Aerodynamic Performance of a Flyable Flapping Wing Rotor With Passive Pitching Angle Variation

Chen, Si; Wang, Le; He, Yanlin; Tong, Mingbo; Pan, Yingjun; Ji, Bing; Guo, Shijun

doi:10.1109/tie.2021.3112964

Cited by 19 publications

(6 citation statements)

References 28 publications

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“…In Cases 3 (φ ∈ [−50, 20]), the linear relationship only stands when the input voltage is over 4.5 V. From the weight parameters listed in Table 1, it is found that the FWR weighs 0.187 N while the maximum average lift (0.201 N) is achieved in Case 1-8 according to Figure 11. In this case, the lift-to-weight ratio reaches 1.07 and the take-off test is conducted in our previous study [29]. During the take-off test, a 4 g wire was used to connect an external power supply to the FWR model (not taking into account the battery weight).…”

Section: The Effect Of Asymmetric Stroke Angles On the Average Lift G...mentioning

confidence: 99%

Effect of Asymmetric Feathering Angle on the Aerodynamic Performance of a Flyable Bionic Flapping Wing Rotor

Chen

Wang

et al. 2022

SSRN Journal

Self Cite

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Section: The Effect Of Asymmetric Stroke Angles On the Average Lift G...mentioning

confidence: 99%

Effect of Asymmetric Feathering Angle on the Aerodynamic Performance of a Flyable Bionic Flapping Wing Rotor

Chen

Wang

et al. 2022

SSRN Journal

Self Cite

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“…Recently, a new biomimetic layout of MAVs called a flapping wing rotorcraft (FWR) was proposed, and it has been proved to achieve higher lift and aerodynamic efficiency at low Reynolds number [5][6][7][8]. Compared with existing flapping wing robots [9][10][11], the wing is not installed symmetrically with respect to the horizontal plane but has an initial installation angle (similar to the collective angle) as shown in figure 1(A).…”

Section: Introductionmentioning

confidence: 99%

“…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%

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.

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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.

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“…Among them, a new type of flapping-wing aircraft-micro Flapping Wing Rotorcrafts (FWRs)-integrates both the advantages of flapping and rotary wings, demonstrating superior capability of lift generation [1]. The state-of-the-art microFWRs even showcase several millimeter/milligram-scale designs [1,9,[12][13][14][15][16][17][18][19] that have rarely been achieved by conventional fixed or rotary-winged vehicles. Such microFWRs are foreseen as alternatives to commercial drones and would be in used in increasing breadths of applications such as search and rescue, surveying and inspection, and aerial photography [20].…”

Section: Introductionmentioning

confidence: 99%

Visual-Inertial Cross Fusion: A Fast and Accurate State Estimation Framework for Micro Flapping Wing Rotors

Dong

Wang

Liu

et al. 2022

Drones

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Real-time and drift-free state estimation is essential for the flight control of Micro Aerial Vehicles (MAVs). Due to the vibration caused by the particular flapping motion and the stringent constraints of scale, weight, and power, state estimation divergence actually becomes an open challenge for flapping wing platforms’ longterm stable flight. Unlike conventional MAVs, the direct adoption of mature state estimation strategies, such as inertial or vision-based methods, has difficulty obtaining satisfactory sensing performance on flapping wing platforms. Inertial sensors offer high sampling frequency but suffer from flapping-introduced oscillation and drift. External visual sensors, such as motion capture systems, can provide accurate feedback but come with a relatively low sampling rate and severe delay. This work proposes a novel state estimation framework to combine the merits from both to address such key sensing challenges of a special flapping wing platform—micro flapping wing rotors (FWRs). In particular, a cross-fusion scheme, which integrates two alternately updated Extended Kalman Filters based on a convex combination, is proposed to tightly fuse both onboard inertial and external visual information. Such a design leverages both the high sampling rate of the inertial feedback and the accuracy of the external vision-based feedback. To address the sensing delay of the visual feedback, a ring buffer is designed to cache historical states for online drift compensation. Experimental validations have been conducted on two sophisticated microFWRs with different actuation and control principles. Both of them show realtime and drift-free state estimation.

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Aerodynamic Performance of a Flyable Flapping Wing Rotor With Passive Pitching Angle Variation

Cited by 19 publications

References 28 publications

Effect of Asymmetric Feathering Angle on the Aerodynamic Performance of a Flyable Bionic Flapping Wing Rotor

Effect of Asymmetric Feathering Angle on the Aerodynamic Performance of a Flyable Bionic Flapping Wing Rotor

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

Visual-Inertial Cross Fusion: A Fast and Accurate State Estimation Framework for Micro Flapping Wing Rotors

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