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BACKGROUND OF THE INVENTION
Deployable structures have found many uses in connection with space
vehicles such as satellites and the like. Deployable structures are very
useful in connection with space vehicles since they can be launched into
space in their compact undeployed configuration and then later deployed
when the space vehicle is located in its proper position in space. Indeed
the proper performance of at least some space vehicles would be greatly
hindered or prevented unless it had some sort of deployable structure.
This is particularly true where the deployable structure is designed to
provide power to the space vehicle.
Such deployable structures have taken many shapes. Some of these deployable
structures have been formed from a single sheet of pre-stressed material
that can be coiled into a compact configuration and then uncoiled to its
deployed configuration to form a hollow tubular element that could be
utilized for an antenna or the like. Another different and perhaps more
important type of deployable space structure has incorporated a series of
panels that can be deployed in space from a space vehicle. These types of
deployable panel structures have many uses. For instance they can be
utilized to supply power to this spacecraft by having the panels covered
with an array of solar cells. They can also be utilized to reflect
sunlight and the like or they can also be utilized to dissipate unwanted
heat from the space vehicle. In most if not all instances the primary
advantage of the deployable panel structure is its large surface area
compared to its relatively low weight and its relatively compact volume
when it is in its non-deployed configuration.
Deployable panel structures have been in use for some years in connection
with space vehicles. For instance such deployable panel structures are set
forth in U.S. Pat. Nos. 3,460,992; 3,525,483; 3,532,299; and 4,155,524.
The deployable panel structures set forth in these patents are deployed
and maintained in their deployed position by means of respectively a lazy
tong linkage, a pair of cables, deployable booms, and cables and springs.
In many instances it is desirable to have a relatively rigid deployable
panel structure when it is deployed or in its deployed configuration.
Unfortunately the invention set forth in these patents do not provide such
a relatively rigid deployed panel structure. Moreover, for reliability's
sake and for weight savings and the like, it is generally desirable to
have as simple a structure as possible and to eliminate as much as
possible any unnecessary structure other than the panels themselves.
Unfortunately the invention set forth in these patents incorporate
additional unwanted structure or structures.
The deployable space panel structure of this invention overcomes these
problems associated with prior deployable panel structures and provides a
deployable panel structure that is very rigid when it is in its deployed
state. In addition, the deployable space panel structure of the invention
utilizes only a minimal amount of structure that is not associated with
the deployable panels themselves. Consequently, the invention saves weight
and is highly reliable.
BRIEF DESCRIPTION OF THE INVENTION
This invention relates to deployable space structures and more particularly
to a deployable space structure that utilizes a series of interconnected
panels.
It is an object of the present invention to provide a deployable space
panel structure that is very stiff or rigid when it is in its deployed
state or configuration.
It is an object of the present invention to provide a deployable space
panel structure that utilizes a minimal amount of structure other than the
panels themselves.
It is also an object of the present invention to provide a deployable space
panel structure that is highly reliable in operation.
It is also an object of the present invention to provide a deployable space
panel structure that is easy to retract from its deployed configuration.
It is also an object of the present invention to provide a deployable space
panel structure that is very compact when it is in its non-deployed
configuration.
It is also an object of the present invention to provide a deployable space
panel structure in which the location of these panels are precisely
located in relation to the spacecraft or the like when the panels are in
their deployed configuration.
It is also an object of the present invention to provide a deployable space
panel structure wherein the deployable panels themselves are utilized to
give the deployed panel structure its rigidity or stiffness.
The present invention provides a deployable space panel structure including
a first series of interconnected panel members and a second series of
interconnected panel members. Interconnecting means are also provided for
interconnecting the first series of panel members and the second series of
panel members and deploying means are also provided for deploying the
first and second series of panel members. The deployable space panel
structure is capable of being packaged in a compact non-deployed
configuration and then being deployed to form a rigid panel structure. The
deployable space panel structure is capable of providing a relatively
large surface area when it is in its deployed configuration and yet it is
capable of being packaged in a compact package in its non-deployed
configuration.
BRIEF DESCRIPTION OF THE DRAWINGS
The invention will be hereinafter more fully described with reference to
the accompanying drawings in which:
FIG. 1 is a perspective view of the deployable space panel structure of the
present invention in its non-deployed configuration;
FIG. 2 is a perspective view of the structure illustrated in FIG. 1
illustrating a deployable space panel structure in its partially deployed
configuration;
FIG. 3 is a perspective view of the structure illustrated in FIGS. 1 and 2
showing the deployable space panel structure in its further stage of
deployment and also showing drive structure that is associated with the
deployable space panel structure;
FIG. 4 is an end view of the deployable space panel structure set forth in
FIG. 3 taken substantially on the line 4--4 thereof;
FIG. 5 is a perspective view of the deployable space panel structure
illustrated in FIGS. 1 through 4 and also the drive members set forth in
FIG. 3 showing a deployable space panel structure in its fully deployed
configuration;
FIG. 6 is a perspective view of another embodiment of the deployable space
panel structure of the present invention showing the deployable space
panel structure in its non-deployed or collapsed configuration;
FIG. 7 is a perspective view of the structure set forth in FIG. 6 showing
the deployable space panel structure in its fully deployed configuration;
FIG. 8 is a perspective view of an interconnecting member that
interconnects one series of interconnected panel members with another
series of interconnected panel members that can be utilized with the
deployable space panel structure set forth in FIGS. 1 through 7;
FIG. 9 is a perspective view of an alternative interconnecting member that
can be utilized in place of the interconnecting member set forth in FIG.
8; and
FIG. 10 is a perspective view of an additional interconnecting member that
can be used in place of the interconnecting members set forth in FIGS. 8
and 9.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS
FIGS. 1, 2, 3, 4 and 5 illustrate one embodiment of the deployable space
panel structure of the invention that is designated generally by the
number 10. The deployable space panel structure 10 comprises a first
series of interconnected, substantially flat, rectangular shaped panel
members designated generally by the number 12 and a second series of
interconnected, substantially similar, flat, rectangular shaped panel
members that are designated generally by the number 14. The first series
of interconnected panel members 12 comprises a plurality of substantially
identical panel members designated by the numbers 16, 18, 20 and 22. In a
similar manner the second series of interconnected panel members 14
comprises a plurality of substantially identical panel members that are
designated by the numbers 24, 26, 28 and 30.
As best illustrated in FIGS. 2, 3, 4 and 5 the various panel members 16,
18, 20 and 22 of the first series of interconnected panel members 12 are
rotatably interconnected with the respective panel members 24, 26, 28 and
30 of the second series of interconnected panel members 14 by
interconnecting means that are designated generally by the number 32. The
interconnecting means 32 will be hereinafter more fully described. Also as
best illustrated in FIGS. 2, 3 and 5 the end portion 34 of the panel
member 16 is rotatably connected to the adjacent end portion 36 of the
panel member 18 by hinge means designated generally by the number 38. The
opposite end portion 40 of the panel member 18 is also rotatably connected
to the adjacent end portion 42 of the panel member 20 by similar hinge
means 38. Also in a similar manner the opposite end portion 44 of the
panel member 20 is rotatably connected to the adjacent end portion 46 of
the panel member 22 by similar hinge means 38.
Also as illustrated in FIGS. 2, 3 and 5 the end portion 48 of the panel
member 24 is rotatably connected to the adjacently located end portion 50
of the panel member 26 by similar hinge means 38. In a similar manner the
end portion 52 of the panel member 26 is rotatably connected to the
adjacently located end portion 54 by the hinge means 38, and the opposite
end portion 56 of the panel member 28 is rotatably connected to the
adjacently located end portion 58 of the panel member 30 by similar hinge
means 38.
As illustrated in FIG. 3 the inner end portion designated by the number 60
of the deployable space panel structure 10 is connected to deploying means
62 for deploying the first series of panel members 12 and the second
series of panel members 14. In the preferred embodiment this deploying
means 62 comprises a series of deploying drive rails 64, 66 and 68. The
deploying means 62 also includes slide members 70 and 72 that are located
on the respective outer edges of the inner portion 74 of the panel member
30. These slide members cooperate and slide within the respective slide
members 64 and 66. In addition, the deploying means 62 includes similar
slide members 76 and 78 that are located on the respective edges of the
inner end portion 80 of the panel member 22. These slide members 76 and 78
cooperate and slide within the respective slide members 66 and 68. The
deploying means 62 itself is known to those skilled in the art.
As best illustrated in FIGS. 3 and 4 the respective panel members 16, 18,
20 and 22 of the first series of interconnected panel members 12 that are
rotatably interconnected with the respective panel members 24, 26, 28 and
30 of the second series of interconnected panel members 14 form an angular
relationship as the panel members 16, 18, 20 and 22 and the panel members
26, 28 and 30 are being deployed. This angular relationship results in an
angle .alpha. when the series of interconnected panel members 12 and 14
are viewed from the end as illustrated in FIG. 4. This angular
relationship results from the rotatable interconnecting means designated
generally by the number 32 and the deploying means 62. As illustrated in
FIG. 5 the interconnected series of panel members 12 and the series of
panel members 14 continue to form an angular relationship with each other
when they are in their fully-deployed position. The fact that the
interconnected series of panel members 12 and the associated relationship
with each other during and after deployment permits the deployable space
panel structure 10 with its series of interconnected panel members 12 and
14 to maintain a fairly strong and stiff structure during and after
deployment. Of course, the same would be true when the interconnected
panel members 12 and 14 are being moved from their fully-deployed
condition to their collapsed or stored configuration as illustrated in
FIG. 1.
Another embodiment of the invention is illustrated in FIGS. 6 and 7 and is
designated generally by the number 82. The embodiment 82 is substantially
similar to the previously described embodiment 10; however, it utilizes a
series of deployable panel members that are constructed in a different
manner than the previously described panel members for the deployable
space panel structure 10. In this connection the deployable space panel
structure 82 comprises a first series of interconnected, substantially
flat and generally rectangular-shaped panel members that are designated
generally by the number 84 and a second series of interconnected
substantially similar, flat, generally rectangular-shaped panel members
that are designated generally by the number 86. The first series of
interconnected panel members 84 comprises a plurality of substantially
identical panel members designated by the numbers 88, 90 and 92. In a
similar manner the second series of interconnected panel members 86
comprises a plurality of substantially identical panel members that are
designated by the numbers 94, 96 and 98. It should be noted that the inner
end portion 100 of the panel member 92 is rotatably connected by hinge
means 38 to the inner end portion 102 of a similar panel member 104 that
has substantially the shape and area of one half of the other panel
members 88, 90 and 92 of the first series of panel members 84. In a
similar manner the inner end portion 106 of the panel member 98 is
rotatably connected by hinge means 38 to the inner end portion 108 of
panel member 110 that is similar to the panel member 104 and has
substantially the shape and area of one half of the other panel members
94, 96 and 98 of the series of panel members 86.
As illustrated in FIG. 7 the various panel members 88, 90 and 92 of the
first series of interconnected panel members 84 are rotatably
interconnected with the respective panel members 94, 96 and 98 of the
second series of interconnected panel members 86 by means of the
interconnecting means 32. Also the end portion 112 of the panel member 88
is rotatably connected to the adjacent end portion 114 of the panel member
90 by hinge means designated generally by the number 38. In a similar
manner the opposite end portion 116 is rotatably connected to the end
portion 118 of the panel member 92 by similar hinge means 38. In a similar
manner the inner end portion 120 of the panel member 94 of the adjacent
series of panel members 86 is rotatably connected to the adjacent end
portion 122 of the panel member 96 by hinge means 38. Also, the opposite
end portion 124 of the panel member 96 is rotatably connected to the
adjacent end portion 126 of the panel member 98 by hinge means 38.
As best illustrated in FIG. 6 for the panel members 88 and 94 the
respective inner edges 128 and 130 of the panel members 88 and 94 have
respective sloping edge portions 132 and 134 and 136 and 138 that slope
inward toward the respective points 140 and 142. This results in the edge
portions 132 and 134 of the panel member 88 making an angle with each
other and in the edge portions 136 and 138 of the panel member 94 making a
similar angle with each other. The other panel members 90 and 92 of the
first series of panel members 84 have substantially identical sloping
inner edge portions, and the associated inner panel member 104 has a
single sloping edge portion that has substantially the same slope and
angular relationship as the sloping edge portions 132 and 134 for the
panel member 88. In a similar manner the other panel members 96 and 98 of
the second series of panel members 86 have substantially the same sloping
edge portions and angular relationships as the edge portions 136 and 138
of the panel member 94. In addition, the inner panel member 110 has a
sloping inner edge portion that is similar to the sloping edge portion of
the panel member 104.
As illustrated in FIG. 6 the center line A of the panel member 88 and the
center line B of the panel member 94 that pass through the respective
points 140 and 142 making an angle .gamma. with each other and the
respective center lines of the other panel members 90 and 92 of the first
series of panel members 84 and the center line of the panel members 96 and
98 of the second series of panel members 86 also make a similar angle
.gamma. with each other. As illustrated in FIG. 7, the inner end portion
144 of the panel member 104 and the inner end portion 146 of the panel
member 110 are rotatably connected to a rigid member designated by the
number 148 by the hinge means 38. These inner end portions 144 and 146 are
connected to the rigid member 148 in such a manner that the inner edges
144 and 146 make the same angle .gamma. with each other. In view of the
arrangement of the first series of panel members 84 and the second series
of panel members 86 of the deployable space panel structure 82 the
centerlines, such as the centerlines A and B for the panel members 88 and
94, maintain their same angular relationship .gamma. with each other as
the first and second series of panel members 88 and 94 are deployed to
their extended configuration or retracted to their collapsed
configuration. In addition, as the first series of panel members 84 and
the second series of panel members 86 are being deployed or retracted, the
center lines, such as the center lines A and B for the panel members 88
and 94, remain in substantially the same plane. The fact that the first
and second series of panel members 84 and 86 maintain the angular
relationship .gamma. between center lines of the panel members during
deployment, retraction and in their deployed state means that the
interconnected series of panel members 84 and 86 provide a rigid structure
not only in the deployed state but also as they are being deployed or
retracted.
It should be noted that the sloping inner edge portions, such as the edge
portions 132 and 134 of the panel member 88 and the sloping inner edge
portions 136 and 138 of the panel member 94, permit the interconnected
first and second series of panel members 84 and 86 to be readily deployed
and retracted without having any binding or interference between the inner
edges of the panel members in the series of the deployable panel members
84 and 86. The deployment of the interconnected first and second series of
panel members 84 and 86 can be accomplished by various means known to
those skilled in the art; however, commonly, such means would exert a
force on one or both of the panel members 104 and 110 such as the Force F
illustrated in FIG. 7 that is being exerted against the panel member 104.
It will be appreciated that the hinge means 38 can take various forms that
are known to those skilled in the art.
Some of the various types of interconnecting means 32 that can be utilized
with the various panel members of the deployable space panel structure 10
illustrated in FIGS. 1 through 5 and the deployable space panel structure
82 illustrated in FIGS. 6 and 7 are illustrated in FIGS. 8 through 10. It
should be noted for convenience that the interconnecting means 32 is
illustrated in FIGS. 8 through 10 as being connected to the panel members
16 and 24. However, it should be understood that the same structure that
forms the inner connecting means 32 would also be used to interconnect the
other previously-described interconnected panel members.
In FIG. 8 the interconnecting means 32 comprises ball joint apparatus 150
that comprises a ball member 152 that has an outer enlarged, substantially
ball-shaped head portion 154 and an integral shank portion 156 that is
rigidly connected to the inner edge of the panel member 24. The ball joint
apparatus 150 also comprises a socket member 158 that has an enlarged
outer socket portion 160 that has a socket 162 that is sized and shaped to
slideably receive the outer head portion 154. The socket member 158 also
has an integral shank portion 164 that is rigidly secured to the inner
edge of the panel member 16. In view of this arrangement, the ball joint
apparatus 150 permits complete rotational freedom of movement between the
inner edge portions of the panel members 16 and 24.
In FIG. 9 the interconnecting means 32 comprises universal joint apparatus
166 that comprises a universal joint member 168 that has an enlarged
U-shaped head portion 170 and an integral shank portion 172 that is
rigidly connected to the inner edge of the panel member 24. The U-joint
apparatus 166 also comprises another U-joint member 174 that has an
enlarged outer U-shaped end portion 176 and an integral,
cylindrical-shaped shank portion 178. The outer U-shaped end portions 170
and 176 are interconnected by the pins 180 and 182 in a manner known to
those skilled in the art. The shank portion 178 of the U-joint member 174
also is free to rotate within the bushing 184 that is rigidly connected to
the inner edge portion of the panel member 16. In view of this arrangement
of the U-joint apparatus 166, substantially the same degree of movement is
available between the inner edge portions of the panel members 16 and 24
as with the embodiment of the interconnecting means 32 that is set forth
in FIG. 8.
In FIG. 10 the interconnecting means 32 comprises the hinge pivot apparatus
186. The hinge pivot apparatus 186 comprises a hinge member 188 that has
an enlarged outer U-shaped portion 190 with a slot 192 and an integral,
cylindrical shank portion 194. The hinge pivot apparatus 186 also
comprises a hinge member 196 that has an enlarged head portion 198 that
fits within the slot 192. The hinge member 196 also has a cylindrical
shank portion 200. The head portions 190 and 198 also have apertures such
as the aperture 202 for receiving the shank portion 204 of a bolt member
206 or the like so that the outer end portions 190 and 198 are pivotally
interconnected. The cylindrical shank portions 194 and 200 are rotatably
mounted within the respective bushings 208 and 210 that are rigidly
located within the respective inner edge portions of the panel members 16
and 24. In view of this arrangement of the hinge pivot apparatus 186,
almost the same degree of movement is available between the inner edge
portions of the panels 16 and 24 as is available in the embodiments of the
interconnecting means 32 illustrated in FIGS. 8 and 9.
The deployable space panel structures 10 and 82 are manufactured and used
in the following manner. The various panel members 16, 18, 20 and 22 of
the first series of interconnected panel members 12 are manufactured from
a suitable material such as a light weight honeycomb structure that is
known to those skilled in the art. In a similar manner the various panel
members 24, 26, 28 and 30 of the second series of interconnected panel
members 14 are manufactured from a similar type of honeycomb material that
is known to those skilled in the art. These various panel members are then
interconnected using the interconnecting means 32 in the manner
illustrated in FIGS. 3 and 5. The deploying means 62 is then manufactured
from suitable stock such as aluminum channel members to form a series of
deploying drive rails 64, 66 and 68 as indicated in FIGS. 3 and 5 the
drive rail 64, 66 and 68 are formed so that the first series of panel
members 12 and the second series of panel members 14 make an angle with
each other as they are being deployed and when they are in their fully
deployed state. This is necessary to insure that the deploying and
deployed panel members of the first and second series 12 and 14 have
strength. After the deploying means 62 has been formed, slide members 70,
72, 76 and 78 are located on the respective outer edges of the inner
portion 74 of the panel member 30 and the respective outer edges of the
inner end portion 80 of the panel member 22. These slide members 70, 72,
76 and 78 are then located so that they slide within the respective drive
rails 64, 66 and 68 and as a result the first and second series of
interconnected panel members 12 and 14 are connected to the deploying
means 62. The actual deployment of the interconnected panel members 12 and
14 is accomplished by causing the slide members 70, 72, 76 and 78 to move
along the respective drive rails 64, 66, 66 and 68 by means known to those
skilled in the art such as by applying force to the panel members 30 and
22. It should be noted that in the preferred embodyment it is desirable to
have the outermost panel members such as panel member 16 and 24 of the
respective interconnected deployable panel members 12 and 14 deploy at
least slightly before the innermost panel members 22 and 30.
The deployable space panel structure 82 is manufactured in a manner similar
to the deployable space panel structure 10. In this connection the panel
members 88, 90, 92 and 104 of the first series of interconnected panel
members 84 and the panel members 94, 96, 98 and 110 of the second series
of interconnected panel members 86 may be manufactured from a similar type
of lightweight honeycomb material by means known to those skilled in the
art. The first series of interconnected panel members 84 is then connected
to the second series of interconnected panel members 86 by means of the
inner connecting means 32 as illustrated in FIG. 7. As illustrated in FIG.
7 the inner end portion 144 of the panel member 104 and the inner end
portion 146 of the panel member 110 are rotatably connected to a rigid
member designated by the number 148 by the hinge means 38 that are known
to those skilled in the art. As indicated a downward force F up on the
upper surface of the panel member 104 can result in deployment of the
first and second interconnected series of panel members 84 and 86 in a
similar manner an upward force F upon the panel member on 110 can result
in the retraction of the interconnected series of panel members 84 and 86.
It should be noted that the first and second series of interconnected
panel members 84 and 86 make an angle with each other when they are in
their deployed state and also as they are being deployed or retracted.
This of course is a necessary so that the interconnected series of panel
members 84 and 86 have strength. As indicated for the deployable space
panel structure 10 it is desirable to have the outer panel members deploy
slightly before the inner panel members and that is also true for the
deployable space panel structure 82. Consequently the panel members 88 and
94 should be deployed before the inner panel members 104 and 110.
In using the deployable space panel structures 10 and 82 they are normally
stored within a space vehicle or the like (not shown) in their stored or
collapsed configuration. Then when the space vehicle reaches its
designated location in space the first and second series of interconnected
panel members such as the interconnected panel members 12 and 14 or the
deployable space panel structure 10 the interconnected panel members 84
and 86 for the deployable space panel structure 82 are then deployed in
the manner previously indicated. Should it be deemed desirable these
series of interconnected panel members 12 and 14 and 84 and 86 can then be
retracted into their stored position as indicated in the respective FIGS.
1 and 6. It will of course be appreciated that the deployable panel
members 16, 18, 20, 22, 24, 26, 28 and 30 of the deployable space panel
structure 10 and the panel members 88, 90, 92, 104 94, 96, 98 and 110 of
the deployable space panel structure 82 can have solar cells (not shown)
located on them so as to provide power to the space vehicle or the like.
Although the invention has been described in considerable detail with
reference to certain preferred embodiments, it will be understood that
variations or modifications may be made within the spirit and scope of the
invention as defined in the appended claims.
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