[특허]Aircraft skin attachment system

THE BOEING COMPANY

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특허 상세정보

MyON담기

내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Aircraft skin attachment system

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-001/12 B64C-003/26
출원번호	US-0947430 (2013-07-22)
등록번호	US-9156538 (2015-10-13)
발명자 / 주소	Stern, Eric Joseph Hanks, Ryan Lee
출원인 / 주소	THE BOEING COMPANY
대리인 / 주소	Yee & Associates, P.C.
인용정보	피인용 횟수 : 1 인용 특허 : 6

초록
▼

A method and apparatus for operating an aircraft. The aircraft is flown. A skin panel is held on a support structure. The support structure has flanges on a number of edges of the support structure, the flanges being substantially orthogonal to the edges. The support structure also has openings into the support structure substantially orthogonal to the flanges. First connecting structures on clips are connected to the flanges and positioned such that an opening in each clip is aligned with one of the openings in the support structure. The skin panel is p...

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청구항
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1. An apparatus comprising: a clip having a first connecting structure, and a second connecting structure configured to be connected to a second structure, wherein the second connecting structure comprises a first opening;a support structure of an aerospace vehicle having an edge and a second opening along the edge into the support structure; anda flange extending in a substantially orthogonal direction from the edge around the second opening, wherein the second opening is substantially orthogonal to the flange, wherein the first connecting structure of the clip is configured to receive the flange, and wherein the first opening and the second opening are aligned when the clip is in a desired position. 2. The apparatus of claim 1 further comprising the second structure having a hole there through, wherein the second connecting structure is configured to be placed through the hole in the second structure. 3. The apparatus of claim 2, wherein the second connecting structure receives a fastener to secure the second structure to the second connecting structure. 4. The apparatus of claim 1 further comprising a rod configured to be placed through the first opening and the second opening, wherein the first opening and the second opening are receive the rod when the clip is aligned with the flange in the desired position. 5. The apparatus of claim 1, wherein the first connecting structure has a channel extending there through, wherein a shape of the channel conforms to a cross-sectional shape of the flange, wherein the channel is configured to receive the flange. 6. The apparatus of claim 5, wherein the first connecting structure has a cylindrical shape. 7. The apparatus of claim 5, wherein the channel is configured to receive the flange with an interference fit. 8. The apparatus of claim 1, wherein the support structure further comprises an aircraft frame structure selected from one of a rib, a spar, and a stringer. 9. The apparatus of claim 3, wherein the fastener is a nut. 10. The apparatus of claim 8, wherein the support structure is comprised of a material selected from one of titanium, aluminum, steel, plastic, a composite material, a metal, and polycarbonate. 11. The apparatus of claim 2, wherein the second structure further comprises an aircraft panel structure selected from one of a skin panel, a floor panel, a wall panel, and a honeycomb structure panel. 12. A skin panel attachment system comprising: a frame of an aerospace vehicle having a number of edges;a number of flanges formed on the number of edges of the frame;a number of clips having first connecting structures and second connecting structures, wherein the first connecting structures are configured to receive one of the number of flanges in channels in the first connecting structures, and wherein the second connecting structures are configured be connected to a skin panel, wherein each second connecting structure comprises a first opening;a number of second openings along the number of edges into the frame, wherein each flange on the number of edges of the frame is formed around one of the number of second openings, and wherein each of the number of second openings are aligned with the first opening of one of the second connecting structures when the number of clips are in desired positions;the skin panel having holes, wherein the second connecting structures are received in the holes; andfasteners connected to the second connecting structures and securing the skin panel to the frame. 13. The skin panel attachment system of claim 12, wherein the frame is for an outlet of an aircraft engine. 14. The skin panel attachment system of claim 12, further comprising: a rod configured to be placed through one of the number of first openings and the second opening and align each of the number of clips with one of the number of flanges in the desired positions. 15. A method for connecting structures, the method comprising: placing clips on flanges on a support structure of an aerospace vehicle such that first connecting structures on the clips receive the flanges;aligning first openings in a second connecting structure on the clips with second openings on the support structure to position the clips into a desired position with the flanges; wherein the support structure comprises an edge, wherein the second openings are along the edge into the support structure, and wherein the flanges extend in a substantially orthogonal direction from the edge around the second openings;positioning a second structure, wherein second connecting structures on the clips are received in holes in the second structure; andattaching fasteners to the second connecting structures to secure the second structure to the second connecting structure. 16. The method of claim 15, wherein aligning the first openings with second openings further comprises: placing rods through the first openings and the second openings, wherein the clips are aligned with the flanges in desired positions. 17. The method of claim 15, wherein placing the clips on the flanges on the support structure comprises: receiving the flanges in channels in the first connecting structures in the clips, wherein a shape of the channel conforms to a cross-sectional shape of the flange, wherein the channel is configured to receive the flange with an interference fit. 18. The method of claim 15, wherein the fasteners are nuts. 19. The method of claim 15, wherein the support structure further comprises an aircraft frame structure selected from one a rib, a spar, and a stringer, and wherein the second structure further comprises an aircraft panel structure selected from one of a skin panel, a floor panel, a wall panel, and a honeycomb structure panel. 20. A method of operating an aircraft, the method comprising: flying the aircraft; andholding a skin panel on a support structure of the aircraft, wherein the clips have first and second connecting structures, wherein the first connecting structures are configured to receive one of a number of flanges in channels in the first connecting structures, the second connecting structures are configured to be connected to the skin panel, and each second connecting structure comprises a first opening; wherein the support structure has a number of edges, a number of second openings along the number of edges into the support structure, and a number of flanges on the number of edges of the support structure, each flange being formed around one of the number of second openings; and wherein each of the number of second openings are aligned with the first opening of one of the second connecting structures when the clips are in desired positions, the skin panel positioned such that the clips are received in holes in the skin panel, and fasteners attached to the second connecting structures such that the support structure holds the skin panel.

이 특허에 인용된 특허 (6)

이 특허를 인용한 특허 피인용횟수: 1

Wilkerson, Jeffrey A.. Wing and method of manufacturing. USP20190110179640.

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특허 상세정보

Aircraft skin attachment system

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이 특허에 인용된 특허 (6)

이 특허를 인용한 특허 피인용횟수: 1

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Aircraft skin attachment system

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이 특허에 인용된 특허 (6)

이 특허를 인용한 특허 피인용횟수: 1

IPC 상위 출원인

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IPC 상세정보(version : 201201)

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