U.S. patent number 3,680,144 [Application Number 05/112,988] was granted by the patent office on 1972-07-25 for singly-curved reflector for use in high-gain antennas.
Invention is credited to George M. Acting Administrator of the National Aeronautics & Space Low, Arthur C. Ludwig, N/A.
United States Patent |
3,680,144 |
Low , et al. |
July 25, 1972 |
SINGLY-CURVED REFLECTOR FOR USE IN HIGH-GAIN ANTENNAS
Abstract
A furlable antenna particularly suited for use aboard
spacecraft. The antenna is characterized by an improved reflector
plate conforming to a frusto-conical configuration combined with a
point-source feed and a secondary reflector having a reflective
surface conforming to a figure of revolution generated by rotating
a segment of a parabola about an axis parallel the ray path of the
intermediate rays, whereby the antenna can be stowed in a furled
configuration without substantially reducing its efficiency.
Inventors: |
Low; George M. Acting Administrator
of the National Aeronautics & Space (N/A), N/A
(Lacanada, CA), Ludwig; Arthur C. |
Family
ID: |
22346945 |
Appl.
No.: |
05/112,988 |
Filed: |
February 5, 1971 |
Current U.S.
Class: |
343/781R;
343/837; 343/915; 343/840 |
Current CPC
Class: |
H01Q
1/288 (20130101); H01Q 19/191 (20130101); H01Q
15/161 (20130101) |
Current International
Class: |
H01Q
19/10 (20060101); H01Q 1/28 (20060101); H01Q
1/27 (20060101); H01Q 19/19 (20060101); H01Q
15/16 (20060101); H01Q 15/14 (20060101); H01q
015/20 () |
Field of
Search: |
;343/781,840,837,915 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Primary Examiner: Lieberman; Eli
Claims
What is claimed is:
1. An antenna comprising:
A. a base having an annular configuration;
B. a point-source feed operatively associated with said base;
C. a plurality of substantially rigid ribs fixed to said base and
extended therefrom;
D. a reflector plate of an annular configuration supported by said
ribs and having a reflective surface conforming to a frustum;
and
E. a sub-reflector coaxially related to said plate and operatively
associated with said point-source feed and said plate having a
reflective surface conforming to a figure of revolution of a
segment of a parabolic curve.
2. The antenna of claim 1 wherein said plate includes a plurality
of arcuate gores suspended between said ribs and having a common
radius of curvature.
3. The antenna of claim 2 wherein each of said gores is fabricated
from impervious sheet stock and includes a singly-curved reflective
surface.
4. The antenna of claim 1 wherein the reflector plate is fabricated
from flexible sheet stock of impervious material and said ribs are
pivotally coupled with said base and displaceable between a stowed
position wherein the plate is caused to assume a pleated
configuration, and an operative position wherein the reflector
plate is caused to assume an expanded frusto-conical
configuration.
5. In a high-gain antenna adapted to be deployed into an operative
configuration and furled into a stowed configuration, a reflector
comprising an annular plate having a singly-curved reflective
surface formed of a plurality of flexible, thin-gauge metal sheets
defining a frustum when deployed into an operative configuration
and a sinuously curved reflective surface when furled into a stowed
configuration, and means for alternately supporting said reflector
in said deployed and stowed configurations.
6. The reflector of claim 5 wherein said means for supporting said
reflector includes a base and a plurality of substantially rigid
ribs pivotally supported by said base.
Description
ORIGIN OF INVENTION
The invention described herein was made in the performance of work
under a NASA contract and is subject to the provisions of Section
305 of the National Aeronautics and Space Act of 1958, Public Law
85-568 (72 Stat. 435; 42 USC 2457).
BACKGROUND OF THE INVENTION
1. Field of the Invention
The invention generally relates to high-gain antennas for use
aboard spacecraft, and more particularly to an improved primary
reflector plate capable of being pleated to a furled configuration
and subsequently deployed into a frusto-conical configuration.
2. Description of the Prior Art
Where a high-gain antenna is to be employed aboard a spacecraft, it
is highly desirable to reduce the bulk of the antenna during
launch, for purposes of accommodating limited shroud dimensions as
well as to protect the antenna from the deleterious effects of the
high-G environment normally encountered during launch. Of course,
large antennas necessarily must be capable of being readily erected
into desired shapes having illumination characteristics dictated by
prevailing RF (Radio Frequency) requirements.
Doubly-curved, rigid surfaces cannot be folded. For this reason,
parabolic antenna reflecting surfaces larger than those that can be
designed with petals must employ some form of a compliant
structure, such as those of a rib and mesh design. A number of
types have been built, tested, and used. However, such antenna
tends to suffer the common deficiency, mainly that of chording in
both radial and circumferential directions. Consequently, a mesh
cannot be made to assume a configuration which is truly parabolic.
In order to meet this imposed combination of parameters it has been
suggested that large reflectors be segmented into petals so that
these petals could be stowed in various overlapped configurations.
Of course, the structure required in deploying the petals tends to
be rather complex and massive and thus tends to reduce the
feasibility of such structure.
It is the consensus of those engaged in designing antennas that
while singly-curved surfaces are particularly desirable from a
structural standpoint, such are not desirable from an RF
standpoint, primarily because of the poor focusing characteristics
of such surfaces. Therefore, there currently exists a need for a
practical high-gain antenna capable of being stowed and
subsequently deployed into a practical and operatively efficient
configuration.
OBJECTS AND SUMMARY OF THE INVENTION
It is therefore an object of the instant invention to provide an
improved high-gain antenna which overcomes aforementioned
difficulties and disadvantages.
Another object is to provide an improved reflector for use in a
high-gain antenna.
Another object is to provide a singly-curved reflector for use with
a high-gain antenna of the type commonly found aboard spacecraft
and the like.
Another object is to provide a primary reflector plate having a
reflective surface defining a frustum particularly suited for use
with a point-source feed and a secondary reflector having a
reflective surface conforming to a figure of revolution of a
segment of a parabolic curve.
It is another object to provide in a high-gain antenna of the type
employing a two-reflector system, a primary reflector plate having
good electrical properties and greatly simplified structure whereby
the primary reflector plate can be furled for stowage and unfurled
into an efficient configuration.
These and other objects and advantages are achieved through the use
of an antenna including a point-source feed, a secondary reflector
and a primary reflector having an operable frusto-conical
configuration, including a singly-curved reflective surface
fabricated from a furlable, impervious sheet of metal, supported in
an operative configuration by structure which permits the plate to
be stowed aboard spacecraft in a furled configuration and deployed
therefrom into a practical, operative configuration.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a fragmented perspective view of a high-gain antenna
which embodies the principles of the present invention, depicting a
primary and a secondary reflector operatively associated in a
deployed configuration.
FIG. 2 is a side view of the primary reflector shown in FIG. 1.
FIG. 3 is a perspective of the primary reflector shown in FIGS. 1
and 2.
FIG. 4 is a top plan view of the primary reflector shown in FIGS. 1
through 3 illustrating a pleated configuration assumed by the
reflector when it is supported in its furled configuration by
pivotal ribs.
FIG. 5 is a side elevation of the primary reflector shown in FIGS.
1 through 4, also illustrating a furled configuration for the
reflector.
FIG. 6 is a detailed view taken generally along line 6--6 of FIG. 3
illustrating one manner in which adjacent gores can be coupled with
the pivotal ribs.
FIG. 7 is a detailed view of one of the gores illustrating its
preformed configuration.
FIG. 8 is a detailed, enlarged view illustrating a pleated
configuration assumed by a single gore when the primary reflector
is in the furled configuration illustrated in FIGS. 4 and 5.
FIG. 9 is a detailed view depicting one manner in which the ribs
employed in supporting the primary reflector are urged into an
operative disposition for unfurling and deploying the reflector
plate.
FIG. 10 is a schematic view depicting the approximate ray optics
behavior of the antenna system of the instant invention.
FIG. 11 is a schematic view depicting optics behavior of a modified
form of the secondary reflector.
DESCRIPTION OF THE PREFERRED EMBODIMENT
Referring now to the drawings wherein like reference numerals
designate like or corresponding parts throughout the several views,
there is shown in FIG. 1 a high-grain antenna 10 which embodies the
principles of the instant invention.
The antenna 10 includes a primary reflector 12, a sub-reflector,
hereinafter referred to as secondary reflector 14, and a
point-source antenna feed 16 operatively associated with the
secondary reflector. The antenna 10 has particular utility in
celestial space communication systems and accordingly is supported
by suitable structure, generally designated 18. Since the structure
18 employed in mounting the antenna 10 forms no specific part of
the instant invention, a detailed description thereof is omitted in
the interest of brevity. However, it is to be understood that the
structure 18 can be of a type capable of supporting a high-gain
antenna in a projected disposition relative to an operative
spacecraft. As such, the structure 18 and the antenna 10 are
appropriately matched in order to facilitate a desired orientation
and operation of the antenna.
As illustrated in FIG. 10, both of the reflectors 12 and 14 include
a reflective surface conforming to a figure of revolution generated
about the Z axis of the antenna 10. In practice, the primary
reflector 12 is a singly-curved plate having a reflective conical
configuration, while the secondary reflector 14 is a plate having a
reflective surface conforming to a figure of revolution generated
by rotating a segment of a parabolic curve. Since the behavioral
characteristics of the reflectors of the type herein employed are
well known, a detailed discussion of such characteristics is
omitted in the interest of brevity. As is well known, a
singly-curved surface tends to focus in one dimension only and will
convert a plane wave to a cylindrical or conical wave converging
toward a line segment. However, by utilizing a secondary reflective
surface generated by rotating about the axis Z, FIG. 10, a segment
of a parabola, having an axis paralleling the ray path of the
intermediate rays of reflected energy, it is possible to employ a
"point-source" feed rather than a more complex "line-source"
feed.
As also illustrated in FIGS. 1 and 10, the primary reflector 12 is
provided with a concentric opening having a diameter approximately
equal to its radius. Consequently, the illuminated portion of the
primary reflector is such that the antenna 10 has a maximum gain
which is approximately 75 percent of the maximum gain achievable
through the use of a reflector of a full circular aperture of the
same diameter. Since the normal loss encountered is 3 to 6 percent
in a conventional system, due to illumination blockage, the
relative potential gain of the antenna illustrated is about 75 to
78 percent of the potential value for such reflectors. In practice,
the actual gain of this reflector is approximately the same as
conventional reflectors.
Mounted within the opening 20 is the antenna feed 16. As herein
employed, the term "feed" is defined as any device that couples
energy between free space and a transmission line. Since feed
designs are matters well within the skill of the art and form no
specific part of the invention, a detailed description of the feed
16 also is omitted. However, it is to be understood that the
primary reflector 12, the secondary reflector 14, and the feed 16,
in effect, establish a conical-Gregorian antenna system by which
incident plane wave energy can be refocused to a point.
Of course, the secondary reflector 14 can be of an inverted
configuration, as depicted at 14a, FIG. 11, and employed in a
Cassegrainian configuration wherein the rays strike the outer
surface of the reflector.
Turning now to FIGS. 2 and 3, it is noted that the primary
reflector 12 is supported by an annular base 22 having extended
therefrom a plurality of rigid ribs 24. The ribs 24 are spaced at
equi-distances about the periphery of the base 22 and are pivotally
coupled thereto through suitable pivot blocks 26. The blocks 26 are
of a suitable design which serve to pivotally couple the ribs 24 to
the base 22 in a manner such that the ribs can be displaced
pivotally in planes bisecting the base.
The primary reflector 12, in effect, is a singly-curved plate
formed of a plurality of segments or preformed gores 28, FIG. 7,
fabricated from a flexible, imperforate sheet stock such as a
suitable thin-gauge metal, including stainless steel, aluminum and
the like. In order to assure that the plate 12 is caused to assume
a frusto-conical configuration, the gores 28 preferably are
pre-stressed and strained in a manner such that when deployed in
the reflector 12, the reflector is caused to assume a
frusto-conical configuration having a singly-curved surface.
Each of the gores 28 is suspended and secured between a pair of the
ribs 24, FIGS. 6 and 8. Where desired, right-angle hinge plates 30
are coupled to the ribs 24 through the suitable hinges 32,
including piano hinges and the like. Of course, the manner in which
the gores 28 are secured to the hinge plates 30 and the hinges 32
secured to the ribs 24 can be varied as is found practical.
However, these structural components can be bonded quite suitably,
employing high-performance polymeric materials.
When deployed, the reflector 12 assumes a rigid, frusto-conical
configuration so that its reflective surface defines a frustum.
This, of course, requires the ribs 24 to be forced outwardly toward
a common plane, radiating from the base 22. However, due to the
fact that the reflector 12 is of a conical configuration, the ribs
24 do not assume a coplanar relationship.
While any practical actuator can be employed in urging the ribs
outwardly to their deployed disposition, a torsion spring 34
mounted within each of the blocks 26, FIG. 9, serves quite
satisfactorily for this purpose. In some instances, it may be
deemed practical to employ a rack-and-pinion drive, or similar
power train for forcing the ribs 24 into a deployed disposition
relative to the base 22.
As best illustrated in FIGS. 4 and 5, the reflector 12 is furled by
simultaneously pivoting the ribs 24 toward a common point located
on the axis of the base 22. Such displacement of the ribs 24
normally is manually achieved and serves to fold each of the gores
28 in a manner such that the reflector 12 is configured to a series
of adjacent pleats. Hence, by drawing the distal ends of the ribs
24 into close proximity, the reflector 12 is pleated and thus
caused to assume a furled condition particularly practical in
spacecraft launching operations. Of course, for practical
considerations the ribs are secured by suitable means, now shown,
in close proximity for securing the reflector in its furled
condition.
In order to unfurl and thus deploy the primary reflector 12 from
its pleated configuration, the distal ends of the ribs 24 are
released and in response to forces applied by the torsion spring 34
they simultaneously are caused to pivot outwardly toward a coplanar
relationship. This pivotal displacement of the ribs 24 deploys the
reflector 12 into an unfurled condition and fully expanded
configuration. The forces applied by the springs 34 serve to
tension the gores 28 for thus causing the hinge plates 30 to pivot
into an abutting relationship, as best illustrated in FIG. 6.
As shown in FIG. 1, a plurality of extended support struts 36 are
utilized for supporting the secondary reflector 14 in an operative
relationship with respect to the primary reflector 12. It is
preferred that the struts 36 be of a length sufficient to permit
the ribs 24 to be pivoted inwardly beneath the secondary reflector
12. While not shown, it also is to be understood that the secondary
reflector 14 is supported at predetermined distances from the feed
16 for thus appropriately positioning the secondary reflector 14,
relative to the primary reflector 12. This can be accommodated by
including within each of the struts 36 a screw-threaded jack or
similar device, not designated, which accommodates axial adjustment
and alignment of the secondary reflector with respect to the
antenna axis as well as the feed 16. Also, while not shown, it can
be appreciated that the feed 16 preferably is supported by an
adjustable mount which accommodates an axial repositioning of the
feed relative to the antenna axis.
OPERATION
It is believed that in view of the foregoing description, the
operation of the device will be readily understood and it will be
briefly reviewed at this point.
With the antenna 10 assembled in the manner hereinbefore described
it is associated with a given spacecraft. The ribs 24 are pivotally
displaced toward the axis of the antenna 10 for simultaneously
folding the gores 28 to impart to the primary reflector 12 a
pleated configuration. In this configuration the antenna 10 is
enclosed within a protective shroud, not shown, preparatory to
launch. Preferably, the distal ends of the ribs 24 are positioned
in the vicinity of the peripheral surface of the secondary
reflector 14 and operatively secured in this position, by any
suitable means not shown.
Once launched, the shroud is removed and the ribs 24 are released.
Under the influence of the springs 34 simultaneously acting on the
ribs 24, the reflector 12 is unfurled and deployed into an
operative frusto-conical configuration. As the reflector is
unfurled, its reflective surface is caused to define the frustum of
a cone coaxially related to the axis of the secondary reflector 14.
In this configuration the primary reflector 12 presents a
singly-curved surface to the reflective surface of the secondary
reflector 14, whereupon an instant plane wave can be focused at the
feed 16. Due to the capability of the reflector 12 to be unfurled
from a stowed condition, the primary reflector can be fabricated
from imperforate materials into operatively efficient reflectors of
practical dimensions.
In view of the foregoing, it is to be understood that the instant
invention is embodied in a conical-Gregorian high-gain antenna
which provides a practical solution to problems encountered in
developing systems capable of establishing communication with
spacecraft employed in deep space exploration.
Although the invention has been herein shown and described in what
is conceived to be the most practical and preferred embodiment, it
is recognized that departures may be made therefrom within the
scope of the invention, which is not to be limited to the
illustrative details disclosed.
* * * * *