KR0117806Y1 - Door with composite material of landing system for an aircraft - Google Patents
Door with composite material of landing system for an aircraftInfo
- Publication number
- KR0117806Y1 KR0117806Y1 KR2019950044643U KR19950044643U KR0117806Y1 KR 0117806 Y1 KR0117806 Y1 KR 0117806Y1 KR 2019950044643 U KR2019950044643 U KR 2019950044643U KR 19950044643 U KR19950044643 U KR 19950044643U KR 0117806 Y1 KR0117806 Y1 KR 0117806Y1
- Authority
- KR
- South Korea
- Prior art keywords
- door
- layer
- aircraft
- landing gear
- composite material
- Prior art date
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 15
- 239000010410 layer Substances 0.000 claims abstract description 19
- 239000002344 surface layer Substances 0.000 claims abstract description 12
- 239000012792 core layer Substances 0.000 claims abstract description 8
- 239000012779 reinforcing material Substances 0.000 claims description 2
- 229920000049 Carbon (fiber) Polymers 0.000 claims 2
- 239000004917 carbon fiber Substances 0.000 claims 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims 2
- 239000011208 reinforced composite material Substances 0.000 claims 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 abstract description 10
- 229910052782 aluminium Inorganic materials 0.000 abstract description 10
- 239000004918 carbon fiber reinforced polymer Substances 0.000 abstract description 5
- 239000000463 material Substances 0.000 abstract description 3
- 238000000465 moulding Methods 0.000 abstract description 3
- 238000000034 method Methods 0.000 abstract description 2
- 238000004519 manufacturing process Methods 0.000 description 6
- 239000011347 resin Substances 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- 239000003351 stiffener Substances 0.000 description 2
- 241000282994 Cervidae Species 0.000 description 1
- 239000011162 core material Substances 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000011888 foil Substances 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/16—Fairings movable in conjunction with undercarriage elements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2605/00—Vehicles
- B32B2605/18—Aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
- B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
- B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
도어의 고강도와 함께 경량화를 실현하며, 조립시간을 단축할 수 있는 구조를 갖도록 하는 항공기 착륙장치(landing gear)의 복합재 도어(door)를 제공하는 것이다.It is to provide a composite door (landing gear) of the aircraft landing gear (landing gear) to achieve a high strength and light weight of the door and to reduce the assembly time.
종래의 도어는 항공기용 소재로 주로 사용되는 알루미늄 박판을 이용하여 왔다.Conventional doors have used aluminum sheets, which are mainly used for aircraft materials.
이러한 알루미늄 박판으로 도어를 제작시에는 항공기 외형의 자유곡면을 따라 유압성형용 단품치구를 이용하여 기계가공으로 제작한 후 재단된 알루미늄 박판을 단품치구에 설치하여 유압성형공법을 이용하여 제작하였다.When the door was manufactured from the aluminum sheet, the machine was manufactured by using a hydraulic jig for hydraulic molding along the free curved surface of the aircraft, and then the cut aluminum sheet was installed on the single jig and manufactured using the hydraulic molding method.
본 고안은 도어의 표면층과 이면층을 탄소섬유 강화 고분자 복합재료로 하고, 그 표면층과 이면층 사이의 심재층을 하니컴형상으로 이루어지도록 샌드위치구조를 갖는 도어를 구성한 것이다.The present invention is to construct a door having a sandwich structure such that the surface layer and the back layer of the door are made of carbon fiber reinforced polymer composite material, and the core layer between the surface layer and the back layer is formed in a honeycomb shape.
Description
제 1도는 본 고안의 착륙장치에 설치되는 아웃보드 도어의 평면도.1 is a plan view of the outboard door installed in the landing gear of the present invention.
제 2도는 제 1도의 A-A선 단면도.2 is a cross-sectional view taken along the line A-A of FIG.
제 3도는 제 2도의 A부의 상세도.3 is a detailed view of part A of FIG.
*도면의 주요 부분에 대한 부호의 설명** Description of the symbols for the main parts of the drawings *
10 : 도어12 : 표면층10 door 12 surface layer
14 : 이면층16 : 심재층14: back layer 16: core material layer
18 : 보강재20 : 인서트18: stiffener 20: insert
22 : 심(shim)24 : 레진(resin)22: shim 24: resin
본 고안은 항공기 착륙장치(landing gear)의 복합재 아웃보드 도어(door)에 관한 것으로, 특히 도어의 고강도와 함께 경량화를 실현하며, 조립시간을 단축할 수 있는 구조를 갖도록 하는 항공기 착륙장치의 복합재 도어에 관한 것이다.The present invention relates to a composite outboard door of an aircraft landing gear, and in particular, a composite door of an aircraft landing apparatus to realize a light weight with high strength of the door and to shorten the assembly time. It is about.
일반적으로 항공기의 양 날개(wing)에는 항공기의 착륙장치가 설치되며, 착륙장치와 함꼐 연동되는 아웃보드 도어(이하에서 도어라고 약칭함)가 착륙장치에 부착된다. 이에 따라 상기 도어는 항공기가 이륙하여 착륙장치의 작동에 따라 착륙장치가 접혀지게 되면 상기 아웃보드 도어는 날개 에어포일(air foil)의 스킨(skin)에 위치하게 디어 에어포일의 단면을 이루게 된다.In general, the landing gear of the aircraft is installed on both wings of the aircraft, the outboard door (hereinafter referred to as the door) that is interlocked with the landing device is attached to the landing device. Accordingly, when the landing device is folded and the landing device is folded according to the operation of the landing device, the door forms the cross section of the deer airfoil so that the outboard door is located in the skin of the wing air foil.
상기와 같은 역할을 하는 종래의 도어는 항공기용 소재로 주로 사용되는 알루미늄 박판을 이용하여 왔다. 이러한 알루미늄 박판으로 도어를 제작시에는 항공기 외형의 자유곡면을 따라 유압성형용 단품치구를 이용하여 기계가공으로 제작한 후 재단된 알루미늄 박판을 단품치구를 설치하여 유압성형공법을 이용하여 제작하였다.Conventional doors that play a role as described above have been using a thin aluminum sheet mainly used as a material for the aircraft. When the door is manufactured from the aluminum sheet, the aluminum sheet is machined using the hydraulic molding jig along the free surface of the aircraft, and then the cut aluminum sheet is installed using the hydraulic jig.
상기와 같은 방법으로 각기 제작된 단품을 조립하기 위해서는 별도의 조립치구를 제작하여 단품들을 위치시킨 다음 드릴작업 및 리벳작업을 통해 조립하여 도어를 제작한다. 한편 도어의 다른 제작방법으로는 알루미늄 후판을 일체형으로 하여 기계가공을 제작하는 기술도 알려져 있다.In order to assemble the individual parts manufactured in the above manner, a separate assembly jig is produced, the individual parts are placed, and then assembled by drilling and riveting to produce a door. Meanwhile, as another method of manufacturing a door, a technique of manufacturing an aluminum thick plate in one piece is known.
상기와 같은 알루미늄을 이용하여 착륙장치의 도어제작에 있어서는 단품 제작용 치구와 단품들의 조립치구용 치구가 별도로 필요하게 되어 치구를 제작하는데 따른 비용이 많이 소요되고, 이에 따라 도어 조립을 위한 조립시간이 많이 소요되며, 아울러 되어의 단위중량당 구조강도도 현저히 저하되는 문제를 갖게 된다.In the production of the door of the landing device using the aluminum as described above, the jig for single-piece production and the jig for assembly of the single-piece parts are required separately, which requires a lot of cost for manufacturing the jig. It takes a lot, and also has a problem that the structural strength per unit weight is also significantly reduced.
본 고안은 상기와 같은 종래 기술의 문제점을 해결하기 위해 창안된 것으로, 그 목적은 최근 들어 항공기용 소재로 많이 이용되는 복합재를 사용, 도어의 단위중량당 고강도, 고강성도 및 고내구성의 장점을 이용하여 항공기의 기체설계시 주요사항인 구조물의 경량화와 함께 고강도 및 고강성도을 실현하며, 복합재의 적층(lay up)과 규어링(curing)을 하나의 치구에서 동시에 실시하여 도어를 일체형으로 제작하여서 조립시간을 대폭 단축시켜 조립비용 등을 절감할 수 있도록 하는 항공기 착륙장치의 복합재 도어를 제공하는데 있다.The present invention has been devised to solve the problems of the prior art as described above, the purpose of which is the use of a composite material that is used a lot recently for aircraft materials, using the advantages of high strength, high rigidity and high durability per unit weight of the door It realizes high strength and high stiffness as well as light weight of the structure, which is a major factor in the aircraft design of aircraft. It is to provide a composite door of the aircraft landing device that can greatly reduce the assembly cost and the like.
상기의 목적을 구현하기 위한 본 고안은 도어의 표면층과 이면층을 탄소섬유 강화 고분자 복합재료로 하고, 그 표면층과 이면층 사이의 심재층을 하니컴형상으로 이루어지도록 샌드위치구조를 갖는 도어를 구성한 것이다.The present invention for realizing the above object is to construct a door having a sandwich structure such that the surface layer and the back layer of the door are made of carbon fiber reinforced polymer composite material, and the core layer between the surface layer and the back layer is formed in a honeycomb shape.
한편 상기 샌드위치구조의 표면층과 이면층의 내면에 일정간격을 두고 탄소섬유 강화 고분자 복합재료인 보강재(stiffener)를 일체로 부착하는 것이다.On the other hand, at a predetermined interval on the inner surface of the surface layer and the back layer of the sandwich structure is to integrally attach a stiffener (carbon fiber reinforced polymer composite material).
또한 상기 도어의 힌지브래킷과 링크브래킷을 각각 장착시키기 위한 위치에 인서트와 함께 이면층에 심(shim)을 설치하고, 상기 인서트의 주위에 강성보강용 부시를 설치한 것이다.In addition, a shim is installed on the back layer together with an insert at a position for mounting the hinge bracket and the link bracket of the door, and a rigid reinforcing bush is installed around the insert.
이하에서 본 고안의 바람직한 실시예를 첨부된 도면에 의거 상세히 설명하기로 한다.Hereinafter, a preferred embodiment of the present invention will be described in detail with reference to the accompanying drawings.
제 1도는 본 고안의 착륙장치에 설치되는 아웃보드 도어의 평면도이고, 제 2도는 제 1도의 A-A선 단면도이며, 제 3도는 제 2도의 A부의 상세도를 도시한 것이다.FIG. 1 is a plan view of an outboard door installed in the landing apparatus of the present invention, FIG. 2 is a cross-sectional view taken along line A-A of FIG. 1, and FIG. 3 is a detailed view of part A of FIG.
도시된 바와 같이 도어(10)의 표면층(12)과 이면층(14)을 탄소섬유 강화 고분자 복합재료로 형성하고, 그 표면층(12)과 이면층(14) 사이의 심재층(16)을 하니컴형상으로 이루어져 샌드위치구조를 갖는 도어(10)를 구성한 것이다. 그리고 상기 도어(10)의 외곽둘레는 제 2도와 같이 심재층(16)을 형성하지 않고 표면층(12)과 이면층(14)으로 이루어져 있으며, 심재층(16) 모서리(끝단)를 경사지게 처리한 것이다.As shown, the surface layer 12 and the back layer 14 of the door 10 are formed of a carbon fiber reinforced polymer composite material, and the core layer 16 between the surface layer 12 and the back layer 14 is honeycomb. It consists of a door 10 having a sandwich structure consisting of a shape. In addition, the outer periphery of the door 10 is formed of the surface layer 12 and the back layer 14 without forming the core layer 16 as shown in FIG. 2, and inclined the edge (end) of the core layer 16. will be.
한편 상기 샌드위치구조의 표면층(12)과 이면층(14)의 내면에는 일정간격을 두고 탄소섬유 강화 고분자 복합재인 보강재(18)를 일체로 부착한 것이다. 그리고 상기 도어(10)의 힌지브래킷(도시생략)과 링크브래킷(도시생략)을 각각 장착시키기 위한 위치에 인서트(20)와 이면층에 심(22)을 설치하고, 상기 인서트(20)의 주위에 심재층(16) 강성보강용 레진(24)을 형성하여 강성을 보강한 것이다.On the other hand, the inner surface of the surface layer 12 and the back layer 14 of the sandwich structure is integrally attached to the reinforcing material 18, which is a carbon fiber reinforced polymer composite at regular intervals. Then, the shim 22 is installed on the insert 20 and the back layer at the position for mounting the hinge bracket (not shown) and the link bracket (not shown) of the door 10, respectively, and the circumference of the insert 20 is provided. The core layer 16 is formed of a resin 24 for rigid reinforcement to reinforce rigidity.
상기와 같이 구성된 본 고안의 도어(10)에 의하면 샌드위치형 복합재구조로 일체형으로 이루어져 있다. 이에 따라 도어(10)의 고강성 및 고강성도를 실현할 수 있는 효과를 갖게 되는 것이다.According to the door 10 of the present invention configured as described above is made of a sandwich type composite structure integrally. Accordingly, the high stiffness and high stiffness of the door 10 will be achieved.
한편 상기와 같은 도어(10)는 상기 인서트(20)와 심(22)을 통해 각각의 힌지브래킷과 링크브래킷을 장착하여 항공기의 착륙장치와 연동되어 힌지축을 통해 회전운동을 하게 된다.On the other hand, the door 10 as described above is equipped with a hinge bracket and a link bracket through the insert 20 and the shim 22 to be interlocked with the landing device of the aircraft to rotate through the hinge axis.
이상에서 설명한 바와 같이 본 고안의 항공기 착륙장치의 복합재 도어에 의하면 종래 알루미늄 도어보다 경량구조를 가지면서 고강성을 발휘할 수 있는 효과와 함께 일체로 형성되는 것에 의해 제작시간을 크게 단축시키는 효과를 갖게 되는 것이다.As described above, according to the composite door of the aircraft landing gear of the present invention, the composite door of the present invention has a lighter weight structure than the conventional aluminum door, and is formed integrally with the effect that it can exhibit a high rigidity, thereby greatly reducing the manufacturing time. will be.
Claims (1)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| KR2019950044643U KR0117806Y1 (en) | 1995-12-20 | 1995-12-20 | Door with composite material of landing system for an aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| KR2019950044643U KR0117806Y1 (en) | 1995-12-20 | 1995-12-20 | Door with composite material of landing system for an aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| KR970038699U KR970038699U (en) | 1997-07-29 |
| KR0117806Y1 true KR0117806Y1 (en) | 1998-06-01 |
Family
ID=19436350
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| KR2019950044643U KR0117806Y1 (en) | 1995-12-20 | 1995-12-20 | Door with composite material of landing system for an aircraft |
Country Status (1)
| Country | Link |
|---|---|
| KR (1) | KR0117806Y1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100408833B1 (en) * | 1997-02-28 | 2004-03-10 | 한국항공우주산업 주식회사 | Door of composite-material airplane and manufacturing method thereof |
-
1995
- 1995-12-20 KR KR2019950044643U patent/KR0117806Y1/en not_active IP Right Cessation
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100408833B1 (en) * | 1997-02-28 | 2004-03-10 | 한국항공우주산업 주식회사 | Door of composite-material airplane and manufacturing method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| KR970038699U (en) | 1997-07-29 |
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