直升机桨叶载荷校准试验的解耦实践  

Solving-couple Practice of the Helicopter Blade Load Calibration Test

作　　者：李永寿[1] 谢强[1] 程卫真[1] 

机构地区：[1]中国飞行试验研究院直升机飞行试验技术研究室,陕西西安710089

出　　处：《航空科学技术》2014年第10期59-63,共5页Aeronautical Science & Technology

摘　　要：本文围绕直升机桨叶载荷校准试验中出现的摆-挥、挥-摆耦合问题,阐释了一种快速、高效的摆-挥、挥-摆解耦方法。该方法通过建立摆振方向加载角度与挥舞电桥输出电压之间线性拟合关系实现摆-挥解耦,并通过计算挥-摆耦合系数,估算、调整摆振单片位置实现挥-摆解耦。最后,本文以某型直升机桨叶载荷校准试验的解耦结果、校准曲线和载荷方程,验证了该解耦方法的正确性和有效性。This paper focuses on lag-flap, flap-lag coupling problems in the helicopter blade load calibration test, explained a fast and efficient solving-couple method. This method achieved the lag-flap solving-couple by established the linear fit relationship between the loading-angle of lag direction and the flap electrical bridge output voltage, achieved the lag-flap solving-couple by calculated flap-lag coupling coefficient, estimated and adjusted position the strain gauges of lag direction. Finally, this paper verified the correctness and validity of the solving-couple method through the solving-couple results, calibration curve and load equation in the helicopter blade load calibration test.

关 键 词：直升机 桨叶 载荷校准 解耦 

分 类 号：V217.32[航空宇航科学与技术—航空宇航推进理论与工程]