Rudder blade flutter suppression device based on particle damping, suppression method thereof and aircraft

A suppression device and damper technology, applied in non-rotational vibration suppression, aircraft parts, aircraft control, etc., can solve the problems of low stability and poor applicability of aircraft, and achieve high stability, improved stability, and damping The effect of improving

Pending Publication Date: 2020-08-11
XIAMEN ZHEN-WEI TECH CO LED
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, after the rudder blades are adjusted by the appeal method, the applicability of the aircraft becomes worse and the stability becomes lower.

Method used

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  • Rudder blade flutter suppression device based on particle damping, suppression method thereof and aircraft
  • Rudder blade flutter suppression device based on particle damping, suppression method thereof and aircraft
  • Rudder blade flutter suppression device based on particle damping, suppression method thereof and aircraft

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Embodiment 1

[0037] Such as Figure 1~2 As shown, the present embodiment discloses a rudder blade flutter suppressing device based on particle damping, including several particle dampers 2, which are installed on the rudder blade 1, and the rudder blade 1 includes a steering blade main body and a cover plate (not shown in the figure) ), the shape of rudder blade 1 can be square, circular or polygonal etc. Four particle dampers 2 are installed as in the figure of this embodiment. The particle damper 2 includes a damper housing 3 and a plurality of damping particles 4 . A cavity is arranged inside the damper housing 3 , and the damping particles 4 are filled in the cavity. An accommodating groove 5 is arranged on the rudder blade body, and the damper housing 3 is installed on the accommodating groove 5 . The damper housing 3 can be made of rigid material or flexible material: such as a frame welded by thin steel, or made of flexible rubber bag. When the damper housing 3 is made of a rigid...

Embodiment 2

[0042] Such as image 3 As shown, this embodiment discloses a device for suppressing rudder flutter based on particle damping, which includes several particle dampers 2 installed on the rudder 1, and three particle dampers 2 are installed in the figure of this embodiment. The particle damper 2 includes a damper housing 3 and a number of damping particles 4. The damper housing 3 is a square frame made of thin steel. There are four cavities inside the square frame, and the damping particles 4 are evenly distributed and filled in the four chambers. inside a cavity. Three accommodating grooves 5 are arranged on the rudder piece 1 , and three damper shells 3 are arranged in the accommodating grooves 5 , and are fixedly connected with the rudder piece 1 by bolts 10 .

Embodiment 3

[0044] Such as Figure 4 As shown, the present embodiment discloses a kind of aircraft, and the empennage of aircraft comprises the rudder plate 1 of elevator and rudder, and the flutter suppressing device of the present invention is installed on the rudder plate 1, and the flutter suppressing device comprises the particle that is installed on the rudder plate The structure of the damper 2 and the particle damper 2 is the same as that of the first or second embodiment.

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Abstract

The invention discloses a rudder blade flutter suppression device based on particle damping. The device comprises a plurality of particle dampers; each particle damper comprises a damper shell and a plurality of damping particles; a plurality of cavities are arranged in the damper shell; the cavities are filled with the damping particles; a containing groove is formed in a rudder blade; the dampershell is installed in the rudder blade containing groove, or the damper shell and the rudder blade containing groove are integrally formed. The invention further discloses an aircraft applying the rudder blade flutter suppression device. The invention further discloses a rudder blade flutter suppression method. The rudder blade flutter suppression device based on particle damping is installed ona rudder blade. The installation process comprises the steps of finite element pretreatment, model establishment, damping ratio calculation, characteristic parameter determination and particle damperinstallation. With the device and method adopted, the flutter suppression capacity of a rudder blade structure can be effectively improved, and the applicability, stability and safety of the aircraftare improved.

Description

technical field [0001] The present invention relates to the technical field of passive vibration control, and more specifically, relates to a rudder blade flutter suppression device based on the principle of particle damping and vibration reduction, a suppression method thereof, and an aircraft using the same. Background technique [0002] With the continuous development of science and technology, higher requirements are put forward for aircraft, requiring lighter structural weight, better flight speed and greater maneuverability. The rudder flutter is a factor that must be considered in the design of the aircraft. When the flight speed of the aircraft exceeds the critical flutter speed, its amplitude and the aerodynamic force inside the structure may change drastically. For the problem of flutter, component flutter is an important reason, and the rudder is the most important part of the aircraft, so it is very important to study the flutter suppression of the rudder. The c...

Claims

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Application Information

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IPC IPC(8): B64C9/00B64D47/00F16F15/02
CPCB64C9/00B64D47/00F16F15/02
Inventor 肖望强罗元易
Owner XIAMEN ZHEN-WEI TECH CO LED
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