摘要
直升机标准桨叶的动态特性参数通过动平衡试验来校准,为了确定标准桨叶动平衡试验参数,利用叶素理论,把桨叶的挥舞角分解到二阶小量,建立了动平衡试验中孤立桨叶的带三次非线性项的Duffing型挥舞运动方程,用解析的Melnikov函数方法分析Duffing型挥舞方程对风速的稳定性阈值.把桨叶Duffing型挥舞方程与只精确到一阶项的挥舞方程进行数值比较,仿真试验表明在环境风速增大和桨叶挥舞角增大时二者误差变大,并通过仿真试验分析确定了满足标准桨叶动平衡试验的环境风速条件,实测结果与法国直升机桨叶动平衡试验环境风速的技术参数要求很接近.结果表明在动平衡试验中标准桨叶的挥舞对于环境风速是稳定的,并确定了标准桨叶动平衡试验环境的风速范围要求.
Dynamic parameters of standard blades for helicopters were calibrated by dynamic balance test. In order to determine parameters of the dynamic balance test for standard rotor blades, a theoretic analysis method based on the blade element theory is proposed. The Duffing flapping moment equation with cubic nonlinear item for a single blade was set up by breaking up the flapping angle, and the stable threshold value on the parameter of wind speed for the Duffing flapping moment equation was analyzed by Melnikov function. Comparison of the Duffing flapping moment equation with the first-order flapping equation indicates that high wind speed and large flapping angle will bring large errors, and the Wind speed range required in dynamic balance test for standard ro- tor blades is determined by simulation methods, the test data are uniform with the technical parameter of wind speed range required in dynamic balance test for rotor blades of helicopters made in France. The results indicate that the flapping moment of standard rotor blades is stable for wind speed in dynamic balance test, and the determination of the wind speed range for the environment of dynamic balance test is appropriate.
出处
《哈尔滨工业大学学报》
EI
CAS
CSCD
北大核心
2009年第1期24-30,共7页
Journal of Harbin Institute of Technology
基金
国防科技工业“十一五”技术基础科研资助项目(07B240)
