A Torque Adjustment Mechanism for Two Degrees of Freedom Coaxial Rotorcraft

Abstract

The invention relates to a two-degree-of-freedom coaxial rotorcraft torque adjustment mechanism. A support is of a rectangular frame structure. An adjustment piece shaft is supported at the front end and the rear end of the support through coaxial bearings correspondingly. One end of the adjustment piece shaft stretches out of the support to be connected with an adjustment piece. The other end of the adjustment piece shaft is connected with a rotary steering engine through a rotary linkage device, and the rotary steering engine is fixed to the support. The two sides of the support are movably connected with a base through hinge pins. The base is of a U-shaped frame structure. The support is located in a U-shaped opening of the base. A deflection steering engine which is fixed to the base is connected between the base and the support through a deflection linkage device. According to the adjustment mechanism, a gyroscope is used for judging the flight posture, and the torque difference, caused by two coaxial rotors, of the aircraft is counteracted by changing the direction and the inclination angle of the adjustment piece; and meanwhile, since the adjustment piece has two degrees of freedom, the adjustment range is greatly widened, the adjustment precision is greatly improved, and the stability of the aircraft is improved.

Description

technical field [0001] The invention relates to a torque adjustment mechanism for a two-degree-of-freedom coaxial rotorcraft, which belongs to a torque difference adjustment device for an aircraft. Background technique [0002] Traditional coaxial twin-rotor helicopters adjust the torque difference between the two rotors by changing the pitch of the propellers, thereby maintaining the heading of the helicopter. But for the fixed-pitch coaxial rotor, since the pitch of the propeller is fixed, it cannot be adjusted, and because the airflow passes through the two counter-rotating rotors, the airflow flow is more complicated, and it is difficult to achieve stable control of the aircraft. Therefore, for a fixed-pitch coaxial rotor, the torque difference control of the upper and lower rotors and flight stability control have become a difficult problem. Contents of the invention [0003] The technical problem to be solved by the present invention is to provide a two-degree-of-fr...

AI Technical Summary

Problems solved by technology

However, for a coaxial rotor with a fixed pitch, since the pitch of the propeller is fixed, it cannot be adjusted, and since the airflow passes through the two counter-rotating rotors, the airflow flow is more complicated, and it is difficult to achieve stable control of the aircraft

Therefore, for a fixed-pitch coaxial rotor, the torque difference control of the upper and lower rotors and flight stability control have become a difficult problem

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