本研究利用目前可連續飛行達367秒的微飛行器，以變動連桿參數的方式，去改變其拍翼行程角，並放置於風洞內量測氣動力數據，探討其升推力之間的關係。 在此改變拍翼行程角主要的風洞實驗結果為：四種拍翼行程角，升力隨著傾角的增加而上升。而拍翼行程角39度、拍翼行程角52.8度、拍翼行程角70.6度，在考慮推力為正值的情況下，其升力皆可達8克以上。所以在控制全機的重量下，搭配目前本實驗的飛行器套件，調整傾角及飛行速度，使其可以飛行的合適拍翼行程角有39度、52.8度及70.6度。 The purpose of this study is to discuss various flapping angles effect on aerodynamic performance of micro aerial vehicle (MAV). We adopt a transmission system parameter as a criterion which has a successful remote flight with 367 seconds. By adjusting the length of links we can make different stroke angles. This changes result in different aerodynamic output, especially in lift and thrust force. Meanwhile, a lot of flapping signals from wind tunnel tests are acquired, this data help us realizes the relationship between lift and thrust force in various flapping angles. The flappers with four stroke angles are set and tested in the wind tunnel. The results show: Lift forces are increased with increasing inclined angle. From the experimental data, in order to find a successful flight parameter, the lift force must be over 8 gf and the thrust forces are still positive. The stroke angle of 39, 52.8, 70.6 degree are satisfied our need. At the same time, to compare and make sure the wind tunnel tests are correct, several MAV flight test are performed. The total weight of MAV is less than 8 grams, by controlling the tail angle, position of gravity center and the flapping frequency, we can control the velocity and inclined angle in flight. The flight test show the stroke angles of 39, 52,8 and 70.6 degrees are successful.
