Helicopter rotor blade based on seamless trailing edge flap mechanism

A technology for helicopter rotors and trailing edge flaps, applied in the directions of rotorcraft, motor vehicles, aircraft, etc., can solve the problems of high blade ground clearance, reduced aerodynamic efficiency of trailing edge flaps, inconvenient maintenance and repair, etc. The effect of improving the aerodynamic efficiency, improving the practical value of the project, and reducing the workload of system maintenance
CN110979657APending Publication Date: 2020-04-10NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Patent Information

Authority / Receiving Office
CN Β· China
Patent Type
Applications(China)
Current Assignee / Owner
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
Publication Date
2020-04-10

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Abstract

The invention discloses a helicopter rotor blade based on a seamless trailing edge flap mechanism. The helicopter rotor blade comprises a blade body and a plurality of trailing edge flap modules, wherein the trailing edge flap module comprises a shell, a driver, a push-pull rod, a driving rod, a mounting platform, a first flexible hinge, a second flexible hinge, a trailing edge flap and a sealingpiece; the driver generates dynamic linear displacement output; the driver, the push-pull rod, the driving rod and the trailing edge flap are connected in sequence, and the force and displacement generated by the driver are output and transmitted to the trailing edge flap; and the trailing edge flap is connected with the mounting platform through the second flexible hinge, and the linear reciprocating motion of the push-pull rod is converted into the deflection motion of the trailing edge flap through the second flexible hinge. The helicopter rotor blade is applied to the trailing edge flaps of the helicopter to actively control a rotor wing, the aerodynamic load distribution of the blade is dynamically changed through dynamic deflection of the trailing edge flaps, the vibration load of the rotor wing of the helicopter is inhibited, or the noise of the rotor wing is inhibited through a sound field cancellation method.
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Description

technical field

[0001] The invention relates to the field of active control of helicopter rotor vibration and noise, in particular to a helicopter rotor blade based on a seamless trailing edge flap mechanism. Background technique

[0002] Compared with other types of aircraft, helicopters have the characteristics of vertical take-off and landing and efficient hovering, and have been widely used in civil and military fields. However, during the use of the helicopter, its vibration and noise problems have always been prominent, which has brought a negative impact on the further development of the helicopter. When the helicopter is flying forward, the rotor is in an asymmetric and complex working environment. The shock wave of the forward blade, the dynamic stall of the backward blade, and the regurgitation zone cause the rotor to generate strong vibration and noise. Strong vibration and noise problems not only affect the comfort of helicopter pilots, but also adversely affect...

Claims

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