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Publication numberUS3913105 A
Publication typeGrant
Publication dateOct 14, 1975
Filing dateMay 23, 1973
Priority dateApr 5, 1971
Publication numberUS 3913105 A, US 3913105A, US-A-3913105, US3913105 A, US3913105A
InventorsAcker Roy M, Greenbaum Gilbert A, Phillips William J, Williamson Clyde E
Original AssigneeTrw Inc
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Collapsible self-erecting tubular frame structure and deployable electromagnetic reflector embodying same
US 3913105 A
Abstract  available in
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Claims  available in
Description  (OCR text may contain errors)

United States Patent [191 Williamson et al.

[ COLLAPSIBLE SELF-ERECTING TUBULAR FRAME STRUCTURE AND DEPLOYABLE ELECTROMAGNETIC REFLECTOR EMBODYING SAME [75] Inventors: Clyde E. Williamson; Roy M. Acker,

both of Los Angeles; Gilbert A. Greenbaum, Encino; William J. Phillips, Gardena, all of Calif.

[73] Assignee: TRW Inc., Redondo Beach, Calif.

[22] Filed: May 23, 1973 [21] Appl. No.: 363,220

Related US. Application Data [63] Continuation of Ser. No. 131,218, April 5, 1971,

abandoned.

[52] US. Cl. 343/840; 52/646; 52/108; 343/897; 343/915 [51] Int. Cl E04h 12/18 [58] Field of Search 52/108, 646; 343/840, 897, 343/915 [56] References Cited UNITED STATES PATENTS 1,545,129 7/1925 Cook 52/648 3,221,464 12/1965 Miller 52/655 3,277,479 10/1966 Struble... 3,300,910 1/1967 Isaac 3,434,254 3/1969 Rabin 3,564,789 2/1971 Vyvyan 52/108 FOREIGN PATENTS OR APPLICATIONS 282,965 8/1949 Switzerland 52/655 Primary ExaminerFrank L. Abbott Assistant Examinerl'lenry Raduazo Attorney, Agent, or FirmDaniel T. Anderson; Donald R. Nyhagen; Jerry A. Dinardo [57] ABSTRACT A collapsible self-erecting three-dimensional frame structure constructed of relatively thin-walled resiliently flexiblettubular frame members joined at their ends in a selected geometric configuration, such as a tetrahedral truss configuration, whereby the structure is collapsible, by flattening and folding the frame members, to a compact storage configuration wherein the frame members store elastic strain energy for effecting self-erection of the structure when the collapsing forces are removed. A deployable antenna reflector embodying the frame structure.

1 Claim, 7 Drawing Figures U.S. Patent Oct. 14,1975 Sheet10f2 3,913,105

:9 Clyde EWHIicnmson 'Ro M. Acker Gil art A. Greenbaum WiHiClm J. Phillips INVENTORS ATTORNEY COLLAPSIBLE SELF-ERECTING TUBULAR FRAME STRUCTURE AND DEPLOYABLE ELECTROMAGNETIC REFLECTOR EMBODYING SAlVIE This is a continuation of application Ser. No. 131,218 filed Apr. 5, 1971 now abandoned.

BACKGROUND OF THE INVENTION 1. Field of the Invention This invention relates generally to structures of the kind which are collapsible to reduced overall size for storage. More particularly, the invention relates to a three-dimensional collapsible frame structure of the class described which is self-erecting under the force of elastic strain energy stored within the collapsed structure. The invention relates also to a deployable antenna reflector embodying the frame structure.

2. Prior Art There is a continuing need for largetruss structures and the like which can be collapsedfor stowage in greatly reduced volume and subsequently deployed to envelop a volume or form planar, curved or contoured surfaces for space or terrestrial uses. Large parabolic antennas which can be contracted to a small volume for stowage in a space vehicle for launch into space orbit and then deployed are one such example. Maximum surface accuracy and minimum distortion due to mechanical loads and thermal gradients are fundamental requirements. The ultimate in design simplicity is also desired to insure deployment reliability.

Many expandable structure concepts have been proposed to fulfill these needs. Inherent disadvantages, such as inability to maintain desired accuracy in operation, unreliable deployment, design and manufacture complexities, etc., have deterred acceptance. One such concept proposed for space use, for example, is a truss reflector which exhibits good structural integrity and stability against thermal distortion, but possesses extreme mechanical complexity and hence low deployment reliability and high relative specific weight and cost. i

SUMMARY OF THE INVENTION The self-erecting collapsible structure of the present invention is constructed of a plurality of relatively slender tubular beams or frame members joined at their ends to form a unitary frame structure which normally assumes a selected geometric configuration. These frame members are hollow, relatively thin-walled, resiliently flexible sleeves or tubes which are similar to those shown in Patent Nos. 3,217,328 and 3,434,254, and may be flattened and folded to permit collapsing of the frame structure to a compact storage configuration. When thus flattened and folded, the tubular frame members store elastic strain energy which causes the members to spring back to their original shape and thereby erect the frame structure to its normal geometric configuration upon removal of the collapsing forces from the structure.

The present frame structure may assume almost an infinite variety of geometric configurations. The particular frame structure disclosed is a tetrahedral truss structure for use as a deployable antenna reflector for a spacecraft or the like. In this application, one face of the truss structure has a generally parabolic curvature and carries an electromagnetic reflective mesh which is foldable with the truss structure for storage.

BRIEF DESCRIPTION OF THE DRAWINGS In the drawings:

FIG. 1 is a perspective view of a tetrahedral truss structure according to the invention;

FIG. 2 is an enlarged fragmentary perspective view of one frame member of the truss structure;

FIG. 3 is a section through the frame member illustrating the manner in which it may be flattened for folding;

FIG. 4 is an enlarged fragmentary plan view of one joint of the truss structure;

FIG. 5 is an edge view of the joint looking in the direction of the arrow 5 in FIG. 4;

FIG. 6 is a perspective view on reduced scale of the truss structure in its collapsed configuration; and

FIG. 7 diagrammatically illustrates a preferred folding pattern of the truss structure for collapsing it to its folded configuration.

DESCRIPTION OF THE PREFERRED EMBODIMENTS The collapsible self-erecting frame structure 10 selected for illustration in the drawings is a tetrahedral truss structure for use as the supporting frame of a deployable spacecraft antenna reflector. This frame or truss structure is constructed of a plurality of relatively thin-walled resiliently flexible tubular beams or frame members 12 similar to those disclosed in the earlier mentioned patents. Frame members 12 are joined at their ends by connecting means 14 in a manner such that the structure normally assumes its expanded configuration of FIG. 1. The structure is collapsible to its conpact stowage configuration of FIG. 6 by flattening and folding the frame members as described presently.

The illustrated frame or truss structure has a tetrahedral truss frame with opposing sides 16,18 which, in this instance, are generally hexagonal in edge outline and are hereafter referred to as front and rear sides, respectively. The front frame side 16 has a generally hexagonal perimeter P comprising a number of the frame members 12 joined end to end by connecting means 14. Extending between and attached at their ends to opposing connecting means at opposite sides of the perimeter and in oblique intersecting relation to one another are a number of truss members T comprising frame members 12 joined end to end by connecting means 14 which also join the intersecting truss members to one another at their intersections.

The rear truss frame side 18 is similar to the front frame side and has a generally hexagonal perimeter P and intersecting truss members T comprising frame members 12 joined end to end by connecting means 14. Truss members T are attached at their ends to the perimeter connecting means and are attached to one another at their intersections by their connecting means. Extending between and attached at their ends to the connecting means 14 of the front and rear frame sides 16, 18 are frame members 12 providing normal and diagonal connecting struts S which join the frame sides hedral configuration. These tetrahedral frame portions are hereafter referred to as tetrahedral bays and have triangular faces in the front and rear frame sides l6, 18.

The frame members 12 of the truss structure are constructed of a resiliently flexible material, such as a heat treated plastic-like Mylar or Kapton, or metal, which is formed to the flanged tubular beam configuration illustrated in FIGS. 2 and 3. In this case, the frame members are formed in two mating flanged sections whose flanges are joined by stitching 19 to provide frame members or beams of the kind disclosed in copending application Ser. No. 130,574, filed Apr. 2, 1971, under TRW Docket No. 4891, and entitled Strain Energy Erectile Tubular Beam with Stitched Flanges. This resilient construction of the frame members permits them to be flattened, as shown in broken lines in FIG. 3, and then folded in such a way as to enable collapsing of the truss structure to its storage configuration of' FIG. 6.

A significant feature of the illustrated truss structure resides in the fact that each intersection connecting means 14 must accommodate a number of the frame members 12 which must hinge immediately adjacent the intersections. Some of the intersections, for example, such that shown in FIGS. 4 and 5, must accommodate six substantially coplanar frame members and three diagonal frame members or struts S. This is accomplished by using connecting means in the form of hexagonal plate-like fittings 28 and flattening the ends of the frame members and securing their flattened ends to the fittings with rivets 30 or the like. The diagonal struts of each intersection are attached to the underside of its connecting fitting. The flat pinched ends of the frame members permits the latter to hinge freely on hinge axes adjacent and substantially coplanar with their respective connecting fittings. This is a significant feature of the design, since the frame members possess maximum bending strength about axes normal to the planes of the connecting fittings when either flattened or fully open. Hence, the truss connecting fittings are stabilized in their normal orientation when the structure is either folded or deployed- The fold pattern for the illustrated truss structure is diagrammatically illustrated in FIG. 7 and involves folding or doubling the frame members 12 of the front and rear perimeters P P and truss members T F at their centers in inverted V fashion. The diagonal truss members or struts S are not folded, but swing laterally inward in a manner similar to closing a camera tripod. This fold pattern provides the folded truss structure (FIG. 6) with an overall diameter approximating the cumulative across flat dimensions of the individ ual hexagonal intersection fittings. In order to'further reduce packaged size, the frame members in the upper and lower surfaces may be tapered toward their ends. This reduces the intersection fittings size and also results in a truss member configuration which receives column load more efficiently, being larger in diameter at its midpoint.

As noted earlier, the illustrated truss structure is the supporting frame of a deployable electromagnetic reflector for a spacecraft antenna or the like. The RF reflective surface of the antenna is provided by a foldable wire mesh 32 (shown in fragmentary fashion) fixed to the front side 16 of the truss structure. This front side of the structure'isprovided with the desired contour, in this instance a parabolic contour, by dimensioning the connecting struts S of thetruss structure in such a way that the frame members 12 located in the plane of the. front side conform generally to, ie are tangent to, a. theoretical parabolic surface. Improved conformance of the front truss side to a parabolic surface may be ac complished in curving the frame members of the front truss frame side 16. When the reflector is folded to its storage configuration, the mesh 32 nests between the folded front frame members, as shown in FIG. 7, and does not interfer withfolding or deployment of the reflector.

An advantage of the illustrated antenna resides in the fact that its open construction achieves uniform exposure of virtually all parts of the structure to incident solar flux regardless of the orientation of the antenna relative to the sun.

I It will now be understood that the illustrated reflector is collapsible to its compact stowage configuration of FIG. 6 by flattening and folding of the frame members 12. When thus folded, the frame. members store elastic.

strain energy which causes self-erection or deployment of the reflector to itsexpanded or deployed configuration of FIG. 1 when released. I

What is claimed as new in support of Letters Patent the like comprising:

a tetrahedral truss frame constructed of thin-walled,

resilient, collapsible, strain energy erectile tubular frame members and having two spaced and gener ally parallel frame sections forming opposite sides 1 of said frame and connecting struts between and joining said frame sections;

each frame section having a perimeter comprising a number of said tubular frame members joined end to end by first connectingmeans, and truss members each comprising a number of :said tubular frame members joined end to end by second connecting means, said truss members extending between opposite sides of said perimeter in oblique intersecting relation to one another and being form with the tubular frame members of said frame sections a plurality of tetrahedral bays; each said tubular frame member having a tubular portion and coplanar dimetrically opposed flanges along opposite sides of said tubular portion and the ends of the tubular portion of each frame member being flattened into coplanar relation with its flanges; each said connecting means comprising a flat connecting plate located substantially in the plane of I the corresponding frame-section and seating the adjacent flattened frame member ends, each plate having an edge underlying the flattened end of and extending transverse to. each of the corresponding frame members, and means joining the member ends to their respective connecting plates;

the outer side of one frame section conforming generally to an arcuate surface of selected contour; such as a parabolic surface;

l. A deployable antenna reflector for spacecraft and i i and folded and said mesh being adapted to be folded with said frame members to permit collapsing of said reflector to a compact storage configuration whcrein said frame members store elastic strain energy for deploying said reflector when the collapsing force on the reflector is removed.

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US1545129 *Sep 27, 1923Jul 7, 1925Jr John F CookAircraft structure
US3221464 *Mar 17, 1961Dec 7, 1965Alvin E MillerTetrahelical structure
US3277479 *Sep 25, 1963Oct 4, 1966Jr Arthur D StrublePassive communications satellite
US3300910 *Dec 10, 1965Jan 31, 1967Peter IsaacReelable structural members
US3434254 *Oct 4, 1965Mar 25, 1969Trw IncDeployable boom
US3564789 *Dec 9, 1968Feb 23, 1971Ryan Aeronautical CoExtendable-retractable box beam
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US4277922 *Feb 1, 1980Jul 14, 1981Mcallister Jack GFrame assembly apparatus and method of making same
US4308699 *Dec 3, 1979Jan 5, 1982General Dynamics CorporationStructural strut and node for large space structures
US4475323 *Apr 30, 1982Oct 9, 1984Martin Marietta CorporationBox truss hoop
US4557097 *Sep 8, 1983Dec 10, 1985The United States Of America As Represented By The Administrator Of The National Aeronautics And Space AdministrationSequentially deployable maneuverable tetrahedral beam
US4558551 *Oct 25, 1982Dec 17, 1985Creusot-LoireSupport structure for solar collector
US4578920 *Nov 30, 1983Apr 1, 1986The United States Of America As Represented By The Secretary Of The United States National Aeronautics And Space AdministrationSynchronously deployable truss structure
US4835932 *May 13, 1988Jun 6, 1989Trw Inc.D-section structural tubes
US5228258 *Nov 12, 1991Jul 20, 1993Fuji Jukogyo Kabushiki KaishaCollapsible truss structure
US5757335 *Nov 17, 1993May 26, 1998Anutech Pty. LimitedDish antenna structures and hydraulic control of the orientation thereof
US5949594 *Dec 2, 1997Sep 7, 1999Iglseder; HeinrichProcess for the generation of information in space
US6313811Jun 11, 1999Nov 6, 2001Harris CorporationLightweight, compactly deployable support structure
US6618025Oct 25, 2001Sep 9, 2003Harris CorporationLightweight, compactly deployable support structure with telescoping members
US7155872 *Dec 5, 2002Jan 2, 2007Francom Larry ROpen frames for providing structural support and related methods
US7694465Apr 7, 2006Apr 13, 2010Alliant Techsystems Inc.Deployable structural assemblies, systems for deploying such structural assemblies and related methods
US7694486 *Dec 12, 2003Apr 13, 2010Alliant Techsystems Inc.Deployable truss having second order augmentation
US8006462Jan 6, 2010Aug 30, 2011Alliant Techsystems Inc.Deployable truss having second order augmentation
US8042305Mar 15, 2005Oct 25, 2011Alliant Techsystems Inc.Deployable structural assemblies, systems for deploying such structural assemblies
US8689514 *Mar 21, 2012Apr 8, 2014Softronics, Ltd.Expandable structure
EP0082068A1 *Dec 8, 1982Jun 22, 1983Creusot-LoireSupporting structure for a solar collector
EP0681747A1 *Nov 17, 1993Nov 15, 1995Anutech Pty. LimitedDish antenna structures and hydraulic control of the orientation thereof
EP1129260A1 *Nov 3, 1999Sep 5, 2001A.P.S. Advanced Pneumatic Structures Ltd.A collapsible structural element
WO1992022102A1 *May 22, 1992Dec 10, 1992Robert Laxton John BurdonFoldable structures
WO2004053260A2 *Dec 5, 2003Jun 24, 2004Francom LarryOpen frames for providing structural support and related methods
WO2014068538A1 *Nov 4, 2013May 8, 2014Thales Alenia Space Italia S.P.A. Con Unico SocioLarge deployable reflector for a satellite antenna
Classifications
U.S. Classification343/840, 52/108, 343/915, 343/897, 52/646
International ClassificationE04B1/343, H01Q15/14, H01Q15/16, E04H12/18, E04H12/00
Cooperative ClassificationE04B1/34326, H01Q15/161, E04H12/18
European ClassificationE04H12/18, E04B1/343C2, H01Q15/16B