U.S. patent number 3,913,105 [Application Number 05/363,220] was granted by the patent office on 1975-10-14 for collapsible self-erecting tubular frame structure and deployable electromagnetic reflector embodying same.
This patent grant is currently assigned to TRW Inc.. Invention is credited to Roy M. Acker, Gilbert A. Greenbaum, William J. Phillips, Clyde E. Williamson.
United States Patent |
3,913,105 |
Williamson , et al. |
October 14, 1975 |
Collapsible self-erecting tubular frame structure and deployable
electromagnetic reflector embodying same
Abstract
A collapsible self-erecting three-dimensional frame structure
constructed of relatively thin-walled resiliently flexible tubular
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.
Inventors: |
Williamson; Clyde E. (Los
Angeles, CA), Acker; Roy M. (Los Angeles, CA), Greenbaum;
Gilbert A. (Encino, CA), Phillips; William J. (Gardena,
CA) |
Assignee: |
TRW Inc. (Redondo Beach,
CA)
|
Family
ID: |
26829244 |
Appl.
No.: |
05/363,220 |
Filed: |
May 23, 1973 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
Issue Date |
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131218 |
Apr 5, 1971 |
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Current U.S.
Class: |
343/840; 52/108;
343/897; 52/646; 343/915 |
Current CPC
Class: |
H01Q
15/161 (20130101); E04H 12/18 (20130101); E04B
1/34326 (20130101) |
Current International
Class: |
E04B
1/343 (20060101); E04H 12/00 (20060101); E04H
12/18 (20060101); H01Q 15/14 (20060101); H01Q
15/16 (20060101); E04h 012/18 () |
Field of
Search: |
;52/108,646
;343/840,897,915 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Primary Examiner: Abbott; Frank L.
Assistant Examiner: Raduazo; Henry
Attorney, Agent or Firm: Anderson; Daniel T. Nyhagen; Donald
R. Dinardo; Jerry A.
Parent Case Text
This is a continuation of application Ser. No. 131,218 filed Apr.
5, 1971 now abandoned.
Claims
What is claimed as new in support of Letters Patent is:
1. A deployable antenna reflector for spacecraft and the like
comprising:
a tetrahedral truss frame constructed of thin-walled, resilient,
collapsible, strain energy erectile tubular frame members and
having two spaced and generally parallel frame sections forming
opposite sides 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 connecting means,
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 joined at
their ends to said perimeter by said first connecting means and
between their ends to one another at the truss member intersections
by said second connecting means, and connecting struts comprising
tubular frame members extending between and joined at their ends by
said connecting means to said frame sections in such a way as to
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 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;
a flexible and foldable electrically conductive mesh secured to
said outer side of said one frame section in a manner such that
said mesh conforms generally to said surface contour to provide an
electromagnetic reflecting surface when said truss frame occupies
said tetrahedral truss configuration; and
said frame members being adapted to be flattened 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 wherein said frame members store elastic strain
energy for deploying said reflector when the collapsing force on
the reflector is removed.
Description
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 large truss structures and the like
which can be collapsed for 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.
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.sub.F 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.sub.F 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.sub.R and intersecting truss
members T.sub.R comprising frame members 12 joined end to end by
connecting means 14. Truss members T.sub.R 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 into a unitary frame structure. As may be readily
observed in the drawings, the several frame members of the truss
structure 10 form a number of tetrahedral frame portions, that is
portions of the overall frame consisting of six frame members 12
arranged in a tetrahedral configuration. These tetrahedral frame
portions are hereafter referred to as tetrahedral bays and have
triangular faces in the front and rear frame sides 16, 18.
The frame members 12 of the truss structure 10 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 as 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.sub.F, P.sub.R, and truss members T.sub.F, F.sub.R 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
individual 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 is provided with the desired contour, in this
instance a parabolic contour, by dimensioning the connecting struts
S of the truss structure in such a way that the frame members 12
located in the plane of the front side conform generally to, i.e.
are tangent to, a theoretical parabolic surface. Improved
conformance of the front truss side to a parabolic surface may be
accomplished 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 with folding 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.
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 its expanded or
deployed configuration of FIG. 1 when released.
* * * * *