直升机复合材料拉扭条扭转性能分析  

Analysis of Torsional Performance of Helicopter’s Composite Material Stainless Laminated Strip

作　　者：朱慧玲 杨磊[1] ZHU Huiling;YANG Lei(China Helicopter Research and Development Institute,Jingdezhen 333001,China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001

出　　处：《直升机技术》2024年第2期35-38,45,共5页Helicopter Technique

摘　　要：拉扭条作为直升机旋翼桨毂的主要承力结构,承受桨叶旋转产生的离心力并通过自身的大变形实现桨叶的变距,其所承载的离心力和扭角变形随直升机飞行状态的变化而变化。针对复合材料拉扭条组件,基于ABAQUS建立仿真模型并求解应变和角度变形云图;设计静力试验台架进行验证试验来验证仿真模型,并进一步分析离心力、扭角对其扭转性能的影响。结果表明:复合材料拉扭条的扭转刚度随扭角的增大而减小,随离心力的增大而增大,且离心力对复合材料拉扭条的扭转刚度影响更大。As the main load-bearing structure of the helicopter main rotor hub,stainless laminated strips bore the centrifugal force generated by the rotation of the blade and realized variable pitch of the blade through its own large deformation.The centrifugal force and torsional angle deformation carried by it change with the flight state of the helicopter.For the composite material stainless laminated strips,established the simulation model and solved the strain and angular deformation cloud diagram based on ABAQUS.Designed the static test bench to conduct verification test to verify the simulation model,and further analyzed the influence of centrifugal force and torsional angle on its torsional performance.The results showed that,the torsional stiffness of composite material stainless laminated strips decrease with the increase of the torsion angle and increase with the increase of the centrifugal force.The centrifugal force had a greater influence on the torsional stiffness of composite material stainless laminated strips.

关 键 词：复合材料拉扭条 静力试验 离心力 扭角 扭转性能 

分 类 号：V229.7[航空宇航科学与技术—飞行器设计] V216.1