【摘要】 以半转机构为驱动机构的半转翼是一种新型动力翼,在仿生飞行领域具有重要应用前景。针对传统半转机构结构复杂、升重比小,不适应于飞行的缺点,提出采用局部约束设计实现驱动机构的轻量化。根据局部约束作用特点将其作用过程分为4个阶段,进而分别建立不同阶段下机构转角偏差与驱动力矩理论分析模型,并仿真验证了该模型的可靠性。在此基础上,对机构关键构件的结构参数进行多目标优化设计,优化降低了转角偏差和驱动力矩峰值,提高了机构运行平顺性并减小了驱动电机额定功率。研究结果可为半转翼系统的具体结构设计提供理论参考,同时为半转翼的稳定飞行奠定基础。更多还原

【Abstract】 Half-rotating wing(HRW) based on half-rotating mechanism(HRM) was a new power wing which has an important application prospect in the field of bionic flying. In view of the shortcomings of traditional HRM with complicated structure and small ratio of lift to weight, a simplified HRM with local constraint was proposed to realize the lightweight of driving mechanism of HRW. According to the characteristics of local constraint, its process was divided into four stages. The theoretical model of rotating angle error and driving torque at different stages were established respectively. The availability of calculating model of angle error and driving torque was verified by Simulation. The multi-objective optimization of the structural parameters of the key components in driving mechanism of HRW was performed to further reduce rotating angel error and driving torque peak, which would improve ride comfort and decrease the power of motor of HRW. The research results mentioned are helpful to design detailed structure for flying stability of HRW.更多还原