某型无人机碳纤维复合材料翼梁安全寿命预估

Method of Estimating Service Life of Carbon-fibre Composite Wing Spar in a kind of Unmanned Aerial Vehicle

摘要:

提出了一种无人机机翼碳纤维复合材料翼梁安全寿命预估的方法；首先进行了某型无人机静平衡飞行时的有限元分析,获得了碳纤维复合材料机翼的应力分布及应力集中区域；基于地面数据终端的遥测帧数据提取无人机基本飞行参数,在合理假设基础上推导了无人机机体迎角、侧滑角计算公式,再利用动力学方程反演无人机在机动载荷下的重心过载谱,进而结合机翼编制了机翼在各飞行剖面下的应力谱；然后,设计了机翼翼梁碳纤维复合材料试样,开展了试样的静力试验与疲劳试验,拟合得到了机翼翼梁碳纤维复合材料的S-N曲线；最后,基于Miner线性损伤累积原理,完成了某型无人机机翼翼梁的安全寿命评估；文章方法基于无人机地面数据终端的遥测帧数据进行翼梁应力谱编制,简单便捷,特别适用于中小型无人机装备过载谱的获取。

Abstract:

A method of estimating the service life of carbon-fibre composite wing spar is presented. Firstly by the finite element analysis of UAV in static balance, the area of stress concentration to carbon-fibre composite airfoil is acquired. Aiming at the droner flight parameters which is collected from feeder links to earth, the angle of attack and side slip angle can be deduced on the equivalent circuit of the linear induction motor through reasonable assumption, then the weight overload spectrum in dynamic load is inversed by kinetic and the dynamic load about airfoil is drew up in any flight profile. Static and fatigue test is carried out by carbon-fibre composite wing spar and then got the S-N curves. Finally, aiming at Miner theory, the life assessment of wing spar in UAV has been finished. The method aiming at the droner' flight parameters draws up the dynamic load of wing spar, it is convenient and suitable for acquiring dynamic load of UAV in small and medium size.