支柱式起落架航向载荷研究

Research on heading load of pillar landing gear

航向载荷是飞机着陆载荷的重要组成部分,受到起落架航向刚度的影响并影响着起落架的设计。对航向刚度进行理论分析,推导出起落架的挠度计算公式,以某型无人机的缩比验证机起落架为研究对象,并用Hypermesh对公式进行了仿真验证。结果显示,有限元软件仿真得到的挠度最大值与公式计算得到的挠度最大值仅相差3.3%。在进行落震试验过程中发现航向载荷存在滞后,在LMS Virtual.lab motion中建立落震试验模型,仿真分析发现航向载荷滞后是由地面载荷测量平台的惯性力引起的,通过测量平台的航向加速度并转化为平台的航向惯性力,叠加到试验数据上可抵消地面载荷测量平台的惯性力。

The heading load is an important part of the landing load of an aircraft,which is affected by the heading stiffness of the landing gear and affects the design of the landing gear.The heading stiffness is theoretically analyzed,and the deflection calculation formula of the landing gear is deduced.The landing gear of a certain type of UAV is used as the research object,and the formula is simulated and verified by Hypermesh.The results show that the deflection value obtained by the finite element software simulation is only 3.3%different from the maximum deflection value calculated by the formula.During the drop test,it is found that the heading load has hysteresis.The drop test model is established in LMS Virtual.lab motion.The simulation analysis finds that the heading load lag is caused by the inertial force of the ground load measurement platform.The heading of the measurement platform is measured.The acceleration is converted into the heading inertial force of the platform,which can be superimposed on the test data to offset the inertial force of the ground load measurement platform.