A conventional layout helicopter and flight control method

Abstract

The invention discloses a conventional layout helicopter and a flight control method, which relate to the field of aviation technology and include a body, an ABC single rotor and a short wing. The top of the fuselage is fixedly connected with the output end of the driving mechanism, and the driving mechanism can change the rolling moment of the ABC single rotor; the short wing is arranged on the fuselage on the side of the rear blade of the ABC single rotor, and the short wing includes Drive element, frame assembly and skin, the frame assembly is movably connected to the fuselage, one end of the drive element is connected to the fuselage, the other end of the drive element is connected to the frame assembly, and the drive element can drive the frame assembly to reciprocate in the forward flight direction of the helicopter And the area of ​​the frame assembly changes during the reciprocating motion, and the skin covers the frame assembly. The conventional layout helicopter provided by the present invention can improve the maximum forward flight speed of the conventional conventional layout helicopter.

Description

technical field [0001] The invention relates to the field of aviation technology, in particular to a conventional layout helicopter and a flight control method. Background technique [0002] Helicopter has unique application value in many aspects due to its high hovering efficiency. However, compared with aircraft, the low forward speed of helicopter is its shortcoming. [0003] Conventional layout helicopter refers to a helicopter with a single rotor and a tail rotor configuration. The rotation of the single rotor provides the lift and forward power of the helicopter in vertical flight. The single rotor usually used in such helicopters has a swing hinge or equivalent swing hinge, The single rotor with variable pitch hinge and oscillating hinge, and the separation of the shock wave on the forward blade side and the airflow on the rear blade side are the important reasons for limiting the maximum flight speed of the conventional helicopter. In view of these two limitations, ...

AI Technical Summary

Problems solved by technology

In view of these two limitations, it has been proposed to use the ABC (forward blade concept) rotor to increase the maximum flight speed of the helicopter, but the ABC rotor generally adopts two counter-rotating coaxial rigidity due to the lift bias of the single rotor. Rotor, ABC single rotor, due to its structural characteristics, compared with the traditional single rotor when flying forward at high speed, avoids the disadvantage that the backward blade is more likely to enter the aerodynamic stall state due to waving, thereby reducing the aerodynamic efficiency, so that the forward blade can be better. It can exert its lift potential to provide greater power for the forward flight of the helicopter. If the helicopter with the conventional layout can apply the ABC single rotor while overcoming the characteristics of its lift bias, the maximum forward flight speed of the helicopter with the conventional layout can be increased.

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