Experimental and numerical study of flapping wing rotary MAV

Wei, Xu; Li, Daochun; Jiaqi, Jiang; Puxue, Tan; Xiang, Jiawei

doi:10.1109/icus.2017.8278311

Cited by 5 publications

(7 citation statements)

References 20 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Their research claimed that FWR can produce the greatest aerodynamic lift, with power efficiency lying between rotary and insectlike flapping wings. This conclusion was also proved by Wu et al [17,18], and, in the same year, Wei et al [19] designed and tested a motor-driven FWR named RotorBee, achieving the first untethered vertical takeoff and landing of an FWR in the world. It is worth mentioning that in 2020 Xin et al [20] introduced a three-wing motor-driven FWR which can perform controlled stable flight through the control surfaces.…”

Section: Introductionmentioning

confidence: 58%

“…To date, most of the proposed FWRs [8,[19][20][21] still contain complex mechanical transmission structures, which strictly confine the wing's otherwise freely variable flapping trajectory, and further limit the aerodynamic optimization and controller design of FWRs. Furthermore, since the flapping wing part only provides an upward force without control torques, it also needs adjunct control surfaces powered by actuators that are cumbrous to stabilize.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Design, modelling, and experimental validation of a self-rotating flapping wing rotorcraft with motor–spring resonance actuation system

Liu¹,

Song²,

Dong³

et al. 2023

Bioinspir. Biomim.

View full text Add to dashboard Cite

Compared with traditional flapping motion, Flapping Wing Rotor (FWR) frees the rotating freedom by installing the two wings asymmetrically, which introduces rotor’s motion characteristics and enables FWR to have higher lift and aerodynamic efficiency at low Reynolds number. However, most of the proposed FWRs contain linkage mechanical transmission structures, the fixed degrees of freedom (DoFs) of which prohibit the wings from achieving variable flapping trajectories, limiting the further optimization and controller design of FWRs. In order to fundamentally address the above challenges of FWRs, this paper presents a new type of FWR with two mechanically decoupled wings, which are directly driven by two independent motor- spring resonance actuation systems. The proposed FWR has 12.4 grams of system weight and 165-205mm wingspan. In addition, a theoretical electromechanical model based on the DC motor model and quasi-steady aerodynamic forces is established, and a series of experiments are conducted in order to figure out the ideal working point of the proposed FWR. It is notable that both our theoretical model and experiments exhibit uneven rotation of the FWR during flight, i.e., rotation speed dropping in the downstroke while boosting in the upstroke, which further tests the proposed theoretical model and uncover the relationship between flapping and passive rotation in the FWR. To further validate the performance of the design, free flight tests are conducted, and the proposed FWR demonstrates stable liftoff at the designed working point.

show abstract

Section: Introductionmentioning

confidence: 58%

Section: Introductionmentioning

confidence: 99%

Design, modelling, and experimental validation of a self-rotating flapping wing rotorcraft with motor–spring resonance actuation system

Liu¹,

Song²,

Dong³

et al. 2023

Bioinspir. Biomim.

View full text Add to dashboard Cite

show abstract

“…A micro air vehicle (MAV) is a mechanical device with the ability to fly and can be divided into three types according to the way it generates lift: a fixed-wing flying robot like a jet-propelled aircraft, a rotor-wing vehicle like a helicopter, and a flappingwing robot that mimics birds or insects [1,2]. Micro flappingwing air vehicles have many advantages over the first two types of flight, including their ultra-small size, high flexibility, better manoeuvrability, and excellent hovering ability [3]. ese advantages provide MFWAV with the ability of obstacle avoidance and navigation control in tight spaces.…”

Section: Introductionmentioning

confidence: 99%

Mechanism Design and Motion Analysis of a Flapping-Wing Air Vehicle

Shi

Guo

et al. 2022

Mathematical Problems in Engineering

View full text Add to dashboard Cite

Micro flapping-wing air vehicles (FWAV) are highly appreciated by scientists and scholars around the world due to their small size, high flexibility, and better manoeuvrability. There are huge potential applications of flapping-wing robots in rescue, survey, and search, as they can enter more dangerous and narrow spaces to accomplish tasks that were previously impossible for people. In this paper, we first analyze the flapping motion of birds by reviewing a large amount of information and literature and identifying the sources of lift and thrust during flight. Then, the double crank and double rocker mechanisms are optimized as the flapping mechanism. Proper flapping-wing size is further determined by analyzing the relative position between the driving mechanism and the flapping mechanism. Moreover, a pitch mechanism consisting of ball hinges is designed to realize the wing’s pitching motion for additional thrust. The fuselage and landing gear of the flapping-wing robot are designed for low air resistance and lightweight, and the tail mechanism are designed to have both roll and pitch freedoms, offering excellent manoeuvrability during flight. Simulation results show positive lift force is generated based on the novel pitching design for the small wing. The research in this paper is an important resource for novice researchers to design and study the advanced and complex problems of flapping-wing air vehicles.

show abstract

“…It has a variety of flying capabilities such as lowspeed flight, vertical take-off and landing, and hovering. Therefore, it has important military and civilian values, [1][2][3][4] such as unmanned reconnaissance, information transmission, and target tracking tasks in complex and narrow spaces, as well as environmental monitoring, disaster investigation, search, etc. However, the nano rotor is flying at a low Reynolds number, the influence of the viscous force increases significantly, and it is easy to cause laminar flow separation and reduce the aerodynamic performance of the rotor.…”

Section: Introductionmentioning

confidence: 99%

Investigation on aerodynamic characteristics of bionic membrane nano rotor

Zhao

Liu

Lü

et al. 2021

International Journal of Micro Air Vehicles

View full text Add to dashboard Cite

In this paper, the bionic membrane structure is introduced to improve the aerodynamic performance of nano rotor at the low Reynolds number. The aerodynamic characteristics of nano rotor made of hyperelastic material as membrane blades are studied. Firstly, based on the hyperelastic constitutive model, a finite element model of the rotor is established and compared with the results of the modal test to verify the accuracy of the model. Then the computational fluid dynamics model of membrane nano rotor is established which combined with the finite element model. The aerodynamic characteristics of the membrane rotor under hovering conditions are studied using fluid–structure interaction method. It is found that the calculation results matched well with the experiment results. The design of the structural parameters such as the membrane proportion, shape, and position of the membrane rotor is optimized. The influence of each parameter on the aerodynamic performance of the rotor is obtained. Under certain structural conditions, the performance can be effectively improved, which provides a new idea for the design of the nano rotor.

show abstract

Experimental and numerical study of flapping wing rotary MAV

Cited by 5 publications

References 20 publications

Design, modelling, and experimental validation of a self-rotating flapping wing rotorcraft with motor–spring resonance actuation system

Design, modelling, and experimental validation of a self-rotating flapping wing rotorcraft with motor–spring resonance actuation system

Mechanism Design and Motion Analysis of a Flapping-Wing Air Vehicle

Investigation on aerodynamic characteristics of bionic membrane nano rotor

Contact Info

Product

Resources

About