摘要
针对多旋翼无人机机身系统振动过大导致飞行状态不稳的问题,基于有限元仿真技术与实验方法,进行了减振分析。通过频率分析,确定系统振动过大的原因为固有频率与激励频率耦合导致的共振现象,且共振频点的模态振型包含一阶挥舞、一阶摆振和二阶摆振振型。提出了优化机身壳体截面形状的设计方案,在不增加额外质量的情况下,将一阶挥舞、一阶摆振和二阶摆振振型对应的频点分别提高37.23%、22.47%和18.43%,有效规避了机身共振现象。仿真实验证明,提出的有限元仿真与实验结合的减振分析思路及优化设计方法,可为旋翼无人机减振设计提供参考依据。
Aiming at the problem of excessive vibration of the multi-rotor drone,which causes instability of flight state,the vibration reduction analysis work was carried out based on finite element simulation technology and experimental methods.Through frequency analysis,the reason of excessive vibration was determined to be resonance caused by coupling of natural frequency and excitation frequency,and the mode shape corresponding to the resonance frequencies were the first-order waving,the first-order swing and the second-order swing mode shapes.An optimization design method for optimizing the cross-sectional shape of the drone was proposed.Without adding extra weight,the corresponding frequency points of the first-order waving mode,the first-order swing mode,and the second-order swing mode have been increased by 37.23%,22.47% and 18.43%,respectively.Simulation experiments prove that the proposed vibration reduction analysis and optimization design method can provide references for design work of drones.
作者
马维力
和英鹏
崔辉如
李道奎
申柳雷
MA Weili;HE Yingpeng;CUI Huiru;LI Daokui;SHEN Liulei(School of Science,Chang'an University,Xi'an 710064,China;College of Defense Engineering,Army Engineering University,Nanjing 210007,China;College of Aerospace and Science,National University of Defense Technology,Changsha 410073,China;College of Military Basic Education,National University of Defense Technology,Changsha 410072,China)
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2022年第4期134-140,共7页
Journal of National University of Defense Technology
基金
国家自然科学基金资助项目(11902350)。
关键词
旋翼无人机
有限元
模态实验
优化设计
multi-rotor drone
finite element
modal experiment
optimal design
