Energy-absorbing structural composite element
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
E04C-003/29
B64C-001/00
B32B-003/26
B32B-005/18
B32B-003/00
출원번호
US-0342916
(2008-12-23)
등록번호
US-8181422
(2012-05-22)
발명자
/ 주소
Barland, David Eugene
McKinnie, Benjamin Scott
출원인 / 주소
Spirit AeroSystems, Inc.
대리인 / 주소
Hovey Williams LLP
인용정보
피인용 횟수 :
0인용 특허 :
17
초록▼
A structural, energy absorbing composite element for aircraft structures includes a metallic or nonmetallic skin shell with a porous filler material insert positioned within the skin shell. The porous filler material is a material having ligaments that collapse resulting in a densification of the po
A structural, energy absorbing composite element for aircraft structures includes a metallic or nonmetallic skin shell with a porous filler material insert positioned within the skin shell. The porous filler material is a material having ligaments that collapse resulting in a densification of the porous filler material in response to impact loading or a compression force sufficient to cause failure of the combined assembly.
대표청구항▼
1. A structural, energy absorbing composite element comprising: a monolithic skin shell;a porous filler material insert tapered or rounded at one end and positioned within said skin shell; anda single unitary attachment fitting, wherein at least a portion of the attachment fitting is positioned inwa
1. A structural, energy absorbing composite element comprising: a monolithic skin shell;a porous filler material insert tapered or rounded at one end and positioned within said skin shell; anda single unitary attachment fitting, wherein at least a portion of the attachment fitting is positioned inward of the skin shell and adjacent at least one end of the porous filler material insert, wherein said attachment fitting comprises: a clevis fitting extending outward of the skin shell, and an interface portion integral and unitarily formed with the clevis fitting and positioned inward of the skin shell, wherein the interface portion is substantially hollow and the tapered or rounded end of the porous filler material insert is positioned at least partially within the hollow interface portion. 2. The structural, energy absorbing composite element according to claim 1 further comprising a shoulder between the clevis fitting and the interface portion, wherein the skin shell comprises a first end portion and a second end portion opposite of the first end portion, wherein the shoulder has a chamfered face engaging the first end portion or the second end portion of the skin shell. 3. The structural, energy absorbing composite element according to claim 1, further comprising: a fuse pin extending through the attachment fitting and the skin shell. 4. The structural, energy absorbing composite element according to claim 1 wherein the skin shell comprises a metal selected from the group of aluminum, steel, nickel, copper, zinc, and alloys thereof. 5. The structural, energy absorbing composite element according to claim 1 wherein the skin shell comprises at least one of fiber-reinforced thermal set, thermoplastic and metal matrix composite materials. 6. The structural, energy absorbing composite element according to claim 1 wherein said porous filler material insert is formed of a metallic material. 7. The structural, energy absorbing composite element according to claim 6, wherein said metallic material is one of aluminum, steel, nickel, copper, zinc, lead cobalt, cadmium and alloys thereof. 8. A passenger floor stanchion for an aircraft comprising: a tubular, monolithic skin shell;a porous filler material insert having open cells and ligaments positioned within said skin shell, andan attachment fitting, wherein said attachment fitting comprises: an interface portion at least partially located inward of the skin shell and abutting a portion of the porous filler material insert, wherein at least a portion of the porous filler material insert is located inward of the interface portion and the skin shell, wherein at least one end of the porous filler material insert is substantially tapered, and wherein the interface portion is substantially hollow and the tapered end of the porous filler material insert is positioned within the hollow interface portion. 9. The passenger floor stanchion according to claim 8, the attachment fitting further comprising: a clevis fitting extending outward of the skin shell, anda shoulder integrally formed with and located between the clevis fitting and the interface portion having a chamfered face engaging an end portion of the skin shell. 10. The passenger floor stanchion according to claim 8, further comprising: a fuse pin extending through the attachment fitting and the skin shell. 11. The passenger floor stanchion according to claim 8 wherein said tubular skin shell comprises a metal selected from the group consisting of aluminum, steel, nickel, copper, zinc, and alloys thereof. 12. The passenger floor stanchion according to claim 8 wherein said tubular skin shell comprises a composite material selected from the group consisting of fiber-reinforced thermal set, thermoplastic and metal matrix composite materials. 13. The passenger floor stanchion according to claim 8 wherein said porous filler material is formed of a metallic material. 14. The passenger floor stanchion according to claim 13 wherein said metallic material is one of aluminum, steel, nickel, copper, zinc, lead cobalt, cadmium and alloys thereof.
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이 특허에 인용된 특허 (17)
Whitmer,Brett D.; Rockwell,Glen C.; Tanner,Richard B., Apparatuses and methods for attaching engines and other structures to aircraft wings.
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