Volume 17, Issue 12 (2-2018)                   Modares Mechanical Engineering 2018, 17(12): 87-97 | Back to browse issues page

XML Persian Abstract Print


Download citation:
BibTeX | RIS | EndNote | Medlars | ProCite | Reference Manager | RefWorks
Send citation to:

Shams S, Mirzavand Boroujeni B, Mansoori S M, Kazemi M R. Kinematic analysis of articulated flapping wings mechanisms considering nonlinear quasi-steady aerodynamic. Modares Mechanical Engineering 2018; 17 (12) :87-97
URL: http://mme.modares.ac.ir/article-15-1037-en.html
1- Department of new sciences and technologis
2- Department of Aerospace Engineering, Faculty of New Sciences and Technologies, University of Tehran, Tehran, Iran
3- Department of Aerospace Engineering, Faculty of New Sciences & Technologies, University of Tehran, Tehran, Iran
Abstract:   (4271 Views)
In this paper, with the aim of calculating the Quasi-steady aerodynamic forces of articulated wing, a kinematic mechanism model for flapping wings is presented. First of all, the Kempf patent is used for simulating this mechanism, due to its simplicity and proper simulating of the flapping motion of articulated wings. This motion includes not-the-same-phase upstroke and downstroke motion of each part of wing. The angular position, angular velocity, angular acceleration and forces applied to both inner and outer part of the wing are analytically analyzed. Lifting line theory; that predicts the lift distribution of the three-dimensional wings based on the bounded vortex at the aerodynamic center, and is applied for single part wings of insects in the literature; is applied for articulated wings of birds, for the first time, in the present work. The average aerodynamic forces of articulated wing are obtained by calculating downwash and bounded vortex at each wing section and integrating on the wing surface. The results for an Ornithopter like 1kg gull with 5m/s of cruise speed indicate that both parts of the wing provide the lift. In addition, the outer wing has the main role to produce the thrust against the inner wing. The results show good agreement between the present work and the computational fluid dynamics method.
Full-Text [PDF 1190 kb]   (5950 Downloads)    
Article Type: Research Article | Subject: robatic
Received: 2017/08/17 | Accepted: 2017/11/3 | Published: 2017/12/1

Add your comments about this article : Your username or Email:
CAPTCHA

Rights and permissions
Creative Commons License This work is licensed under a Creative Commons Attribution-NonCommercial 4.0 International License.