Helicopter rotor blade variable anhedral blade tip driving mechanism based on centrifugal mass block

Abstract

The invention discloses a helicopter rotor blade variable anhedral blade tip driving mechanism based on a centrifugal mass block. The invention belongs to an intelligent rotor technology in the fieldof helicopter rotor vibration and noise control, and puts forward the driving mechanism that can stably drive helicopter blade tips in a large centrifugal force field and a complex pneumatic environment so as to change the magnitude of a propeller blade tip anhedral angle according to different flight states of a helicopter. According to a technical scheme, the anhedral driving mechanism comprisesa driver unit and a blade tip actuator unit, the driver unit is connected to a blade base body, the blade tip actuator unit is connected to the blade base body and the blade tip respectively, and thepropeller tip actuator unit is driven by the driver unit to turn over in a reciprocating mode to achieve change of the anhedral angle. In a specific flight state, the anhedral state of the blade tipcan suppress the BVI (blade vortex interaction) by weakening the blade tip vortex and increasing the vertical distance between the blade tip vortex and subsequent blades, so that the purposes of noisereduction and vibration attenuation on the rotor wings are achieved.

Description

technical field [0001] The invention belongs to the intelligent rotor technology in the field of helicopter rotor vibration and noise control, and in particular relates to active control applicable to helicopter blade tips. Background technique [0002] Compared with fixed-wing aircraft, helicopters have special flight capabilities such as vertical take-off and landing, and hovering in the air. These unique flight capabilities make them widely used in military and civilian fields. With the continuous development of helicopter technology, the issue of Blade Vortex Interaction (BVI) of helicopter rotors has received extensive attention. When the propeller vortex interference occurs, not only the vibration level of the propeller will increase, but also a strong BVI noise with significant acoustic characteristics will be formed. In order to reduce the strength of BVI, many advanced propeller tips adopt the structure of down-reverse tip, the main purpose of which is to reduce th...

AI Technical Summary

Problems solved by technology

The main reason is that the propeller tip works in a very large centrifugal force field and complex aerodynamic environment, and the space of the propeller blade is narrow, and the recovery torque generated after the propeller tip is reversed is relatively large, which makes it difficult for the general drive mechanism to provide sufficient drive. power to achieve active control of the propeller tip

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