Search Images Maps Play YouTube News Gmail Drive More »
Sign in
Screen reader users: click this link for accessible mode. Accessible mode has the same essential features but works better with your reader.


  1. Advanced Patent Search
Publication numberUS3102451 A
Publication typeGrant
Publication dateSep 3, 1963
Filing dateOct 31, 1958
Priority dateJul 29, 1955
Publication numberUS 3102451 A, US 3102451A, US-A-3102451, US3102451 A, US3102451A
InventorsCampbell Ernest F
Original AssigneeCampbell Ernest F
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Weapon mount
US 3102451 A
Previous page
Next page
Description  (OCR text may contain errors)

Sept. 3, 1963 E. F. CAMPBELL WEAPON MOUNT 4 Sheets-Sheet l Original Filed July 29, 1955 INVENTOR E. F. CAMPBE LL ATTORNEY $122 www0 mObomm-.D zOmqwB ruban-EGO mu-...wjl-qm ZD@ Y wm E Sept. 3, 1963 E. F. CAMPELL WEAPON MOUNT 4 Sheets-Sheet :2

Original Filed July 29, 1955 Y INVENTOR E. FI CAMPBELL BY Z Z ATTORNEY Sept. 3, 1963 E. F. CAMPBELL 3,102,451

wEAPoN MOUNT Original Filed July 29, 1955 4 Sheets-Sheet 5 FIG 5 FIG. 4

INVEVTOR E. E cAMPeELL Sept. 3, 1963 E. F. CAMPBELL WEAPON MOUNT 4 Sheets-Sheet 4 Original Filed July 29, 1955 INVENT OR E.F. CAMPBELL M Maw ATTORNEY United States ddd-2,4m Patented Sept. 3, i963 3 Claims. (Cl. 89--llll) (Granted under Title 35, UE. 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 any royalties thereon or therefor.

This case is a divisional case of application Serial No. 525,403, tiled July 29, 1955, now Patent No. 3,048,087.

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 aircraft and missiles hasv imposed ditlicult 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 firing. Under such circumstances the target couldbe engaged within a relatively short lrange 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 eiective within short ranges since eitorts at short range must be exerted should the extended range operation fail. Therefore, positions requiring complete defensive and offensive 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 t-o the other. The Navy is particularly concerned with this problem since it must be prepared to take instant offensive and defensive measures against maneuvering targets having an initial range from between 30 to 40 miles out until the target is within closer proximity of the ship. Y

The present invention constitutes a single weapon operable and controlled by a single tire 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 substantially from six thousand yards out to approximately 20 to 40 miles, the other device capable of projecting missiles designed for a high kill rate within a range up to approximately six thousand yards. Both missile devices are controlled by a single lire control system 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 provide a weapon system which permits defensive and oiensive action over a large area of combat conditions.

It 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 2() 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 ottering the greatest hit probability within the: instant range or area of the target.

An additional object is to present 4a single, compact, relatively light weight 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 effective against the target under the instant battle conditions.

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

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

FIG. 2 is a side elevational View of a shipboard weapon install-ation 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;

FIG. 5 is a side elevational View of a moditied Iform 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 clarication the weapon system of the present invention will be described in two parts; iirst, the weapon mount and modifications tire-reto disclosed in FIGS. 2 through 6, and secondly, lthe weapon system or fire control system tor the weapon shown in FIG. -1 with one embodiment of the weapon mount.

A preferred embodiment of a weapon mount, generally indicated by the numeral lli, is shown in a shipboard installation in FIG. 2. The weapon 'mount l@ comprises a carriage 1l rotatably mounted on vertical stand l2. A Weapon shield 13 supporting two long range Imissile devices lgenerally Idesignan-:d by numeral i4, and two short range missile ydevices indicated Agenerally by numeral l5, is suitably seated within the :carriage il for yelevational movement. While the weapon mount lll is shown (FIG. 4) supporting two missile devices of each type it i-s to be understood that only one of each .type may 'be supported thereon if desired. Since the structure land operation is the same -f'or Iboth sides 'of the mount the following discussion will be limited to one half of the mount containing one of each yof the missile devices.

To the rear of the weapon mount itl, preferably located below deck, is a missile magazine 16 containing storage rack 17 for storing and retaining ready missiles. When it isdesired to move a missile M up into launching position on the weapon mount a riainmer rail i8 is actuated by chain 19 `and sprockets 20 to move rammer car 21 under the selected missile M. As the -ramrncr car 2l moves under the missile M downwardly depending car engaging lugs 23 enter a coopera-ting closed ended slot (not shown) in the car. The car 2l yand missile M are subsequently moved forward until they are directly over elevatable rammer rail extension Z4 in its horizontal position. The rail extension 24 is Ithen raised by hoist means 25 to the position shown in FIG. 2 whereupon the car and missile Iare further advanced until they rest partly upon a lixed rail 26 which is supported at one end by a portion 27 of the housing for magazine access 28. During the preceding loading operations the Weapon mount lll has been moved in train and elevation such that it is 1n the position shownv in FIG. 3 -whereby the missile launching rail 29 is aligned with the missile M to be received thereon. The raminer car 21 and missile M lare accordingly moved forward up along the lined rail 26 through the pivoted door 30 of `the housing for magazine access .2S until the vertical missile supporting lugs 3l. have reached their forward position within the T-shaped slot 32 (FIG. 4) of the missiley 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 ybeam 34. Once the missile has reached its launching position on the missile launchmg rail 29 the rammer chain 19 4and rammer car 21 are retracted back to their initial position within .the magazine i6, the missile MV ybeing retained in place on the missile launching rail 29 by means of the lspring bias check means commonly employed in missile launchers Iand not illustrated herein.

n Missile` M of the long range missile device 14 is thus in llaunching engagement on the weapon mount` 10 and ready for firing. The short range missile device l5 comprising barrel 35 and conventional loading means (not shown) for automatically feeding rounds linto 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 firing condition, each device capable of expelling a missile iwhich has ballistic characteristics considerably different from the other, one designed for efficient operation at lon-g target ranges, land the other Ispecifically adapted to provide lclose and effective coverage by expelling numerous short range missiles should the yformer fail to destroy the target.

A modified embodiment of the weapon mount :and loading arrangement is disclosed in FIGS. 5 `and 6. VIt is to be noted that in the weapon mount 14 of FIGS. 2 through 4 the wea-pon shield 13 is supported for elevational movement land the missile devices 14 and 15 being rigidly attached thereto lare properly elevated by the raising and lowering of the shield.A FIGS. 5 land 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 3'7 on trunnion shaft 39. The conventional trunnion shaft 39 is modied by coupling trunnion shaft` extensions dll -at each end thereof, the trunnion shaft extensions ttl being supported intermediate their ends by Ebearin-g structure 41. A missile launching rail t2 is secured to the outer ends ofeach of the trunnion shaft extensions 46. A missile magazine 43 is provided having an overhead rammer rail 44, ya ramrner car 45 and suitable ramming means such- Ias the usual ramrner 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 deilectQr 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 .i Subsequently, the car Iand missile are moved forwardly Iand upwardly until the missile M engagesthe missile launching rail 42 and is retained in place Ithereon by the retaining means previously described.

The weapon system which controls either of the Weapon mounts 10 `or 36 is illustrated `in FIG. l. The system comprises the usual lire control components utilized in a conventional system such as a radar unit having a radar antenna 50 and ya rada-r scope 5l; a weapon director 52, mount stabilizer 53, a short range missile ballistic computer (gun) 54, ya long range missile ballistic computer 55, land train and elevation control mechanisms 56 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 :amplier 59 and a computer switch relay 60. Pip senser 58 may be a senser of the photoelectric or photoconductivetype. Since the weapon mount supports two types of missile devices, each device having ballistic characteristics different fromv the other, the primary function of the weapon system is therei fore to continually train and elevateboth missile devices on the target simultaneously analyzing the desired ballistics necessary for intercepting the targetat any instant in its course and selecting the missile 'device whose 4ballistics meet those demanded. ln performing this function the system operates in the following manner. Assume that a target is `detected by the radar unit and `a pip i appears over the numeral '16 on the scale 61, of the radar scope 51 indicating that the targets range is vapproximately 16,000 yards. Since the light sensitive pip senser SS is actuated only when the light emitting pip P appears within a range of 6G00 yards no signal willbe generated thereby and the computer switch relay 6u will not be energized, the switch 62 thus remaining in its spring biased (missie |ballistics computer) posi-tion. Y

The incoming signal is transmitted from theradar antenna Sli tluough weapon director 52 andinto the mount stabilizer' where correction for the ships roll, pitch, etc.

60G() to 18,000 yards wherein the long range missile devi is primarily designed for efficient operation and the system has automatically selected this missile device by channel-ing the incoming signal through the missile ballistic computer 455. As the target approaches, the system continually changes the elevation and range of the missile device l-t and it `is -at all times ready for tiring.v .1f due to the failure of missile device 14 to Vdestroy 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 161, indicating the closing of the target range. When the pip P reaches the 6000 yard range indicia the light given off by the pip P will cause the pip senser 58 to initiate a signal. The signal thus generated will be amplifiedy by -amplilier 59, and further fed to energize the magnetic .coil 6"3 of the computerV from the close range area lout 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 6G00 yard range.

The particular range scale disclosed in PEG. 1 and the range areas used in the description of the operation of the system are but one of many -combinations which can be used, the range scale and range area varying of course with the specific type of missile devices employed. While the .coverage yof 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 exten-ded 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 specically described.

What is claimed is:

1. A multirange target destroying weapon comprising a weapon mount supported for transverse and elevational movement, a iirst and a Isecond missile launching device supported by said weapon mount, a control system for said KWeapon mount, said control system comprising radar lire control apparatus mounted upon said weapon mount, a radar scope associated (with said radar apparatus, pip senser means disposed to sense `a range area of said radar scope, light emitting signals occurring in said range area -being sensed by said pip senser to cause a signal to be generated, an amplifier to amplify said generated signal, a computer switch relay actuated in accordance with the output signals from said amplifier, a Weapon director, a mount stabilizer to modify said Weapon director output in accordance with instantaneous position of said weapon mount, a iirst ballistics computer lfor said lirst missile launching device and a second ballistics computer for said second missile launching device, said computer relay selectively feeding signals to said rst or said second ballistics computer in accordance fwith the presence or absence of light emitting signals in the range area covered by said pip senser, and train and elevational control means selectively responsive to signals from said lirst and said second ballistic computers to effect train and elevational control of the weapon mount in accordance with the attitude requirements of the missile launcher device corresponding to the selected missile computer.

2. A multirange target destroying weapon comprising a rst missile device suitable for destruction of a target at a relatively long range, a second missile device suitable or destruction of a target at a comparatively short range, a weapon director to give a signal output corresponding to varying azimuth and elevational directions of said target, a stabilizing means to effect corrective train and elevational control means serving to actuate selectively the lirst missile device or the second missile device for correct iiring attitude to destroy the target, target detection means disposed in proximity to said missile devices, said target detection means comprising visu-al presentation means, said visual presentation means having a visible sweep graduated in accordance with target range, a iirst area of said sweep corresponding to optimum elective destroying range of said second missile device, a second portion ot the sweep corresponding .to the optimum eifective range of destruction af said first missile device, target range indication means disposed ion said sweep means in accordance with the instantaneous range of the target, means to sense and detect said target range indication means over a selected portion of the sweep corresponding to the effective target range of said second missile device, and means responsive to said target indication detecting and sensing means to select the appropriate tirst missile computer `or second missile computer to thereby cause train and elevation control and liring of the appropriate missile device in accordance with instantaneous range of the target.

3. A missile destroying system for destroying a target comprising a support means, a iirst missile ejector and a second missile ejector mounted on said support means, means to alternatively engage and fire said rst and said second missile ejectors, means to effect train and elevation control selectively of said first and said second missile ejectors, a rst computer to supply information relative to said first missile ejector to said train and elevation control means, a second computer to supply information relative to said second missile ejector to said train and elevation control means, computer switch relay means to selectively steed signals to said rst computer and said second computer, an amplifier having output to actuate j said computer switch relay to selectively engage said rst signals in laccordance with a fixed reference position of the target destroyer at a particular instant, a rst missile computer, a second missile computer, means tEor effecting train control, means for eiecting elevational control, said missile ejector computer and said second missile ejector computer, a radar device having a radar scope with a scale representation thereon, said scale representation being graduated in accordance with target range, a sensing means to sense target pips on said scan presentation within a range from zero range to a range limit determined by the maximum range of said second missile ejector, target pips occurring within said last-named range being sensed by said sensing means, said amplifier amplifying said sensing signals thereby providing for said selective train and elevation control of said iirst missile ejector and said second missile ejector in accordance with instantaneous range of the target to provide a missile system capable of destroying at relatively long and relatively short ranges of the target.

References Cited in the tile of this patent UNITED STATES PATENTS 1,479,840 Stone Jan. 8, 1924 2,557,949 Deloraine June 26, 1951 2,670,134 Lakatos Feb. 23, 1954

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US1479840 *Aug 1, 1918Jan 8, 1924 stone
US2557949 *Aug 22, 1942Jun 26, 1951Standard Telephones Cables LtdFire control system
US2670134 *Dec 29, 1944Feb 23, 1954Bell Telephone Labor IncComputer for multiple ballistics
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3538318 *Aug 21, 1968Nov 3, 1970Hughes Aircraft CoWear weighting function generator for the determination of the proper aiming of a gun
US5661254 *Jan 21, 1997Aug 26, 1997Diehl Gmbh & Co.System for protecting a target from missiles
U.S. Classification89/41.7, 235/400, 89/127
International ClassificationF41F3/00, F41F3/04
Cooperative ClassificationF41F3/0406
European ClassificationF41F3/04B