Helicopter damping device and control method thereof

Abstract

The invention provides a helicopter damping device and a control method thereof. The damping device comprises a main damping supporting rod, a first measuring element, a second measuring element, a controller unit and an active control force output device. The first measuring element and the second measuring element are used to measure a vibration load signal transmitted to a fuselage by the maindamping supporting rod and a vibration signal of the active control force output device; and the controller unit controls the active control force output device to generate active control force according to the vibration signal and the vibration load signal in a self-adaptive feedforward control and feedback control combined mode, so that the vibration load of the fuselage is reduced. The device is provided with the active control force output device, and active control of rotor wing-main damping dynamic load transmitted to the fuselage is achieved by driving the active control force output device, thereby overcoming the technical defects that the control performance is poor and the vibration level of a rotor wing-main damping system is increased due to the fact that the main damping supporting rod is directly driven by traditional active control, and effectively reducing the vibration level of the fuselage.

Description

technical field [0001] The invention relates to the technical field of helicopter vibration active control, in particular to a helicopter vibration damping device and a control method thereof. Background technique [0002] During the flight of the helicopter, the vibration of the body and the noise in the cabin are very serious, and the rotor and the main damper are the main vibration sources of the vibration of the helicopter body and the noise in the cabin. Helicopter main reducer strut is the inevitable path for the helicopter rotor and main reducer dynamic load to be transmitted to the fuselage. Controlling the main reducer strut is an effective measure to reduce the dynamic load transmitted to the fuselage, reduce the vibration of the fuselage and the noise in the cabin. Passive vibration isolation measures such as mechanical dynamic anti-resonance, liquid-elastic vibration isolator, node beam vibration isolation and other technical measures on the force transmission pa...

AI Technical Summary

Problems solved by technology

[0004] The purpose of this invention is to provide a kind of helicopter damping device and its control method, to realize the active control of the rotor-main damping load transmitted to the fuselage, to overcome the poor control performance caused by the traditional active control directly driving the main damping strut And increase the technical defect of the vibration level of the rotor-main reduction system, effectively reduce the vibration level of the fuselage

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