KR101678319B1

KR101678319B1 - Bird strike prevention device

Info

Publication number: KR101678319B1
Application number: KR1020150182612A
Authority: KR
Inventors: 김동수
Original assignee: 한국공항공사
Priority date: 2015-12-21
Filing date: 2015-12-21
Publication date: 2016-11-21

Abstract

An apparatus for preventing a bird strike is disclosed. The apparatus for preventing a bird strike comprises a latticed cover part which is formed on the front surface of an aircraft engine, thereby reducing the impact applied to an aircraft.

Description

[0001] BIRD STRIKE PREVENTION DEVICE [0002]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a bird strike, and more particularly, to a bird strike prevention apparatus capable of reducing the impact of a bird impact on an engine generated during an aircraft operation.

There is no other device in front of the existing aircraft engine. In order to prevent the bird from approaching the engine of the moving aircraft on the ground, a method such as algae is used mainly.
In order to prevent bird clashes, only the airport area is equipped with a bird-fighting device and firearms, but there is no countermeasure against bird clashes in areas outside the airport area.
In addition, the bird strike on the aircraft is a problem of the amount of impact caused by various kinds of algae colliding with the aircraft operating at high speed, so when a 1.8kg bird hits a 960km plane, the impact is the same as pressing a weight of 96 tons.
In order to reduce the amount of impact applied to the aircraft, it is necessary to reduce the weight of the bird causing the impact or to reduce the time between the colliding bird and the engine There is a way to extend the length, and it is important to reduce the risk of impact from the algae on the aircraft engine.
Therefore, it is urgent to develop a device capable of reducing the amount of impact applied to the aircraft engine.

SUMMARY OF THE INVENTION An object of the present invention is to provide a bird strike prevention device capable of reducing an amount of impact applied to an aircraft.
Yet another object of the present invention is to provide a bird strike prevention device capable of reducing the risk of an impact applied from algae to an aircraft engine by prolonging the time between the bird and the engine.

A bird strike according to embodiments of the present invention will be described. A bird strike prevention device having a lattice-shaped cover portion on the front of an aircraft engine.
According to one aspect, the cover portion is formed in a lattice form of the horizontal plate and the vertical plate, and the horizontal plate and the vertical plate may be formed in the form of a blade.
According to one aspect, the fixing portion may be interposed between the cover portion and the engine so as to connect the engine and the cover portion.
According to one aspect, the fastening portion may be a compression spring.
According to one aspect, the cover portion may be formed in a conical shape.
According to one aspect, the horizontal and vertical plates may be in detachable form.
According to one aspect, the height of the horizontal plate and the vertical plate may be different from each other.
A bird striking prevention apparatus according to embodiments of the present invention will be described. A cover portion for protecting the engine is provided on the front portion of the aircraft engine, and the cover portion may be formed in the form of a blade.
According to one aspect, the cover portion is formed in a lattice form of the horizontal plate and the vertical plate, and the horizontal plate and the vertical plate may be formed in the form of a blade.
According to one aspect, the fixing portion may be interposed between the cover portion and the engine so as to connect the engine and the cover portion.
According to one aspect, the fastening portion may be a compression spring.
According to one aspect, the cover portion may be formed in a conical shape.
According to one aspect, the horizontal and vertical plates may be in detachable form.
According to one aspect, the height of the horizontal plate and the vertical plate may be different from each other.
A bird striking prevention apparatus according to embodiments of the present invention will be described. The cover portion of the aircraft engine is provided with a cover portion in the form of a lattice, and the cover portion is formed in a lattice form of a horizontal plate and a vertical plate, and the height of the horizontal plate and the vertical plate may be different from each other.
According to one aspect, the horizontal plate and the vertical plate may be formed in the form of a blade.

According to the present invention, by extending the time between the bird and the engine, the risk of impact from the bird on the aircraft engine can be reduced.
Further, the cover portion is mounted on the engine, and the amount of impact applied to the aircraft can be reduced.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a front view showing a cover mounted on an aircraft engine according to an embodiment of the present invention; FIG.
2 is a side view of a cover mounted on an aircraft engine according to an embodiment of the present invention.
3 is a front view of a cover according to an embodiment of the present invention.
4 is a side view of a first cover according to an embodiment of the present invention.
5 is a side view of a second cover according to an embodiment of the present invention.
6 is a perspective view of a second cover according to an embodiment of the present invention.
FIG. 7 is a simplified diagram for representing blade height according to an embodiment of the present invention. FIG.
FIG. 8 is a schematic view showing a blade replacement according to an embodiment of the present invention. FIG.

Hereinafter, embodiments will be described in detail with reference to exemplary drawings. It should be noted that, in adding reference numerals to the constituent elements of the drawings, the same constituent elements are denoted by the same reference symbols as possible even if they are shown in different drawings. In the following description of the embodiments, detailed description of known functions and configurations incorporated herein will be omitted when it may make the best of an understanding clear.
In describing the components of the embodiment, terms such as first, second, A, B, (a), and (b) may be used. These terms are intended to distinguish the constituent elements from other constituent elements, and the terms do not limit the nature, order or order of the constituent elements. When a component is described as being "connected", "coupled", or "connected" to another component, the component may be directly connected or connected to the other component, Quot; may be "connected,""coupled," or "connected. &Quot;
The cover and the cover are mounted on the engine, and when the bird and the engine collide with each other, the danger and the impact of the impact from the algae on the aircraft engine can be reduced. FIG. 2 is a side view of a cover mounted on an aircraft engine according to an embodiment of the present invention. FIG. 3 is a side view of the cover of the aircraft engine according to an embodiment of the present invention. Fig. 7 is a front view of a cover portion according to an embodiment. Hereinafter, a description will be given with reference to the drawings.
The bird striking prevention apparatus of the present invention comprises a cover portion 20 mounted on an engine 11 of an aircraft 10, a cover portion 20 interposed between the cover portion 20 and the engine 11, (Not shown).
The cover part 20 may be provided at the inlet side of the engine 10 of the aircraft 10 and the cover part 20 may include a body 24 and a horizontal plate 212 and the vertical plate 211 can be arranged and fixed in a lattice shape.
A fixing part 30 can be mounted between the cover part 20 and the engine 11 and a shock absorbing material 21 is provided in the fixing part 30 so that a bird So that it is possible to buffer the impact to the engine 11 in the event of a collision.
The impact-absorbing material 21 may be a compression spring or a material having good elastic force.
The fixing portion 30 may be configured to serve to fix the cover portion 20 to the engine 11,
The cover portion 20 may be provided at the upper end of the fixing portion 30 and the fixing portion 30 may be fixed to the front portion of the engine 11. [
The horizontal plate 212 and the vertical plate 211 which are formed in a lattice shape of the cover unit 20 are connected to the horizontal plate 212 of the engine 11 so as to disassemble the body 24 of the algae And the vertical plate 211 may be configured to be sharp and thin in the form of a blade to decompose the algae.
4 is a side view of the first cover portion 31 according to an embodiment of the present invention. Referring to FIG.
The cover part 20 mounted on the engine 11 may be arranged in a grid shape such that the horizontal plate 212 and the vertical plate 211 formed in the form of a blade inside the body 24 and the body 24 .
Here, the body 24 may be formed larger than the circumference of the engine 11 of the aircraft 10. In particular, it is possible to make the surface area of the engine greater than the surface area of the engine in consideration of the amount of air flow which is disturbed by the cross sectional area of the grid plate and decreases in the amount of air flowing into the engine. The height of the horizontal plate 211 and the vertical plate 212 fixed to the body 24 may be different from each other. For example, the center of the body 24 may be formed such that the height of the blade is the highest, and the height of the blade is lower than the center.
The horizontal plate 211 and the vertical plate 212 provided on the body 24 are formed at the highest height and the height of the horizontal plate 211 and the vertical plate 212 is decreased toward the edge of the body 24 .
The body 24 is formed to be larger than the size of the engine 11 so that the bird 20 is not in direct contact with the engine 11 and the cover 20 mounted on the inlet side of the engine 11 constitutes a structure This is possible.
In addition, since the blade has the longest center at the center, the blade at the other end disassembles the algae after puncturing the algae from the center, so that the algae can be more easily broken down.
It is possible to reduce the risk and impact of the impact from the algae on the engine 11 of the aircraft 10 by prolonging the time between the algae and the engine 11 by means of the grid-shaped blade.
5 is a side view of a second cover part 32 according to an embodiment of the present invention, and FIG. 4 is a perspective view of a second cover part 32 according to an embodiment of the present invention. Referring to FIG.
The cover portion 20 mounted on the engine 11 includes a body 24 formed in a lunar conical shape, a horizontal plate 212 formed in the form of a blade inside the body 24 and a vertical plate 211 formed in a lattice shape As shown in FIG.
The body 24 may be formed in a conical shape so that the height of the blade at the center portion is high and the blade height is decreased toward the edge.
That is, the horizontal plate 211 and the vertical plate 212 provided on the body 24 have the highest height at the center, and the height of the horizontal plate 211 and the vertical plate 212 toward the edge of the body 24 .
In particular, the middle horizontal plate 211 and the vertical plate 212 may be formed in the shape of a sharp point.
This may be that after the bird is pierced from the central portion of the cover portion 20, the blade at the other end breaks down the algae to further decompose the algae.
In addition, after receiving the first impact on the center portion of the body 24, the impact is dispersed on the edge side so as to disassemble the algae, so that the blade 24 of the body 24 is damaged . &Lt; / RTI >
The horizontal plate 211 and the vertical plate 212 on the center side can be configured to be replaceable.
This is because the body 24 of the algae collides against the edge of the grid plate with a time lag from time to time so that the impact applied to the cover 20 is further mitigated and the body 24 of the algae is knife- The rain can be shaped and the effect of cutting the algae better.
The impact applied between the engine 11 and the cover portion 20 while the bird and the engine 11 do not directly collide and the primary impact is applied to the center portion of the cover portion 20 and the secondary impact is applied to the edge portion, The impact applied to the engine 11 of the aircraft 10 can be reduced by transmitting the amount of the impact to the fixing portion 30 equipped with the absorbent material.
FIG. 7 is a simplified diagram for representing blade height according to an embodiment of the present invention. FIG. Referring to FIG.
The X axis can be the lattice plate, and the Y axis can be the height of the lattice plate.
The vertical plates 211 at the even positions of the X axis may be formed so as to have different heights, and conversely, the horizontal plates 212 may be configured to have a predetermined height.
The height of the vertical plate 211 at an even position may be formed to be high at the center, the height of the blade may be set to be lower toward the edge, and the horizontal plate 212 may have the same height.
The horizontal plate 212 may be configured to correspond to the height of the vertical plate 211.
This can be configured such that the algae are decomposed from the vertical plate 211 and the algae is finely decomposed from the horizontal plate 212 spaced apart from the vertical plate 211 by a certain distance.
The bird's nest is punctured by the longest formed blade at the primary center portion and then finely disintegrated by the vertical lattice plate in the form of an edge blade and the birds are made smaller from the horizontal plate 212 spaced apart from the vertical plate 211 by a certain distance And may be configured to be decomposed.
In addition, the vertical plates 211 having different heights can be formed in a detachable form, and are configured to be replaceable, so that the broken blade can be replaced with a new one.
This makes it possible to reduce the risk and impact of the impact from the algae on the engine 11 of the aircraft 10 by prolonging the time between the algae and the engine 11 by means of the grid-shaped blade.
FIG. 8 is a schematic view showing a blade replacement according to an embodiment of the present invention. FIG.
A plurality of fins 211 may be formed in a lattice shape at the bottom 25 of the body 24 and a replacement blade 203 may be detachably attached to an upper end of the fins 211.
The fins 211 may be arranged in a lattice shape, and may be formed in a truncated conical shape, and may have a longest center and a small edge.
At the upper end of the pin 211, a sharp V-shaped sharp blade 203 may be provided.
This may be for replacing only the blade when the blade is intensively collided with the center portion, or when the blade is worn or broken.
This is because the first impact is applied to the center portion of the cover portion 20 and the second impact is applied to the edge portion while the bird and the engine 11 do not directly collide with each other, The impact applied directly to the engine 11 of the aircraft 10 can be reduced by transmitting the amount of the impact to the fixed portion 30 of the shock absorbing type.
Although the present invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not limited to the disclosed embodiments. In addition, the present invention is not limited to the above-described embodiments, and various modifications and changes may be made thereto by those skilled in the art to which the present invention belongs. Therefore, the spirit of the present invention should not be construed as being limited to the above-described embodiments, and all of the equivalents or equivalents of the claims, as well as the following claims, are included in the scope of the present invention.

10: Aircraft 11: Engine
20: cover part 24: body
30: fixing part 211: pin
203: Replacement blade 211: Vertical plate
212: horizontal plate

Claims

And a cover portion disposed on the front portion of the aircraft engine,
The cover portion
Body;
A plurality of horizontal plates spaced apart in parallel to the body; And
And a plurality of vertical plates disposed on the body in a direction perpendicular to the plurality of horizontal plates,
The horizontal plate and the vertical plate are formed in a blade shape, have a hyperbolic shape,
Wherein the plurality of vertical plates have the highest height of the vertical plate located at the center, the height of the vertical plates decreases with the position of the edge of the body,
The plurality of horizontal plates are formed to have the same height,
Wherein the cover portion has a lattice shape on the basis of a front view of the aircraft engine and has a conical shape with respect to a side view of the aircraft engine,
The V-shaped strike prevention blade is provided at the upper end of the horizontal plate and the vertical plate. The V-shaped strike prevention blade is detachable from the horizontal plate and the vertical plate.

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The method according to claim 1,
Further comprising a fixing portion provided between the cover portion and the engine for connecting the engine and the cover portion.

The method of claim 3,
Wherein the fixed portion is a compression spring.

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The method according to claim 1,
Wherein the horizontal plate and the vertical plate are detachably attachable to each other.

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