直升机自转飞行的最大过载系数试飞验证  

Flight Test Verification of Maximum Overload Coefficient for Helicopter Autorotation Flight

作　　者：李永寿[1] LI Yong-shou(Chinese Flight Test Establishment,Xi'an 710089,China)

机构地区：[1]中国飞行试验研究院,西安710089

出　　处：《科学技术与工程》2021年第5期2085-2092,共8页Science Technology and Engineering

摘　　要：为了验证直升机自转飞行的最大过载系数,首先从直升机最大过载系数理论估算模型入手,分析最大过载系数的关键影响因素;其次,通过对模拟自转下滑和俯冲拉起试飞方法的研究,确定自转情况俯冲拉起的初始试验高度、自转进入速度以及纵向重心位置;最后,提出了一种自转情况俯冲拉起试飞方法并经飞行试验验证,结果表明:该方法能够验证直升机自转飞行的最大过载能力;获取的过载系数随拉杆量、旋翼转速的变化关系曲线与理论分析吻合。这对试飞工程师和试飞员理论、驾驶技术培训具有较高的科学研究和推广应用价值。The research aims to verify the maximum overload coefficient of the helicopter's autorotation flight.Firstly,the study started with the theoretical estimation model of the helicopter's maximum overload coefficient and analyzed the key influencing factors of the maximum overload coefficient.Secondly,the dive of the autorotation situation was simulated by the method of autorotation glide and dive pull test flight to determine the initial test altitude,rotation entry speed,and longitudinal center of gravity of the helicopter.Finally,a method of dive-and-pull test flight under rotation was proposed,and the relationship between the overload coefficient and the amount of tie rod and rotor speed was studied to determine the maximum overload factor value of the rotation flight.This method fills the gap of my country's flight test method,and has high scientific research value and popularization and application value for flight test engineers and test pilots.

关 键 词：直升机 自转飞行 俯冲拉起 过载系数 试飞方法 

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]