The invention discloses a helicopter without a tail rotor, which is characterized in that a helicopter body comprises a fan propeller, a main rotor, an engine and a double-shaft double-speed output transmission located in the center of the helicopter body, wherein the engine is connected with the double-shaft double-speed output transmission; an upper shaft of the double-shaft double-speed outputtransmission is connected with the main rotor, and a lower shaft is connected with the fan propeller; adjustable yawing blades are radially distributed in a duct air ring of the fan propeller; 80% ofreverse torsion generated by rotation of the main rotor is counteracted by the fan propeller which is connected to the same transmission and rotates reversely at a high speed, and the other 20% of thereverse torsion is counteracted by force generated when discharged airflow generated by high-speed rotation of the fan propeller flows through framework of the duct air ring; angle-adjustable bladesare distributed in the duct air ring, the angle between the movable yawing blades and the plane of the duct air ring is adjusted, and yawing turning of the helicopter is achieved; and the plane wherethe main rotor is located is parallel to the plane where the fan propeller is located, thereby reducing the loss of the helicopter.
本发明公开了一种无尾桨直升机,机身包括:风扇螺旋桨,主旋翼,发动机,位于机身中心的双轴双速输出变速器;所述发动机连接双轴双速输出变速器;双轴双速输出变速器的上轴连接主旋翼,下轴连接风扇螺旋桨;风扇螺旋桨的涵道风圈中径向分布有可调偏航叶片;主旋翼转动产生的反扭力中80%由连接的在相同变速器上的高速反转的风扇螺旋桨抵消,其余20%由风扇螺旋桨高速旋转产生的下泄气流流过涵道风圈骨架时产生的力抵消;涵道风圈内分布有可调节角度叶片,调节可动偏航叶片与涵道风圈平面的角度,实现直升机的偏航转弯;而且主旋翼所在平面与风扇螺旋桨所在平面平行也减少直升机的损耗。
Helicopter without tail rotor
一种无尾桨直升机
2020-07-31
Patent
Electronic Resource
Chinese