KR101693009B1 - Apparatus for forming gasket of aircraft and method for sealing gasket - Google Patents

Apparatus for forming gasket of aircraft and method for sealing gasket Download PDF

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Publication number
KR101693009B1
KR101693009B1 KR1020150103094A KR20150103094A KR101693009B1 KR 101693009 B1 KR101693009 B1 KR 101693009B1 KR 1020150103094 A KR1020150103094 A KR 1020150103094A KR 20150103094 A KR20150103094 A KR 20150103094A KR 101693009 B1 KR101693009 B1 KR 101693009B1
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KR
South Korea
Prior art keywords
aircraft
gasket
heating
main body
sealant
Prior art date
Application number
KR1020150103094A
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Korean (ko)
Inventor
이경민
Original Assignee
한국항공우주산업 주식회사
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Priority to KR1020150103094A priority Critical patent/KR101693009B1/en
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Publication of KR101693009B1 publication Critical patent/KR101693009B1/en

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • B64F5/0009—
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/02—Sealings between relatively-stationary surfaces
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B1/00—Details of electric heating devices
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B2213/00—Aspects relating both to resistive heating and to induction heating, covered by H05B3/00 and H05B6/00
    • H05B2213/07—Heating plates with temperature control means

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Gasket Seals (AREA)

Abstract

The present invention relates to an apparatus for forming a gasket for an aircraft and a gasket sealing method capable of performing a heat treatment in a gasket sealing process of an airframe body, which is detachably attachable to an aircraft and which can be applied with a sealant on one side facing the aircraft And a heating unit provided on the main body and heating the main body in close contact with the aircraft and the main body to allow the sealant to harden from the surface of the aircraft to the gasket. Accordingly, the gasket forming apparatus and the gasket sealing method for an aircraft are capable of forming a gasket at a short time by heat treating the aircraft body during the manufacture and maintenance of an aircraft.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to an apparatus for forming a gasket for an aircraft,

The present invention relates to a gasket forming apparatus for an aircraft and a gasket sealing method, and more particularly, to a gasket forming apparatus for an aircraft and a gasket sealing method used in a structure adhering process of an aircraft.

Generally, gaskets are provided in joints between structures or structures that need to be closely contacted, so that the structures can be brought into close contact with each other.

The prior art for such a gasket has already been disclosed by Korean Patent Laid-Open Publication No. 2007-0109947 (Gasket, Nov. 15, 2007). The present invention is characterized in that a sealant is applied to form a gasket for securing the sealing property in a plurality of metal plate lamination layers.

In the process of forming the gasket, after the sealant is applied to the structure to form the gasket in a short time, a heat treatment process such as an oven process may be performed. However, when the gasket is formed on the aircraft body during the manufacture and maintenance of the aircraft, the oven process for the heat treatment can not be performed, thereby delaying the formation of the gasket.

Korean Patent Publication No. 2007-0109947 (Gasket, November 15, 2007)

An object of the present invention is to provide a gasket forming apparatus for an aircraft and a gasket sealing method capable of performing heat treatment in a gasket sealing process of an aircraft body.

The apparatus for forming a gasket for an aircraft according to the present invention comprises: a body detachably mountable to an airplane and having a coated region on which a sealant can be applied on a face facing the airplane; and a body provided on the body, And a heating portion for heating the body to allow the sealant to harden from the aircraft surface to the gasket.

The main body may be formed in the same shape as the structure to be adhered to the aircraft, and may be closely attached to the aircraft body before the aircraft and the structure are closely contacted to form the gasket.

The heating unit may include a heating member for heating the application region and a control unit connected to the heating member to control the heating of the heating member.

The control unit may include a temperature control unit for controlling the heating temperature of the heating member, and a time control unit for controlling the heating time of the heating member to stop the heating of the heating member after a predetermined time.

According to another aspect of the present invention, there is provided a method for sealing an aircraft gasket, including the steps of: applying a sealant on one surface of a main body and attaching the main body to the aircraft such that the sealant application area faces the aircraft; A curing step of curing the sealant from the surface of the aircraft to a gasket, a separating step of separating the body from the aircraft, and a sealing step of sealing the structure between the aircraft and the structure by bringing the structure into close contact with the area where the gasket is formed .

The method for sealing an aircraft gasket may further include an applying step of applying a gasket separating liquid to the body so that the gasket formed on the aircraft and the body are detachable from each other before the attaching step.

The air gasket sealing method may further include a setting step of setting a heating temperature and a heating time of the heating unit before the curing step. In the curing step, the heating of the heating unit may be stopped after the set time in the setting step.

The gasket forming apparatus and gasket sealing method for an aircraft according to the present invention have an effect of forming a gasket at a short time by heat treating an aircraft body during the manufacture and maintenance of an aircraft.

The technical effects of the present invention are not limited to the effects mentioned above, and other technical effects not mentioned can be clearly understood by those skilled in the art from the following description.

1 is a view showing the combination of an aircraft body and a structure,
2 is a perspective view showing an aircraft gasket forming apparatus according to the present embodiment,
FIG. 3 is an enlarged view of the aircraft gasket forming apparatus according to the present embodiment showing A marked in FIG. 2,
4 is a block diagram showing an aircraft gasket forming apparatus according to the present embodiment,
5 is a flowchart showing an aircraft gasket sealing method according to the present embodiment,
6 to 9 are views illustrating an aircraft gasket sealing method according to the present embodiment.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings. However, it should be understood that the present invention is not limited to the disclosed embodiments, but may be implemented in various forms, and the present embodiments are not intended to be exhaustive or to limit the scope of the invention to those skilled in the art. It is provided to let you know completely. The shape and the like of the elements in the drawings may be exaggerated for clarity, and the same reference numerals denote the same elements in the drawings.

2 is a perspective view showing an apparatus for forming an aircraft gasket according to an embodiment of the present invention. FIG. 3 is a cross-sectional view of an apparatus for forming an aircraft gasket according to an embodiment of the present invention, Fig.

1 to 3, an apparatus 100 (hereinafter, referred to as a forming apparatus) for an aircraft gasket according to the present embodiment may perform a heat treatment in a gasket forming process of the aircraft body 10. Here, the forming apparatus 100 is attached to the aircraft body 10 before attachment of the structure 30 to be attached to the aircraft body 10 in the process of assembling and maintenance of the aircraft, The gasket 110 (see FIG. 8) may be formed on the gasket 10a.

The forming apparatus 100 includes a main body 110 and a heat generating portion 130.

First, the body 110 is provided in the same shape as the structure 30. At this time, the main body 110 may be provided in the same form as the structure 30 as a whole. However, even if the main body 110 is provided in a form different from that of the structure 30, it may have the same shape as the attachment surface 30a of the structure 30 to be attached to the attachment region 10a, It is also possible to provide only the mounting surface of the second lens unit.

The body 110 may be made of aluminum and the sealant 110b may be applied to the attachment surface 100a of the body 110 to form the gasket 110c. At this time, the application region P to which the sealant 110b is applied is a structure in which a conventional car custody is formed to adhere the structure 30 to the aircraft body 10 when the actual airframe 10 and the structure 30 are in close contact with each other Area.

On the other hand, before the sealant 110b is applied to the application region P, the gasket separation liquid 110a may be applied to the application region P. [ The gasket separating liquid 110a is made of a fluxing agent so that the gasket 110c can be easily separated from the main body 110 when the gasket 110c is formed due to curing of the sealant 110b. The main body 110 is easily separated from the aircraft body 10 in a state where the gasket 110c is formed on the aircraft body 10 when the main body 110 is detached from the aircraft body 10 after curing the gasket 110c .

The heat generating unit 130 heats the main body 110 when the main body 110 is closely attached to the aircraft body 10 so as to form the gasket 110c on the aircraft body 10. [ The main body 110 includes a heating member 131 and a control unit 133.

The heat generating member 131 is installed in the main body 110. Here, the heat generating member 131 may be provided adjacent to the region where the sealant 110b is applied, but it may be uniformly provided over the entire region of the main body 110. 2, the heating member 131 is installed on the outer surface of the main body 110. However, the heating member 131 may be installed inside the main body 110, .

The heat generating member 131 may be provided by a heat ray or a heat pipe, but the kind of the heat generating member 131 is not limited.

Meanwhile, the control unit 133 may be connected to the heating member 131 to control the heating of the heating member 131. Here, the control unit 133 may be installed in the main body 110, but may be provided outside the main body 110 by being connected to the heating member 131 by a cable C as shown in FIG. The control unit C can perform overall control of the heat generating member 131, and the control unit 133 will be described in detail with reference to the accompanying drawings.

4 is a block diagram showing an aircraft gasket forming apparatus according to the present embodiment.

As shown in FIG. 4, the controller 133 according to the present embodiment is connected to the heat generating member 131. Here, the control unit 133 may include a power control unit 133a, a temperature control unit 133b, and a time control unit 133c.

First, the power control unit 133a receives power from the outside and controls the overall power of the heat generating unit 130. [ The power control unit 133a controls the power supplied to the heating member 131 so that the heating member 131 can supply a stable current. Thus, the supply of the overcurrent to the heat generating member 131 can be blocked.

The temperature control unit 133b controls the heating temperature of the heat generating member 131 to be controlled. Here, the temperature control unit 133b may include a temperature switch 133ba. Accordingly, the temperature of the heating member 131 is adjusted according to the adjustment of the user's temperature switch 133ba, and the heating member 131 can generate stable heat at a predetermined temperature.

The time control unit 133c controls the heating time of the heating member 131. [ Here, the time control unit 133c includes a time switch 133ca. Accordingly, the user can adjust the heat generation time, and the time control unit 133c can stop the heat generation of the heat generation member 131 after the predetermined heat generation time has elapsed.

Hereinafter, a gasket sealing method using a gasket forming apparatus will be described in detail with reference to the accompanying drawings. However, the detailed description of the above-described components will be omitted and the same reference numerals will be given.

FIG. 5 is a flowchart illustrating an aircraft gasket sealing method according to an embodiment of the present invention, and FIGS. 6 to 9 illustrate an aircraft gasket sealing method according to the present embodiment.

5 to 9, the method of sealing an aircraft gasket may perform an aircraft gasket sealing process based on the aircraft gasket forming apparatus 100.

First, the gasket separation liquid 110a and the sealant 110b are sequentially applied to the main body 110 (S100). Here, the sealant 110b may be applied to the application region P. The gasket separating liquid 110a is spread over the region to which the sealant 110b is applied before the application of the sealant 110b so that the body 110 can be easily separated from the aircraft body 110 after the gasket 110c is formed .

Then, the main body 110 is attached to the aircraft body 10 (S200, refer to Fig. 6). At this time, the main body 110 may be attached so as to correspond to an attachment region of the structure 30 to be attached to the aircraft main body 110 in the future. The gasket 110c formed on the airplane body 10 by the main body 110 is attached to the airplane body 10 after the main body 110 is removed, The structure 30 can be closely attached to the aircraft body 10 in close contact with the structure 30.

When the main body 110 is attached to the aircraft body 10, power is supplied from the outside to the control unit 133 and the user controls the temperature control unit 133b so that the heating temperature of the heating member 131 provided in the main body 110 . If predetermined data exist in the process environment, the user controls the time control unit 133c to set the heat generation time of the heat generating member 131. The control unit 133 causes the heating member 131 to generate heat at a predetermined temperature for a predetermined period of time so that the sealant 110b is stably heat treated and cured by the gasket 110c.

Thereafter, when the sealant 110b is cured to form the gasket 110c, the main body 110 is separated from the aircraft body 10 (S400, see Fig. 8). At this time, the gasket 110c is easily separated from the main body 110 by the gasket separating liquid 110a previously applied to the main body 110, and is present on the aircraft body 10. [ Thereafter, the cleaning process may be performed on the region to which the gasket 110c is applied, but the cleaning process may be omitted.

Finally, when the gasket 110c is formed on the surface of the aircraft body 10, the same structure 30 as the body 110 is attached to the aircraft body 10, and the process of sealing the aircraft gasket can be completed (S500 , See Fig. 9).

As described above, the gasket forming apparatus and the gasket sealing method for aircraft have the effect of forming the gasket at a short time by heat treating the aircraft body during the manufacture and maintenance of the aircraft.

One embodiment of the invention described above and shown in the drawings should not be construed as limiting the technical idea of the present invention. The scope of protection of the present invention is limited only by the matters described in the claims, and those skilled in the art will be able to modify the technical idea of the present invention in various forms. Accordingly, such improvements and modifications will fall within the scope of the present invention as long as they are obvious to those skilled in the art.

10: Aircraft body
30: Structure
100: Aircraft gasket forming device
110:
130:
131:
133:

Claims (7)

A body detachably mountable to an airplane and having an application region on which a sealant can be applied on one side facing the airplane; And
And a heating portion provided in the main body, for heating the main body in close contact with the aircraft and the main body so that the sealant is hardened to the gasket at the surface of the aircraft.
The method according to claim 1,
The body
Wherein the gasket is formed in the same shape as the structure to be adhered to the aircraft and is closely contacted with the aircraft body before the aircraft and the structure are closely contacted to form the gasket.
The method according to claim 1,
The heat-
A heating member for heating the application region;
And a control unit connected to the heating member to control the heat generation of the heating member.
The method of claim 3,
The control unit
A temperature control unit for controlling a heat generation temperature of the heating member,
And a time control unit for controlling the heating time of the heating member to stop the heating of the heating member after a predetermined time.
An attaching step of applying a sealant to one surface of the body and attaching the body to the aircraft such that the sealant application area faces the aircraft;
A curing step in which a heat generating unit provided in the main body heats the main body to cure the sealant from the surface of the aircraft into a gasket;
A separating step of separating the main body from the aircraft; And
And sealing the structure to the region where the gasket is formed to seal between the aircraft and the structure.
6. The method of claim 5,
Prior to the attachment step,
Further comprising applying a gasket separating liquid to the main body so that the gasket formed on the aircraft and the main body are detachable from each other.
6. The method of claim 5,
Before the curing step,
Further comprising a setting step of setting a heating temperature and a heating time of the heating unit,
In the curing step
And stopping the heat generation of the heating unit after the set time in the setting step.
KR1020150103094A 2015-07-21 2015-07-21 Apparatus for forming gasket of aircraft and method for sealing gasket KR101693009B1 (en)

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Application Number Priority Date Filing Date Title
KR1020150103094A KR101693009B1 (en) 2015-07-21 2015-07-21 Apparatus for forming gasket of aircraft and method for sealing gasket

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Application Number Priority Date Filing Date Title
KR1020150103094A KR101693009B1 (en) 2015-07-21 2015-07-21 Apparatus for forming gasket of aircraft and method for sealing gasket

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KR101693009B1 true KR101693009B1 (en) 2017-01-05

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH08175498A (en) * 1994-12-26 1996-07-09 Japan Airlines Co Ltd Device used for repair of bonded structure member for aircraft
KR20000055173A (en) * 1999-02-04 2000-09-05 정몽규 bus roof panel bonding device
KR20050101799A (en) * 2004-04-20 2005-10-25 한국항공우주산업 주식회사 To form gasket in checking window of aircraft structure
KR20070109947A (en) 2006-05-12 2007-11-15 이시카와 가스킷 가부시키가이샤 Gasket
JP2014523657A (en) * 2011-05-11 2014-09-11 ジャガー・ランド・ローバー・リミテッド Assembly capable of being sealed by thermosetting and method for manufacturing the same

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH08175498A (en) * 1994-12-26 1996-07-09 Japan Airlines Co Ltd Device used for repair of bonded structure member for aircraft
KR20000055173A (en) * 1999-02-04 2000-09-05 정몽규 bus roof panel bonding device
KR20050101799A (en) * 2004-04-20 2005-10-25 한국항공우주산업 주식회사 To form gasket in checking window of aircraft structure
KR20070109947A (en) 2006-05-12 2007-11-15 이시카와 가스킷 가부시키가이샤 Gasket
JP2014523657A (en) * 2011-05-11 2014-09-11 ジャガー・ランド・ローバー・リミテッド Assembly capable of being sealed by thermosetting and method for manufacturing the same

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