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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。
Considering the problems of low flight speed and short range of existing quadrotor helicopters, considering the characteristics that the quadrotor can take off and land vertically and the fixed wing can sail over long distances, a method of adding a pair of fixed wings And turbofan thrust motor variable structure UAV, and gives three-dimensional modeling; in the horizontal flight on both sides of the fuselage duo-ducted turbofan and wing tilt together forward to produce backward thrust and upward lift . The prototype of the UAV was developed, the fluid-structure interaction mechanics simulation analysis was performed on the fixed wing of the aircraft, and the dynamics of the UAV was modeled. The results of the unidirectional fluid-solid coupling calculation of the fixed wing show that the designed wing lift meets the design requirements. The analysis of the cross-sectional airfoil position is of some importance, proving that the maximum stress is not at the leading edge or the trailing edge of the airfoil, but at the upper surface and also verifies that the lift generated by the CLARK Y airfoil shape plays a major role in flight .