Application and Improvements of the Wing Deformation Capture with Simulation for Flapping Micro Aerial Vehicle
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Journal of Bionic Engineering http://www.springer.com/journal/42235
Application and Improvements of the Wing Deformation Capture with Simulation for Flapping Micro Aerial Vehicle Wee-Beng Tay1*, Siddharth Jadhav1, Jian-Lei Wang2 1. Centre for Aerodynamics & Propulsion, Temasek Laboratories, National University of Singapore, Singapore 117411, Republic of Singapore 2. Shaanxi Aerospace Flight Vehicle Design Key Laboratory, School of Astronautics, Northwestern Polytechnical University, Xi’an 710072, China
Abstract Wing deformation capture with simulation is a mixed experimental-numerical approach whereby the wing deformation during flapping is captured using high-speed cameras and used as an input for the numerical solver. This is an alternative approach compared to pure experiment or full fluid structure interaction simulation. This study is an update to the previous paper by Tay et al., which aims to address the previous limitations. We show through thrust and vorticity contour plots that this approach can simulate Flapping Micro Aerial Vehiclex (FMAVs) with reasonable accuracy. Next, we use this approach to explain the thrust improvement when an additional rib is added to the original membrane wing, which is due to longer duration for the new wing to open during the fling stage. Lastly, by decreasing the number of points and frames per cycle on the wing, we can simplify and shorten the digitization process. These results show that this approach is an accurate and practical alternative which can be applied to general bio-inspired research. Keywords: flapping MAV, immersed boundary method, wing deformation, membrane wings Copyright © Jilin University 2020.
1 Introduction There are many different types of Flapping Micro Aerial Vehicles (FMAVs) prototypes[1–5]. Although there are some FMAVs with complicated wing designs[6,7], due to weight constraint, the design of most FMAVs wings[1–3] consist of a relatively rigid leading edge spar with “ribs reinforced” Mylar membrane, as shown in Fig. 1a. Although simple and light-weight, there are rooms for improvement through flow field and vorticity contour analysis. From the experimental aspect, using Particle Image Velocimetry (PIV), we can obtain only the velocity flow field. To obtain pressure values, an indirect way is to calculate it through the integral form of the momentum equation together with the velocity flow field data, as demonstrated by van Oudheusden et al.[8] and Tronchin et al.[9]. On the other hand, while using numerical methods with Fluid Structure Interaction (FSI) can capture the entire 3D velocity flow fields and pressure, it is more complex and computationally more expensive. Some of the works reported include the FSI simulations of a ci*Corresponding author: Wee-Beng Tay E-mail: [email protected]
cada insect by Tian et al.[10], and a hovering hawkmoth by Nakata and Liu[11]. Another alternative is a mixed experimentalnumerical approach whereby the wing deformation during flapping is captured using high-speed cameras and used as an input for the numeri
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