Helicopter co-axis double rotator rotate speed differential device

Abstract

The invention relates to a device for realizing rotor rotating speed differential of a coaxial helicopter with twin rotors which can be used for realizing the yawing control of the coaxial helicopterwith twin rotors. The device is a set of three-level gear drive mechanism: a first drive divides single power input into two parts according to the same drive ratio; a second drive is two planetary gear reducers with the same structure and the two parts of power after the first drive respectively drive sun wheels of the two planetary gear reducers; a third drive allows the output of the two planetary gear reducers to respectively drive a rotor internal shaft and a rotor external shaft according to the same drive ratio so as to realize that the rotary directions of the internal shaft and the external shaft is opposite. The key of realizing the rotating speed differential lies in drive configurations of the planetary gear reducer in the second lever, which has two structures: first, planetary wheel disks are used as the output and internal gears of the two planetary gear reducers can rotate and be catenated; second, the internal gears are used as the output and the planetary wheel disksof the two planetary gear reducers can rotate and be catenated. When two internal gears (the first configuration) or the two planetary wheel disks (the second configuration) are static, the rotor internal shaft and the rotor external shaft rotate at the same speed and in the opposite directions; when the two internal gears (the first configuration) or the two planetary wheel disks (the second configuration) rotate synchronously at the same speed driven by an execution mechanism for controlling the yawing, the rotating speed of the rotor internal shaft and the rotor external shaft increases anddecreases respectively and the increasing amount and the decreasing amount is the same.

Description

Technical field [0001] The invention belongs to the technical field of helicopters. Background technique [0002] There are two existing coaxial dual-rotor helicopter yaw control methods, one is realized by pitch differential, that is, the pitch of the upper and lower rotors is different through the pitch-variable rod mechanism (the pitch of the upper and lower rotors is increased by one). One is larger and the other is smaller), resulting in a torque difference, which drives the fuselage to rotate to achieve the purpose of yaw; the other is the dual-motor speed differential method, which is often used in small coaxial model helicopters. This method uses two motors to drive a pair of The rotor uses an electronic speed control circuit to control the speed of the two motors to realize the differential speed of the two rotors, thereby generating a torque difference and realizing yaw. The pitch differential method is mostly used in large-scale manned coaxial helicopters. Due to...

AI Technical Summary

Problems solved by technology

[0003] In order to avoid adding a differential variable pitch rod mechanism on the rotor shaft of a microcoaxial helicopter to cause an overly complicated structure, and to overcome the shortcomings that the existing dual-motor speed differential method cannot be used for non-electric helicopters or single-engine helicopters, the present invention provides A gear transmission device that distributes a single power input to the upper and lower rotors, and can realize the speed difference between the two rotors according to the needs, so as to realize the yaw control of the helicopter

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