New Methodology for Achieving Trim Condition for a small Flapping Wing Air Vehicle.
Fanni, M., El-Gayyar, M., Sameh, A. (2020). New Methodology for Achieving Trim Condition for a small Flapping Wing Air Vehicle.. EKB Journal Management System, 40(1), 21-31. doi: 10.21608/bfemu.2020.100784
Mohammed A. Fanni; M. Samy El-Gayyar; Ahmed Sameh. "New Methodology for Achieving Trim Condition for a small Flapping Wing Air Vehicle.". EKB Journal Management System, 40, 1, 2020, 21-31. doi: 10.21608/bfemu.2020.100784
Fanni, M., El-Gayyar, M., Sameh, A. (2020). 'New Methodology for Achieving Trim Condition for a small Flapping Wing Air Vehicle.', EKB Journal Management System, 40(1), pp. 21-31. doi: 10.21608/bfemu.2020.100784
Fanni, M., El-Gayyar, M., Sameh, A. New Methodology for Achieving Trim Condition for a small Flapping Wing Air Vehicle.. EKB Journal Management System, 2020; 40(1): 21-31. doi: 10.21608/bfemu.2020.100784

New Methodology for Achieving Trim Condition for a small Flapping Wing Air Vehicle.

MEJ- Mansoura Engineering Journal
Article 9, Volume 40, Issue 1, March 2015, Page 21-31  XML PDF (967 K)
Document Type: Research Studies
DOI: 10.21608/bfemu.2020.100784
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Authors
Mohammed A. Fanni1; M. Samy El-Gayyar2; Ahmed Sameh* 3
1Assoc.Prof., Dept. of Mechanics and Robotics, Egypt-Japan University and Technology (E-Just), Alexandria, on leave, prod. Eng. & Mech. Design, Dept., Mansoura University
2Assoc. Prof., Prod. Eng. & Mechanical Design Dept., Mansoura University
3A demonstrator, B. Sc. of Prod. Eng. & Mechanical Design Dept., Mansoura University
Abstract
When dealing with a conventional aircraft, the design must be based on simplification assumptions, such as a cruising flight or a trimmed flight condition, which requires aircraft to have forces and moments equilibrium with respect to the center of gravity without any continuous control efforts. However, in case of ornithopters, there is no such equilibrium point due to the continuous flapping wing motion during the cruising flight. Therefore, this paper introduces a new methodology to obtain trimmed flight condition for a small flapping wing air vehicle. This methodology is based on applying initial impulsive forces to the air vehicle in such a way that the flapping wing air vehicle reaches almost constant flight speed after removing the initial impulsive forces. This enables the designer to examine the design parameters of the vehicle during realistic flight performance. A refined aerodynamic model programmed with MATLAB® is integrated into a flapping vehicle model using efficient multi body dynamics software MSC.ADAMS® to test the system. The results show perfect trimmed flight condition for a flapping wing air vehicle that never presented before in the literature. 
Keywords
Flapping flight; Multi-body dynamics; Flight simulation; MSC.ADAMS®; Trim condition
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