Ihe invention relates to the launching of projectiles and in particular to trainable launchers for operation on ships.

Defensive weapon systems generally require a scanning target detection system, a trainable launcher for launching one or moreprojectiles towards the target and means to guide the projectiles to the target. Known systems are cc-πplex and heavy, leading to reliability, cost and top-weight penalties when used in a marine environment.

Theobjectof the invention is toprovide alauncher to overcomeabove mentioned problems associated with existing launchers.

The invention provides a ship's projectile launcher comprising:

a) a projectile magazine having walls defining an enclosure for storing projectiles and one wall member adapted to locate projectiles in a firing position; b) means to move projectiles from the stored position to the firing position; and c) a plinth mounting cooperating with the magazine such that, in use, the magazine is rotatable about an axis parallel to the longitudinal axes of the projectiles; thearrangement being such that themagazinewall e_±>er is rotatable about an axis perpendicular to the magazine rotation axis and a means is provided to move the wall member between the closed and a pivotally rotated open position whereby the projectiles in the firing positionmay be directed towards a target.

In an advantageous arrangement a target detection device is rotatably mounted on the magazine. Preferably an optical target tracker is located on the pivotal magazine wall.

In one embodiment the magazine is arranged such that the one wall member is hinged to themagazine and thewallmember ispivotallymovable from

a closed position to a firing position. Ahydraulic rammay be used to open the magazine. Inthis arrangementdeflectorplatesareprovided todeflect missile exhaust gases away from the magazine.

In a second erjόodiment themagazine comprises two opposed sidewalls and a means to retain missiles adjacent to the respective side walls and a further means to rotate the sidewalls togetherwith the retainedmissilesto afiringposition. Advantageously inthisembodimenttwocolinear elevation shafts are connected to the side walls and these are arranged such that on initiationof the firing sequence thesidewalls arefirstmovedawayfromthe magazine and then rotated to the correct elevation angle for firing.

Preferablymissiles are stored in atleastonelinebetweenupperano lower conveyors, the conveyors being oveable synchronously to move one or moremissiles to a loadeα position adjacent said at least onewallmember. A releaseable retaining means is preferably provided to retain said loa eo missiles. Convenientlytheconveyors eachcompriseanendlessbeltmoveable onpulleys around a carriage, indexingmeans tomovethecarriage froma first position to a secondposition adjacent saidatleastonewallmember, means to lock the belt relative to the carriage and a further means to lock the belt relative to the magazine, the belt locking arrangements and the carriage movements being such that missiles can be transportec froma storedposition to afiring position as required. Preferably the endless belts areproviαe with locating holes for respectively engaging the top and bottcr.* of each missile.

The invention will now be describee by way of example only with reference to the accompanying Drawings of which:

Figure 1 shows a perspective view of a launcher in target detection mode; Figure 2 shows the launcher in target tracking mode; Figure3 showsa sideelevationofanalternativearrangementofthelauncher; Figure 4 is a side elevation perpendicular to the Figure 3 view; Figure 5 is a perspective view of the Figure 3 launcher in target tracking mode;

Figure 6 is a perspective view, part cut away, of a missile conveyor arrangement; Figure 7 is a sectioned view through one pulley carrying the upper conveyor

belt of Figure 6;

Figure 8 is an illustrative section through the upper conveyor of Figure 6 showing the conveyor carriage support and conveyor belt brake arrangements;

Figure 9 is a schematic plan section for illustrating the missile loading sequence; and

Figure 10 is a cut away end view of the launcher showing the mechanism for retaining the missiles in the launch position.

A ship's projectile launcher, shown in Figures 1 and 2, comprises a magazine 10 rotatablymounted on aplinth11. Oneendwall 12 of themagazine 10 is attached to themagazinebymeansof ahinge13 extendingalong thelower edge 14 of the end wall. A radar 15 is electronically stabilisedand rotated about the vertical axis by a driven shaft (not sham) which extends through themagazine 10 such that there isnotorqueon themagazine. Movement of the launcher assemblydue toshipmotion ismeasuredbyan inertial reference unit εituateo in the plinth 11 which provides signals needed for electronic stabilisation of the radar 15. At the upper end 16 of the pivotal magazine wall 12 there is provided an electro-optic tracking sensor 17.

As can be seen in Figure 2 themagazinewall 12 canbeopened toapre¬ determined zenithanglebymeans ofa ram18. Preferably the ram ishydraulic or pneuiriatic, hα-/ever an electro-mechanical ram properly protected to prevent sparking could also be used. As sham the projectiles 19 are stored in side-by-siάe pairs in two columns. A conveying means (not sham) is provided inside themagazine tomove theprojectiles19 t -zards thewall 12 so as to fill the two missile receptacles 20 provided in the wall 12. The projectiles will have retracted fins (not shown) fordeployment in flight and are retainedwithsufficient separation inthewall receptacles20 so that the projectiles do not mutually interfere on launch.

Drive motors for the magazine and radar unit are housed within the plinth 11. A "quill" drive is connected to the radar 15: a drive shaft locatedwithinacylindrical housinglengthwisewithinthemagazine such that torque effects on the magazine are min__mal. At the base of the pivotal wall 12 there are provided two angled deflector plates 21, one at thebase of each missile receptacle 20. The deflector plates 21 act to deflect projectile exhaust gases downwards and away from the magazine.

On firing a salvo of four projectiles there islittleor no reaction moment on the elevation and azimuthal training drives. On completion of firing, thepivotalwallmember12 isclosedfor rechargingwithmissiles from the magazine.

The invention provides a simple rugged solution which can be made lightweight, and cheaply. Where, for a particular application, the electro- optic sensor 17 cannot be located on the wall 12 it can pivotallymounted on the side 22 of the magazinewith a link connected to thepivoted wall 12 such that the axis of the sensor 17 is parallel to the projectile 19.

Figures 3-5 shew an alternative arrangement of the invention. As in the previous arrangement amagazine 30 is rotatablymounted on aplinth31 withmissilesstoredverticallyinthemagazine. Aradar32 ismountedontop of the magazine 30 for rotation about an axis 32'colinear with the magazine rotation 30' axis. Two opposed wall members 33,34 of the magazine 30 are provided to move missiles 35 from a stored position to a firing position as sh m in Figure 5. Two colinear half shafts 36,37 are connected to the respective wall merr ers 33 and 34. On initiating target trackin- the two shafts 36,37 move axially away from one another to thereby move the wall me oers 33,34 fromclosed positions toopenpositions indicatedbythebroken lines 38,39. Fromthe openposition, rotationof theshafts35,36 alters the elevation of four missiles, as sham, located in each of the wall members 33,34 and rotationofthemagazineabout theplinthaxis30'alterstheazimutli angle of the missiles.

Figures6-10 illustrateonemechanismforloading themissiles35 in the launching position on the wall members 33 and 34. As can be seen particularlywith reference toFigures 6 and9 themissilesarelocated intwo lines arranged side-by-side adjacent eachlongfixed side 40 of themagazine 30. Each pair of lines of missiles 35 is located in the magazine between upperandlowercontinuousconveyorbelts41and42 rotatableaboutpulleys43 extending along the magazine between positions 44 and 45 when centralised (Figure 9). One upper pulley 43 has an axially connected toothed gear 46 engaging a similar toothed gear 47 which has a toothed portion 48 driving a toothed belt 49 engaging a similar toothed portion 50 on the lcwer pulley43

beneath the toothed gears. Tne toothed belt 49 ensures that the upper and lα/er conveyor belts remain in register. Thepulleys 43 are located at each end of upper and lower carriages 51 and 52. Upstanding lugs 53 on both sides of the two carriages 51 and 52 are provided to locate the carriages between complementary lugs on the upper and lower members of the magazine (54 in Figure 8) such that the carriages can be selectively slid axially together tαrardswall member 33 or 34 (position55 or 56), as indicatedby arrows 57 on rotation of an indexing rod 58. A pulley brake (indicated by reference numeral 59) is provided such that the conveyor movement relative to the carriagescanbelocked. Eachmissile isprovidedwithanumber of spigots60 on the expansion cone 61 to engage holes 62 provided therefore in the lαver conveyor belt 42. Theupper belt is alsoprovidedwithholes63 toengage the noses of the missiles.

As canbe seen in Figure7 theconveyorbelts41 and42 are formedwith a central longitudinally extending toothed section 64 engaging a cor.ple entary geared portion 65 on the respective pulleys 43. ϊi.e upper pulleys 43 are cut away to produce two axially spaced portions 66,67 of reduced radial extent to alia; passage of themissile noses. Abeltbrake68 fixed to the side of the magazine is provided to lock the conveyor belts relative to the magazine.

Operation of the loading mechanism, assuming thatbothwall launchers (33 and 34) are initially empty, is as follα ^* .s:

1. Engage the pulley brake 59.

2. Move the indexing rod 58 connected to one pair of side carriages 51,52 of onemissilelaneand the indexing rod69 connected to the othermissilelaneso as to move pivoted links 70,71 connecting the indexing rods to the carriages from position (2) to position (1).

3. Energise retaining wings 72 on launch wall 33 (Figure 10) to retain missiles 1-4

4. Release pulley brake 59 and engage belt brake 68.

5. Move indexing rods 58,69 fromposition (1) to (2), leaving launchwall 33 loaded with missiles 1-4 (Figure 9).

6. Release belt brake 68 and engage pulley brake 59.

7. Move indexing rods from position (2) to position (3).

8. Disengage pulley brake 59 and engage belt brake 68.

9. Move indexing rods from position (3) to position (2).

10. Disengage belt brake 68 and engage pulley brake 59.

11. Move indexing rodsfromposition (2) toposition (3), leavingmissiles5-8 loaded in launch wall 34.

12. Energise retaining wings 72 on launch wall 34.

13. Disengage pulley brake 59 and engage belt brake 68.

14. Move indexing rods fromposition (3) to position (2) leaving launchwall 34 loaded and ready to fire missiles 5-8.

The launcher arrangement illustrated in Figures 3-10 having side launch "panniers" in place of a front opening door offers three main advantages: a) Improvedchannelsof fire-onepanniercanbeloaded as theotherisbeing fired; b) Improved balance compared to the front door arrangement; and c) Problems due to missile efflux on rounds remaining in the magazine are minimised.

Bymoving apart thesidepanniers prior to rotation, weather sealing oftheseunitstothebodyof themagazine isfacilitated. It isnevertheless possible for the side wall panniers to be rotated directed f om the closed condition providing a suitable sealing arrangement is provided.