Publication: Experimental analysis of lift generated by flapping wing micro air vehicle
| datacite.subject.fos | oecd::Engineering and technology::Mechanical engineering | |
| dc.contributor.author | Chuah, Hanxen | |
| dc.date.accessioned | 2024-08-01T06:33:47Z | |
| dc.date.available | 2024-08-01T06:33:47Z | |
| dc.date.issued | 2008-04-01 | |
| dc.description.abstract | Flapping wing MAVs show great promise in civilian and military applications as it possesses good maneuverability at low speeds and relatively good energy efficiency. Hence, it is vital for the MAV to be able to carry a certain load of additional equipment in accordance to performing its function successfully. Experimental testing was conducted on the Cybird to analyze its wing design and flapping lift potential under different flapping frequencies, wind speeds and angles of attack. Lift force generated increases with the increasing flapping frequency at the corresponding wind speed. The Cybird is capable of a maximum lift of up to 4.5 N at 7.5 Hz. Positive net lift does not occur until after it breaks the 4Hz barrier. Lift increases with rising wind speeds until it reaches a critical frequency of 4.5 Hz, where lower wind speeds generates better lift. The increase in angle of attack would lead to better lift by the flapping wings. | |
| dc.identifier.uri | https://erepo.usm.my/handle/123456789/19980 | |
| dc.language.iso | en | |
| dc.title | Experimental analysis of lift generated by flapping wing micro air vehicle | |
| dc.type | Resource Types::text::report | |
| dspace.entity.type | Publication | |
| oairecerif.author.affiliation | Universiti Sains Malaysia |