processing are shown in Figure 4.…”

Section: Experimental Apparatus and Validationmentioning

confidence: 99%

“…, the lift gradually increased although the rotational speed of the wing decreased sharply as increased from 0 to10 . The peak value of the lift reached 20 mN when was about 15 ; it was almost 30 times more than that at ¼ 0 with the fastest rotational speed.…”

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confidence: 94%

Experimental study on the lift generated by a flapping rotary wing applied in a micro air vehicle

Zhou

Guo

et al. 2013

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Most of these excellent performance features have been extensively studied with the goal of enhancing bio-structure features applicable for the design of a micro air vehicle (Kummari et al, 2010;Zhou et al, 2014;Guo et al, 2012). Significant advances have been made in understanding the insect wing geometric structure, material characteristics, flying mechanism, controlling mode and bionic wing design Rajabi et al, 2015;Wang and Zhong, 2014).…”

Section: Introductionmentioning

confidence: 99%

Functional morphology and structural characteristics of wings of the ladybird beetle,Coccinella septempunctata(L.)

Xiang

et al. 2016

Microsc. Res. Tech.

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In recent years, the surface morphology and microstructure of ladybird (Coccinella septempunctata) wings have been used to help design the flapping-wing micro air vehicle (FWMAV). In this study, scanning electron microscopy (SEM) was used to verify the functional roles of the ladybird forewing and hindwing. Surface morphology and the cross-sectional microstructure of the wings are presented. Detailed morphology of ladybird forewings was observed using atomic force microscopy (AFM) and the composition of the wings was characterized using Fourier transformed infrared spectroscopy (FTIR). The ladybird forewing may possess different performance characteristics than the beetle, Allomyrina dichotoma. Additionally, the circular holes in the forewing might be important for decreasing the weight of the forewing and to satisfy requirements of mechanical behavior. Microsc. Res. Tech. 79:550-556, 2016. © 2016 Wiley Periodicals, Inc.

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“…The LionFly mechanism is able to generate a 46°flap and a 44°peak to peak rotation amplitude with relative phase of 12°and maximum lift of 71 µN at 37 Hz. In [60], the authors presented a design of a simple flapping wing rotor composed of three basic elements (see Figure 8. Author of [60] has granted the permission to use the pictures): the PEA, the shaft, and the flapping wings.…”

Section: Current Pea-based For Flapping-wing Mavsmentioning

confidence: 99%

“…In [60], the authors presented a design of a simple flapping wing rotor composed of three basic elements (see Figure 8. Author of [60] has granted the permission to use the pictures): the PEA, the shaft, and the flapping wings. The actuator used is the THUNDER TH-8R, made of five layers of different materials.…”

Section: Current Pea-based For Flapping-wing Mavsmentioning

confidence: 99%

Getting Started with PEAs-Based Flapping-Wing Mechanisms for Micro Aerial Systems

et al. 2016

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This paper introduces recent advances on flapping-wing Micro and Nano Aerial Vehicles (MAVs and NAVs) based on Piezoelectric Actuators (PEA). Therefore, this work provides essential information to address the development of such bio-inspired aerial robots. PEA are commonly used in micro-robotics and precise positioning applications (e.g., micro-positioning and micro-manipulation), whereas within the Unmanned Aerial Vehicles (UAVs) domain, motors are the classical actuators used for rotary or fixed-wing configurations. Therefore, we consider it pertinent to provide essential information regarding the modeling and control of piezoelectric cantilever actuators to accelerate early design and development stages of aerial microrobots based on flapping-wing systems. In addition, the equations describing the aerodynamic behavior of a flapping-wing configuration are presented.

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Theoretical and experimental study of a piezoelectric flapping wing rotor for micro aerial vehicle

Cited by 72 publications

References 19 publications

Experimental study on the lift generated by a flapping rotary wing applied in a micro air vehicle

Experimental study on the lift generated by a flapping rotary wing applied in a micro air vehicle

Functional morphology and structural characteristics of wings of the ladybird beetle,Coccinella septempunctata(L.)

Getting Started with PEAs-Based Flapping-Wing Mechanisms for Micro Aerial Systems

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