The invention provides a differential control tilt rotor vertical take-off and landing aircraft design method, which comprises an aircraft body, a canard, a rotor on a wingtip of the canard, a main wing, a rotor on a wingtip of the main wing, a tilt connecting mechanism, a horizontal tail and a vertical tail, torque is generated through rotor speed differential motion on the canard and the main wing, the canard, the main wing and the rotors on the canard are driven to integrally tilt, and conversion between a rotor mode and a fixed wing mode is achieved. In a fixed wing mode, rotors of the canards and the main wings are in a horizontal state; in the rotor wing mode, all the rotor wings are in a vertical state; the aircraft is in a typical three-wing-surface layout in a fixed wing mode, the front canard wings are located at the lower position of the aircraft body, the main wings are located at the upper position of the aircraft body, the lift force and the lift-drag ratio of the whole aircraft can be increased by reasonably designing the positions of the canard wings and the main wings, and under the same fuel oil or battery weight, energy consumption in the cruising stage can be reduced, so that the voyage is increased.
本发明提供了一种差速控制的倾转旋翼垂直起降飞行器设计方法,包括机体、鸭翼及其翼梢上的旋翼、主翼及其翼梢上的旋翼、倾转连接机构、平尾及垂尾,倾转连接机构将鸭翼及主翼在翼根弦向中点位置处固连,通过鸭翼及主翼上的旋翼转速差动产生力矩,带动鸭翼、主翼及其上的旋翼整体倾转,实现旋翼模态及固定翼模态的转换。处于固定翼模态时,鸭翼和主翼的旋翼均处于水平状态;处于旋翼模态时,所有旋翼均处于垂直状态;所述飞行器在固定翼模态时为典型的三翼面布局,前置鸭翼在机体偏下位置,主翼在机体偏上位置,通过合理设计鸭翼与主翼位置,可以增加全机升力及升阻比,在相同燃油或电池重量下,可以减少巡航阶段耗能,从而增加航程。
Differential control tilt rotor vertical take-off and landing aircraft design method
一种差速控制的倾转旋翼垂直起降飞行器设计方法
2023-03-31
Patent
Electronic Resource
Chinese
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