Method and systems for use in assembling a fuselage
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-001/00
출원번호
US-0465395
(2012-05-07)
등록번호
US-8870118
(2014-10-28)
발명자
/ 주소
Moselage, III, John H.
출원인 / 주소
The Boeing Company
대리인 / 주소
Armstrong Teasdale LLP
인용정보
피인용 횟수 :
1인용 특허 :
11
초록▼
A fuselage assembly is provided. The fuselage assembly includes a first barrel section including a body that extends from a first end to a second end and a second barrel section coupled to said first barrel section. The second barrel section includes a body that extends from a first end to a second
A fuselage assembly is provided. The fuselage assembly includes a first barrel section including a body that extends from a first end to a second end and a second barrel section coupled to said first barrel section. The second barrel section includes a body that extends from a first end to a second end, and the second end of the first barrel section is coupled to the second end of the second barrel section. At least one member maintains a coupling between the first barrel section and the second barrel section. The at least one member induces a compressive force to at least one of the first barrel section and the second barrel section.
대표청구항▼
1. A method of assembling a fuselage, said method comprising: providing a first barrel section including a body that extends from a first end to a second end, wherein a thickness of the first barrel section second end is greater than a thickness of the first barrel section body, and the first barrel
1. A method of assembling a fuselage, said method comprising: providing a first barrel section including a body that extends from a first end to a second end, wherein a thickness of the first barrel section second end is greater than a thickness of the first barrel section body, and the first barrel section has an inner surface that at least partially defines a cavity and an outer surface opposite the inner surface;providing a second barrel section including a body that extends from a first end to a second end, wherein a thickness of the second barrel section second end is greater than a thickness of the second barrel section body, and the second barrel section has an inner surface that at least partially defines the cavity and an outer surface opposite the inner surface;coupling the first barrel section second end to the second barrel section second end at a joint;positioning a compression member adjacent to the joint within the cavity, wherein a cross-sectional shape of the compression member includes a surface configured to substantially conform to the first barrel section second end and the second barrel section second end; andsecuring the compression member circumferentially against the inner surface of at least one of the first barrel section and the second barrel section to induce a compressive force from the compression member to the at least one of the first barrel section and the second barrel section to maintain the coupling therebetween. 2. The method in accordance with claim 1 further comprising: positioning a tension member adjacent to the joint; andsecuring the tension member circumferentially against the outer surface of at least one of the first and second barrel sections to induce a compressive force to the at least one of the first and second barrel sections to maintain the coupling therebetween. 3. The method in accordance with claim 1, wherein coupling the first barrel section second end to the second barrel section second end comprises using a plurality of interlocking members to couple the first barrel section end to the second barrel section end. 4. A fuselage assembly comprising: a first barrel section comprising a body extending from a first end to a second end, wherein a thickness of said first barrel section second end is greater than a thickness of said first barrel section body, and said first barrel section has an inner surface that at least partially defines a cavity and an outer surface opposite said inner surface;a second barrel section comprising a body extending from a first end to a second end, wherein a thickness of said second barrel section second end is greater than a thickness of said second barrel section body, the second end of said first barrel section is coupled to the second end of said second barrel section at a joint, and said second barrel section has an inner surface that at least partially defines the cavity and an outer surface opposite said inner surface; anda compression member positioned adjacent to said joint within the cavity, a cross-sectional shape of said compression member includes a surface configured to substantially conform to said first barrel section second end and said second barrel section second end such that said compression member maintains a coupling between said first barrel section and said second barrel section, wherein said compression member is secured circumferentially against said inner surface of at least one of said first barrel section and said second barrel section to induce a compressive force to said at least one of said first barrel section and said second barrel section. 5. The fuselage assembly in accordance with claim 4, wherein a thickness of said first barrel section tapers continuously from said first barrel section second end to said first barrel section body. 6. The fuselage assembly in accordance with claim 5, wherein a thickness of said second barrel section tapers continuously from said second barrel section second end to said second barrel section body. 7. The fuselage assembly in accordance with claim 4 further comprising at least one barrel nut configured to secure said compression member to said first barrel section and said second barrel section. 8. The fuselage assembly in accordance with claim 4, wherein at least one of said first barrel section second end and said second barrel section second end comprises a composite material. 9. The fuselage assembly in accordance with claim 4, wherein said first barrel section second end is configured to interlock with said second barrel section second end when said first barrel section is coupled to said second barrel section. 10. The fuselage assembly in accordance with claim 9, wherein said first barrel section second end comprises a plurality of second end portions that extend past said joint and engage with said second barrel section body, and wherein said second barrel section second end comprises a plurality of second end portions that extend past said joint and engage with said first barrel section body, said first barrel section plurality of second end portions is interlocked with said second barrel section plurality of second end portions. 11. The fuselage assembly in accordance with claim 10 wherein said compression member surface tapers from a midpoint adjacent said joint to an edge adjacent a terminal edge of said first barrel section plurality of second end portions. 12. The fuselage assembly in accordance with claim 11, wherein said compression member surface tapers from said midpoint to an edge adjacent a terminal edge of said second barrel section plurality of second end portions. 13. The fuselage assembly in accordance with claim 4, wherein said fuselage assembly further comprises a tension member adjacent to said joint that extends circumferentially about said outer surface of said at least one of said first and second barrel sections to induce a compressive force to said at least one of said first and second barrel sections to maintain the coupling therebetween. 14. The fuselage assembly in accordance with claim 4, wherein said compression member is formed integrally with at least one of said first barrel section and said second barrel section. 15. An aircraft comprising: a first fuselage component comprising a body extending from a first end to a second end, said first fuselage component body comprising an arcuate configuration, wherein a thickness of said first fuselage component second end is greater than a thickness of said first fuselage component body, and said first fuselage component has an inner surface that at least partially defines a cavity and an outer surface opposite said inner surface;a second fuselage component comprising a body extending from a first end to a second end, said second fuselage component body comprising an arcuate configuration, wherein a thickness of said second fuselage component second end is greater than a thickness of said second fuselage component body, said second end of said first fuselage component is coupled to said second end of said second fuselage component at a joint, and said second fuselage component has an inner surface that at least partially defines the cavity and an outer surface opposite said inner surface; anda compression member positioned adjacent to said joint within the cavity, a cross-sectional shape of said compression member includes a surface configured to substantially conform to said first fuselage component second end and said second fuselage component second end, said compression member operable to maintain a coupling between said first fuselage component and said second fuselage component, wherein said compression member is securable circumferentially against said inner surface of at least one of said first fuselage component and said second fuselage component to induce a compressive force to said at least one of said first fuselage component and said second fuselage component. 16. The aircraft in accordance with claim 15 further comprising a tension member adjacent to said joint that extends circumferentially about said outer surface of said at least one of said first and second fuselage components to induce a compressive force to said at least one of said first and second fuselage components to maintain the coupling therebetween. 17. The aircraft in accordance with claim 15 wherein a thickness of said first fuselage component tapers continuously from said first fuselage component second end to said first fuselage component body. 18. The aircraft in accordance with claim 17 wherein a thickness of said second fuselage component tapers continuously from said second fuselage component second end to said second fuselage component body. 19. The aircraft in accordance with claim 15, wherein said compression member is sized to extend circumferentially about said joint.
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