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。
Aimed at retaining the merit of the vertical landing and taking-off of multi-rotor unmanned aerial vehicles but increasing their flying distance and payload capacities,it presents a design of a new airframe made of adding fixed wings and tiltable turban engines to original quadrotor fuselage. In level flight,both sides of the fuselage of the double bypass turbofan and wing common lean forward to generate backward thrust and to lift. Based on the 3D model produced a prototype has been developed. The results of fluid mechanics study are presented obtained from computer simulation. Its dynamic model developed will be introduced. The results show that the lift of the wing is designed to meet the design requirements. It has some significance to analyze the position of the airfoil. It is proved that the maximum stress is not in the leading edge or the trailing edge of the airfoil,but on the upper surface,and it is also verified that the lift generated by the shape of the CLARK Y airfoil plays a major role in the flight.
出处
《机械设计与制造》
北大核心
2016年第4期186-189,共4页
Machinery Design & Manufacture
基金
国家自然科学基金资助项目(61340016)
关键词
变结构
无人飞行器
四旋翼
固定翼
设计
Variable Structure
Unmanned Aerial Vehicles
Multi-Rotor Aircraft
Airplanes
Design
