US3048087A - Weapon mount - Google Patents

Description

4 Sheets-Sheet 1 IN VENTOR ATTORNEYS E. F. CAMPBELL WEAPON MOUNT E. E CAMPBE LL 2.9...3 .s 2..,m v N o um Hlm Aug. 7, 1962 FiledJuly 29, 1955 um .vm

Aug. 7, 1962 E. F. CAMPBELL 3,048,087

WEAPON MOUNT Filed July 29, 1955 4 Sheets-Sheet 2 aix Ii ha".

N c5 E MA arm 5 INVENTOR Q E.F.CAMPBE|.L

BYE

0f/SWW ATTORNYS FIG.5

FIG. 4

Aug. 7, 1962 E. F. CAMPBELL WEAPON MOUNT Filed July 29, 1955 4 Sheets-Sheet 3 HHH /1 L mm INVENTOR E. E CAMPBELL ATTORNEYS Aug. 7, 1962 E. F. CAMPBELL 3,048,087

WEAPON MOUNT Filed July 29, 1955 4 Sheets-Sheet 4 L INVENTOR E. F. CAMPBELL BY dwz- ATTORNEYS United States Patent O 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 payment of yany royalties thereon or therefor.

This invention relates to an ordnance system and apparatus therefor, and more particularly to `a single, compact, relatively light weight weapon which offers maximum protection over a variety of combat conditions.

The advent of supersonic laircraft and missiles has imposed dillcult problems in regard to the design of defensive and offensive equipment adequate for use against these type of targets. Heretofore, the speed of attacking aircraft and the early type of missiles was relatively slow in comparison to those in present day use, thus providing an ample time factor for locating the target, bringing a weapon to bear thereon and ring. Under such circumstances the target could be engaged a relatively short range and the equipment generally employed against such a target was accordingly designed for short range operation.

The tremendous increase in speed of present day attacks has, however, reduced this time factor to such an extent that it is now necessary to initiate defensive or offensive measures when the target is located at a considerable range or distance from the weapon station. Long range weapons for operation against high speed aircraft and missiles have been developed, such weapons are generally large in size and of heavy construction and limited to long range use. While existing requirements now call for these long range weapons, the need still exists for the conventional weapons which are particularly eifective within short ranges since efforts :at short range must be exerted should the extended range operation fail. Therefore, positions requiring complete defensive and oiensive equipment must include two separate weapons, the long range weapon and the short range weapon.

This solution of utilizing two separate weapons is not, however, generally satisfactory with many branches of the armed forces where space and weight factors are critical. For instance, installation of two separate weapons on naval vessels would require doubling the space and weight allowances previously accorded ordnance weapons on naval vessels. Moreover, where separate systems are used there is always the problem of coordination and the possibility of a` fatal delay between the switching from one system to the other. The Navy is particularly concerned with this problem vsince it must be prepared to take instant oifensive and defensive measures against maneuvering targets having an initial range yfrom between to 40 miles out until the target is within close proximity of the ship.

The present invention constitutes a single weapon oper- -able and controlled by a single fire control system which weapon and system provides the desired overall protection without the previous existing disadvantages above discussed. The weapon mount of the weapon system supports two complementing missile devices, one of which is adapted to launch missiles having a high kill probability within a range ysubstantially from six thousand yards out to approximately 20 to 40 miles, the other device capable of projecting missiles designed for ya high kill rate within a range up to approximately -six thousand yards. Both missile devices are controlled by a single tire control sysi 3,i8,87 Patented Aug. 7, i962 tem which automatically switches from one device to the other as the target moves through the respective operating 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 provide 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 wide range weapon having a lire control system which continuously directs the weapon on target automatically switching and selecting that portion of the weapon offering the greatest hit probability within the instant range or area of the target.

An additional object is to present a single, compact, relatively lightweight weapon system providing extensive coverage throughout a wide target range area wherein the target is continuously covered by a missile device which is exceedingly efficient in contact performance for the particular instant target area or range.

A further aim is to obtain a weapon system which automatically selects a missile device which is most elfec- -tive against the target under the instant battle conditions.

Other objects and many of the attendant advantages of this'invention will (be readily appreciated as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:

FIG. 1 is a diagrammatic representation of one embodiment of the present invention;

FIG. 2 is aside elevational wiew of ia shipboard weapon installation embodying the present invention with a portion of the ship broken away to show missile handling equipment;

FIG. 3 is an enlarged side view of the weapon of FIG. 2 in the missile loading position;

FIG. 4 is a front elevation view of the embodiment of FIG. 3;

FlG. 5 is a side elevational view of a modilied form of the present invention with portions broken away; and

FIG. 6 is a top plan View of the right hand of the mount illustrated in FIG. 5 with a portion of the weapon shield broken away.

For purposes of clarification the weapon system of the present invention will be described in two parts; rst, the weapon mount and modifications thereto dis-closed in FIGS. 2 through 6, and secondly, the weapon system or tire control system for the weapon shown in FIG. l with one embodiment of the weapon mount.

A preferred embodiment of a Weapon mount, generally indicated by the numeral l0, is shown in a shipl board installation in FIG. 2. The weapon mount 10 comprises a carriage 11 rotatably mounted on vertical stan 12. A weapon shield `1'3` `supporting two long range mis sile devices generally designated by numeral 14, and tw( short range missile devices indicated generally by numera 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 thereon if desired. Since the structure and operation i the same for both sides of the mount the following discus sion will be limited to one half of the mount containin,` one of each of the missile devices.

To the rear of the weapon mount l0, preferably locatet below deck, is a missile magazine 16 containing storag rack 17 for storing and retaining ready missiles. When i is desired to move a missile M up into launching posi tion on the weapon mount Al0 a rammer rail 18 is actuaten by chain 19 and sprockets 20 to move rammer car 21 under the selected missile M. As the rammer car 21 moves under the missile M downwardly depending car engaging lugs 23 enter a cooperating closed ended slot (not shown) in the car. The car 21 and missile M are subsequently moved forward until they are directly over elevatable rammer rail extension 24 in its horizontal position. The rail extension 24 is then raised by hoist means 25 to the position shown in FIG. 2 whereupon the car and missile are further advanced until they rest partly upon a xed rail 26 which is supported at one end by a portion 27 of the housing for magazine access 2S. During the preceding loading operations the weapon mount has been moved in train and elevation such that it is in the position shown in FIG. 3 whereby the missile launching rail 29 is aligned with the missile M to be received thereon. The rammer car 21 and missile M are accordingly moved forward up along the `fixed rail 26 through the pivoted door 30 of the housing for magazine access 28 until the vertical missile supporting lugs 31 have reached their forward position within the T-shaped slot 32 (FIG. 4) of the missile launching rail 29. The missile launching rail 29 is positioned outwardly from the side of the weapon shield 13 by fore and aft supporting plates 33 and connecting beam 34. Once the missile has reached its launching position on the missile launching rail 29 the rammer chain 19 and rammer car 21 are retracted back to their initial position within the magazine 16, the missile M being retained in place on the missile launching rail 29 by means of the spring bias check means commonly employed in missile launchers and not illustrated herein.

Missile M of the long range missile device 14 is thus in launching engagement on the weapon mount 10 and ready for firing. The' short range missile device 15 comprising barrel 35 and conventional loading means (not shown) for automatically feeding rounds into the breech end of the barrel 35 has also been operated to place the device in a ready tiring position. Hence, the weapon mount has two missile devices in tiring condition, each device capable of expelling a missile which has ballistic characteristics considerably different from the other, one designed for efcient operation at long target ranges, and the other specifically adapted to provide close `and effective coverage by expelling numerous short range missiles should the former fail to destroy the target.

A modified embodiment of the weapon mount and loading arrangement is disclosed in FIGS. 5 and 6. It is to benoted that in the weapon mount 1'4 of FIGS. 2 through 4 the weapon shield 13 is supported for elevational movement and the missile devices 14 and 15 being rigidly attached thereto are properly elevated by the raising and lowering of the shield. FIGS. 5 and 6 show a more conventional weapon mount 36 having a rotatable shield 37 and a missile barrel 38 mounted for elevational movement within the shield 37 on trunnion shaft 39. The conventional trunnion shaft 39 is modified by coupling trunnion shaft extensions 40 at each end thereof, the trunnion shaft extensions 410 being supported intermediate their ends by bearing structure 41. A missile launching rail 42 is secured to the outer ends of each of the trunnion shaft extensions 40. A missile magazine 43 is provided having an overhead rammer rail 44, `a rammer car 45 and suitable ramming means such as the usual rammer chain (not shown). The missile M is moved into missile launching rail engagement in a manner somewhat similar to that previously described in that the missile M, being attached to the rammer car 45 by lugs 46, is advanced to a position beneath the elevatable rammer rail extension 47. A pivoted door 48 (which serves as a blast deflector in door closed position) is then opened to allow the rammer rail extension 47 to be raised by hoist means 49 to its dotted line position shown in FIG. 5. Subsequently, the car and missile are moved forwardly andupwardly until the missile M engages the missile launching rail 42 and is retained i in place thereon by the retaining means previously described.

The weapon system which controls either of the weapon mounts 10 or 36 is illustrated in FIG. 1. The system cornprises the usual fire control components utilized in a conventional system such as a radar unit having a radar antenna 50 and a radar scope 51; a weapon director 52, mount stabilizer 53, a short range missile ballistic computer (gun) 54, a long range missile ballistic computer 55, and train and elevation control mechanisms v56 and 57, respectively. In addition, to the above components the system also includes an analyzing and selecting circuit means composed of a pip senser 58 which operates in conjunction with the radar scope 51, an amplilier 59 and a computer switch relay 60. Pip senser 58 may be a senser of the photoelectric or photoconductive type. Since the weapon mount supports two types of missile devices, each device having ballistic characteristics ditferent from the other, the primary function of the weapon system is therefore to continually train and elevate both missile devices on the target simultaneously analyzing the desired ballistics necessary for intercepting the target at any instant in its course and selecting the missile device whose ballistics meet those demanded. In performing this function the system operates in the following manner. Assume that a target is `detected by the radar unit and a pip P appears over the numeral 15 on the scale 61 of the radar scope 5-1 indicating that the targets range is approximately 15,000 yards. Since the light sensitive pip senser 58 is actuated only When the light emitting pip P appears within a range of 6000 yards no signal will be generated thereby and the computer switch relay 60 will not be energized, the switch 62 thus remaining in its spring biased (missile ballistics computer) position.

The incoming signal is transmitted from the radar antenna 50 through weapon director 52 and into the mount stabilizer 53 where correction for the ships roll, pitch, etc. are made. The information derived from the weapon director S2 and mount stabilizer 53 is then fed into the missile ballistic computer 55, since the computer switch 62 is in its spring biased position. Subsequently, the intelligence obtained from the missile ballistic computer 55 is transmitted into the train control 56 and the elevation control 57 which will in turn act to move the weapon mount such that the missile devices thereon are on target. It is to be noted that in the above example the targets range of 15,000 yards fell Within the range area of between 6000 to 18,000 yards .wherein the long range missile device is primarily designed for eicient operation and the system has automatically selected this missile device by channeling the incoming signal through the missile ballistic computer 55. As the target approaches, the system continually changes the elevation and range of the missile device 14 and it is at all times ready for tiring. If due to the failure of missile device 14 to destroy the target, or for various tactical reasons the target continues, or is allowed to continue to approach the weapon, then the pip P will gradually recede down scale 61 indicating the closing of the target range. When the pip P reaches the 6000 yard range indicia the light given of by the pip P will cause the pip senser 58 to initiate a signal. The signal thus generated lwill be amplified by -amplier 59, and further fed to energize the magnetic coil 63 of the computer switch relay 60. Switch 62 is thereby urged upperwardly causing the ilow of signals and information to bypass 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 range and the weapon system is thereby locked in engagement with the short range missile device which is specifically designed for operation within Ithis range area. Should a target pass from the close range area out into the distant range area then the above-described procedure will be reversed, the weapon system automatically switching over to the long range missile device as the target moves out beyond the 6000 yard range.

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.

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 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 missile storage chamber positioned generally below and to one side of said Weapon mount, said missile storage chamber having an upper pivoted door in that portion of the chamber nearest the weapon mount, a missile carrier located within said chamber for engaging and moving a missile from the chamber to one of said missile receiving and launching devices, a pivoted guide -rail within the chamber adjacent the pivoted door for directing said missile carrier to said door, and means for elevating said pivoted guide rail'to an elevated missile ejection position, whereby when said weapon mount is moved in azimuth and elevation to a position such that one of said missile receiving and launching devices is aligned with said pivoted guide rail in its elevated position, said missile carrier with a missile thereon may be advanced along said guide rail until said missile is engaged with the aligned missile receiving 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 overhead rammer rail extending along the top wall of the missile storage chamber, said guide rail forming an extension 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 missile storage chamber, said guide rail forming an elevatable extension of the rammer rail.

4. A missile storage l'and loading apparatus for a 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 access compartment, cover means hingedly attached to said compartment and adapted to open in a direction toward 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 missile supporting and launching device, said missile carrier 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 position to an elevated position in alignment with said cover means, hoist means for raising sa-id pivotal extension 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 supporting and launching device is moved in train and elevation to a position such that it is aligned with the cover means said missile carrying car with a missile thereon may be moved by the rammer means along the rammer rail until thecar and missile are supported entirely by the forward pivotal extension in its horizontal position, said extension .then being raised to its elevated aligned positionto allow for further advancement of the car and missile through the missile storage chamber access compartment andacover means until the missile is engaged and retained by said missile supporting and launching device.

References Cited in the iile of this patent UNITED STATES PATENTS 2,425,425 Jorgensen Aug. 12, 1947 2,557,949 Deloraine June 26, 1951 2,629,289 Hunter Feb. 24, 1953 2,655,079 Aldrin et al. Oct. 13, 1953 FOREIGN PATENTS 692,140 Great Britain ,g May 27, 1953

Images