摘要
为提升某型无人机前起落架抗弯和抗扭性能,减轻结构重量,设计了一种摇臂支柱式起落架结构。采用液压阻尼器+弹簧缓冲器结构形式,与机体连接采用对称支柱式限位连接结构,以起落架实际使用载荷为基础,分析仿真模型的载荷工况及边界条件,并运用ABAQUS软件对其进行有限元分析。计算结果表明,前起落架最大变形位于轮叉根部与机轮轮轴连接处,最大应力位于前起落架根部固支处,满足静强度要求。
In order to improve the bending and torsional properties of the nose landing gear for a certain unmanned aerial vehicle and reduce the structure weight,a swing arm strut landing gear structure was designed,adopting hydraulic damper and spring damper structure form,symmetry is used to connect with the body pillar type limit connection structure; based on the landing gear actual load,the loading case and boundary conditions of the model were analyzed and simulated,ABAQUS software was used for finite element analysis,the calculation results show that the maximum deformation is located in the landing gear wheel fork before root and wheel axle joint,maximum stress is located at clamped before landing gear root,which satisfies the requirement of static strength.
作者
李浩
吴文志
LI Hao;WU Wen-zhi(The 38th Research Institute of CETC,Hefei 230088,China;National Industrial Design Center,Hefei 230088,China)
出处
《电子机械工程》
2018年第5期5-8,共4页
Electro-Mechanical Engineering
关键词
前起落架
摇臂式
阻尼器
有限元分析
nose landing gear
swing arm
damper
finite element analysis
