Soft main rotor locking device of rotor aircraft

Abstract

The invention provides a soft main rotor locking device of a rotor aircraft. The soft main rotor locking device comprises a constraining assembly, a frictional speed-reducing assembly, an elastic compressing component and a braking component. Through arrangement of the frictional speed-reducing assembly, the rotating speed of a rotor is quickly reduced and conversion of the flight process is completed relatively fast; the impact load is relatively small in the locking process, and in the braking process of the braking component and an upper locking sleeve, the elastic component is arranged between the upper locking sleeve and a main rotor rotating shaft and a frictional force increases along with increase in the circumferential phase difference between the upper locking sleeve and a lowerfixing base, so that the time from rotation starting to rotation stop of the rotor is prolonged and impact energy is absorbed by elastic and frictional components; in the braking process of the braking component and the main rotor rotating shaft, the main rotor is already in the reverse rotating process after forward rotation stops, so that a rotating spring has relatively low elasticity, the rotating speed of the rotor is very low, and at the moment, the impact load is very small; therefore, in the whole locking process, almost no impact load exists, so that the reliability of the soft main rotor locking device is improved, the service life of the soft main rotor locking device is prolonged, and thus the soft main rotor locking device can be applied to medium and large rotor aircrafts.

Description

technical field [0001] The invention relates to the technical field of rotary wing aircraft, in particular to a soft locking device for a main rotor of a rotary wing aircraft. Background technique [0002] Rotary wing aircraft is a new type of unmanned aircraft that has both the vertical take-off and landing performance of a helicopter and the high-speed cruise performance of a fixed-wing aircraft. The patent number is ZL201110213680.1, and the Chinese patent titled "A Rotary Wing Aircraft with Variable Flight Mode" is a typical model. The aircraft has a three-plane aerodynamic layout consisting of canards, main wings and empennage. Among them, in the helicopter flight mode, the main wing rotates as a rotor to provide the required pulling force for the aircraft. At the same time, when the aircraft has a certain flight speed, it can be locked as a fixed wing to achieve high-efficiency fixed-wing flight. Therefore, during the take-off and landing phases, the aircraft adopts ...

AI Technical Summary

Problems solved by technology

[0005] In order to solve the problems of low locking speed and high impact of the locking device used in the conversion flight of the existing rotary wing, the present invention proposes a soft main rotor locking device applied to medium and large rotary wing aircraft, which can Actively and quickly reduce the rotor speed, and there is no impact when the rotor rotates

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