Department of Mechano-Informatics, The University of Tokyo, Bunkyo-ku, Japan.
Bioinspir Biomim. 2010 Sep;5(3):036005. doi: 10.1088/1748-3182/5/3/036005. Epub 2010 Aug 16.
This paper presents direct measurements of the aerodynamic forces on the wing of a free-flying, insect-like ornithopter that was modeled on a hawk moth (Manduca sexta). A micro differential pressure sensor was fabricated with micro electro mechanical systems (MEMS) technology and attached to the wing of the ornithopter. The sensor chip was less than 0.1% of the wing area. The mass of the sensor chip was 2.0 mg, which was less than 1% of the wing mass. Thus, the sensor was both small and light in comparison with the wing, resulting in a measurement system that had a minimal impact on the aerodynamics of the wing. With this sensor, the 'pressure coefficient' of the ornithopter wing was measured during both steady airflow and actual free flight. The maximum pressure coefficient observed for steady airflow conditions was 1.4 at an angle of attack of 30 degrees . In flapping flight, the coefficient was around 2.0 for angles of attack that ranged from 25 degrees to 40 degrees . Therefore, a larger aerodynamic force was generated during the downstroke in free flight compared to steady airflow conditions.
本文对基于鹰蛾（Manduca sexta）模型的自由飞行昆虫扑翼飞行器的机翼气动特性进行了直接测量。使用微机电系统（MEMS）技术制造了一个微型差分压力传感器，并将其安装在扑翼飞行器的机翼上。传感器芯片的面积小于机翼面积的 0.1%。传感器芯片的质量为 2.0 毫克，不到机翼质量的 1%。因此，与机翼相比，传感器既小巧又轻便，使得测量系统对机翼的空气动力学特性影响最小。利用该传感器，在稳定气流和实际自由飞行中测量了扑翼飞行器机翼的“压力系数”。在迎角为 30 度的稳定气流条件下，观察到的最大压力系数为 1.4。在扑翼飞行中，在 25 度到 40 度的迎角范围内，系数约为 2.0。因此，与稳定气流条件相比，在自由飞行的下降阶段产生了更大的空气动力。
