IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
UP-0555829
(2006-11-02)
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등록번호 |
US-7735779
(2010-07-05)
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발명자
/ 주소 |
- Griess, Kenneth H.
- Georgeson, Gary E
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출원인 / 주소 |
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
13 인용 특허 :
0 |
초록
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A fuselage structure including an upper fuselage portion defined by a first cross-section including at least three different radii of curvature. The fuselage structure may also include a lower fuselage portion defined by a second cross-section including at least three different radii of curvature, w
A fuselage structure including an upper fuselage portion defined by a first cross-section including at least three different radii of curvature. The fuselage structure may also include a lower fuselage portion defined by a second cross-section including at least three different radii of curvature, wherein the first cross-section is different from the second cross-section.
대표청구항
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What is claimed is: 1. A fuselage structure, comprising: an upper fuselage portion defined by a first cross-section including at least three different radii of curvature; a lower fuselage portion defined by a second cross-section including at least three different radii of curvature, wherein the fi
What is claimed is: 1. A fuselage structure, comprising: an upper fuselage portion defined by a first cross-section including at least three different radii of curvature; a lower fuselage portion defined by a second cross-section including at least three different radii of curvature, wherein the first cross-section is different from the second cross-section; an integrated keel beam formed in the lower fuselage portion; wherein the integrated keel beam comprises: an outer layer of material; a core structure disposed on the outer layer; an inner layer of material formed on the core structure; wherein the core structure comprises: a first panelized portion formed of a plurality of stacked tapering layers extending from the inner layer toward the outer layer; a second panelized portion formed of a plurality of stacked tapering layers extending from the outer layer toward the inner layer; a first core member having a first wedge portion on a first side of the first and second panelized portions; a second core member having a second wedge portion on a second side of the first and second panelized portions; and the first and second wedge portions are disposed between corresponding tapered sections of the first and second panelized portions. 2. The fuselage structure of claim 1, wherein the first cross-section is wider than the second cross-section. 3. The fuselage structure of claim 1, wherein the upper fuselage portion comprises a hybrid structure including a solid laminate structure section and a section including a core structure. 4. The fuselage structure of claim 1, wherein the upper fuselage portion and the lower fuselage portion are formed as separate fuselage pieces. 5. The fuselage structure of claim 1, wherein the upper fuselage portion and the lower fuselage portion are integrally formed as one unitary fuselage piece. 6. The fuselage structure of claim 1, wherein the upper fuselage portion and the lower fuselage portion each comprise a sandwich structure. 7. The fuselage structure of claim 6, wherein the sandwich structure comprises: an outer layer of material; a inner layer of material; and a core structure disposed between the outer layer and the inner layer. 8. The fuselage structure of claim 7, wherein the core structure comprises one of a group including a honeycomb type structure and foam. 9. The fuselage structure of claim 1, further comprising a unitized one-piece passenger floor disposed substantially between the upper fuselage portion and the lower fuselage portion. 10. The fuselage structure of claim 9, further comprising a floor attachment longeron to attach the one-piece passenger floor to at least one of the upper fuselage portion and the lower fuselage portion. 11. The fuselage structure of claim 9, further comprising a joining element to define a combination passenger floor attach and fuselage lap splice fitting to attach the passenger floor and upper and lower fuselage portions. 12. The fuselage structure of claim 10, further comprising a unitized stanchion and cargo wall disposed between an underside of the passenger floor and the lower fuselage portion. 13. The fuselage structure of claim 1, further comprising a unitized cargo floor integrated into a substantially flattened base section of the lower fuselage portion. 14. The fuselage structure of claim 1, wherein the lower fuselage portion comprises a substantially flattened bottom section to provide added rotational clearance for take-off and landing compared to a substantially circular cross-sectional fuselage. 15. The fuselage structure of claim 1, further comprising a frame structure formed in at least one of the upper fuselage portion and the lower fuselage portion to reinforce the fuselage structure. 16. The fuselage structure of claim 15, wherein the frame structure is integrated into an inner skin. 17. A fuselage structure, comprising: an upper fuselage portion including a sandwich structure and a non-circular cross-section defined by a first set of varying radii of curvature; a lower fuselage portion including another sandwich structure and a non-circular cross-section defined by a second set of varying radii of curvature, wherein the first set of varying radii is different from the second set of varying radii; an integrated keel beam formed in the lower fuselage portion; wherein the integrated keel beam comprises: an outer layer of material; a core structure disposed on the outer layer; an inner layer of material formed on the core structure; wherein the core structure comprises: a first panelized portion formed of a plurality of stacked tapering layers extending from the inner layer toward the outer layer; a second panelized portion formed of a plurality of stacked tapering layers extending from the outer layer toward the inner layer; a first core member having a first wedge portion on a first side of the first and second panelized portions; a second core member having a second wedge portion on a second side of the first and second panelized portions; and the first and second wedge portions are disposed between corresponding tapered sections of the first and second panelized portions. 18. The fuselage structure of claim 17, wherein the lower fuselage portion narrows from the upper fuselage portion toward a bottom section of the lower fuselage portion. 19. The fuselage structure of claim 17, wherein the lower fuselage portion comprises a bottom section that is substantially flattened relative to a circular cross-section to provide added rotational clearance for take-off and landing. 20. The fuselage structure of claim 19, further comprising a unitized cargo floor integrated into the substantially flattened bottom section of the lower fuselage portion. 21. The fuselage structure of claim 17, wherein the upper fuselage portion and the lower fuselage portion are integrally formed as one unitary fuselage piece. 22. The fuselage structure of claim 17, wherein the upper fuselage portion and the lower fuselage portion comprise: an outer layer of material; a inner layer of material; and a core structure disposed between the outer layer and the inner layer. 23. The fuselage structure of claim 19, further comprising: a unitized one-piece passenger floor disposed substantially between the upper fuselage portion and the lower fuselage portion; and a joining element to define a combination passenger floor attach and fuselage lap splice fitting to attach the passenger floor and upper and lower fuselage portions. 24. An aircraft, comprising: a fuselage including: an upper fuselage portion defined by a first cross-section including at least three different radii of curvature, a lower fuselage portion defined by a second cross-section including at least three different radii of curvature, wherein the first cross-section is different from the second cross-section; a wing attached to the fuselage; an integrated keel beam formed in the lower fuselage portion; wherein the integrated keel beam comprises: an outer layer of material; a core structure disposed on the outer layer; an inner layer of material formed on the core structure; wherein the core structure comprises: a first panelized portion formed of a plurality of stacked tapering layers extending from the inner layer toward the outer layer; a second panelized portion formed of a plurality of stacked tapering layers extending from the outer layer toward the inner layer; a first core member having a first wedge portion on a first side of the first and second panelized portions; a second core member having a second wedge portion on a second side of the first and second panelized portions; and the first and second wedge portions are disposed between corresponding tapered sections of the first and second panelized portions. 25. The aircraft of claim 24, wherein the lower fuselage portion narrows from the upper fuselage portion toward a bottom section of the lower fuselage portion. 26. The aircraft of claim 24, wherein the lower fuselage portion comprises a bottom section that is substantially flattened relative to a circular cross-section to provide added rotational clearance for take-off and landing and less wetted surface area. 27. The aircraft of claim 26, further comprising a unitized cargo floor integrated into the substantially flattened bottom section of the lower fuselage portion. 28. The aircraft of claim 24, wherein the upper fuselage portion and the lower fuselage portion are integrally formed as one unitary fuselage piece. 29. The aircraft of claim 24, wherein the upper fuselage portion and the lower fuselage portion each comprise a composite sandwich structure. 30. A method for making a fuselage structure, comprising: forming an upper fuselage portion including a non-circular cross-section defined by a first set of varying radii of curvature; and forming a lower fuselage portion including a non-circular cross-section defined by a second set of varying radii of curvature, wherein the first set of varying radii is different from the second set of varying radii; forming an integrated keel beam in the lower fuselage portion; wherein forming the integrated keel beam comprises: forming an outer layer of material; forming a core structure disposed on the outer layer; forming an inner layer of material formed on the core structure; wherein forming the core structure comprises: forming a first panelized portion of a plurality of stacked tapering layers extending from the inner layer toward the outer layer; forming a second panelized portion of a plurality of stacked tapering layers extending from the outer layer toward the inner layer; forming a first core member having a first wedge portion on a first side of the first and second panelized portions; forming a second core member having a second wedge portion on a second side of the first and second panelized portions; and forming the first and second wedge portions disposed between corresponding tapered sections of the first and second panelized portions. 31. The method of claim 30, further comprising joining the upper fuselage portion to the lower fuselage portion. 32. The method of claim 30, further comprising integrally forming the upper fuselage portion and the lower fuselage portion as one unitary fuselage piece. 33. The method of claim 30, wherein forming the upper fuselage portion and the lower fuselage portion comprises: forming an outer layer of material; depositing a core structure on the outer layer of material; and forming an inner layer of material on the core structure. 34. The method of claim 30, wherein forming the upper fuselage portion comprises forming a hybrid structure. 35. The method of claim 34, wherein forming the hybrid structure comprises: forming a solid laminate structure in an upper section of the upper fuselage portion; forming a sandwich core type structure in a lower section of the upper fuselage portion; and transitioning between the solid laminate structure and the sandwich core structure. 36. The method of claim 30, wherein forming the lower fuselage portion comprises forming a bottom section that is substantially flattened relative to a circular cross-section to provide added rotational clearance for take-off and landing. 37. The method of claim 36, further comprising forming a unitized cargo floor integrated into the substantially flattened bottom section of the lower fuselage portion.
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