摘要
针对直升机旋翼风洞试验载荷配平需求,发展了基于牛顿迭代法的旋翼风洞试验载荷自动配平方法。根据悬停和前飞不同的配平需求分别制定了相应的配平策略,并利用1.5m直径旋翼模型在FL-52风洞开展了悬停及前飞不同工况下的旋翼载荷自动配平验证试验。结果表明,不同悬停状态下,CT配平相对误差小于0.8%;不同前飞状态下,CT配平相对误差控制在3%,桨毂力矩Mx、Mz控制在1.5N·m以内,并且随着CT的增大,配平精度逐渐提高。可以看出该方法实现了配平过程的闭环控制,提高了配平的自动化水平,适用于旋翼风洞试验。
Aiming at the requirements on helicopter rotor automatic trim in wind tunnel test,a rotor wind tunnel test system is built,and an automatic trim method for rotor wind tunnel test based on Newton-Raphson method is developed.According to the different trimming requirements on hovering and forward flight,the corresponding trimming strategy is formulated,and the 1.5m rotor model wind tunnel test research is carried out in the FL-52 wind tunnel under different conditions of hovering and forward flight.The results show that the relative error of C.is less than 0.8%under different hovering conditions,the relative error of C,is less than 3%under different forward flight,the hub torque M,Mis controlled within 1.5Nm,and with the increase of Cr,the trimming accuracy is gradually improved.It can be seen that the close-loop control of the trim process is realized and the automation level of trimming is improved.This method is suitable for rotor wind tunnel test.
作者
刘向楠
刘实
刘兴旺
周国成
Liu Xiangnan;Liu Shi;Liu Xingwang;Zhou Guocheng(Low Speed High Reynolds Number Aeronautical Key Laboratory,AVIC Aerodynamics Research Institute,Harbin 15001,China;Heilongjiang ProvinceKey Laboratory of Aerodynamic Noise and Its Control,Harbin 150001,China)
出处
《气动研究与试验》
2024年第2期113-118,共6页
Aerodynamic Research & Experiment
关键词
直升机
旋翼
风洞试验
自动配平
牛顿迭代法
helicopter
rotor
wind tunnel test:automatic trim
Newton-Raphson
