Parameters identification of gyroplane longitudinal/lateral model from flight test

This paper presents the linear modelling of the gyroplane by the parameters identificaton method using the flight test data of a gyroplane. In recent years, unique advantages of gyroplanes have just been discovered, making it valuable in military or civilian fields. The research about unmanned gyroplanes has been initiated recently. The difficulty, which greatly impedes the research of unmanned gyroplanes, is the nonexistence of dynamic model. To solve this problem, the aerodynamic parameters indentification, based on actual flight test data in the manned gyroplane, is required. In order to get aerodynamic parameters of the linear dynamic model of the gyroplane, flight synchronous acquisition system was designed and established. Repeated flight tests based on excitation signal 211, was conducted. Through operation excitation, sufficient information was obtained to estimate parameters. Equation error method in frequency-domain was used to identify gyroplane aerodynamic parameters. The fitting degree between the flight test data and the responses of identified model proves the reliability of the the identified model. The degree of dispersion of multiple identification results characterizes recognition accuracy. Finally, based on the analysis of object properties, control law design was then carried out and the transformation from manned to unmanned control of gyroplane was therefore completed.