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Insect RoboFlyers are interesting and active focuses of study but producing high-quality flapping robots that replicate insect flight is challenging., due to the dual requirement of both a sophisticated transmission mechanism with light weight and minimal intervening connections. This innovative mechanism was created to address the need for a produ...
Citations
... From the computational studies for the proposed design, it is noticed that with higher frequency of flap, there is a severe compromise in the resultant lift and drag coefficients. In previous study performed by Singh et al., [33], for similar geometric modifications, it was inferred that an unsymmetric parabolic trend is noticed in the variation of the flapping frequency for a particular geometric configuration, where increasing the flapping frequency only increased the crucial fluid dynamic properties only to a certain extent. Any modifications further resulted in gradual drop of the performance. ...
... It was noticed that the peak coefficient of lift (attained at approximately 0.05 secondsperiodically) is just about 0.08, which is 72% -84% lower than the peak lift coefficients obtained in previous explorations made by Singh et al., [33] A similar trend is also noticed in the obtained force and coefficient of drag metric, as depicted in Figure 10, Figure 11, Figure 12 and Figure 13. ...
The study of insect-inspired flapping robo drones is exciting and ongoing, but creating realistic artificial flapping robots that can effectively mimic insect flight is difficult due to the transmission mechanism's need for lightweight and minimal connecting components. The objective of this work was to create a system of constructing a flapping superstructure with the fewest feasible links. This is one of the two strokes where the fast return mechanism turns circular energy into a variable angled flapping motion (obtained through simulation results). We have simulated the displacement modifications of the forward and return stroke variation. also conducted a kinematic study of the design processes differences, finding that it is significantly faster than the advance stroke. It was also seen that one of its levers lagged behind the others when flapping because of poor boundary conditions. Modelling the suggested motor-driven flapping actuation system helps verify its structural analysis and determine if it is appropriate for use in micro air vehicle applications.
... The importance of fluttering actuations and wing orientation to the generation of lift is evident from the above-described studies and recent literature review of prototype design mechanisms. Due to the complexity of designing and fabricating lighter, more efficient, and smaller FWMAVs, an efficient design approach is essential to obtain a superior conclusion [13][14][15]. ...
The transmission mechanism of artificial flapping-wing drones generally needs low weight and the fewest interconnecting components, making their development challenging. The four-bar
Linkage mechanism for flapping actuation has generally been used till now with complex and heavy connecting designs, but our proposed novel perpendicularly organized 3-cylindrical joint mechanism is designed to be unique and lighter weight with smooth functioning performance. The proposed prototype transforms the rotary motion of the motor into a specific angle of flapping movement, where the dimensions and specifications of the design components are proportional to the obtained flapping angle. Power consumption and flapping actuation can be monitored by adjusting the motor’s rotational speed to control the individual wing in this mechanism. The proposed mechanism consists of a crank with three slightly slidable cylindrical joints perpendicularly arranged to each other with a specified distance in a well-organized pattern to produce a flapping movement at the other end. In order to examine the kinematic attributes, a mathematical process approach is formulated, and kinematic simulations are performed using SIMSCAPE multibody MATLAB, PYTHON programming and COMPMECH GIM software. The proposed invention’s real-time test bench prototype model is
designed, tested and analyzed for flapping validation.
... CFD analysis has been extensively employed in the field of biomimetics. In [10], the authors performed a two-dimensional analysis on the base ornithopter configuration of an insect flying robot using commercial CFD codes: the results have yielded deeper insights regarding the influence of varying flapping frequency on critical flow metrics regarding adequate lift and thrust generation. Flying systems have been investigated also in [11], where CFD methods have been employed to model the transitional aerodynamics of the variable camber morphing wing. ...
The paper features a computational fluid dynamics study of a flapping NACA0015 hydrofoil moving with a combination of sinusoidal heaving and pitching. Several kinematic configurations are explored, varying sequentially pitch and heave amplitude, Strouhal number and phase angle, in an attempt to determine the influence of each parameter on the propulsive performance. To optimize efficiency the angle of attack should assume the highest value that also avoids the arise of the leading edge vortex generated in the dynamic stall state. At low Strouhal number optimum is reached at high heave amplitudes, which correspond to the configurations minimizing the hysteresis in the (Cy,Cx) plane. The same outcome in terms of hysteresis minimization has been verified to occur when optimal phase shift was considered. Differently, when the Strouhal number and the angle of attack become higher, to exploit efficiently the lift increment owed to dynamic stall it emerged the necessity of adopting low heave amplitude to improve separation resistance, avoiding the occurrence of deep stall.
Artificial flapping-wing robots necessitate a lightweight transmission mechanism with minimal interconnected parts, posing challenges to their development. This paper explores the design and analysis of a flapping actuation mechanism utilizing a crank and sliding lever configuration to convert rotational motion into angular flapping. The proposed mechanism represents a minimalist design concept with lightweight components specifically tailored for mosquito-sized flapping wing applications, contrasting with traditional, heavier four-bar mechanisms. Flight control is achieved through the crank slider design, facilitating essential maneuverability. Moreover, variations in forward and return stroke velocities contribute to enhanced lift generation. Structural and kinematic analysis of the flapping actuation mechanism are conducted to determine parameters such as wing angular velocity, acceleration, flapping angle, and frequency under maximum input voltage. Experimental validation of the concept is performed using data from a designed prototype, or flapping-wing testbed. Flapping angle measurements, similar to those of a mosquito, are verified using an ultrasonic sensor. Frequency validation involves separate flapping measurements on the testbench model using an infrared sensor and a laser tachometer, with validation of forward and reverse stroke durations. The return stroke consumed 37 percent of the cycle period, making it significantly faster than the forward stroke, which takes up 63 percent. Consequently, the time ratio between the forward and return strokes is 2:1, generating a favorable lift force throughout the wing's flapping cycle. This validates the sliding lever movement concept, with variations in the time and speed of flapping for both strokes observed in analytical results, simulation outcomes, and real-time testing.The suitability of the sliding lever mechanism for Micro Aerial Vehicle(MAV) flapping-wing applications is confirmed through these analysis and experiments.
