Data Gathering for Gyroplane Flight Dynamics and Simulation Research

Kurzfassung

DLR’s Institute of Flight Systems performs flight dynamics and simulation research on modern lightweight gyroplanes. The lack of understanding the flight dynamics of gyroplanes during sideslip has been the trigger to start a flight test program in order to gather objective data. For this purpose DLR used an MTOsport gyroplane by AutoGyro GmbH – the D-MTOS. This lightweight gyroplane, which has an MTOW of 450kg, is a two-seater tandem configuration driven by a Rotax 912 ULS engine with a propeller in pusher configuration. The D-MTOS has been equipped with a special Flight Test Instrumentation (FTI) by messWERK GmbH. The design of the FTI has been optimized with respect to the limited space and payload of a small aircraft. This enabled the use of highly accurate sensors and an advanced real-time data-acquisition system that is usually used in larger aircraft. As only the pilot was on board, the system was set up to require a minimal workload. In order to deliver high-quality measurements of the airflow, a nose boom with a length of more than two meters has been installed. At its tip special vanes for measuring the Angle of Attack and sideslip were installed. Compared to fixed-wing aircraft, the measurement range of the airflow angle is a real chal-lenge as the Angle of Attack (AoA) reached values of up to 80°. Static and dynamic pressures were measured to provide airspeed and altitude. Beside the control inputs and forces also the attitude and inertial data were measured. The measurement of the rotor blade flapping angle has been also a challenge. Two laser sensors were mounted at the top of the rotor mast, providing distance measurements that may be used to determine the blade flapping angle at two positions (forward and right hand side). After a specific flight safety review with respect to the severe sideslip maneuvers the flight test program has been initiated in October 2012. In total 26 sideslip maneuvers have been con-ducted during landing approach. Preliminary results from this test program are presented in this paper.