Coaxial helicopter operation system

Abstract

The invention discloses a coaxial helicopter operation system, which comprises an upper rotor wing operation system and a lower rotor wing operation system, wherein the upper rotor wing operation system comprises a plurality of first servo steering engines, a first inclination device, an operation long pull rod and a head supporter; the first inclination device is positioned under the head supporter and is connected with the head supporter through the operation long pull rod; the plurality of first servo steering engines are connected with the first inclination device; the head supporter is connected with an upper rotor wing variable pitch rocker arm; the lower rotor wing operation system comprises a second inclination device, a plurality of second servo steering engines and servo small wings; the plurality of servo steering engines are connected with the second inclination device; the servo small wings are arranged above the lower rotor wing and are connected with the second inclination device and the lower rotor wing variable pitch rocker arm. A propeller pitch sub-control operation system is used; a mechanical system is simple, safe and attractive; the stability of the helicopter is improved through the additional arrangement of the servo small wings at the lower rotor wing; the problem that the servo small wing cannot be installed on an upper rotor wing of a conventional propeller pitch sub-control operation system is solved.

Description

technical field [0001] The invention relates to the technical field of aircraft design and manufacture, in particular to a coaxial helicopter control system. Background technique [0002] The coaxial helicopter does not have the tail rotor and its transmission system in the conventional layout, and its required power is less than that required by the single rotor with tail rotor helicopter; at the same time, the coaxial helicopter has a more compact structure, compared with the single rotor The size of the helicopter with rotor and tail rotor should be reduced by 35% to 40%, so as to have a smaller moment of inertia, thereby increasing the controllability and maneuverability of the coaxial helicopter. [0003] The coaxial helicopter control system is mainly divided into two forms, one is the joint control of the upper and lower rotors, that is, the upper and lower tilters are connected together through a parallelogram, so that the two tilters perform collective pitch movemen...

AI Technical Summary

Problems solved by technology

[0007] The purpose of the present invention is to provide a coaxial helicopter control system to solve the problems in the prior art mentioned above. Adding servo winglets to the lower rotor improves the stability of the helicopter and solves the problem of the conventional pitch control control system for the upper rotor. The problem of not being able to install the servo winglet

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