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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。
When the helicopter flew forward, the periodically varying hinge moment is transmitted to the fuselage through the operating system, causing the steering column to vibrate and the body to vibrate, which can easily cause the fatigue damage of the related components. The excessive hinge moment will make the helicopter flight difficult to control. Combined with the calculation method of helicopter blade hinge moment, two engineering practical methods to improve the hinge moment of blade are given. The hinge torque adjustment test was carried out on the dynamic balance table, and the influence rule of the balance weight and the trailing edge adjustment piece on the blade hinge moment was obtained. For a single-rotor helicopter with a blade mounted on a flight test, a better hinge moment level was obtained by moving the counterweight and changing the bending angle of the trailing edge adjustment piece, which eventually allowed the pilot to easily control the total rotor pitch.