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�������պ����ѧѧ�� 2011, Vol. 37 Issue (8) :918-922    DOI:
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��ڷ�, ����*
�������պ����ѧ ���տ�ѧ�빤��ѧԺ, ���� 100191
Control response analysis of small coaxial helicopter in hovering state
Xu Guanfeng, Chen Ming*
School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

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Abstract�� Based on the engineering reality, a calculation model of the rotor unsteady aerodynamics of the small coaxial helicopter in hovering state was set up. An airfoil unsteady aerodynamic model was established by introducing a set of Leishman-Beddoes semi-empirical indicial response formula. The induced velocity of the aerodynamic interaction between upper and lower rotors of a coaxial helicopter was set up by bringing in an interferential factor in the dynamic inflow model, the Runge-Kutta method was used to obtain the numerical solution of the rigid blade flapping angle. According to the calculation and analysis, the thrust and torque response to a rapid collective pitch increase in hovering state was gotten, and the course response differences between the semi-differential and full-differential direction control modes was compared.The results would be a necessary preparation for the research of coxial helicopter-s maneuvering flight.
Keywords�� small-scale coaxial helicopter   rotor unsteady   dynamic inflow   dynamic response     
Received 2010-04-07;
About author: ��ڷ�(1980-),��,����������,��ʿ��,bryantfeng@126.com.
��ڷ�, ����.��ͣ״̬��С�͹���ֱ����������Ӧ���Է���[J]  �������պ����ѧѧ��, 2011,V37(8): 918-922
Xu Guanfeng, Chen Ming.Control response analysis of small coaxial helicopter in hovering state[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2011,V37(8): 918-922
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