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Патент USA US3048097

код для вставки
Aug. 7, 1962
3,048,087
E. F. CAMPBELL
WEAPON MOUNT
FiledJuly 29, 1955
4 Sheets-Sheet 1
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INVENTOR
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ATTORNEYS
Aug. 7, 1962
E. F. CAMPBELL
3,048,087
WEAPON MOUNT
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Filed July 29, 1955
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E. E CAMPBELL
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Aug. 7, 1962
E. F. CAMPBELL
3,048,087
WEAPON MOUNT
4 Sheets-Sheet 4
Filed July 29, 1955
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INVENTOR
E. F. CAMPBELL
BY ßdáwíz
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ATTORNEYS
United States Patent O "
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3,i8,87
Patented Aug. 7, ‘i962
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tem which automatically switches from one device to the
other as the target moves through the respective operat
3,048,087
WEAPON MOUNT
'
Ernest F. Campbell, Springfield, Va., assigner to the
United States of America as represented by the Secre
tary-of the Navy
Filed July 29, 1955, Ser. No. 525,403
4 Claims. (Cl. 89-41)
(Granted under Title 35, U.S. Code (1952), sec. 266)
_ The invention described herein may be manufactured
and used by or for the Government of the United States
of America for governmental purposes without the pay
ment of yany royalties thereon or therefor.
This invention relates to an ordnance system and appa
ratus therefor, and more particularly to `a single, compact,
ing range areas.
Accordingly, it is an object of «the present invention to
Vprovide a weapon system which permits defensive and
offensive action over a large Karea of combat conditions.
lt is a further object of the present invention to pro
vide a single weapon system which is _capable of expelling
missiles having a high kill probability within a range area
from several hundred yards out to a distance of between
20 »to 40 miles.
»
Another object of the present invention is to obtain a
relatively light weight weapon which offers maximum pro
wide range weapon having a lire control system which
continuously directs the weapon on target automatically
switching and selecting that portion of the weapon offer
ing the greatest hit probability within the instant range or
tection over a variety of combat conditions.
area of the target.
An additional object is to present a single, compact,
The advent of supersonic laircraft and missiles has
relatively lightweight weapon system providing extensive
imposed dillîcult problems in regard to the design of
defensive and offensive equipment adequate for use against 20 coverage throughout a wide target range area wherein the
target is continuously covered by a missile device which
these type of targets. Heretofore, the speed of attacking
is exceedingly efficient in contact performance for the
aircraft and the early type of missiles was relatively slow
particular instant target area or range.
in comparison to those in present day use, thus providing
A further aim is to obtain a weapon system which
an ample time factor for locating the target, bringing a
automatically selects a missile device which is most elfec
weapon to bear thereon and ñring. Under such circum
-tive against the target under the instant battle conditions.
stances the target could be engaged
a relatively
Other objects and many of the attendant advantages of
short range and the equipment generally employed against
this'invention will (be readily appreciated as the same be
such a target was accordingly designed for short range
operation.
The tremendous increase in speed of present day at
comes better understood by reference to the following
detailed description when considered in connection with
tacks «has, however, reduced this time factor to such an
the accompanying drawings wherein:
extent that it is now necessary to initiate defensive or
offensive measures when the target is located at a con
bodiment of the present invention;
siderable range or distance from the weapon station. Long
FIG. 1 is a diagrammatic representation of one em
FIG. 2 is aside elevational wiew of ia shipboard weapon
range weapons for operation against high speed aircraft 35 installation embodying the present invention with a por
and missiles have been developed,- such weapons are gen
tion of the ship broken away to show missile handling
erally large in size and of heavy construction and limited
equipment;
'
FIG. 3 is an enlarged side view of the weapon of FIG.
to long range use. While existing requirements now call
2 in the missile loading position;
for these long range weapons, the need still exists for the
FIG. 4 is a front elevation view of the embodiment
conventional weapons which are particularly eifective 40
within short ranges since efforts :at short range must be
of FIG. 3;
FlG. 5 is a side elevational view of a modilied form of
exerted should the extended range operation fail. There
the present invention with portions broken away; and
fore, positions requiring complete defensive and oiîen
FIG. 6 is a top plan View of the right hand of the mount
sive equipment must include two separate weapons, the
long range weapon and the short range weapon.
45 illustrated in FIG. 5 with a portion of the weapon shield
broken away.
This solution of utilizing two separate weapons is not,
For purposes of clarification the weapon system of the
however, >generally satisfactory with many branches of
present invention will be described in two parts; ñrst, the
the armed forces where space and weight factors are criti
weapon mount and modifications thereto dis-closed in
cal. For instance, installation of two separate weapons
on naval vessels would require doubling the space and 50 FIGS. 2 through 6, and secondly, the weapon system or
tire control «system for the weapon shown in FIG. l with
weight ‘allowances previously accorded ordnance weapons
one embodiment of the weapon mount.
on naval vessels. Moreover, where separate systems are
A preferred embodiment of a Weapon mount, gen
used there is always the problem of coordination and the
erally indicated by the numeral l0, is shown in a shipl
possibility of a` fatal delay between the switching from
one system to the other. The Navy is particularly con 55 board installation in FIG. 2. The weapon mount 10 com
prises a carriage 11 rotatably mounted on vertical stan?
cerned with this problem vsince it must be prepared to take
12. A weapon shield `1'3` `supporting two long range mis
instant oifensive «and defensive measures against maneu
sile devices generally designated by numeral 14, and tw(
vering targets having an initial range yfrom between 30
short range missile devices indicated generally by numera
to 40 miles out until the target is within close proximity
of the ship.
60 15, is suitably seated within the carriage l1 for elevationa
movement. While the weapon mount `l0 is shown (FIG
4) support-ing two missile devices of each type it is to bl
understood that only one of each type may be supporte
weapon and system provides the desired overall protec
thereon if desired. Since the structure and operation i
tion without the previous existing disadvantages above
discussed. The weapon mount _of the weapon system 65 the same for both sides of the mount the following discus
sion will be limited to one half of the mount containin,`
supports two complementing missile devices, one of which
one of each of the missile devices.
is adapted to launch missiles having a high kill probability
To the rear of the weapon mount l0, preferably locatet
-within a range ysubstantially from six thousand yards out
below deck, is a missile magazine 16 containing storag
to approximately 20 to 40 miles, the other device capable
of projecting missiles designed for ya high kill rate within 70 rack 17 for storing and retaining ready missiles. When i
is desired to move a missile M up into launching posi
a range up to approximately -six thousand yards. Both
tion on the weapon mount Al0 a rammer rail 18 is actuaten
missile devices are controlled by a single tire control sys
The present invention constitutes a single weapon oper
-able and controlled by a single fire control system which
3
by chain 19 and sprockets 20 to move rammer car 21
under the selected missile M. As the rammer car 21
¿i
in place thereon by the retaining means previously de
scribed.
moves under the missile M downwardly depending car
The weapon system which controls either of the weapon
engaging lugs 23 enter a cooperating closed ended slot
mounts 10 or 36 is illustrated in FIG. 1. The system corn
(not shown) in the car. The car ‘21 and missile M are Ul prises the usual fire control components utilized in a con
subsequently moved forward until they are directly over
ventional system such as a radar unit having a radar an
elevatable rammer rail extension 24 in its horizontal posi
tenna 50 and a radar scope 51; a weapon director 52,
tion. The rail extension 24 is then raised by hoist means
mount stabilizer 53, a short range missile ballistic com
25 to the position shown in FIG. 2 whereupon the car and
puter (gun) 54, a long range missile ballistic computer 55,
missile are further advanced until they rest partly upon a
and train and elevation control mechanisms v56 and 57,
ñxed rail 26 which is supported at one end by a portion 27
respectively. In addition, to the above components the
of the housing for magazine access 2S. During the pre
system also includes an analyzing and selecting circuit
ceding loading operations the weapon mount 10 has been
means composed of a pip senser 58 which operates in con
moved in train and elevation such that it is in the position
junction with the radar scope 51, an amplilier 59 and a
shown in FIG. 3 whereby the missile launching rail 29 is 15 computer switch relay 60. Pip senser 58 may be a senser
aligned with the missile M to be received thereon. The
of the photoelectric or photoconductive type. Since the
rammer car 21 and missile M are accordingly moved for
weapon mount supports two types of missile devices, each
ward up along the `fixed rail 26 through the pivoted door
device having ballistic characteristics ditferent from the
30 of the housing for magazine access 28 until the vertical
other, the primary function of the weapon system is there
missile supporting lugs 31 have reached their forward posi 20 fore to continually train and elevate both missile devices
tion within the T-shaped slot 32 (FIG. 4) of the missile
on the target simultaneously analyzing the desired ballis
launching rail 29. The missile launching rail 29 is posi
tics necessary for intercepting the target at any instant in
tioned outwardly from the side of the weapon shield 13
its course and selecting the missile device whose ballistics
by fore and aft supporting plates 33 and connecting beam
meet those demanded. In performing this function the
34. Once the missile has reached its launching position 25 system operates in the following manner. Assume that
on the missile launching rail 29 the rammer chain 19 and
a target is `detected by the radar unit and a pip P appears
rammer car 21 are retracted back to their initial position
over the numeral 15 on the scale 61 of the radar scope 5-1
within the magazine 16, the missile M being retained in
indicating that the target’s range is approximately 15,000
place on the missile launching rail 29 by means of the
yards. Since the light sensitive pip senser 58 is actuated
spring bias check means commonly employed in missile 30 only When the light emitting pip P appears within a range
launchers and not illustrated herein.
of 6000 yards no signal will be generated thereby and the
Missile M of the long range missile device 14 is thus in
computer switch relay 60 will not be energized, the switch
launching engagement on the weapon mount 10 and ready
62 thus remaining in its spring biased (missile ballistics
for firing. The' short range missile device 15 comprising
computer) position.
barrel 35 and conventional loading means (not shown)
The incoming signal is transmitted from the radar an
for automatically feeding rounds into the breech end of the
tenna 50 through weapon director 52 and into the mount
barrel 35 has also been operated to place the device in a
stabilizer 53 where correction for the ship’s roll, pitch, etc.
ready tiring position. Hence, the weapon mount has two
are made. The information derived from the weapon
missile devices in tiring condition, each device capable of
director S2 and mount stabilizer 53 is then fed into the
expelling a missile which has ballistic characteristics con 40 missile ballistic computer 55, since the computer switch
siderably different from the other, one designed for ef
62 is in its spring biased position. Subsequently, the in
ñcient operation at long target ranges, and the other specif
telligence obtained from the missile ballistic computer 55
ically adapted to provide close `and effective coverage by
is transmitted into the train control 56 and the elevation
expelling numerous short range missiles should the former
control 57 which will in turn act to move the weapon
fail to destroy the target.
mount such that the missile devices thereon are on target.
A modified embodiment of the weapon mount and load
It is to be noted that in the above example the target’s
ing arrangement is disclosed in FIGS. 5 and 6. It is to be
range of 15,000 yards fell Within the range area of be
tween 6000 to 18,000 yards .wherein the long range mis
noted that in the weapon mount 1'4 of FIGS. 2 through 4
sile device is primarily designed for eñicient operation
the weapon shield 13 is supported for elevational move
and the system has automatically selected this missile
ment and the missile devices 14 and 15 being rigidly at
device by channeling the incoming signal through the mis
tached thereto are properly elevated by the raising and
sile ballistic computer 55. As the target approaches, the
lowering of the shield. FIGS. 5 and 6 show a more con
system continually changes the elevation and range of the
ventional weapon mount 36 having a rotatable shield 37
missile
device 14 and it is at all times ready for tiring. If
and a missile barrel 38 mounted for elevational movement
due to the failure of missile device 14 to destroy the tar
within the shield 37 on trunnion shaft 39. The conven
get, or ‘for various tactical reasons the target continues, or
tional trunnion shaft 39 is modified by coupling trunnion
is allowed to continue to approach the weapon, then the
shaft extensions 40 at each end thereof, the trunnion shaft
pip P will gradually recede down scale 61 indicating the
extensions 410 being supported intermediate their ends by
closing of the target range. When the pip P reaches the
bearing structure 41. A missile launching rail 42 is se
6000 yard range indicia the light given ofï” by the pip P
cured to the outer ends of each of the trunnion shaft ex
60 will cause the pip senser 58 to initiate a signal. The sig
tensions 40. A missile magazine 43 is provided having an
nal thus generated lwill be amplified by -ampliñer 59, and
overhead rammer rail 44, `a rammer car 45 and suitable
ramming means such as the usual rammer chain (not
further fed to energize the magnetic coil 63 of the com
puter switch relay 60. Switch 62 is thereby urged upper
shown). The missile M is moved into missile launching
wardly causing the ilow of signals and information to by
pass the missile ballistic computer 55 and enter the gun
ballistic computer 54 in lien thereof. This circuit remains
closed as long as pip P remains within the 6000 yard
to the rammer car 45 by lugs 46, is advanced to a posi
range and the weapon system is thereby locked in engage
tion beneath the elevatable rammer rail extension 47. A
ment with the short range missile device which is specif
pivoted door 48 (which serves as a blast deflector in door
70 ically designed for operation within Ithis range area.
closed position) is then opened to allow the rammer rail
Should a target pass from the close range area out into
extension 47 to be raised by hoist means 49 to its dotted
the distant range area then the above-described procedure
line position shown in FIG. 5. Subsequently, the car and
will be reversed, the weapon system automatically switch
missile are moved forwardly andupwardly until the mis
ing over to the long range missile device as the target
sile M engages the missile launching rail 42 and is retained 75 moves out beyond the 6000 yard range.
rail engagement in a manner somewhat similar to that
previously described in that the missile M, being attached
3,048,087
6
weapon system comprising, a missile supporting and
launching device mounted for movement in elevation and
train, la missile storage chamber positioned generally
below and to the rear of said missile supporting and
launching device, said `chamber including a door and a
ceiling, the forward portion of the ceiling being inclined
upwardly in a direction toward the missile supporting
and launching device to form a missile storage chamber
The particular range scale disclosed in FIG. 1 and thel
range areas used in the description of the operation of
Ythe system are but one of many combinati-ons which can
be used, the range scale and range area varying of course
with the specific .type of missile devices employed. While
the coverage of the scale of FIG. »l is limited to 18,000
yards in the interest of simplicity, it is envisioned that the
scale in actual use will be extended to considerably
greater ranges.
access compartment, cover means hingedly attached to
'
Obviously many modifications and variations of the
present invention are possible in the light of the above
teachings. It is therefore to be understood that within
the scope of the appended claims the invention may be
practiced otherwise than as specifically described.
What is claimed is:
s1. A missile handling apparatus for a multirange target
said compartment and adapted to open in a direction to
ward the missile supporting and launching device, rack
means Within the chamber 4for retaining and storing ready
missiles, missile carrier means located in said chamber for
engaging and moving a missile from the rack to said mis
15 sile supporting and launching device, said missile carrier
destroying weapon comprising, a weapon mount movable
in azimuth and elevation, a plurality of missile receiving
and launching devices disposed on said weapon mount, a
means including a missile carrying car, a rammer rail,
and rammer means for moving said missile carrying car
along the rammer rail, said rammer rail having a forward
pivotal extension adapted to be raised from a horizontal
missile storage chamber positioned generally below and to 20 position to an elevated position in alignment with said
one side of said Weapon mount, said missile storage cham
cover means, hoist means for raising sa-id pivotal exten
sion to said elevated -aligned position, the length of the
pivotal extension being at least equal to the length of
said missile carrying car whereby when the missile sup
cated within said chamber for engaging and moving a mis
sile from the chamber to one of said missile receiving and 25 porting and launching device is moved in train and eleva
tion to aÍ position such that it is aligned with the cover
launching devices, a pivoted guide -rail within the chamber
means said missile carrying car with a missile thereon
adjacent the pivoted door for «directing said missile car
ber having an upper pivoted door in that portion of the
chamber nearest the weapon mount, a missile carrier lo~
rier to said door, and means for elevating said pivoted
may be moved by the rammer means along the rammer
guide rail'to an elevated missile ejection position, whereby
rail until thecar and missile are supported entirely by
when said weapon mount is moved in azimuth and eleva 30 the forward pivotal extension in its horizontal position,
said extension .then being raised to its elevated aligned
tion to a position such that one of said missile receiving
positionto allow for further advancement of the car and
and launching devices is aligned with said pivoted guide
missile through the missile storage chamber access com
rail in its elevated position, said missile carrier with a mis
partment andacover means until the missile is engaged
sile thereon may be advanced along said guide rail until
said missile is engaged with the aligned missile receiving 35 and retained by said missile supporting and launching
device.
'
and launching device and secured thereon.
2. The apparatus vas deiined in claim l wherein said
missile carrier comprises a missile carrying car and an
References Cited in the iile of this patent
overhead rammer rail extending along the top wall of the
missile storage chamber, said guide rail forming an ex 40
tension of said overhead rammer
3. The apparatus as deiinedein claim- 1 wherein said
missile carrier includes -a missile carrying car and a
rammer rail disposed along the lower Wall of said mis
sile storage chamber, said guide rail forming an elevatable 45
UNITED STATES PATENTS
2,425,425
2,557,949
Jorgensen ____________ __ Aug. 12, 1947
Deloraine ___________ .__ June 26, 1951
2,629,289
Hunter _______________ _ Feb. 24, 1953
2,655,079
Aldrin et al. _________ _.. Oct. 13, 1953
FOREIGN PATENTS
extension of the rammer rail.
4. A_ missile storage l'and loading apparatus for a
692,140
Great Britain ,g ____ -_„__,.. May 27, 1953
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