[특허]Self-locking joints for panel structures and methods of fabricating the same

The Boeing Company

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특허 상세정보

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Self-locking joints for panel structures and methods of fabricating the same

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F16B-012/26
미국특허분류(USC)	403/252; 403/381
출원번호	US-0605991 (2012-09-06)
등록번호	US-8961059 (2015-02-24)
발명자 / 주소	Reeves, Brad J. Gooch, Paul L.
출원인 / 주소	The Boeing Company
인용정보	피인용 횟수 : 5 인용 특허 : 10

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A method of fabricating a self-locking joint in a panel structure. The method provides a panel structure having at least two face sheets and a core portion sandwiched therebetween. The method further fabricates in a first portion of the panel structure at least one mortice opening having self-locking end portions. The method further fabricates on a second portion of the panel structure at least one tenon extension having flexible self-locking members. The method further interlocks the flexible self-locking members of the at least one tenon extension with...

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1. A method of fabricating a self-locking joint in a single composite panel structure, the method comprising: providing a single composite panel structure comprising at least two composite face sheets and a core portion sandwiched therebetween;fabricating in protruding portions along a first portion of peripheral sides of the single composite panel structure at least one mortise opening having self-locking end portions, each self-locking end portion comprising a tip portion and an angled portion on each side of the tip portion;fabricating on a second portion of peripheral sides of the single composite panel structure at least one tenon extension having flexible self-locking members with lip portions and engaging portions, the at least one tenon extension having a size and a length that is greater than a size and a length of the at least one mortise opening, each lip portion located at a top portion of the at least one tenon extension and having a tapered side tapering downwardly and inwardly from the lip portion to a base portion of the at least one tenon extension, and each engaging portion being substantially straight and parallel to the second portion of peripheral sides; and,interlocking the flexible self-locking members of the at least one tenon extension with the self-locking end portions of the at least one mortise opening to form a self-locking joint in the single composite panel structure, wherein when the at least one tenon extension is inserted into the at least one mortise opening, the flexible self-locking members deform, and once the flexible self-locking members interlock with the respective self-locking end portions of the mortise opening to form the self-locking joint, the flexible self-locking members expand back to their original positions. 2. The method of claim 1 wherein providing the single composite panel structure further comprises providing the single composite panel structure comprising a honeycomb core composite sandwich panel. 3. The method of claim 1 wherein fabricating in protruding portions along the first portion of peripheral sides of the single composite panel structure further comprises fabricating at least one mortise opening comprising a mortise pocket or a mortise slot. 4. The method of claim 1 wherein fabricating on the second portion of peripheral sides of the single composite panel structure further comprises fabricating at least one tenon extension comprising a tenon tab formed on the second portion of peripheral sides of the single composite panel structure through the two composite face sheets and through the core portion. 5. The method of claim 1 wherein fabricating on the second portion of peripheral sides of the single composite panel structure further comprises fabricating at least one tenon extension comprising a tenon blade formed on the second portion of peripheral sides of the single composite panel structure through only the two composite face sheets. 6. The method of claim 1 wherein fabricating on the second portion of peripheral sides of the single composite panel structure further comprises fabricating at least one tenon extension having tapered sides adapted for insertion into the at least one mortise opening and wherein the at least one mortise opening has a length at its most distant points across that is less than a length of the at least one tenon extension at its most distant points across, such that the flexible self-locking members interlock with the self-locking end portions in a manner to prevent withdrawal of the at least one tenon extension from the at least one mortise opening. 7. The method of claim 1 wherein fabricating of the at least one mortise opening and the at least one tenon extension comprises using a computerized numerically controlled (CNC) apparatus and a cutting apparatus to cut the at least one mortise opening in the protruding portions along the first portion of peripheral sides of the single composite panel structure and to cut the at least one tenon extension on the second portion of peripheral sides of the single composite panel structure. 8. The method of claim 1 wherein forming the self-locking joint in the single composite panel structure secures the first portion of peripheral sides of the single composite panel structure to the second portion of peripheral sides of the single composite panel structure without use of any additional fixtures, fasteners, adhesive tape, or clamp devices. 9. The method of claim 1 further comprising integrally forming the single composite panel structure with the self-locking joint in an aircraft interior structure. 10. A method for joining two or more honeycomb core composite sandwich panels together, the method comprising: providing a first honeycomb core composite sandwich panel comprising at least two first composite face sheets and a first honeycomb core sandwiched therebetween;fabricating in protruding portions along a first portion of peripheral sides of the first honeycomb core composite sandwich panel at least one mortise opening having self-locking end portions, each self-locking end portion comprising a tip portion and an angled portion on each side of the tip portion;providing a second honeycomb core composite sandwich panel comprising at least two second composite face sheets and a second honeycomb core sandwiched therebetween;fabricating on a second portion of peripheral sides of the second honeycomb core composite sandwich panel at least one tenon extension having flexible self-locking members with lip portions and engaging portions, the at least one tenon extension having a size and a length that is greater than a size and a length of the at least one mortise opening, each lip portion located at a top portion of the at least one tenon extension and having a tapered side tapering downwardly and inwardly from the lip portion to a base portion of the at least one tenon extension, and each engaging portion being substantially straight and parallel to the second portion of peripheral sides; and,interlocking the flexible self-locking members of the at least one tenon extension with the self-locking end portions of the at least one mortise opening to form a self-locking joint in the first honeycomb core composite sandwich panel and the second honeycomb core composite sandwich panel together, wherein when the at least one tenon extension is inserted into the at least one mortise opening, the flexible self-locking members deform, and once the flexible self-locking members interlock with the respective self-locking end portions of the mortise opening to form the self-locking joint, the flexible self-locking members expand back to their original positions. 11. The method of claim 10 wherein fabricating in the first honeycomb core composite sandwich panel further comprises fabricating at least one mortise opening comprising a mortise pocket or a mortise slot. 12. The method of claim 10 wherein fabricating on the second honeycomb core composite sandwich panel further comprises fabricating at least one tenon extension comprising a tenon tab formed on the second portion of peripheral sides of the second honeycomb core composite sandwich panel through the two second composite face sheets and through the second honeycomb core. 13. The method of claim 10 wherein fabricating on the second honeycomb core composite sandwich panel further comprises fabricating at least one tenon extension comprising a tenon blade formed on the second portion of peripheral sides of the second honeycomb core composite sandwich panel through only the two second composite face sheets. 14. The method of claim 10 wherein forming the self-locking joint joining the first honeycomb core composite sandwich panel to the second honeycomb core composite sandwich panel secures the first honeycomb core composite sandwich panel to the second honeycomb core composite sandwich panel without use of any additional fixtures, fasteners, adhesive tape, or clamp devices. 15. A self-locking joint in a single composite panel structure, the self-locking joint comprising: at least one mortise opening formed in protruding portions along a first portion of peripheral sides of the single composite panel structure comprising at least two composite face sheets and a core portion sandwiched therebetween, the at least one mortise opening having self-locking end portions, each self-locking end portion comprising a tip portion and an angled portion on each side of the tip portion; and,at least one tenon extension formed on a second portion of peripheral sides of the single composite panel structure, the at least one tenon extension having flexible self-locking members with lip portions and engaging portions, the at least one tenon extension having a size and a length that is greater than a size and a length of the at least one mortise opening, each lip portion located at a top portion of the at least one tenon extension and having a tapered side tapering downwardly and inwardly from the lip portion to a base portion of the at least one tenon extension, and each engaging portion being substantially straight and parallel to the second portion of peripheral sides,wherein the flexible self-locking members of the at least one tenon extension and the self-locking end portions of the at least one mortise opening, in combination, include interlocking elements adapted to form a self-locking joint in the single composite panel structure, wherein when the at least one tenon extension is inserted into the at least one mortise opening, the flexible self-locking members deform, and once the flexible self-locking members interlock with the respective self-locking end portions of the mortise opening to form the self-locking joint, the flexible self-locking members expand back to their original positions. 16. The self-locking joint of claim 15 wherein the single composite panel structure comprises a honeycomb core composite sandwich panel. 17. The self-locking joint of claim 15 wherein the at least one mortise opening comprises a mortise pocket or a mortise slot. 18. The self-locking joint of claim 15 wherein the at least one tenon extension comprises a tenon tab formed on the second portion of peripheral sides of the single composite panel structure through the two composite face sheets and through the core portion. 19. The self-locking joint of claim 15 wherein the at least one tenon extension comprises a tenon blade formed on the second portion of peripheral sides of the single composite panel structure through only the two composite face sheets. 20. A self-locking joint joining two or more honeycomb core composite sandwich panels together, the self-locking joint comprising: at least one mortise opening formed in protruding portions along a first portion of peripheral sides of a first honeycomb core composite sandwich panel comprising at least two composite face sheets and a first honeycomb core sandwiched therebetween, the at least one mortise opening having self-locking end portions, each self-locking end portion comprising a tip portion and an angled portion on each side of the tip portion; and,at least one tenon extension formed on a second portion of peripheral sides of a second honeycomb core composite sandwich panel comprising at least two second composite face sheets and a second honeycomb core sandwiched therebetween, the at least one tenon extension having a size and a length that is greater than a size and a length of the at least one mortise opening, the at least one tenon extension having flexible self-locking members with lip portions and engaging portions, each lip portion located at a top portion of the at least one tenon extension and having a tapered side tapering downwardly and inwardly from the lip portion to a base portion of the at least one tenon extension, and each engaging portion being substantially straight and parallel to the second portion of peripheral sides,wherein the flexible self-locking members of the at least one tenon extension and the self-locking end portions of the at least one mortise opening, in combination, include interlocking elements adapted to form a self-locking joint joining the first honeycomb core composite sandwich panel and the second honeycomb core composite sandwich panel together, wherein when the at least one tenon extension is inserted into the at least one mortise opening, the flexible self-locking members deform, and once the flexible self-locking members interlock with the respective self-locking end portions of the mortise opening to form the self-locking joint, the flexible self-locking members expand back to their original positions. 21. The self-locking joint of claim 20 wherein the at least one mortise opening comprises a mortise pocket or a mortise slot. 22. The self-locking joint of claim 20 wherein the at least one tenon extension comprises a tenon tab formed on the second honeycomb core composite sandwich panel through the two composite face sheets and through the honeycomb core. 23. The self-locking joint of claim 20 wherein the at least one tenon extension comprises a tenon blade formed on the second honeycomb core composite sandwich panel through only the two composite face sheets.

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Self-locking joints for panel structures and methods of fabricating the same

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