|Publication number||US3386128 A|
|Publication date||Jun 4, 1968|
|Filing date||Sep 26, 1966|
|Priority date||Sep 26, 1966|
|Publication number||US 3386128 A, US 3386128A, US-A-3386128, US3386128 A, US3386128A|
|Inventors||Vyvyan Wesley W|
|Original Assignee||Ryan Aeronautical Co|
|Export Citation||BiBTeX, EndNote, RefMan|
|Patent Citations (1), Referenced by (63), Classifications (9)|
|External Links: USPTO, USPTO Assignment, Espacenet|
June 4, 1968 w. w. VYVYAN 3,386,128
SELF-ACTUATING, SELF-LOCKING HINGE Filed Sept. 26, 1966 I 2 Sheets-Sheet 1 [N VENTOR.
WESLEY W. VYVYAN BY maww June 4, 1968 w. w. VYVYAN 3,386,128
SELF-ACTUATING, SELF-LOCKING HINGE Filed Sept. 26, 1966 2 Sheets-Sheet 2 INVENTOR. WESLEY W. VYVYAN United States Patent 3,386,128 SELF-ACTUATING, SELF-LOCKING HINGE Wesley W. Vyvyan, San Diego, Calif., assignor to The Ryan Aeronautical Co., San Diego, Calif. Filed Sept. 26, 1966, Ser. No. 581,862 4 Claims. (Cl. 16-150) The present invention relates to hinges and specifically to a self-actuating, self-locking hinge.
Various types of self-opening hinges have been developed, usually involving a conventional pin centered hinge with a spring device attached to spread, or at least assist in spreading the hinge. To hold the hinge in a specific open position some type of stop or locking mechanism must be incorporated. This type of hinge is subject to binding or jamming to the extent that the spring cannot open the hinge properly, particularly after prolonged storage or non-use, or under adverse environmental conditions.
The hinge described hercin has no pivotal parts to bind and requires no limiting stops. Instead, a plurality of resilient strap-like elements interconnect the members to be hinged, each resilient element being pre-formed to be substantially rigid in its normal extend position, yet being easily folded by making a slight intentional deformation. The collective resilient elements are attached to the hinged members in spaced parallel relation to interfit in a compact arrangement when folded in either direction and to form an extremely rigid open box type connecting structure resistant to compression and bending loads when extended.
The hinge and its operation are illustrated in the drawings, in which:
FIGURE 1 is a perspective view of the basic hinge structure in open or extended position;
FIGURE 2 is a perspective view of the hinge fully folded;
FIGURE 3 is a side elevation view of the extended hinge;
FIGURE 4 is a side elevation view showing the initial deformation of the hinge elements for folding;
FIGURE 5 is a side elevation view of the fully folded hinge;
FIGURE 6 is a sectional view taken on line 6-6 of FIGURE 3;
FIGURE 7 is a sectional view similar to FIGURE 6, but showing the hinge elements reversed; and
FIGURE 8 is a sectional view of a multiple element hinge for large members.
Similar characters of reference indicate similar or identical elements and portions throughout the specification and throughout the views of the drawing.
The two structural members 10 and 12 to be hinged together are shown, for purposes of illustration, as simple rectangular bar or beam members, but could be panels, doors, or other unitary or built up members. The only requirement is that the members have suflicient thickness, or at least end portions of sufficient thickness, to space the hinge elements far enough apart for rigidity, as hereinafter described.
Each hinge element 14 is an elongated, straplike element having a bowed or cambered cross section and being made from metal, plastic, or composite material with sufficient resiliency to return to its normal shape when deformed. At least one hinge element 14 is attached to each side of the members 12 and 14, the preferred minimum being two on one side and one on the other in a triangular arrangement when viewed in section, as in FIGURE 6. This provides torsional rigidity and maintains alignment of the two connected members. The hinge elements 14 are staggered on opposite sides and spaced in parallel relation so that the hinge element from one side can pass alongside or between those on the other side without contact. The ends of the hinge elements are secured to members It) and 12 by screws 16, or any other suitable means depending on the material and structure of the members.
It should be noted that the members 10 and 12 are spaced apart at a distance slightly more than the combined thickness of the confronting ends 18 and 20, the hinge elements 14 bridging the gap and forming a boxlike open frame structure. As illustrated in FIGURES l to 6, the hinge elements are secured with their convex faces 22 against the members.
However, the hinge elements can also be secured with their concave faces 24 toward the members, as in FIG- URE 7, with small filler blocks 26 inserted to prevent flattening of the elements by their attachment screws. Each hinge element has inherent stiffness due to its bowed or cambered cross section and will resist bending in either direction, although more so when bent toward the convex side than to the concave side. Thus the box-like frame arrangement joining the two structural members, with corresponding sides of the hinge elements facing each other, will have considerable resistance to bending and will maintain a rigid coupling.
To fold the hinge it is only necessary to deform the hinge element on one side by flattening the central portion 28 and pressing the element inwardly between the members 10 and 12, as in FIGURE 4. By so collapsing one side of the box frame structure the hinge elements on the other side can be bent back with a minimum of effort. Continuing the folding action will cause the deformed hinge element to bow inwardly and pass between the hinge elements on the other side, the latter being stretched across the ends 18 and 20. In the fully folded position the members 10 and 12 are in closely spaced parallel relation, with just sufficient space therebetween for the now return folded hinge element whose looped portion 30 projects beyond the ends of the members. It will now be evident why the members 10 and 12 must be spaced apart in the extended position as mentioned above. The spacing is sufiicient to allow the bridging portions 32 of the hinge elements now on the outside of the hinge to extend across the combined thickness of ends 18 and 20 and leave space between the members for the return folded hinge element.
In the folded position the members can be restrained by any suitable means, according to the nature of the structure. When released, the natural resiliency of the hinge element 14 will snap the assembly to the extended, rigid position without any assistance.
For wide members or panels, any required number of hinge elements may be used, the elements being staggered in spaced relation on opposite sides of the members, as indicated on the member 34 in FIGURE 8. Regardless of the number of elements used the hinge will fold in either direction.
The light weight and simplicity of the hinge structure make it ideal for use on spacecraft for such operations as extending solar cell panels, antennas, booms and the like. In addition, the self-actuating feature eliminates the need for special drive or operating mechanisms and greatly increases the reliability of operation. Many other uses will be apparent, such as for folding doors, screens, or the like.
It is understood that minor variation from the form of the invention disclosed herein may be made without departure from the spirit and scope of the invention, and that the specification and drawings are to be considered as merely illustrative rather than limiting.
1. A self-actuating, self-locking hinge for interconnecting a pair of adjacent members, the confronting edge portions of which have a certain thickness, the hinge comprising:
a plurality of elongated, strap-like hinge elements of resilient material each having a cambered cross section;
the ends of said hinge elements being secured to the pair of members with the confronting edges of the members spaced apart and the hinge elements bridging the gap therebetween in substantially parallel relation;
said hinge elements being secured to both sides of the members and thus spaced apart by the thickness of the members to form a box-like open frame structure connecting the members.
2. The structure according to claim 1, wherein said hinge elements are staggered on opposite sides of the 4 members and spaced apart so that the hinge elements on one side, when folded, can pass alongside and between the hinge elements on the other side.
3. The structure according to claim 1, wherein said hinge elements all have the correspondingly curved faces thereof disposed toward the members.
4. The structure according to claim 1, wherein the confronting edges of the members are spaced apart a distance slightly greater than the combined thickness of the confronting edges.
References Cited UNITED STATES PATENTS 2,526,129 10/1950 Groesbeck et a1. 16-150 BOBBY R. GAY, Primary Examiner.
|Cited Patent||Filing date||Publication date||Applicant||Title|
|US2526129 *||Oct 31, 1947||Oct 17, 1950||Savage Arms Corp||Flexible hinge|
|Citing Patent||Filing date||Publication date||Applicant||Title|
|US3474488 *||Aug 24, 1967||Oct 28, 1969||Bendix Corp||Foldable and compressible self-erecting devices|
|US3670358 *||Apr 29, 1970||Jun 20, 1972||Hughes Aircraft Co||Self actuating self locking flexible hinge|
|US3701295 *||Feb 2, 1971||Oct 31, 1972||Nakamura Seisakkusho Kk||Torque wrench|
|US4163303 *||Oct 4, 1977||Aug 7, 1979||G. D. Hanna Incorporated||Hinge structure|
|US5086541 *||Jul 31, 1989||Feb 11, 1992||Aerospatiale Societe Nationale Industrielle||Self-motorized antifriction joint and an articulated assembly, such as a satellite solar panel, equipped with such joints|
|US6334235 *||Nov 18, 1997||Jan 1, 2002||Metravib, R.D.S.||Self-driving, self-locking and damping hinge strap, and a hinge fitted with such straps|
|US6910304||Sep 3, 2002||Jun 28, 2005||Foster-Miller, Inc.||Stiffener reinforced foldable member|
|US7093804||Mar 25, 2004||Aug 22, 2006||Eads Space Transportation Sa||Foldable and deployable assembly of elements mounted on board a spacecraft|
|US7435032||Aug 8, 2006||Oct 14, 2008||The United States Of America As Represented By The Secretary Of The Air Force||Resilient joint for deployable structures|
|US7513461||Oct 17, 2003||Apr 7, 2009||Thales||Articulated assembly of solar generator panels and space vehicle|
|US8070006 *||Apr 26, 2006||Dec 6, 2011||Evergreen Innovation Partners I, Lp||Deployable and disposable container assemblies with bendable support members|
|US8074324 *||Jul 15, 2004||Dec 13, 2011||Foster-Miller, Inc.||Flexible, deployment rate damped hinge|
|US8151414 *||Jun 20, 2007||Apr 10, 2012||Thales||Self-driven articulation for an articulated assembly such as a satellite solar panel|
|US8303663||Jul 22, 2010||Nov 6, 2012||Spinex Tec, Llc||Methods and apparatuses for vertebral body distraction and fusion employing a coaxial screw gear sleeve mechanism|
|US8523944||Dec 31, 2009||Sep 3, 2013||Spinex Tec, Llc||Methods and apparatus for vertebral body distraction and fusion employing flexure members|
|US8540452||Dec 31, 2009||Sep 24, 2013||Spinex Tec, Llc||Flexible joint arrangement incorporating flexure members|
|US8556100||Mar 31, 2011||Oct 15, 2013||Evergreen Innovation Partners LLP||Deployable and disposable container assemblies with bendable support members|
|US8628577||Mar 19, 2009||Jan 14, 2014||Ex Technology, Llc||Stable device for intervertebral distraction and fusion|
|US8636746||Jul 22, 2011||Jan 28, 2014||Spinex Tec, Llc||Methods and apparatus for insertion of vertebral body distraction and fusion devices|
|US8771360||Aug 22, 2012||Jul 8, 2014||Spinex Tec, Llc||Methods and apparatuses for vertebral body distraction and fusion employing a coaxial screw gear sleeve mechanism|
|US8906100||May 10, 2013||Dec 9, 2014||Ex Technology, Llc||Methods and apparatus for vertebral body distraction and fusion employing flexure members|
|US8932302||Oct 26, 2012||Jan 13, 2015||Spinex Tec, Llc||Methods and apparatus for insertion of vertebral body distraction and fusion devices|
|US8940049||Apr 1, 2014||Jan 27, 2015||Ex Technology, Llc||Expandable intervertebral cage|
|US8959719 *||Jun 21, 2013||Feb 24, 2015||First Dome Corporation||Dual-shaft synchronous movement device|
|US9358125||Jul 22, 2010||Jun 7, 2016||Spinex Tec, Llc||Coaxial screw gear sleeve mechanism|
|US9381092||Sep 12, 2013||Jul 5, 2016||Ex Technology, Llc||Flexible joint arrangement incorporating flexure members|
|US9445917||Dec 8, 2014||Sep 20, 2016||Ex Technology, Llc||Methods and apparatus for expandable medical device employing flexure members|
|US9469474||Sep 30, 2013||Oct 18, 2016||Evergreen Innovation Partners I, Lp||Deployable and disposable container assemblies with bendable support members|
|US9474626||Jun 27, 2014||Oct 25, 2016||Spinex Tec Llc||Methods and apparatuses for vertebral body distraction and fusion employing a coaxial screw gear sleeve mechanism|
|US9486328||Dec 30, 2014||Nov 8, 2016||Ex Technology, Llc||Expandable intervertebral cage|
|US9498270||Jan 8, 2015||Nov 22, 2016||SpineX Tee, LLC||Methods and apparatus for insertion of vertebral body distraction and fusion devices|
|US9668879||May 25, 2016||Jun 6, 2017||Ex Technology, Llc||Expandable intervertebral cage|
|US9714519 *||Sep 23, 2009||Jul 25, 2017||Astrium Limited||Extendable structure|
|US20020056248 *||Jan 11, 2002||May 16, 2002||Foster-Miller, Inc.||Foldable member|
|US20030019180 *||Jul 2, 2002||Jan 30, 2003||Warren Peter A.||Foldable member|
|US20040245402 *||Mar 25, 2004||Dec 9, 2004||Eads Space Transportation Sa||Foldable and deployable assembly of elements mounted on board a spacecraft|
|US20050022465 *||Jul 15, 2004||Feb 3, 2005||Warren Peter A.||Flexible, deployment rate damped hinge|
|US20060049317 *||Oct 17, 2003||Mar 9, 2006||Alcatel||Articulated assembly of solar generator panels and space vehicle|
|US20070053504 *||Oct 29, 2004||Mar 8, 2007||Matsushita Electric Industrial Co., Ltd.||Connection device, electronic apparatus with the same, and folding portable terminal device|
|US20070253648 *||Apr 26, 2006||Nov 1, 2007||Evergreen Innovation Partners, Llc||Deployable and disposable container assemblies and associated systems and methods|
|US20080190949 *||Feb 12, 2007||Aug 14, 2008||Aaron Charles Rosso||Magnetic insulator pad for container|
|US20090184207 *||Jan 22, 2008||Jul 23, 2009||Warren Peter A||Synchronously self deploying boom|
|US20090282646 *||Jun 20, 2007||Nov 19, 2009||Thales||Self-driven articulation for an articulated assembly such as a satellite solar panel|
|US20100163684 *||May 24, 2007||Jul 1, 2010||Qinetiq Limited||Self opening hinges|
|US20100185291 *||Dec 31, 2009||Jul 22, 2010||Jimenez Omar F||Methods and apparatus for vertebral body distraction and fusion employing flexure members|
|US20100209184 *||Dec 31, 2009||Aug 19, 2010||Jimenez Omar F||Flexible joint arrangement incorporating flexure members|
|US20100319270 *||Sep 23, 2009||Dec 23, 2010||Astrium Limited||Extendable structure|
|US20110138948 *||Jul 22, 2010||Jun 16, 2011||Jimenez Omar F||Coaxial screw gear sleeve mechanism|
|US20110160861 *||Jul 22, 2010||Jun 30, 2011||Jimenez Omar F|
|US20140373654 *||Jun 21, 2013||Dec 25, 2014||First Dome Corporation||Dual-shaft synchronous movement device|
|US20150083642 *||Sep 23, 2014||Mar 26, 2015||Glamglow Inc.||Container with an exterior reversible strip and method for making the same|
|US20170185104 *||Dec 24, 2015||Jun 29, 2017||Intel Corporation||Orbiting Hinge|
|DE102007026452A1||Jun 5, 2007||Dec 11, 2008||Hts - Hoch Technologie Systeme Gmbh||Selbst verriegelnde Gelenkvorrichtung|
|DE102007026452B4 *||Jun 5, 2007||Sep 9, 2010||Hts - Hoch Technologie Systeme Gmbh||Selbst verriegelnde Gelenkvorrichtung|
|DE102007026452B8 *||Jun 5, 2007||Dec 16, 2010||Hts - Hoch Technologie Systeme Gmbh||Selbst verriegelnde Gelenkvorrichtung|
|EP0354837A1||Aug 7, 1989||Feb 14, 1990||AEROSPATIALE Société Nationale Industrielle||Frictionless self-erecting joint and articulated assembly, e.g. a solar panel for a satellite provided with said joints|
|EP1415909A1 *||Oct 17, 2003||May 6, 2004||Alcatel Alsthom Compagnie Generale D'electricite||Articulated solar generator panel assembly and spacecraft|
|EP1468912A1||Mar 15, 2004||Oct 20, 2004||EADS SPACE Transportation SA||Variable geometry structure for a device on board of a spacecraft|
|EP2000407A2||May 29, 2008||Dec 10, 2008||HTS Hochtechnologie Systeme GmbH||Self-locking hinge device|
|EP2000407A3 *||May 29, 2008||Nov 13, 2013||HTS Hochtechnologie Systeme GmbH||Self-locking hinge device|
|WO1998022343A1 *||Nov 18, 1997||May 28, 1998||Metravib R.D.S.||Automotive, self-locking and damping articulated joint and articulation equipped with same|
|WO2004039673A1 *||Oct 17, 2003||May 13, 2004||Alcatel||Articulated assembly of solar generator panels and space vehicle|
|WO2007141478A1 *||May 24, 2007||Dec 13, 2007||Qinetiq Limited||A self opening hinges|
|International Classification||E05D1/00, E05D1/02, E05F1/12, E05F1/00|
|Cooperative Classification||E05D1/00, E05F1/1284, E05D1/02|