IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0860456
(2007-09-24)
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등록번호 |
US-7798444
(2010-10-11)
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발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
Klintworth & Rozenblat IP LLC
|
인용정보 |
피인용 횟수 :
3 인용 특허 :
8 |
초록
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In one embodiment, an aircraft comprises a plurality of hoop frame support members and a landing gear enclosure comprising a curved surface. The plurality of hoop frame support members abut against and extend over the curved surface to provide support to the landing gear enclosure. In another embodi
In one embodiment, an aircraft comprises a plurality of hoop frame support members and a landing gear enclosure comprising a curved surface. The plurality of hoop frame support members abut against and extend over the curved surface to provide support to the landing gear enclosure. In another embodiment, loads are transferred from a landing gear strut through a strut fitting, through at least one inner surface of the landing gear enclosure, through at least one outer surface of the landing gear enclosure, and into the plurality of hoop frame support members.
대표청구항
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The invention claimed is: 1. An aircraft comprising a landing gear strut attached with a landing gear wheel, a strut fitting attached to the landing gear strut, the strut fitting abutting against an inner surface of an unpressurized landing gear enclosure, and a plurality of hoop frame support memb
The invention claimed is: 1. An aircraft comprising a landing gear strut attached with a landing gear wheel, a strut fitting attached to the landing gear strut, the strut fitting abutting against an inner surface of an unpressurized landing gear enclosure, and a plurality of hoop frame support members forming loops extending within a pressurized fuselage of the aircraft, the unpressurized landing gear enclosure comprising side surfaces and a top surface extending away from the side surfaces, the plurality of hoop frame support members abutting against and extending over and around the side surfaces and the top surface of the unpressurized landing gear enclosure, wherein loads from the landing gear wheel transfer through the landing gear strut, through the strut fitting, through the inner surface of the unpressurized landing gear enclosure, through an outer surface of the unpressurized landing gear enclosure, and into the plurality of hoop frame support members, and wherein pressure differential loads, between the unpressurized landing gear enclosure and the pressurized fuselage, transfer from the unpressurized landing gear enclosure, through the inner and the outer surfaces of the unpressurized landing gear enclosure, and into the plurality of hoop frame support members. 2. The aircraft of claim 1 wherein the side surfaces of the unpressurized landing gear enclosure are substantially straight side, and the top surface of the unpressurized landing gear enclosure comprise a concave dome curved surface extending away from the substantially straight side surfaces. 3. The aircraft of claim 1 wherein the strut fitting comprises a substantially straight surface abutting against said inner surface of the unpressurized landing gear enclosure. 4. The aircraft of claim 1 wherein the landing gear strut comprises a plurality of arm members attached to separate strut fittings, the separate strut fittings abutting against the inner surface of the unpressurized landing gear enclosure. 5. The aircraft of claim 1 wherein the plurality of hoop frame support members are spaced-apart. 6. The aircraft of claim 1 wherein the unpressurized landing gear enclosure is dome-shaped. 7. The aircraft of claim 1 wherein the outer surface of the unpressurized landing gear enclosure is curved. 8. The aircraft of claim 1 wherein the loops formed by the plurality of hoop frame support members continuously extend around the pressurized fuselage and carry fuselage loads of the aircraft independently from the unpressurized landing gear enclosure. 9. The aircraft of claim 1 wherein the side surfaces of the unpressurized landing gear enclosure are substantially straight, and the top surface of the unpressurized landing gear enclosure is curved. 10. The aircraft of claim 1 wherein peripheral edges of the unpressurized landing gear enclosure are compressed against at least one of a surface of a frame support member and a surface of a fitting member. 11. The aircraft of claim 10 wherein the compression is caused by the pressure differential loads. 12. The aircraft of claim 1 wherein the aircraft is made of a composite. 13. The aircraft of claim 1 wherein the unpressurized landing gear enclosure is made of a composite. 14. The aircraft of claim 1 wherein the plurality of hoop frame support members are made of at least one of Titanium and Aluminum. 15. A method of transferring loads in an aircraft comprising: providing an aircraft comprising a landing gear strut attached with a landing gear wheel, a strut fitting attached to the landing gear strut, the strut fitting abutting against an inner surface of an unpressurized landing gear enclosure, the unpressurized landing gear enclosure comprising side surfaces and a top surface extending away from the side surfaces, and a plurality of hoop frame support members forming loops extending within a pressurized fuselage of the aircraft, the plurality of hoop frame support members abutting against and extending over and around the side surfaces and the top surface of the unpressurized landing gear enclosure; transferring loads from the landing gear wheel, through the landing gear strut, through the strut fitting, through the inner surface of the unpressurized landing gear enclosure, through an outer surface of the unpressurized landing gear enclosure, and into the plurality of hoop frame support members; and transferring pressure differential loads, comprising the pressure differential between the unpressurized landing gear enclosure and the pressurized fuselage, from the unpressurized landing gear enclosure, through the inner and the outer surfaces of the unpressurized landing gear enclosure, and into the plurality of hoop frame support members. 16. The method of claim 15 wherein the side surfaces of the unpressurized landing gear enclosure are substantially straight, and the top surface of the unpressurized landing gear enclosure comprises a concave dome top curved surface extending away from the substantially straight side surfaces. 17. The method of claim 15 wherein the plurality of hoop frame support members are spaced-apart. 18. The method of claim 15 wherein the unpressurized landing gear enclosure is dome-shaped. 19. The method of claim 15 wherein the loops formed by the plurality of hoop frame support members continuously extend around the pressurized fuselage, and further comprising the plurality of hoop frame support members carrying fuselage loads of the aircraft independently from the unpressurized landing gear enclosure. 20. The method of claim 15 wherein the outer surface of the unpressurized landing gear enclosure is curved. 21. The method of claim 15 wherein the side surfaces of the unpressurized landing gear enclosure are substantially straight, and the top surface of the unpressurized landing gear enclosure is curved. 22. The method of claim 15 wherein the transfer loads from the landing gear wheel are from landing of the aircraft. 23. The method of claim 15 wherein the landing gear strut comprises a plurality of arm members attached to separate strut fittings, and the separate strut fittings abut against the inner surface of the unpressurized landing gear enclosure. 24. The method of claim 15 further comprising compressing peripheral edges of the unpressurized landing gear enclosure against at least one of a surface of a frame support member of the aircraft and a surface of a fitting member of the aircraft. 25. The method of claim 24 wherein the compression is due to the transferred pressure differential loads. 26. The method of claim 15 wherein the aircraft is made of a composite. 27. The method of claim 15 wherein the unpressurized landing gear enclosure is made of a composite. 28. The method of claim 15 wherein the plurality of hoop frame support members are made of at least one of Titanium and Aluminum.
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