01.1 - Aircraft Design and Integrated System (Basics and Theory)
NUMERICAL AND THEORETICAL INVESTIGATION OF HELICOPTER DITCHING WITH VARIOUS INITIAL VELOCITY AND PITCHING ANGLE
L. Zheng¹, M. Wang², Y. Lu², H. Qiao¹, T. Xiao¹, S. Deng¹; ¹Nanjing University of Aeronautics and Astronautics, China ;²Chinese Aeronautical Establishment, China
Results demonstrate the effects of initial downward velocity and pitching angle on the helicopter ditching process in detail. A shape factor and an average deadrise angle are introduced to extend the theoretical model for predicting the kinematic parameters during ditching.