Mohammadreza Radmanesh, Iman Samani, Omid Nematollahi, Ahmad Sedaghat, Mahdi Niliahmadabadi,IUT MAV2013, Part II: Flight test results, IMAV2013, France, 2013.
IUT MAV2013, Part II: Flight test results
Mohammadreza Radmanesh (Rezaradmanesh90@hotmail.com), *Iman Samani (firstname.lastname@example.org), Mostafa Hassanalian (Mostafa.Alian@gmail.com), Omid Nematollahi (O.Nematollahi@gmail.com), Ahmad Sedaghat (email@example.com), and Mahdi Niliahmadabadi (firstname.lastname@example.org)
Department of Mechanical Engineering, Isfahan University of Technology,
Isfahan 84156-83111, I.R. of Iran
As the final stage, the IUT MAV2013 was tested in flight. The main goal of was to assess the manoeuvrability of the MAV through some flight tests programmes. For tracking this goal and showing efficiency of the procedure a control system was installed on MAV and data of flight was collected. The main purpose of using a control system during the flight is to stabilize the aircraft after being disturbed from its wing-level equilibrium flight attitude. In this study by using a Gyro sensor and the control circuit, the longitudinal angle of MAV has been measured.
The main reason of measuring the longitudinal angle is to find out the efficiency of the proposed cycle. The Gyro sensor has been normally placed on the wing with the Angle of 4 degrees and this angle has been considered as the Level Angle. Sensors data has been saved every 0.5 second and plotted for each Flight test. Flight tests include hand lunch, increasing altitude, cruse flying and landing.
Keywords: Micro Aerial Vehicle (MAV); Aerofoil flows, Flight tests, Tailless wing and body.