U.S. patent number 3,680,143 [Application Number 05/051,423] was granted by the patent office on 1972-07-25 for shaped beam antenna.
This patent grant is currently assigned to Hughes Aircraft Company. Invention is credited to James S. Ajioka, Harold A. Rosen.
United States Patent |
3,680,143 |
Ajioka , et al. |
July 25, 1972 |
SHAPED BEAM ANTENNA
Abstract
The apparatus of the present invention provides an antenna
adapted to optimize the transmission or reception performance of a
satellite subject to the usually encountered weight and volume
constraints. The antenna features dual mode operation which
provides two independent terminals, each providing the same gain
pattern and polarization sense, but having differing senses of
phase progression across the beam pattern. In addition, the
beamwidth of the antenna is designed to cover a prescribed area on
earth wherein minimum gain in this area is maximized rather than
the gain at the beam center. The disclosed antenna system may also
be used with a single reflector and two orthogonal polarizations,
providing a total of four antenna terminals. To provide the second
polarization which may be either crossed linear or counter rotating
circular, each of the feeds must support the two polarizations, and
the two pairs of terminals of a given polarization interconnected
via individual hybrids.
Inventors: |
Ajioka; James S. (Fullerton,
CA), Rosen; Harold A. (Santa Monica, CA) |
Assignee: |
Hughes Aircraft Company (Culver
City, CA)
|
Family
ID: |
21971214 |
Appl.
No.: |
05/051,423 |
Filed: |
July 1, 1970 |
Current U.S.
Class: |
343/778;
343/DIG.2; 343/840; 343/779 |
Current CPC
Class: |
H01Q
25/001 (20130101); H01Q 19/17 (20130101); Y10S
343/02 (20130101) |
Current International
Class: |
H01Q
25/00 (20060101); H01Q 19/10 (20060101); H01Q
19/17 (20060101); H01q 019/14 () |
Field of
Search: |
;343/840,853,854,705,DIG.2,778,779 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Lieberman; Eli
Claims
What is claimed is:
1. A satellite antenna system comprising a parabolic reflector
having a focal point; first, second, third and fourth feed horns
disposed in the order named along a linear array in the region of
said focal point facing said reflector; dual terminal means
responsive to a signal at either terminal for generating first and
second output signals at first and second output terminals,
respectively, said first and second output signals being of equal
power and having a 90.degree. phase difference; first, second and
third magic-T's each having terminals 1, 2, 3, and 4, terminals 1
of said first and second magic-T's being connected to said first
and second output terminals, respectively, of said dual terminal
means, terminals 2 and 3 of said second magic-T being connected to
said second and third feed horns, respectively, terminals 2 and 3
of said first magic-T being connected to terminal 4 of said second
and third magic-T's, respectively, terminals 2 and 3 of said third
magic-T being connected to said first and fourth feed horns,
respectively; and means for terminating terminal 4 of said first
magic-T and terminal 1 of said third magic-T.
2. The satellite antenna system as defined in claim 1 wherein said
dual terminal means constitutes a 90.degree. hybrid.
3. A dual mode, dual polarized satellite antenna system comprising
a parabolic reflector having a focal point, means including first
and second dual polarized feeds disposed in the region of said
focal point facing said reflector and offset symmetrically from the
axis of rotation thereof for generating overlapping field intensity
patterns, means for feeding said first and second feeds with a
first set of equal amplitude signals of 90.degree. phase difference
having a predetermined polarization, and means for feeding said
first and second feeds with a second set of equal amplitude signals
of 90.degree. phase difference and of a polarization orthogonal to
said predetermined polarization.
Description
BACKGROUND OF THE INVENTION
Antenna systems having aperture shaped excitation functions having
beam patterns with flat or saddle tops are well known. These
antenna systems, however, invariably require much larger apertures
than conventional antennas. A typical linear dimension of such an
antenna system is three times that of a conventional system.
Because of the large dimensional requirements of a shaped beam
satellite antenna system, the volume and weight constraints of the
booster may preclude the use of two completely independent antennas
to provide the two terminals desired.
SUMMARY OF THE INVENTION
In accordance with the present invention, a dual mode satellite
antenna system having a shaped beam is realized by a plurality of
linearly disposed off-set feeds at the focal region of a reflector.
The feeds are spaced sufficiently close so that the patterns
overlap and are fed in a manner to produce differing senses of
phase progression across the pattern. Because of this phase
progression, the overlapping patterns add vectorially to produce an
over-all saddle or flat beam pattern rather than a pattern with a
peak in the plane of the linearly disposed feeds. The feed system
is adaptable to the outputs from a 90.degree. hybrid, thereby
providing two independent terminals to the antenna system. The
importance of two independent terminals in transmission is in
alleviating the multiplexing problem encountered when multiple
transmitters separated in frequency must share the same antenna.
When only two transmitters are involved, the provision of two
terminals eliminates the requirement for a transmitter multiplexer.
When a large number of transmitters is required, the provision of
two terminals permits connecting to each a set of transmitters
having twice the adjacent channel frequency separation, thereby
simplifying the multiplexer. For use in reception, the provision of
two antenna terminals reduces the switching required to provide
redundancy in the receivers.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 illustrates dual mode transmitting and receiving antennas in
accordance with the invention installed on a satellite;
FIG. 2 shows a cross-section through the feed structure of the
antenna of FIG. 1;
FIG. 3 illustrates far field patterns of a single off-center feed,
two off-center feed, and the dual mode feed of FIG. 1;
FIG. 4 illustrates a plan view of an off-set feed dual
polarization, dual mode, four terminal antenna;
FIG. 5 is an implementation of cross-polarized feed horns for the
antenna of FIG. 4; and
FIG. 6 illustrates a two-terminal, four-feed horn system in
accordance with the invention.
Referring now to FIG. 1 of the drawings, there is shown a
transmitting antenna 10 and a receiving antenna 12 installed on a
satellite 14 which includes solar cell panels 15 and 16 at the
lower portion thereof, as shown in the drawing. The transmitting
and receiving antennas 10, 12 are mounted on a vertical support
shaft 18 which is topped by a telemetry and command antenna 20.
Cross-section A - A' of antenna 10 is shown in FIG. 2. In
particular, antenna 10 includes a conductive parabolic reflector 22
with feeds 23, 24 disposed in the region of the focal point 25 of
parabolic reflector 22 and off-set equally from the axis of
rotation thereof. Feeds 23, 24 may assume the form of horns or
other contemporary radiating element. In the event horns are
utilized, the apertures thereof are directed towards the central
region of reflector 22. Lastly, transmission lines 26, 27 connect
from the body of satellite 14 through a 90.degree. hybrid 29 to the
feeds 23, 24, respectively. Similarly, transmitting antenna 12
includes a parabolic reflector 30 with transmission lines 31, 32
connected from the body of satellite 14 through a 90.degree. hybrid
33 to feeds 34, 35, respectively, which are disposed in positions
corresponding to the feeds 23, 24 of antenna 10.
Referring to FIG. 3(a), there is shown a far field pattern 40 for a
single off-center feed 23 or 34. In FIG. 3(b) there is shown far
field pattern 40 plus a far field pattern 42 for the single
remaining feed 24 or 35. Under normal circumstances with the
electric fields both in phase, the intersecting point 43 of far
field patterns 40, 42 would represent 0.5 the peak amplitude shown
by dashed line 44. In the present case, however, the far field
patterns 40, 42 are added "vectorially" and, in particular for the
antenna of FIG. 1, are added at 90.degree.. That is, the 90.degree.
hybrids 29, 33 provide two terminals for each of the antennas 10,
12 and excite the feed horns 23, 24 and 34, 35, respectively, with
signals that are equal in intensity and 90.degree. out of phase.
Under these circumstances, the far field patterns 40, 42 add to
give the "shaped" pattern 46, FIG. 3(c) for each terminal of the
90.degree. hybrids 29 and 33. The beam dimension thus developed
permits "shaping" the beam in its long angular dimension while
using a conventional beam shape in its short dimension, by
adjusting the off-set of the beam centers generated by the feeds
23, 24 and 34, 35. This off-set may, for example, be approximately
.+-. 1.6 degrees.
In a typical installation, receiving antenna 12 is designed to
receive signals in the 5.925 - 6.425 GHz band and the transmitting
antenna 10 is designed to transmit signals in the 3.7 - 4.2 GHz
band. By making the diameter of the reflectors 22, 30 24
wavelengths, the angular dimensions of the beam generated by both
antennas 10, 12 is roughly an ellipse with a major axis of
6.degree. and a minor axis of 2.5.degree.. Under these
circumstances, the reflector 22 of transmit antenna 10 is
approximately 6 feet in diameter while the reflector 30 of receive
antenna 12 is 4 feet in diameter. This beam configuration can be
oriented to provide coverage over the contiguous 48 states of the
United States from the stationary satellite's altitude of 19,300
nautical miles.
The size required for the transmitting antenna reflector may
preclude the use of two separate antennas. In this instance, the
use of the antenna system of FIG. 4 is required when two
independent terminals are required. Referring to FIG. 4, there is
shown a dual-polarization, dual-mode, four-terminal antenna 50 in
accordance with the present invention. Antenna 50 comprises a
reflector 52 which constitutes a circular section of a paraboloid
having a diameter extending outwards from the center thereof. Dual
polarization feeds 54, 55 are off-set horizontally from the axis of
rotation of the paraboloid in the region of the focal point
thereof, as viewed in the drawing. Terminals 56, 57, are connected
by transmission lines 58, 59, respectively, through a 90.degree.
hybrid 60 to common polarization inputs to feeds 54, 55. Similarly,
terminals 61, 62 are connected by transmission lines 63, 64,
respectively, through a 90.degree. hybrid 65 to the remaining
common polarization inputs of feeds 54, 55. Referring to FIG. 5,
there is shown an implementation of the dual-polarization feeds 54,
55 of FIG. 4. In this case, waveguides 68, 69 constitute the
transmission lines 58, 59 and connect from terminals 56, 57 to feed
horns 54, 55 in a manner to excite vertically polarized signals
therein, as viewed in the drawing. Waveguides 73, 74, on the other
hand, constitute the transmission lines 63, 64 and connect from
terminals 61, 62, respectively, to feed horns 54, 55, respectively,
in a manner to excite horizontally polarized signals therein, as
viewed in the drawing. The use of contra-rotating circularly
polarized signals instead of orthogonally polarized signals is
considered to be within the spirit and scope of the present
invention.
Referring now to FIG. 6 of the drawings, there is shown an
embodiment of the invention wherein a linear array of four feed
horns 81, 82, 83, 84 are disposed in the region of the focal point
of a parabolic reflector, not shown, and including magic-T's 85,
86, 87 and a 90.degree. hybrid 88. Magic-T's are characterized by
four terminals designated 1, 2, 3, and 4, as labeled on magic-T's
85, 86, and 87, wherein there is no direct coupling between
terminals 1 and 4 and terminals 2 and 3. Terminal 1 is also
designated the summation or .SIGMA. input and terminal 4 the
difference or .DELTA. input. Signals applied to the summation
terminal divide equally between terminals 2 and 3 and have the same
phase, whereas signals applied to the difference terminal divide
equally between terminals 2 and 3, but are of opposite phase. On
the other hand, the sum of signals applied to terminals 2 and 3
appear at the summation terminal and the difference appear at the
difference terminals. Returning now to FIG. 6, antenna terminals
90, 91 are connected through 90.degree. hybrid 88 to the summation
terminals of magic-T's 86, 85, respectively; difference terminals
of magic-T's 85, 87 are connected to terminals 2 and 3,
respectively, of magic-T 86; terminals 2 and 3 of magic-T 85 are
connected to feed horns 82, 83, respectively; terminals 2 and 3 of
magic-T 87 are connected to feed horns 81, 84, respectively; the
summation terminal of magic-T 87 is terminated; and the difference
terminal of magic-T 86 is terminated.
Thus, in operation, a signal E, applied to antenna terminal 90 of
90.degree. hybrid 88 results in applying signals
to summation terminals of magic-T's 86, 85, respectively. The
signal
applied to the summation terminal of magic-T 86 divides equally
between terminals 2 and 3 thereof to provide the signal
at each of these terminals. The signal
applied to the difference input of magic-T 87 results in a
signal
applied to feed horn 81 and a signal
applied to feed horn 84. The signal
applied to the difference terminal of magic-T 85 along with the
signal
applied to the summation terminal results in the signal
Summarizing, signal E applied to terminal 90 results in the
following signals:
Feed horn 81 0.36 E.vertline.90.degree. Feed horn 82 0.61
E.vertline.35.6.degree. Feed horn 83 0.61 E.vertline.-35.6.degree.
Feed horn 84 0.36 E.vertline.-90.degree.
the resulting beam constitutes the vector addition of the
overlapping portions of the individual beam patterns. In the event
a signal is applied to the antenna terminal 91, the signal
amplitudes are the same but the phase progression occurs in the
opposite direction.
* * * * *