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

A technology of helicopter rotor and centrifugal mass, which is applied in the direction of rotorcraft, motor vehicles, and wing adjustment, etc., can solve the problems of narrow blade space, difficulty in providing driving power to the blade tip, and large restoring torque, so as to ensure safety and reduce The effect of small overall size and reduced impact

Active Publication Date: 2020-06-09
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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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

Method used

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

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Embodiment Construction

[0031] In order to clearly illustrate the technical characteristics of this patent, the following describes this patent in detail through specific implementation methods and in conjunction with the accompanying drawings.

[0032] The invention as Figure 1-9 As shown, the rotor blade of the helicopter includes a blade base body 33 and a blade tip 36 arranged at one end of the blade base body, and the lower counter drive mechanism includes a driver unit and a blade tip actuator unit, and the driver unit is connected to the The paddle base body, the paddle tip actuator unit is respectively connected with the paddle base body and the paddle tip, and the paddle tip actuator unit is driven by the driver unit to flip back and forth to realize the change of the down angle.

[0033] The blade tip actuator unit includes a centrifugal mass 15, a linkage assembly and a blade tip actuator 18;

[0034] The centrifugal mass 15 is slidably connected in the paddle base 33 and connected with ...

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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...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/32B64C3/38F16C35/00H02K7/06
CPCB64C27/32B64C3/38F16C35/00H02K7/06
Inventor 董凌华郑庆卓杨卫东
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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