变化风场中直升机阵风载荷分析  

Analysis of gust load for helicopters in variable wind field

作　　者：刘通[1] 戴玉婷[1] 洪冠新[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《哈尔滨工业大学学报》2016年第2期173-178,共6页Journal of Harbin Institute of Technology

基　　金：国家自然科学基金(11302011;11172025);高等学校博士学科点专项科研基金(20131102120051)

摘　　要：为精确计算直升机阵风载荷,建立了同时考虑变化风场时间导数和空间梯度的直升机非线性动力学模型.通过质心处过载系数的时域响应仿真实现直升机阵风载荷计算分析,并与工程估算公式计算结果进行对比.由于全面考虑了直升机旋翼、尾桨、机身、垂直安定面和水平安定面等部件对阵风载荷的影响,对比结果验证了该方法在小前进比前飞时具有更高的精度.分析表明垂直方向阵风载荷对直升机结构强度影响较大,且在相同前进比时阵风载荷与阵风强度呈近似线性关系,所发展的方法能够适用于直升机在不同飞行状态和变化风场中的阵风载荷分析.In order to accurately calculate the result of gust load, a mathematical model of nonlinear system for helicopter flight dynamics is developed with the consideration of both temporal derivative and spatial gradient of variable wind velocity. The gust load for helicopter is analyzed through the time-domain overload coet/ieients simulation, which is compared with the result from engineering estimation formula. By consideing the influences of helicopter rotor, tail rotor, fuselage, vertical stabilizer and horizontal stabilizer on gust load, this method provides more accurate result of gust load in a forward flight with small advanced ratios. The comparison result shows that the vertical gust load has more significant influences on helicopter structural strength than gust in other directions. Moreover, the relationship between gust load and gust velocity strength is linear under the same advanced ratio. Numerical results indicate that the proposed method can be applied to analyze gust load in different flight states and variable gust fields.

关 键 词：直升机飞行力学 非线性系统 过载系数 阵风载荷 飞行安全 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程]