民用飞机运营中突风速度的识别方法研究  

Analysis on gust recognition method for civil aircraft operation

作　　者：刘滢滢 Liu Yingying(School of Astronautics,Harbin Institute of Technology,Heilongjiang Harbin,150001,China;The Load Department of Shanghai Aircraft Design and Research Institute,Commercial Aircraft Corporation of China Ltd.,Shanghai,201210,China)

机构地区：[1]哈尔滨工业大学航天学院,黑龙江哈尔滨150001 [2]中国商用飞机有限责任公司上海飞机设计研究院,上海201210

出　　处：《机械设计与制造工程》2023年第9期106-110,共5页Machine Design and Manufacturing Engineering

摘　　要：为了能够使用试飞数据进行突风速度识别,首先构建大展弦比单机翼突风计算模型,通过对气动力影响系数矩阵进行有理化处理,并对突风激励采用傅里叶变换和傅里叶逆变换处理,完成气动弹性混合建模,然后在Simulink中实现状态空间内的时域响应分析,分别采用重心及翼梢过载,考虑质量、刚度、阻尼及非定常气动力的影响,实现突风速度的识别,并提出使用试飞气动参数进行识别方法修正的措施。分析结果显示:采用重心及翼梢过载,对单频及多频突风速度最大值的识别误差不超过1%;使用气动参数可有效修正识别方法;只采用过载、姿态角及速度的试飞数据,可实现民用飞机在运营过程中突风速度识别统计,为飞行品质评估、控制律设计及疲劳突风载荷谱编制提供数据基础。The gust analysis model of single wing of civil aircraft is constructed,and analysis on the recognition method of the gust velocity using acceleration and attitude angle is performed for civil aircraft operation.The state-space equations of single wing are established by applying rational function approximation of unsteady aerodynamics with the fourier and inverse fourier transform of gust velocity input matrix in Simulink.The gust velocity with one frequency and two frequencies are recognized with the acceleration of grid at centre of gravity and the acceleration of grid in the flexible wingtip considering mass,stiffness,damping and unsteady aerodynamics matrices.The procedure correcting the recognition method with actual civil aircraft aerodynamic parameter is presented.The pick velocity difference between actual gust velocity input and recognized gust velocity is less than 1%.The analysis results demonstrate the presented aerodynamic parameter identification and correction method is efficient and effective with acceleration attitude and velocity.The gust recognition method provides the foundation method for flying quality assessment,control law design and fatigue gust load spectrum design.

关 键 词：气动弹性 突风响应 突风速度识别 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]