The invention provides a tilting type vertical take-off and landing aircraft and a control method thereof. Through an engine vector rotating system, all power motors of the aircraft participate in thewhole process of flight operation, so that he average load of a single power motor is reduced; and the task load and the cruise time in a fixed wing mode are greatly increased by utilizing the relatively high propeller force effect and system force effect when the power motors are low in load. And fine adjustment of the aircraft attitude can be realized through the torque of the engine. The rotating directions of the two rear power motors of the aircraft are backward and downward, so that the distance between the supporting rod of the engine vector rotating system and the wings can be shortened as much as possible on the premise of not changing the rotating directions of the motors, and the aircraft body is further simplified. Vector rotation of the four vector rotating motors is controlled by the two steering engines, so that the number of the control steering engines is reduced, the weight of the fuselage is further reduced, and the energy utilization efficiency and the flight stability of the vertical take-off and landing aircraft can be improved.
本发明提供一种倾转式垂直起降飞行器及其控制方法,通过发动机矢量旋转系统使得飞行器的所有动力电机参与飞行作业的全过程,降低单个动力电机平均负载,并利用其低负载时相对较高的螺旋桨力效和系统力效,大幅增加固定翼模式下的任务负载与巡航时间。通过发动机的扭矩可以实现飞机姿态的细微调整。飞机靠后的两个动力电机的旋转方向是向后与向下,可以在不改变电机旋转方向的前提下尽可能缩短发动机矢量旋转系统支撑杆与机翼的距离,使得飞行器机身得到进一步精简。四个矢量旋转电机的矢量旋转由两个舵机完成控制,减少控制舵机数量,进一步降低机身重量,能够提升垂直起降飞行器的能量利用效率与飞行稳定度。
Tilting type vertical take-off and landing aircraft and control method thereof
一种倾转式垂直起降飞行器及其控制方法
2020-09-18
Patent
Electronic Resource
Chinese
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