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Device for reducing rotor wing vibration

A technology of rotor and piezoelectric driver, which is applied in the aviation field, can solve the problems of reduced mechanism performance and small driving displacement, and achieve the effect of small size and light weight

Inactive Publication Date: 2017-03-22
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The purpose of the present invention is to solve the problem that the existing driver used to drive the rotor trailing edge winglet has small driving displacement and needs a spring to provide restoring force, resulting in greatly reduced performance of the mechanism

Method used

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  • Device for reducing rotor wing vibration
  • Device for reducing rotor wing vibration
  • Device for reducing rotor wing vibration

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specific Embodiment approach 1

[0025] Specific implementation mode one: refer to Figure 1 to Figure 5 Describe this embodiment in detail, the device for reducing the vibration of the rotor described in this embodiment, the rotor includes a basic blade 1, a trailing edge winglet 5 and a trailing edge winglet connecting piece 6,

[0026] The trailing edge winglet 5 is connected to the basic blade 1 through the winglet connecting piece 6, and the winglet connecting piece 6 can be bent and deformed.

[0027] The device for reducing the vibration of the rotor includes a metal frame 2, a piezoelectric driver 3 and a winglet connecting shaft 4,

[0028] The metal frame 2 is solidified into the inside of the basic paddle 1 during the blade forming process, and the piezoelectric driver 3 is fixed in the metal frame 2,

[0029] The piezoelectric driver 3 includes a spring steel elliptical amplifying mechanism 7, a piezoelectric stack ceramic 8 and a wedge-shaped pre-tightening block 9,

[0030] The spring steel el...

specific Embodiment approach 2

[0037] Specific embodiment two: This embodiment is to further illustrate the device for reducing rotor vibration described in specific embodiment one. In this embodiment, the chord length of the trailing edge winglet 5 is 20% of the length of the basic blade 1 .

specific Embodiment approach 3

[0038] Specific Embodiment 3: This embodiment is a further description of the device for reducing rotor vibration described in Specific Embodiment 1. In this embodiment, one end of the two wedge-shaped pretensioning blocks 9 is provided with three piezoelectric stacks Ceramic 8, two piezoelectric stacked ceramics 8 are arranged at the other end of the two wedge-shaped pretensioning blocks 9 .

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Abstract

The invention provides a device for reducing rotor wing vibration and relates to the field of aviation. The problem that the performance of a mechanism is greatly reduced due to the fact that the drive displacement of existing drivers used for driving a rotor wing trailing edge little wing is small, and the restoring force needs to be provided by a spring is solved. Five piezoelectric stack ceramics are installed between the inner walls of the short edges of a spring steel oval amplification mechanism and are connected through two wedge-shaped pre-tightening blocks. The spring steel oval amplification mechanism is used for amplifying the drive displacement produced by the piezoelectric stack ceramics. The amplification multiple alpha of the spring steel oval amplification mechanism is related to the wall thickness l of the spring steel oval amplification mechanism and the angle theta formed by arc edges. After applying voltage, a piezoelectric driver shrinks to the left side so as to produce the drive displacement, drives a trailing edge little wing connecting rod to move and then drives a trailing edge little wing to deflect around a little wing connection piece. The device is used for reducing rotor wing vibration.

Description

technical field [0001] The invention relates to a device for reducing rotor vibrations. belongs to the field of aviation. Background technique [0002] Since its inception, helicopters have played a very important role in both military and civilian applications. Helicopters have the advantages of vertical take-off / landing capabilities, hovering, and high maneuverability at low speeds, which enable helicopters to complete many unique tasks, such as sea rescue, reconnaissance, etc. However, there have always been many problems that have limited the development of helicopter technology during the development of helicopters, such as poor ride quality due to vibration and noise, low fatigue life of structures, and very high maintenance costs. [0003] Unlike fixed-wing aircraft, due to the periodic torque conversion of the helicopter rotor, the blades bear alternating aerodynamic loads at 1 / rev frequency and inertial loads in the azimuth direction, and at the same time, relativ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/51
CPCB64C27/51
Inventor 刘彦菊冷劲松鲁庆庆孙健
Owner HARBIN INST OF TECH
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