Dove: A biomimetic flapping-wing micro air vehicle

Yang, Wenqing; Wang, Liguang; Song, Bifeng

doi:10.1177/1756829317734837

Cited by 89 publications

(46 citation statements)

References 23 publications

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“…From the study, a wing in a trapezoidal shaped with an aspect ratio of 3.50 (for a complete wing), a taper ratio of 0.552, and stiffener locations of 84 • and 35 • gives better thrust characteristics [22]. Besides, it is also mentioned that wings with larger aspect ratios gain a higher lift to drag ratio, which is similar to the common rules used in fixed-wing aircraft [23]. In conclusion, the aspect ratio AR used for this paper is 3.50 (for a complete wing) and the taper ratio λ, is 0.55.…”

Section: Step 3-selecting the Wing Parametersmentioning

confidence: 88%

Wing Design, Fabrication, and Analysis for an X-Wing Flapping-Wing Micro Air Vehicle

Cheaw

Bakar

2019

Drones

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Flapping-wing Micro Air Vehicles (FW-MAVs), inspired by small insects, have limitless potential to be capable of performing tasks in urban and indoor environments. Through the process of mimicking insect flight, however, there are a lot of challenges for successful flight of these vehicles, which include their design, fabrication, control, and propulsion. To this end, this paper investigates the wing design and fabrication of an X-wing FW-MAV and analyzes its performance in terms of thrust generation. It was designed and developed using a systematic approach. Two pairs of wings were fabricated with a traditional cut-and-glue method and an advanced vacuum mold method. The FW-MAV is equipped with inexpensive and tiny avionics, such as the smallest Arduino controller board, a remote-control receiver, standard sensors, servos, a motor, and a 1-cell battery. Thrust measurement was conducted to compare the performance of different wings at full throttle. Overall, this FW-MAV produces maximum vertical thrust at a pitch angle of 10 degrees. The wing having stiffeners and manufactured using the vacuum mold produces the highest thrust among the tested wings.

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Section: Step 3-selecting the Wing Parametersmentioning

confidence: 88%

Wing Design, Fabrication, and Analysis for an X-Wing Flapping-Wing Micro Air Vehicle

Cheaw

Bakar

2019

Drones

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“…Flapping wing micro air vehicles (FWMAVs) are bionic aircraft that generate lift and thrust through the active movement of wings [1]. With the understanding of the flight mechanism of birds and the development of mechanical electronics and aerodynamics, researchers have developed a variety of bird-like FWMAVs [2][3][4][5], including "Dove" as developed by our group [5]. However, most of these FWMAVs are in the experimantal stage, and there are still some problems to be solved regarding practical military and civilian applications.…”

Section: Introductionmentioning

confidence: 99%

Active Disturbance Rejection Attitude Control for a Bird-Like Flapping Wing Micro Air Vehicle During Automatic Landing

2020

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To solve the attitude control problem of bird-like flapping wing micro air vehicles (FWMAVs) during automatic landing, an active disturbance rejection control (ADRC) architecture is proposed in this paper. This control scheme takes into account the attitude control of flapping , transition and gliding modes in the process of automatic landing. To verify the control effect, the aerodynamic estimation method of the flapping wing based on quasi-steady theory and the dynamics of an FWMAV in Lagrangian form are applied in the simulation. The proposed control architecture consists of two independent ADRC controllers to stabilize the attitude of the pitch and roll channels. The system disturbance and the coupling effects between channels are estimated by an extended state observer (ESO) and compensated in real time in the control output. The convergence of the ESO and ADRC is proven. Simulation results show that even if the aircraft is in different flight modes, the ADRC controller can track the target trajectory quickly and accurately. Then, to realize automatic landing in a real environment, a simplified two-stage landing trajectory is designed. A landing test is carried out on this basis. The test results show that ADRC can not only stabilize the flight attitude in flapping mode but also obtain a satisfactory control accuracy and convergence speed when the aircraft is in the transition and gliding modes, confirming its usefulness in automatic landing. INDEX TERMS flapping wing micro air vehicle, active disturbance rejection control, attitude control automatic landing

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“…Inspired by the unmatched flying capabilities of birds in nature, researchers have developed many types of bird-like flapping wing air vehicles, [1][2][3][4] The Dove flapping wing micro air vehicle (FWMAV) is one of them. 4 Similar to large-and medium-sized birds, the Dove FWMAV often flies via a process consisting of lowfrequency flapping flight, transition and gliding flight due to the high mass and large inertial force of the flapping wings. This combined flight mode integrating low-frequency flapping flight and gliding flight is often called the intermittent flapping and gliding flight mode.…”

Section: Introductionmentioning

confidence: 99%

Active disturbance rejection attitude control for the dove flapping wing micro air vehicle in intermittent flapping and gliding flight

Liang

Song

Xuan

et al. 2020

International Journal of Micro Air Vehicles

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This paper proposes an attitude control scheme for the Dove flapping wing micro air vehicle in intermittent flapping and gliding flight. The Dove flapping wing micro air vehicle adopts intermittent flapping and gliding flight to make the wing movements more natural; this strategy also has the potential to reduce energy consumption. To implement this specific flight mode, this paper proposes a closed-loop active disturbance rejection control strategy to stabilize the attitude during the processes of flapping flight, transition and gliding flight. The active disturbance rejection control controller is composed of three parts: a tracking differentiator, a linear extended state observer and a nonlinear state error feedback controller. The tracking differentiator estimates the given target signal and the differential signal in real time. The extended state observer estimates the system states and system nonlinearity. Moreover, the bandwidth parameterization method is applied to determine the observer gains. The stability of the closed-loop system is verified using Lyapunov’s theorem. Several outdoor flight experiments have been conducted to verify the effectiveness of the proposed control method, and the results show that the proposed method can guarantee the stability of intermittent flapping and gliding flight.

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Dove: A biomimetic flapping-wing micro air vehicle

Cited by 89 publications

References 23 publications

Wing Design, Fabrication, and Analysis for an X-Wing Flapping-Wing Micro Air Vehicle

Wing Design, Fabrication, and Analysis for an X-Wing Flapping-Wing Micro Air Vehicle

Active Disturbance Rejection Attitude Control for a Bird-Like Flapping Wing Micro Air Vehicle During Automatic Landing

Active disturbance rejection attitude control for the dove flapping wing micro air vehicle in intermittent flapping and gliding flight

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