Abstract
Recent studies of flapping-wing aerial vehicles have been focused on the aerodynamic performance based on linear materials. Little work has been done on structural analysis based on nonlinear material models. A stress analysis is conducted in this study on membrane flapping-wing aerial vehicles using finite element method based on three material models, namely, linear elastic, Mooney-Rivlin non linear, and composite material models. The purpose of this paper is to understand how different types of materials affect the stresses of a flapping-wing. In the finite element simulation, each flapping cycle is divided into twelve stages and the maximum stress is calculated in each stage. The results show that 1) there are two peak stress values in one flapping cycle; one at the beginning stage of down stroke and the other at the beginning of upstroke, 2) maximum stress at the beginning of down stroke is greater than that at the beginning of upstroke, 3) maximum stress based on each material model is different. The composite and the Mooney-Rivlin nonlinear models produce much less stresses compared to the linear material model; and 4) the ratio of downstroke maximum stress and upstroke maximum stress varies with different material models. This research is helpful in answering why insect wings are so impeccable, thus providing a possibility of improving the design of flapping-wing aerial vehicles.
Highlights
All flying animals in the nature use flapping-wing flight mode
Fitzgerald et al [4] studied the fluid-structure interaction of flexible flapping-wing systems using the direct numerical simulations and unsteady vortex lattice method (UVLM).They found that the UVLM was more suitable in calculating unsteady aerodynamic forces; their material model was based on a linear model
Only simple flapping-wing aerial vehicles can be manufactured to simulate the motion of the insect wings
Summary
All flying animals in the nature use flapping-wing flight mode. Compared with the traditional fixed-wing and rotary-wing aerial vehicles, the main characteristics of flapping-wing unmanned aerial vehicle (UAV) include that it can produce the lift and thrust at the same time. (2014) Stress Analysis of Membrane Flapping-Wing Aerial Vehicle Based on Different Material Models. Fitzgerald et al [4] studied the fluid-structure interaction of flexible flapping-wing systems using the direct numerical simulations and unsteady vortex lattice method (UVLM).They found that the UVLM was more suitable in calculating unsteady aerodynamic forces; their material model was based on a linear model. Nakata et al [5] presented a fluid-structure interaction model of insect flapping flight with a flexible wing, using a linear material model. Mason et al [9] designed a small unmanned aerial systems to simulate the flapping kinematics of insects and birds, and used a linear material model to calculate the displacement amplitudes
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
