U.S. patent number 3,699,574 [Application Number 04/867,101] was granted by the patent office on 1972-10-17 for scanned cylindrical array monopulse antenna.
This patent grant is currently assigned to The United States of America as represented by the Secretary of the Navy. Invention is credited to Francis J. O'Hara, Troy E. Plunk.
United States Patent |
3,699,574 |
O'Hara , et al. |
October 17, 1972 |
SCANNED CYLINDRICAL ARRAY MONOPULSE ANTENNA
Abstract
A cylindrical antenna array system having two cylindrical
subarrays flush unted on a conducting cylinder, each consisting of
a plurality of linear phased arrays fed through a pair of feed
rings on the conducting cylinder that has a diode switch for each
linear phased array coupled through a switching network to switch
one-quarter to one-third of the linear phased arrays ON in a
rotating manner to scan throughout 360.degree. around the cylinder
axis, and each linear phased array having a pair of rotatable
dielectric slabs behind the waveguide slots thereof with all
dielectric slabs mechanically coupled to rotate in synchronism to
phase the radio waves for angular direction with respect to the
cylinder axis, the received signals being coupled through a magic-T
junction to provide sum and difference monopulse signals of targets
in sight of the antenna.
Inventors: |
O'Hara; Francis J. (Bedford,
MA), Plunk; Troy E. (Bedford, MA) |
Assignee: |
The United States of America as
represented by the Secretary of the Navy (N/A)
|
Family
ID: |
25349084 |
Appl.
No.: |
04/867,101 |
Filed: |
October 16, 1969 |
Current U.S.
Class: |
342/154; 342/153;
342/374; 343/768; 342/157; 343/705 |
Current CPC
Class: |
H01Q
3/242 (20130101); H01Q 3/32 (20130101) |
Current International
Class: |
H01Q
3/30 (20060101); H01Q 3/24 (20060101); H01Q
3/32 (20060101); G01s 009/22 () |
Field of
Search: |
;343/16M,1SA,768,771,854 |
References Cited
[Referenced By]
U.S. Patent Documents
|
|
|
3474446 |
October 1969 |
Shestag et al. |
3531803 |
September 1970 |
Rosen et al. |
|
Primary Examiner: Tubbesing; T. H.
Claims
I claim:
1. A flush mounted cylindrical array monopulse scanning antenna
comprising:
a conducting cylinder with two subsystems of linear phased
waveguide arrays arranged longitudinally around said cylinder to
produce a flush cylindrical monopulse antenna;
a waveguide feeder ring on one end of each subarray to feed radio
frequency into and out of said array, said feeder ring having a
crystal coupler for each linear phased array with all crystal
couplers coupled to a switching network to activate one-fourth to
one-third of adjacent linear phased arrays in a rotating manner to
scan 360.degree. around said cylinder axis;
a pair of rotatable dielectric slabs extending through each linear
phased array with rotation means thereon to rotate same to vary the
phase angle and the scan beam over an angle with respect to said
cylinder axis;
master means in coupled co-operation with all said rotation means
of said dielectric slabs to rotate same in synchronism; and
transmitting means and receiving means coupled to said waveguide
feeder rings, said receiver means having means therein to obtain
sum and difference of all target signals scanned by said antenna
whereby said antenna is aerodynamically constructed for high speed
and capable of scanning a spherical section forward thereof to
identify targets for destruction.
2. A flush mounted cylindrical array monopulse scanning antenna as
set forth in claim 1 wherein
said linear phased waveguide arrays each have a double row of slots
with one each pair of dielectric slabs therein and one said crystal
coupler for each double row of slots of the linear phased
array.
3. A flush mounted cylindrical array monopulse scanning antenna as
set forth in claim 2 wherein
said master means coupled in co-operation with all said rotation
means of said dielectric slabs is a positive mechanical reversible
driving means.
4. A flush mounted cylindrical array monopulse scanning antenna as
set forth in claim 3 wherein
said receiving means includes two inputs, one coupled to each of
said feeder rings, each input coupled through a first thruplexer, a
phase shifter, and a second thruplexer in common to the inputs of a
magic-T, the output of which provides sum and difference signals of
a target.
Description
BACKGROUND OF THE INVENTION
This invention relates to monopulse antennas and more particularly
to monopulse flush mounted cylindrical missile seeker antennas.
Until about 1962 no great need for a flush mounted missile seeker
antenna was foreseen, primarily because no antenna scheme could be
envisioned which could compete, performance wise, with a
conventional flat plate antenna in a missile nose radome. About
1962 jet engine technology had advanced to the point where it was
very likely that they could be used in high velocity missiles. In
such a missile a flush mounted seeker antenna is imperative. More
recent studies indicate that a flush mounted antenna can be used to
improve missile kill probabilities in that the warhead can be
placed in the missile nose where it is more effective. Considerable
interest has been generated also in a flush mounted microwave
missile seeker antenna through consideration of dual mode seeker
systems. An example of the latter would be an X-band flush mounted
antenna which would allow for placement of an infrared seeker in
the missile nose.
SUMMARY OF THE INVENTION
In the present invention two subassemblies of linear phased arrays
placed longitudinally around a conduction cylinder produce a flush
mounted cylindrical antenna. Each subarray has a ring feed with
waveguide feed openings corresponding to openings in each linear
phased array to feed same and each ring feed opening is controlled
by a diode coupler that is in circuit with a switching network to
control the bias on selected diode couplers to commutate a rotating
group of linear phased arrays thereby producing a 360.degree.
rotation of transmitted and reflected beams of radio frequency.
Each linear phased array has a pair of eccentrically rotatable
dielectric slabs therein that have mechanical connections, as by
gear means to a ring gear, to drive all slabs alike to phase the
transmitted and reflected signals for angular direction with
respect to the centerline of the cylinder. The rotatable dielectric
slabs and the diode coupler switches provide a 360.degree. beam
rotation of 45.degree. fan for both antenna arrays. The reflected
signal outputs from both subarrays are coupled to a magic-T
junction from which the signals are processed for sum and
difference for target identification and angle tracking. It is
therefore a general object of this invention to provide a flush
mounted monopulse cylindrical antenna array consisting of two
subarrays for missiles or other aircraft vehicles for use in enemy
missile detection and destruction.
BRIEF DESCRIPTION OF THE DRAWINGS
These and other objects and the attendant advantages, features, and
uses will become more apparent to those skilled in the art as the
description proceeds when considered along with the accompanying
drawings in which,
FIG. 1 is an isometric view of a missile or other aircraft device
illustrating the subarray items of this invention,
FIG. 2 illustrates one of the linear phased array elements making
up the composite subarray items disclosing the waveguide phasing
slab adjustment means,
FIG. 3 illustrates an isometric view of the phasing slabs used in
the linear array of FIG. 2,
FIG. 4 shows an isometric view of the waveguide feeder ring for the
subarray antenna of FIG. 1,
FIG. 5 is a block circuit schematic in the receiver component of
the antenna system, and
FIGS. 6, 7, 8, and 9, illustrate the .theta. plane, the .PHI.
plane, and the sum and difference graphs produced by the received
signals of a target in space.
DESCRIPTION OF THE PREFERRED EMBODIMENT
Referring more particularly to FIG. 1 with occasional reference to
FIGS. 2 and 3, there is illustrated an isometric view of a device,
such as a missile 10, having a nose cone 11 and a propulsion
section 12 with flush mounted subarray antenna means A and B
circumferentially about the middle portion. The subarrays A and B
may be placed on any aircraft device for detecting and angle
tracking a target by monopulse radar means. Each subarray A and B
consists of a plurality of linear phased array sections 20 more
particularly shown in FIG. 2 arranged circumferentially about the
central body portion of the missile device.
The linear phased array shown in FIG. 2, and identified by the
reference character 20, generally consists of a rectangular
waveguide section having an inlet port 21 on one end and two rows
of radiating or outlet ports 22 and 23 along one face thereof. The
opposite end of the linear phased array waveguide section 20 to the
inlet port 21 includes an enclosed end 24 with two gear driven
eccentric slabs shown by the exterior gears 25 and 26. The
waveguide slabs which extend into the linear phased array waveguide
20 are more particularly shown in FIG. 3, in the reverse direction,
to more particularly illustrate the two eccentric slabs 27 and 28
extending outwardly from the end plate 24. The two gears 25 and 26,
together with like gears on all other linear phased array waveguide
elements 20 constituting the subarray A or the subarray B, are
driven in unison by a ring gear 29. The ring gear 29 is preset with
the gears 25 and 26 of all the linear phased array elements 20 to
cause the radar beam to radiate at the same angle with respect to
the longitudinal axis of the missile device 10 for all array
elements 20. One extreme of the radar beam would be approximately
in the end-fire direction which produces a beam parallel to the
longitudinal axis of the missile 10. The other limit of phasing the
radar beam out of the linear phased array ports 22 and 23 would be
about 45.degree. from the longitudinal center line of the missile
10, the purpose of which will be more readily understood as the
description proceeds. The ring gear 29 may be driven by some motor
means, herein illustrated as being an electric motor 30, which may
be computer controlled or otherwise automatically controlled to
phase all the linear phased arrays 20 for the same angle of
transmission and reception between the limits of near end-fire and
about 45.degree. . One ring gear 29 and motor means 30 are required
for each subarray A and subarray B for the purpose and in the
manner to be described.
Referring more particularly to FIG. 4 there is illustrated an
isometric view of a rectangular waveguide feeder ring 31 which is
illustrated in FIG. 1 as the circular rings 31 between subarrays A
and B. While both feeder rings 31 are shown centrally in FIG. 1, it
is to be understood that these feeder rings could be on opposite
ends of the subarrays A and B or on the same end of each subarray A
and B, as desired. Each feeder ring is made of a plurality of
rectangular feeder input sections 32 having rectangular ports 33
which are connected by bolting or otherwise affixed to the inlet
end of the linear phase arrays 20 so that the rectangular ports 33
of the feeder rings are each in alignment with the rectangular
inlet ports 21 of the linear phased array elements 20. Each
waveguide feeder ring 31 has waveguide coupling members 34 and 35
for coupling inlet and outlet waveguide sections for the radar
system, as is well understood by those skilled in the radar art.
Each waveguide feeder ring 31 has a crystal 36 for each ring
section 32. Each crystal 36 is coupled to a switching circuit,
herein illustrated in block form by the reference character 37, to
switch the radio frequency as from the inlet 34 to the port 33 in a
manner to activate about one-fourth to one-third of the linear
phased arrays 20 at any one time. The switching circuit 37 may be
any switchable electronic switch designed, such as a commutating
device, to cause the one-fourth to one-third linear phase arrays to
be activated in a circularly rotating manner. As may be understood
from the description in FIG. 1, each phased array A and B will be
made to produce a transmitted radar beam to travel radially
outwardly from the longitudinal center line of the missile at an
angle set by the phased arrays shown in FIG. 2 from near end-fire
to about 45.degree. to produce a cone scan about the missile 10
forwardly through the 45.degree. angle. Such transmitted radar
signals will be reflected by any targets in the area illuminated by
the transmitting signals and reflected back through the subarrays A
and B to the radar system in a monopulse mode readily understood by
those skilled in the radar art.
Referring more particularly to FIG. 5, a block diagram illustrates
the components in the receiver section of the radar system in which
the outlet, such as 35 from the subarray A, is applied as an input
40 to a thruplexer 41 while the output 35 of subarray B conducts as
an input 42 to a thruplexer 43. The thruplexer 41 is coupled
through a waveguide phase shifting means 44 through a second
thruplexer 45 to a magic-T junction 46 while the thruplexer 43 is
coupled through a waveguide phase shifter 47 and a second
thruplexer to the magic-T 46. The output of the magic-T junction 46
is the waveguide output 49 to the receiving equipment of the
monopulse radar system in the well known manner to produce sum and
difference radar signals for use in angle target tracking of any
radar target illuminated by the antenna. The thruplexers 41 and 43
are each waveguide adapters to convert rectangular mode waveguide
inputs 40 and 42 into circular waveguide sections for the phase
shifters 44 and 47. The thruplexers 45 and 48 are also waveguide
adapters to reconvert the circular mode of the waveguide back to
the rectangular mode for coupling to the magic-T junction 46. For
the purpose of definition, the phasing of the radio frequency at an
angle with respect to the longitudinal axis of the missile device
by the slab means 27 and 28 may be referred to as the .theta.
position, while the rotation of the radio frequency
circumferentially about the missile axis may be referred to as the
.PHI. position. The radio frequency (rf) outputs (or inputs on
transmit) can be added in a conventional monopulse network to
produce monopulse information in the .theta. direction. In antenna
terminology this is a phase monopulse system in the .theta. plane
since the monopulse beams are formed as a result of the physical
space of the two cylindrical areas in this plane. The rf beams from
the two subarrays A and B can be scanned together with .theta.
direction by identically controlling the linear array scanning
within each subarray by the motor control 30. To complete effective
.theta. direction scan of the sum and difference monopulse beams,
it is necessary to maintain proper phase control versus scan angle
.theta. between the two subarrays. This is accomplished by the two
phase shifters 44 and 47 although only one phase shifter may be
used in either of the rf outputs from the subarrays A or B. In this
way the sum and difference array factors formed by the addition or
subtraction of the two subarrays A and B can be scanned in the
.theta. direction thus completing the phase requirements for
.theta. scan of the monopulse beam. The phase shifters 44 and 47
are preferably of a type to change the phase while in the circular
mode since this is a more practical method.
FIG. 6 shows a graph of the subarray resulting radar signal from
near end-fire in the .theta. plane starting at near 0.degree. to
about 45.degree. giving the amplitude of the signal in decibels and
the abscissa co-ordinate in degrees.
FIG. 7 illustrates the sum and difference output from the end-fire
angle in the .theta. plane while FIG. 9 illustrates the sum and
difference pattern in the .PHI. plane.
FIG. 8 shows the .theta. scan signal for the decibel output when
the scan beam is 20.degree. from end-fire in the .PHI. plane.
OPERATION
In the operation of the antenna means illustrated in FIGS. 1
through 5, let it be assumed that the antenna means of FIG. 1 is
coupled to a conventional monopulse radar system with the received
signal coupled through a circuit as shown in FIG. 5. Either by
computer means of other automatic driving means the two motors 30
and the switching circuit 37 can be made operative to cause the rf
beam to traverse the angle from near end-fire of the missile to
approximately 45.degree. to the longitudinal centerline of the
missile for subarrays A and B while at the same time the switch
circuit 37 is energizing one-third to a one-fourth of the linear
phased arrays 20 to cause antenna illumination in two full circle
cones of scan by both subarray antennas A and B. The returned or
reflected signals from any targets in the cones of illumination
will be received through the circuit of FIG. 5 to produce sum and
difference signals of the target for angle tracking of that target.
The output signal on the waveguide output 49 may be used for
automatically piloting the missile 10, which may include a warhead
element in the nose cone 11, to seek out, track, and collide with
the enemy target missile to destroy same. If the missile 10 is of
the ram-jet engine type, for which this invention would be
particularly adaptable, it would make this missile a high velocity
missile which would improve the missile kill probability in that
the warhead could be placed in the missile nose where it is more
effective. This flush mounting type of missile microwave seeker
antenna could be used for dual mode seeker systems in which X-band
frequencies could be used which would allow for the placement of an
infrared or optical type seeker in the missile nose, where
desired.
While many modifications may be made in rearrangement of parts as
described herein to produce the same results and functions, we
desire to be limited in the scope of our invention only as limited
by the accompanying claims.
* * * * *