| Budget Amount *help |
¥4,810,000 (Direct Cost: ¥3,700,000、Indirect Cost: ¥1,110,000)
Fiscal Year 2017: ¥1,300,000 (Direct Cost: ¥1,000,000、Indirect Cost: ¥300,000)
Fiscal Year 2016: ¥1,430,000 (Direct Cost: ¥1,100,000、Indirect Cost: ¥330,000)
Fiscal Year 2015: ¥2,080,000 (Direct Cost: ¥1,600,000、Indirect Cost: ¥480,000)
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| Outline of Final Research Achievements |
In order to develop a high efficiency Micro Air Vehicle (MAV) with a flapping mechanism, we attempted to control the aerodynamic force of flapping airfoils by using the plasma actuator (PA). Wind tunnel experiments and numerical simulation were carried out with respect to the motion period of the flapping motion using the ratio of PA driving and the switched timing as control parameters. As a result, aerodynamic lifting force could be increased by 6.8% compared with the case without PA control when PA is driven up to half of the flapping motion simultaneously with the start of swing up. In addition, it was possible to reduce the fluctuating lift by performing this control. From the results of the numerical simulations, the timing at which the vortex generates lift, efficient flapping motions, and control method were clarified. It was confirmed that the lift can be obtained stably with the control by the plasma actuator even in the turbulent flow fields.
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