This invention relates generally to modular structural systems and, more specifically, to a Tubular Framing System and Method.
As discussed herein, tubular framing systems are components that can be used to create structures by interconnecting tubular members. Steel and aluminum tubular framing systems are well-known, and have been practiced for decades. In recent years, the use of light-weight composite materials has become very popular. Carbon fiber has very desirable strength and weight characteristics that allow it to be substituted for metal components whenever feasibly possible. This has become particularly valuable in the aircraft industry because reducing aircraft weight allows the aircraft to carry more onboard fuel, while also reducing fuel consumption because there is less weight to keep aloft.
Unlike the prior metal tubular structures, however, carbon fiber has serious restrictions. First, carbon fiber tubes cannot be welded to one another in order to create structures. Since the carbon fiber tubing is essentially a high-strength fiberglass, they can only be attached to one another by adhesive or by mechanical connection (or some combination of the two). One problem with adhesive bonded joints is that each glued joint will exhibit an unknown strength, since there are many variables involved in achieving a glued connection. The only way to be sure is to strength test each and every joint once they are glued. This quality assurance testing can only really be done in the facility in which the joint was glued, and not out in the field.
Another problem with the adhesive approach is that the glue and the carbon fiber tubes will expand and contract at different rates in response to temperature fluctuations (which are common in the aviation environment). This difference in temperature sensitivity will ultimately result in a breakdown of the glued joints over time, thereby making these glued joints weak (and therefore unacceptable in many applications).
A final problem with glued joints is that the glue joint is permanent. There is not opportunity to disassemble the glued joints once they are bonded. Any adjustment or modification to the tubular structure is therefore not possible.
To date, a strictly mechanical system for interconnecting carbon fiber tubes (and panels) in order to form structures (e.g. shelf units, storage units, and many others) that exhibit the strength and weight-reducing benefits of the composite materials, while also providing the ability to create, assemble and disassemble the structures “in the field” has not been created.
In light of the aforementioned problems associated with the prior systems and methods, it is an object of the present invention to provide a Tubular Framing System and Method. The system and method should enable users to create structures from tube stock, such as carbon fiber or other composites without the need for a specialized workspace or customized tooling. The system should allow the user to create joints, attachment points and mounting points for tubular and sheet composite material. When assembled, the joints between tubular segments and the attached termination fittings should provide unparalleled tensile strength without the need for adhesives or special testing for verification. The system should include base assemblies, mid-span bracket and mounting assemblies and a wide range of versatile connectors that can provide the user with the flexibility to easily and rapidly create a wide variety of structures from strong and lightweight composite tube stock and aircraft-grade aluminum connectors.
The objects and features of the present invention, which are believed to be novel, are set forth with particularity in the appended claims. The present invention, both as to its organization and manner of operation, together with further objects and advantages, may best be understood by reference to the following description, taken in connection with the accompanying drawings, of which:
The following description is provided to enable any person skilled in the art to make and use the invention and sets forth the best modes contemplated by the inventor of carrying out his invention. Various modifications, however, will remain readily apparent to those skilled in the art, since the generic principles of the present invention have been defined herein specifically to provide a Tubular Framing System and Method.
The system of the present invention is a collection of fittings, components and fasteners that are intended to be used to fasten segments of tubular material to one another in order to create a wide variety of structures. While the system will work with tubing material of virtually any type, it is intended to be used with composite (e.g. carbon fiber) material because of the substantial weight and strength benefits provided by that particular material. The user is able to fabricate these structures using the system of the present invention without the need for specialty tools or a specialized workspace. It is simply a matter of cutting the tubing into segments of the desired length, cutting a few holes in the walls of the tubing through which fasteners will attach the tubing to the fittings/components/assemblies of the instant system, and then assembling the joints between the tubing segments from a selection of the fittings, components and fasteners of the instant system. We will now proceed through a description of the most common components that make up the system of the present invention.
The present invention can best be understood by initial consideration of
The basic element of the end assembly 10 is the main block 12. The main block 12, and virtually all of the other components in the system, is made from aircraft grade aluminum (e.g. 6061-T6). The components are typically sized to interface with 1-inch, 1.5-inch or 2-inch (inner diameter) carbon fiber tubing, but other sizes would be available under this system, if desired. Two or more main sleeve adapters 14 are attached to the main block 12 by a plurality of adapter mounting bolts 22. These bolts 22 and the others discussed herein below preferably are extremely strong—on the order of 170,000 pounds per square inch tensile strength.
The main sleeve adapters 14 are selected by diameter so that they will fit snugly within the inner diameter of a segment of tubing. There is a central bore 13 through the adapters 14 along its longitudinal axis, as well as a plurality of tube mounting bores 16 (typically smooth-walled—without threads) running around the periphery of the central bore 13. In this version, there are supplemental bores 18 in between each mounting bore 16. The supplemental bores 18 simply reduce the weight of the sleeves 14 while still providing sufficient rigidity and strength to support the fabrication of structures.
The peripheral face 15 of the sleeves 14 have two or more tube mounting bores 20 formed through them (actually there are typically a pair of bores 20 on opposing sides of the peripheral face 15). These bores 20 are threaded in order to engage tube mounting bolts [26] as depicted in
The corner bracket element 44 is named as such because it is not straight, but rather has a pair of “arms” that extend at 90 degrees from one another. The top face 50 of the element 44 has a pair of accessory mounting bores 52 formed through it and through the entire element 44. These bores 52 are typically smooth-walled, and provide an attachment point for other elements in the system. There are panel mounting bores 60 formed through each end face 58 to provide an attachment point for panels (ideally made of carbon fiber). These are preferably threaded in order to accept mounting bolts very similar to the tube mounting points [26] discussed above.
The bracket element 44 is attached to the outside of a tube segment by mounting bolts (not shown) passing through mounting bores 56 formed in the side faces 54 of the element 44, then through apertures formed in the tubing segment, and threadedly engaging bracket mounting bores 46 formed in the inner base ring 42.
Three tube segments 24 have been interconnected to one another by end assembly 10, so that the tube segments 24 extend at 90 degree angles from one another. Sidewall bracket assemblies 40 are attached to the segments 24 in appropriate locations along the length of the segments 24 such that the end faces [58] face outwardly. Panel members 62 are attached to the panel mounting bores [60] by mounting bolts 64 that pass through apertures formed in the panels 62 for this purpose (presumably by the user/assembler).
A straight bracket element 66 bolts onto the outside of the tube segment [24] by mounting bolts [22] (typically shorter in length) that pass through the mounting bores 56 formed in the end face 72 and apertures formed in the tube segment [24] and then threadedly engaging a bracket mounting bore [46].
The straight bracket assembly 66 has a pair of (typically smooth-walled, unthreaded) accessory mounting bores 52 formed through the top face 68 (through to the bottom face) of the element 66.
The sleeve adapter 74 has a longitudinal bore 76 formed along its length (a through-hole). Bracket mounting bores 84 (threaded) are formed in the outer face 78 of the adapter 74. Additionally, there are smooth-walled, somewhat larger transverse bores 82 that cross each other at the midpoint of the adapter 74.
The second tube segment 24 has an end bracket 94 attached to it. In this particular arrangement, one of the straight bracket elements 66 (the one on the left) has threads on its accessory mounting bores [52] so that mounting bolts can threadedly attach to them. As should be apparent, the tab portion [98] can be placed between the two straight bracket elements, and then the mounting bolts 22 inserted and tightened down to the (left) straight bracket element 66. This provides a secure attachment between the two tube segments [24], that is also easily disassembled when desired.
The assembly 100 comprises an assembly bolt 108 that holds the assembly together. The bolt 108 passes through a first axle element 110A, a spacer element 112, and then threadedly engages a second axle element 110B. Turning the handle 114 will cause the assembly bolt 108 to turn, and thereby either tighten or loosen axle elements 110A, 110B (i.e. the squeezing force against the spacer element 112). When the bolt 108 is loosened, the axles 110A, 110B are free to rotate around the bolt 108 so that their relative angles can be changed (and then the bolt 108 can be re-tightened).
Those skilled in the art will appreciate that various adaptations and modifications of the just-described preferred embodiment can be configured without departing from the scope and spirit of the invention. Therefore, it is to be understood that, within the scope of the appended claims, the invention may be practiced other than as specifically described herein.
This application is filed within one year of, and claims priority to Provisional Application Ser. No. 62/173,306, filed Jun. 9, 2015.
Number | Name | Date | Kind |
---|---|---|---|
553525 | Hankin | Jan 1896 | A |
2926941 | Thompson | Mar 1960 | A |
3263692 | Questi | Aug 1966 | A |
3513610 | Devonport | May 1970 | A |
3787134 | Burr | Jan 1974 | A |
4045104 | Peterson | Aug 1977 | A |
4093167 | Rooklyn | Jun 1978 | A |
4116573 | Fuchs | Sep 1978 | A |
4124317 | Dauth | Nov 1978 | A |
4235559 | Rooklyn | Nov 1980 | A |
4505609 | Vella | Mar 1985 | A |
4630550 | Weitzman | Dec 1986 | A |
4766712 | Hale | Aug 1988 | A |
4900184 | Cleveland | Feb 1990 | A |
4923322 | Burg | May 1990 | A |
5046882 | Ju | Sep 1991 | A |
5353892 | Lu | Oct 1994 | A |
5383723 | Meyer | Jan 1995 | A |
5457929 | Kim | Oct 1995 | A |
5481842 | Gautreau | Jan 1996 | A |
5536097 | Hazan | Jul 1996 | A |
5556218 | Homer | Sep 1996 | A |
5620272 | Sheng | Apr 1997 | A |
5640811 | Boyle | Jun 1997 | A |
5661942 | Palmer | Sep 1997 | A |
5888015 | Brown | Mar 1999 | A |
6219989 | Tumura | Apr 2001 | B1 |
6247869 | Lichvar | Jun 2001 | B1 |
6277069 | Gray | Aug 2001 | B1 |
6447201 | McCracken | Sep 2002 | B1 |
6503020 | Mascioletti | Jan 2003 | B1 |
7682099 | Cole | Mar 2010 | B2 |
8511033 | Kumakawa | Aug 2013 | B2 |
9126613 | Savage | Sep 2015 | B2 |
9458874 | Sim | Oct 2016 | B2 |
D805883 | Evitt | Dec 2017 | S |
D805884 | Evitt | Dec 2017 | S |
9868008 | Todokoro | Jan 2018 | B2 |
9993677 | Todokoro | Jun 2018 | B2 |
20020090256 | Chin | Jul 2002 | A1 |
20040226249 | Wang | Nov 2004 | A1 |
20050008430 | Kahl | Jan 2005 | A1 |
20050036829 | Trull | Feb 2005 | A1 |
20050265778 | Tzeng | Dec 2005 | A1 |
20060138066 | Hung | Jun 2006 | A1 |
20070209314 | Vaughn | Sep 2007 | A1 |
20070245677 | Nguyen | Oct 2007 | A1 |
20070261356 | Vaughn | Nov 2007 | A1 |
20090194991 | Yang | Aug 2009 | A1 |
20110036798 | Chen | Feb 2011 | A1 |
20110194892 | Huang | Aug 2011 | A1 |
20120009013 | Evitt | Jan 2012 | A1 |
20120013236 | Fan | Jan 2012 | A1 |
20120301215 | Huang | Nov 2012 | A1 |
20130036702 | Pacetti | Feb 2013 | A1 |
20130156495 | Li | Jun 2013 | A1 |
20130294817 | Augustsson | Nov 2013 | A1 |
20130306808 | Huang | Nov 2013 | A1 |
20140294500 | Schaaf | Oct 2014 | A1 |
20150167713 | Schaerer | Jun 2015 | A1 |
20150267735 | Bacon | Sep 2015 | A1 |
20150377414 | Pirseyedi | Dec 2015 | A1 |
20160250509 | Todokoro | Sep 2016 | A1 |
20160363153 | Lakoduk | Dec 2016 | A1 |
20170020282 | Bensen | Jan 2017 | A1 |
20170030390 | Su | Feb 2017 | A1 |
20170145708 | Chen | May 2017 | A1 |
20170233995 | Abernathy | Aug 2017 | A1 |
20170233996 | Abernathy | Aug 2017 | A1 |
20170261022 | Schirmer | Sep 2017 | A1 |
20170295956 | Lin | Oct 2017 | A1 |
20170356178 | Corbett | Dec 2017 | A1 |
20180058625 | McPhillips | Mar 2018 | A1 |
20180064245 | Huang | Mar 2018 | A1 |
20180066688 | Koepke | Mar 2018 | A1 |
20180251265 | Egertz | Sep 2018 | A1 |
Number | Date | Country | |
---|---|---|---|
20170356178 A1 | Dec 2017 | US |
Number | Date | Country | |
---|---|---|---|
62173306 | Jun 2015 | US |