采用局部约束的半转翼驱动机构运动误差分析及其结构参数优化

发布时间：2018-01-01 23:11

本文关键词：采用局部约束的半转翼驱动机构运动误差分析及其结构参数优化　出处：《机械科学与技术》2017年06期 　论文类型：期刊论文

【摘要】：半转翼是一种以转动式拍动替代摆动式拍动的新型类扑翼系统,针对传统半转机构传动复杂、重量大不适合飞行的缺点,提出一种采用局部约束的简约化半转机构作为半转翼驱动机构。给出了局部约束的形成过程和作用特点,根据运动构件间的接触状态将局部约束作用过程分成4个阶段,分别建立了不同阶段下的驱动机构半转杆转角偏差理论分析模型。在以上模型基础上,对驱动机构关键构件的结构进行优化设计。实例验证了半转杆转角偏差理论模型具有较好的可靠性,优化结果降低了转角偏差从而提高了驱动机构运行的平稳性。以上研究结果表明局部约束及其在简约化半转机构中的应用可为半转翼驱动机构设计提供新途径、新方法。
[Abstract]:Half-rotor is a new type of flapping-wing system, which uses rotary flapping instead of swing flapping. It aims at the disadvantages of traditional semi-rotating mechanism which is complex in transmission and unfit for flight with heavy weight. A reduced semi-rotating mechanism with local constraints is proposed as a semi-rotor drive mechanism. The forming process and action characteristics of local constraints are given. According to the contact state between moving members, the process of local constraint action is divided into four stages, and the theoretical analysis models of the rotation angle deviation of the semi-rotating rod of the driving mechanism in different stages are established respectively. The optimization design of the key components of the drive mechanism is carried out, and the reliability of the theoretical model of the rotation angle deviation of the semi-rotating rod is verified by an example. The results show that the local constraint and its application in the reduced semi-rotating mechanism can provide a new way for the design of the semi-rotor drive mechanism. New method
【作者单位】：安徽工业大学机械工程学院;
【基金】：国家自然科学基金项目(51375014)资助
【分类号】：V276
【正文快照】： 扑翼仿生飞行器因具有固定翼和旋翼微飞行器难以比拟的机动性而成为各国学者研究热点[1-4]。驱动机构是扑翼仿生飞行器的核心部件,其性能直接影响到飞行效率和飞行质量。美国加州理工学院将两套完全一样的曲柄摇杆机构叠加研制出MicroBat[5-6],Madangopal等[7]把曲柄滑块机

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