Investigation of wing clappers for micro-air vehicle
An experimental study was conducted to assess the aerodynamic benefits of using ‘Clap-and-Fling’ flapping flight mechanics for the development of Micro-Aerial Vehicle (MAV). The overall flight performance in terms of thrust generation of the ‘Clap-and-Fling’ flight was compared with the ‘no-clap’ fl...
محفوظ في:
| المؤلف الرئيسي: | |
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| مؤلفون آخرون: | |
| التنسيق: | Final Year Project |
| اللغة: | English |
| منشور في: |
2015
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| الموضوعات: | |
| الوصول للمادة أونلاين: | http://hdl.handle.net/10356/64022 |
| الوسوم: |
إضافة وسم
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| الملخص: | An experimental study was conducted to assess the aerodynamic benefits of using ‘Clap-and-Fling’ flapping flight mechanics for the development of Micro-Aerial Vehicle (MAV). The overall flight performance in terms of thrust generation of the ‘Clap-and-Fling’ flight was compared with the ‘no-clap’ flight in order to distinguish the effect of ‘clapping’ wings for flapping flight applications. The comparison was tested for both wing stroke angle of 65° and 100° respectively to identify the effect of wing amplitude angle on the efficiencies of Clap-and-Fling configuration. The experimental results clearly revealed that the ‘Clap-and-Fling’ mechanics provided significant aerodynamic benefits. The thrust/frequency ratio and the thrust/power ratio is higher for the ‘Clap-and-Fling’ flight. It was found out that the ‘clapping’ effect is significantly dominant in flapping frequency above 20Hz for the 65° stroke angle model. For flapping at 100° wing stroke angle, external factors such as motor overloading and wing stiffness had override the desired ‘clapping’ effect. |
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