直升机桨叶铰链力矩改善方法研究  

The Study of Improving Helicopter Blade Hinge Moment

作　　者：谢梅莹 王道明 张晓星[1] 习娟[1] XIE Meiying WANG Daoming ZHANG Xiaoxing XI juan(China Helicopter Research and Development Institute, Jingdezhen 333001, China Army Aviator Flight Test Team, Jingdezhen 333001, China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001 [2]陆军航空兵试飞大队,江西景德镇333001

出　　处：《直升机技术》2017年第2期10-15,共6页Helicopter Technique

摘　　要：直升机前飞时,周期变化的铰链力矩通过操纵系统传给机身,使驾驶杆抖动和机身振动,并容易引起相关构件的疲劳损伤,过大的铰链力矩将使直升机的飞行难以控制。结合直升机桨叶铰链力矩的计算方法,给出两种改善桨叶铰链力矩的工程实用方法。在动平衡台上进行铰链力矩调整试验,得出平衡配重和后缘调整片对桨叶铰链力矩的影响规律。对某单旋翼直升机桨叶装机试飞,通过移动平衡配重和改变后缘调整片折弯角,获得了较好的铰链力矩水平,最终使飞行员轻松控制了旋翼总距。During forward flight, time -periodic hinge moment acting ter through the operating system could result in stick column tingling on the fuselage of the helicopairframe vibrating and is hkely to cause fatigue damage to relevant structural components. Excessive hinge moment could even make it difficult to control the flight. In combination with the calculation method of helicopter blade hinge moment, two methods for engineering applications that could improve the helicopter blade hinge moment without changing the helicopter blade airfoil were proposed. Hinge moment adjustment tests were con- ducted on dynamic balance bench and the effects of mass -balance and trailing edge tabs on blade hinge moment were obtained. The efficacy of the proposed adjusting plan was tested on certain type of single rotor helicopter, better hinge moment level was obtained by moving mass -balance weight and changing trailing edge tabs, which enable the pilots to control rotor collective pitch easily.

关 键 词：旋翼桨叶 铰链力矩 后缘调整片 试验 总距 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]