摘要
针对旋翼飞行器本体微型化的瓶颈问题,介绍了一种新型非对称变距结构,研究并分析了其变距机理和控制特性,并对变距关键件弹性连杆进行了弹性力学分析和有限元计算,得到桨距变化与旋翼主轴电机的输出扭矩成线性关系。再通过光电传感器和位置控制码盘检测旋翼所在相位,以便在预期变距相位改变电机转速,从而实现微型旋翼飞行器各向机动飞行。
A novel asymmertrical pitch system faced to rotary wing MAV is introduced. The pitch mechanism and control characteristics are studied and analyzed. Because the deformation of elasticity link is key to generate the blade pitch, it is analyzed and caculated by elasticity finite element method. And the results illustrate the linear relationship between blade pitch angles and the output torque of the motor. The phase of rotary wing can be measured by the photoelectric encoder. So the flight to all directions can be carried out when the motor is accelerated at expectant phase.
出处
《机械设计与研究》
CSCD
北大核心
2007年第2期8-11,22,共5页
Machine Design And Research
基金
国家自然科学基金资助项目(50405046和60605028)
上海市优秀青年教师培养计划项目(04Y0HB094)
国家重点学科和上海市重点学科项目(Y0102和BB67)
关键词
微型旋翼飞行器
非对称变距
弹性连杆
有限元
rotary wing micro air vehicle
the ansymmetrical pitch system
elasticity link
finite element method
