Linear actuator powered flapping wing

Small scale unmanned aerial vehicles (UAVs) have proven themselves to be useful, but often too noisy for certain operations due to their rotary motors. This project examined the feasibility of using an almost silent linear actuator to power a flapping wing UAV. In order to this, a wing was designed and installed into a test set-up to replicate normal flight conditions of flapping wing flight (FWF). The designs of the wing, the test set-up and the actual experiments were biomimetic, looking to approximate the flight of real birds. The main goal of this study was to characterize a novel new linear actuator being developed in the Bio-Instrumentation Lab at MIT based on important parameters for FWF including the mounting position, the frequency of oscillation and the amplitude of oscillation of the wing. Ultimately the linear actuator performed well under all of the tests and was only limited by the control software. When the frequency and amplitude of oscillation were raised, the force on the actuator increased. The mounting position ended up not having a correlation with the force on the actuator, leading one to believe that it is not a critical parameter for this actuator-wing system.

Department dc:contributor.department

Massachusetts Institute of Technology. Dept. of Mechanical Engineering.

Grantor dc:publisher

Massachusetts Institute of Technology

Year dc:date.issued

2010

Author dc:creator

• Benson, Christopher Lee

Advisor dc:contributor.advisor

• Ian W. Hunter.

• Mechanical Engineering.

Statement dc:rights

• M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission.

Licence dc:rights.uri

• http://dspace.mit.edu/handle/1721.1/7582

Language dc:language.iso

eng

Handle dc:identifier.uri

http://hdl.handle.net/1721.1/59892

OAI identifier oai:identifier

oai:dspace.mit.edu:1721.1/59892