摘要
为了提高仿生扑翼飞行器飞行的稳定性,在对传统的曲柄摇杆驱动机构分析的基础上,设计了一种以空间RSSR机构为驱动机构的新型仿生扑翼飞行器。首先,通过运动学和动力学分析,建立了空间RSSR机构的运动学和动力学模型,对扑翼飞行器进行了运动学和动力学分析。结果表明:所设计的驱动机构运动平稳,扑动上极限夹角为21.92°,下极限夹角为-18.11°,扑动幅度为40.03°,设计的扑翼飞行器运动参数与仿生鸟类飞行运动参数一致;计算了曲柄处输入力矩与机构各个关键点的受力情况,为今后优化扑翼飞行器驱动机构、提高其结构强度、进一步提高扑翼飞行器性能提供了理论依据和参考。
In order to improve the flight stability of bionic ornithopter,a new bionic ornithopter driven by space RSSR mechanism was designed based on the analysis of the traditional crank-rocker mechanism.Firstly,the kinematic and dynamic models of space RSSR mechanism were established through kinematic and dynamic analysis.Then,the ornithopter designed by ADAMS simulation software was simulated and analyzed,and the theoretical analysis was verified.The results show that the designed drive mechanism moves smoothly,the upper limit Angle of flapping is 34.80°,the lower limit Angle is-29.15°,and the flapping amplitude is 63.95°.The input torque at the crank and the stress of each key point of the mechanism are calculated,which provides a theoretical basis and reference for further optimization of the performance of the flapping wing aircraft in the future.
作者
张瑞坤
何畏
ZHANG Rui-kun;HE Wei(Chongqing Electric Power College,School of Intelligent Engineering,Chongqing 400043;Southwest Petroleum University,School of Mechanical and Electrical Engineering,Chengdu,Sichuan 610500)
出处
《液压与气动》
北大核心
2023年第12期176-183,共8页
Chinese Hydraulics & Pneumatics
关键词
扑翼飞行器
RSSR
气动力
动力学分析
flapping wing vehicle
RSSR
aerodynamic force
kinetic analysis
