可变结构小型多旋翼无人飞行器的设计

发布时间：2018-05-02 13:42

本文选题：变结构 + 无人飞行器　；参考：《机械设计与制造》2016年04期

【摘要】：针对现有的四旋翼直升机存在飞行速度低、航程短等问题,综合考虑了四旋翼可以垂直起降和固定翼能够长距离航行的特点,提出一种在四旋翼的基础上添加一对固定翼和涡扇推力电机的变结构无人飞行器,并给出三维建模;在水平飞行时机身两侧的双涵道涡扇和机翼共同向前倾斜以产生向后的推力和向上的升力。开发出该变结构无人飞行器样机,对飞行器固定翼进行流固耦合力学仿真分析,最后对变结构飞行器动力学建模。固定翼的单向流固耦合计算结果显示,设计的机翼升力满足设计要求。从截面翼型位置上分析有一定意义,证明最大应力并非在翼型的前缘或后缘,而是在上表面,同时也验证了CLARK Y翼面形状产生的升力在飞行过程中起主要作用。
[Abstract]:In view of the problems of low flying speed and short range of the existing four-rotor helicopter, the characteristics of the four-rotor can take off and land vertically and the fixed-wing can navigate long distance are considered comprehensively. A variable structure unmanned aerial vehicle (UAV) with a pair of fixed wings and a turbofan thrust motor is proposed on the basis of four rotors, and the 3D modeling is given. In horizontal flight, the double ducted vortex fan and the wing both sides of the fuselage incline forward to generate backward thrust and upward lift. The prototype of the variable structure unmanned aerial vehicle (UAV) is developed, and the fluid-solid coupling mechanics of the fixed wing of the vehicle is simulated and analyzed. Finally, the dynamic model of the variable structure unmanned aerial vehicle is established. The results of unidirectional fluid-solid coupling of the fixed wing show that the lift of the designed wing meets the design requirements. It is significant to analyze the position of the section airfoil. It is proved that the maximum stress is not on the front edge or the rear edge of the airfoil, but on the upper surface. It is also proved that the lift generated by the shape of the CLARK Y wing plays a major role in the flight process.
【作者单位】：安徽理工大学机械工程学院;中国科学院合肥智能机械研究所;中国科学技术大学自动化系;
【基金】：国家自然科学基金资助项目(61340016)
【分类号】：V279

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