The invention discloses a coaxial dual-rotor aircraft, and relates to the technical field of aircrafts. The aircraft comprises an aircraft body, a coaxial double-rotor assembly, a deformable stub wing and a vector thrust paddle, an operating system and an aircraft body sensor are arranged on the aircraft body, and the aircraft body sensor is in communication connection with the operating system. The fuselage structure of a conventional coaxial rigid double-rotor helicopter is reserved, the propeller hub without upper rotor control is adopted, compared with a conventional propeller hub with upper and lower rotor control, the propeller hub has the advantages that the control structure is simplified, and the structural performance is improved, meanwhile, due to the fact that upper rotor control is omitted, the deformable stub wings and the vector thrust propellers are arranged on the fuselage, and the structure performance is improved. The deformable stub wings can make up for the possible unbalance of the overall rolling torque of the aircraft when the upper rotor flies forwards at a high speed, the tilting device can drive the thrust paddles to tilt towards the fuselage relative to the fuselage, and yaw torque is generated by changing the thrust direction of the thrust paddles, so that the reaction torque of the upper rotor and the lower rotor flies at a high speed is balanced, and the stability of the aircraft is improved. And therefore, the controllability of yaw control is ensured.
本发明公开了一种共轴双旋翼飞行器,涉及飞行器技术领域。其包括机身、共轴双旋翼组件、可变形短翼和矢量推力桨,机身上配置有操纵系统和机身传感器,机身传感器与操纵系统通讯连接。本发明保留了常规共轴刚性双旋翼直升机的机身构型,采用取消了上旋翼操纵的桨毂,相比常规具有上下旋翼操纵的桨毂,具有操纵结构简化、结构性能提升的优势,同时由于取消了上旋翼操纵,还在机身配置了可变形短翼和矢量推力桨,可变形短翼可弥补上旋翼在高速前飞时可能导致的飞行器整体滚转力矩不平衡,倾转装置能够驱动推力桨相对机身朝机身倾转,通过改变推力桨的推力方向产生偏航力矩,来使上下旋翼在高速飞行时的反扭矩达到平衡,进而保证偏航操纵的可控性。
Coaxial double-rotor aircraft
一种共轴双旋翼飞行器
2025-03-18
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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