[an error occurred while processing this directive]
   
 
���¿��ټ��� �߼�����
   ��ҳ  �ڿ�����  ��ί��  Ͷ��ָ��  �ڿ�����  ��������  �� �� ��  ��ϵ����
�������պ����ѧѧ�� 2011, Vol. 37 Issue (9) :1147-1150    DOI:
���� ����Ŀ¼ | ����Ŀ¼ | ������� | �߼����� << | >>
������϶���ѧҪ����������������Է���
������1, �����1, ����ӥ2*
1. �������պ����ѧ ���տ�ѧ�빤��ѧԺ, ���� 100191;
2. �й�ֱ��������о���, ������ 333001
Rotor damping analysis based on helicopter dynamic requirement with rotor/fuselage coupling
Guo Junxian1, Xiang Jinwu1, Qin Haiying2*
1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
2. China Helicopter Research and Development Institute, Jingdezhen 333001, China

ժҪ
�����
�������
Download: PDF (0KB)   HTML 1KB   Export: BibTeX or EndNote (RIS)      Supporting Info
ժҪ ��������������ֱ��������ѧ�����Ҫ��֮һ,����ȫ������ѧ���Ҫ��,���е��湲�������/����/����Ť��ϵͳ�ȶ��Է���,���ݴ��������ϵͳ�������Բ������Ҫ��.������ճ������������Һѹ���������ص�,�о����������նȺ������ȫ����϶���ѧ��Ӱ��;ͨ���Ƚϲ�ͬ�׾������׵���������,ȷ������������Ʒ���.�����������Լ���������������������ͻ���������֤�������:���������ܹ�������湲�������/����/����Ť��ϵͳ�ȶ���Ҫ��,����ʵ�������ڽ�Ҷ�۵��Ĺ���Ҫ��.
Service
�ѱ����Ƽ�������
�����ҵ����
�������ù�����
Email Alert
RSS
�����������
�ؼ����� ֱ����   ��϶���ѧ   ����   ����     
Abstract�� The rotor damping is one of the key points for a helicopter dynamic design. An introduction to the theoretical and practical study of one of the helicopter dynamic problems, which describesd the development of the rotor damping based on the helicopter dynamic with rotor/fuselage coupling that contains the stability analysis of ground resonance and the stability of rotor/power/transmission coherent was given. Based on the dynamic requirement of rotor/frame, damping analysis of the elasto-damper and the fluid-damper, which considered the effect of the stiffness and the damping was presented. The parametric sensitivity of the damper stiffness and damping was estimated. With constraints from engine control and ground resonance, the different effect was given with various available designs.Calculating and testing results performed demonstrating that, as solution to the dynamic problem, the damping with suitable orifice design for a variable liquid damper is reasonable for the helicopter dynamic problem solution and rotor blade folding.
Keywords�� helicopter   coupling dynamics   rotor   damping     
Received 2010-04-28;
About author: ������(1966-),��,����������,��ʿ��,gjx66@yahoo.com.cn.
���ñ���:   
������, �����, ����ӥ.������϶���ѧҪ����������������Է���[J]  �������պ����ѧѧ��, 2011,V37(9): 1147-1150
Guo Junxian, Xiang Jinwu, Qin Haiying.Rotor damping analysis based on helicopter dynamic requirement with rotor/fuselage coupling[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2011,V37(9): 1147-1150
���ӱ���:  
http://bhxb.buaa.edu.cn//CN/     ��     http://bhxb.buaa.edu.cn//CN/Y2011/V37/I9/1147
Copyright 2010 by �������պ����ѧѧ��