GB2157405A - Multiple launcher for guided missiles - Google Patents

Abstract

A multiple missile launcher comprises a frame 1 including a support member 7 capable of carrying a plurality of missile canisters 10, the support member being adjustable in the frame to vary the direction of aiming of the missiles. An aiming unit 21 to control guidance of the missiles is positively located on a saddle 20 of the frame 1, yet is releasable so as to be independently moveable with respect thereto. In one arrangement (Fig. 2) the aiming unit is pivotably mounted on the frame 1, with locking pins (49, 50) actuable to selectively lock the aiming unit and frame together, or release the aiming unit to pivot independently, while in an alternative arrangement (Fig. 3) the aiming unit is received within a cradle (51) so as to be removeable from the frame when required. <IMAGE>

Description

SPECIFICATION Multiple launcher for guided missiles This invention relates to guided missiles, and especially those in which the guidance control is effected by an operator who must continu ously keep the intended target in his field of view.

Known guided weapon systems employ a control link between the operator and missile which may be by means of radar, radio, infra red, laser or other electromagnetic radiation.

In a known type of guidance system the missile is launched, either from a stand or supported by the shoulder of the operator.

The operator is further provided with an aim ing unit which includes an optical sight through which he must keep both the intended target and the missile in his field of view. The aiming unit further includes a joy stick control the position of which governs the directional instructions supplied to the missile via the control link. By manoeuvring the joy stick control the operator may guide the missile so as to intercept the target. This type of guidance where the operator must keep both target and missile in his field of view is known as Command Line of Sight (CLOS) guidance.

An alternative form of missile guidance is known as Semi-Automatice Command Line of Sight (SACLOS) guidance. In this system the aiming unit includes a television camera which is movable independently of the optical sight to track the missile as it recedes from the operator. The displacement of the missile from the centre of the field of view of the camera is automatically calculated and commands are automatically transmitted to the missile to maintain it in the centre of the camera's field of view. A stabilised aiming mark, corresponding to the centre of the field of view of the camera, is generated in the optical sight. The operator must keep the target in the field of view of the sight and uses the joystick to centre the aiming mark on to the target in the sight.The operator thus need not follow the path of the missile but may use the aiming mark to decide which joystick movements are necessary in order to intercept the target.

The SACLOS system repeatedly compares the position of the missile as seen by the camera and the line of sight through the aiming mark. To minimise errors the camera and the optical sight must both have a synchronised datum and both are therefore conveniently mounted closely one to the other on the aiming unit.

In an alternative SACLOS guidance system the requirement for the operator to operate a joystick control is obviated. In this arrangement the television camera and the optical sight are in a mutually fixed predetermined relative orientation one to the other. As before commands are automatically transmitted to the missile such that it is maintained in the centre of the camera's field of view. To guide the missile on to a target the operator merely manoeuvres the aiming unit so as to maintain the target in the centre of the field of view of the optical sight. Movement of the aiming unit to track a target in the optical sight correspondingly produces movement of the camera causing the missile to be continually guided into the centre of the optical sight.

It will be readily apparent that the optical sight and the aiming unit must be in a mutually fixed, predetermined relative orientation one to the other so that tracking the target in the sight correspondingly orients the aiming unit. Additionally the position from where the missile is launched must not be too great a distance from the aiming unit otherwise errors may be introduced into the guidance of the missile at short distances from the operator.

Even with these advanced semi-automatic guidance systems the task facing the operator is a particularly arduous and skilled one.

When the missile is shoulder launched, the operator must repeatedly raise and lower the missile launcher. Additionally he must keep steady the aiming unit to provide a clear view of the target in the optical sight throughout launch of the missile and subsequently its guidance. Furthermore when the intended target is an aircraft, both the target and the missile will be travelling at great speeds, often greater than the speed of sound. It is therefore very difficult for the operator to keep the target (as in the SACLOSA system) and possibly even the missile as well (as in the CLOS system) centrally located in the field of view of the sight.

After the operator has engaged a target there is a time period during which the spent missile canister is disconnected and replaced by a new canister containing a fresh missile.

During this reloading time the operator has no firing capability and is vulnerable to counter fire from hostile elements. The reloading period may be such that where the intended targets are supersonic aircraft, engagement of more than one of a group of aircraft is difficult as the other aircraft are often past and out of range.

There is therefore a requirement for a guided missile launcher which is capable of sequentially firing a multiplicity of missiles without the necessity of reloading therebetween. However the weight of a single missile plus the guidance equipment already approaches the maximum which can be controllably supported by the shoulder of an operator. Further missiles preclude such firing from the shoulder and make necessary the provision of a supporting stand or frame.

Such a frame must permit pivoting both in elevation and in azimuth, in order that the operator may orient the missile in any direc tion and after firing to keep the target (and missile if necessary) in the operator's field of view.

However, because of the added weight of the additional missiles the inertia of the supporting frame will be considerable. Having such a high inertia it will be difficult or even impossible for the frame to be manoeuvred sufficiently quickly or steadily to keep the target in the operator's field of view. Especially where the path of flight of an oncoming aircraft is laterally offset from the position of the missile launcher, the supporting frame may have to be pivoted very quickly in order to follow the aircraft as it approaches and even bypasses the launcher.

One known multiple launcher system overcomes the problem of high inertia with a motor driven supporting frame. There is provided a power driven turret, carrying a number of guided missiles and forming part of an armoured vehicle. This arrangement, however, suffers from a number of intrinsic disadvantages. Firstly the batteries powering the electric motors to drive the turret will require regular charging. Any generator used to charge the batteries will produce a considerable noise in operation, thereby aiding detection of the vehicle by hostile forces. In addition the generator will produce a heat signature, easily detectable by thermal imaging equipment. Furthermore, as the missile launcher is integral with the vehicle, the use of the launcher is limited by the accessibility of the desired launch site. The effectiveness of the missile system is thus dependent upon the vehicle.Should the vehicle be put out of service, either by hostile forces or due to mechanical failure, the effectiveness of the missile launcher is severely reduced.

It is an object of the present invention to provide a multiple launcher for guided missiles which overcomes or reduces the disadvantages associated with the prior art launchers previously described.

Accordingly there is provided a multiple launcher for guided missiles comprising a frame including a support member adapted to support a plurality of guided missiles each aligned in a predetermined direction with respect to the support member, the support member being adjustable in the frame to vary the absolute direction of aiming of the missiles; means for firing and guided missiles one at a time; and means for mounting and positively locating an aiming unit in a predetermined orienta tion with respect to the support member, the aiming unit being releasable so as to be moveable with respect thereto.

The invention also resides in a multiple launcher including an aiming unit, adapted to control guidance of the missiles when in flight.

The aiming unit preferably includes a transmitter for transmitting guidance signals to the missiles when in flight. The transmitter is conveniently a radio transmitter although frequencies throughout a wide range of the electromagnetic spectrum may provide suitable guidance signals. The transmitter aerial may conveniently also be mounted on the aiming unit. Alternatively there may be provided individual aerials in a canister containing each missile.

There is preferably provided a firing control unit adapted to control sequential firing of the missiles. This electronic unit is designed to select a missile for firing and activate a firing sequence in response to actuation of a trigger.

The requirement for electrical wiring to be disconnected from a missile after firing and reconnected to a subsequent missile is therefore obviated. It is only when all of the missiles supported by the support member have been fired that it is necessary to stop and reload. The firing control unit is conveniently integral with the aiming unit. An operator can therefore cause a missile to be fired whilst continuing to track a target with the aiming unit.

In a convenient embodiment the aiming unit includes a joystick, movement of which controls the guidance of the missiles. Alternatively the orientation of the aiming unit controls the guidance of the missiles.

The aiming unit is preferably mounted so as to be pivotable with respect to the support member about at least one of its axes, and there is provided means for locking the aiming unit and support member one to the other in mutually fixed predetermined relative orientation.

Preferably the aiming unit is mounted so as to be pivotable relative to the support member about two mutually perpendicular axes. This will permit the aiming unit to be oriented in any direction without it being necessary for the support member to be moved accordingly.

When there are missiles supported by the support member, its inertia can be considerable and the ability independently to adjust the direction of the aiming unit will considerably assist in the efficient tracking of targets.

In one convenient embodiment the support member and the means for mounting the aiming unit are provided one with one or more recesses and the other with one or more retractable pins, the pins being actuable to move into the one or more recesses to lock the aiming unit and support member one to the other. By actuating or retracting the one or more pins, the aiming unit can therefore be selectively either locked to the support mem ber in a predetermined orientation therewith, or alternatively released to pivot independently therefrom.

In an alternative embodiment the means for mounting the aiming unit is such that the aiming unit is removable from the support member. The aiming unit may be arranged so that when thus removed, it is constrained only by any electrical connections that must be maintained between the aiming unit and the support member. The aiming unit is thus easily oriented in any desired direction.

Conveniently in this case, the means for mounting the aiming unit comprises a cradle provided on the support member and adapted to receive and positively locate the aiming unit. The means for mounting the aiming unit may furthermore be provided with one or more arms of shaped cross section, the cradle being of complementary shape to receive and positively locate the arms and restrain the aiming unit The one or more arms may conceivably be integral with the aiming unit.

The invention also resides in a multiple launcher including one or more guided missiles supported by the support member.

The invention further resides in a vehicle incorporating a multiple launcher as heretofore described.

The invention will now be more particularly described, by way of example only, with reference to the accompanying drawings in which, Figure 1 is a rear view of a multiple launcher according to the invention, the launcher including missiles and an aiming unit, Figure 2 is a pictorial view of a part of the multiple launcher of Fig. 1, shown without the aiming unit, and Figure 3 is a pictorial view of a part of an alternative embodiment of multiple launcher in accordance with the invention.

In Fig. 1 there is shown a multiple launcher comprising a U-shaped frame, shown generally at 1, pivotally mounted on a heavy base 2 by means of a spindle 3 and bearing 4. The frame comprises two upright arms 5 con joined by a horizontal member 6 through which the spindle projects in the bearing 4.

Pivotally mounted between the two upright arms 5 is a support member 7 which includes a horizontal chassis 8 having four attachment saddles 9 in each of which is received and accurately located a canister 10 containing a guided missile (not shown). Also mounted on the chassis 8 is a firing control unit 11 connected to the missile canisters 10 by means of electrical connections 1 2.

Depending from the chassis 8 is a U-shaped subframe 13, the horizontal crossbeam 14 of which is interrupted at its mid-point by a lockable bearing 1 5 shown in greater detail in Fig. 2. The bearing 1 5 connects the subframe 1 3 to a yoke 1 6 which comprises two diverging arms 17, 1 8. At the end of one of the arms 17, is a trigger 1 9 for controlling locking of the bearing 1 5 whilst at the end of the other arm 1 8 there is a saddle 20 constituting means for mounting an aiming unit 21.

The aiming unit 21 includes an optical sight 22, a transmitter 23 and a joystick 24. The aiming unit further includes a trigger 25 for actuating the first control unit 11 to which it is connected by means of an electrical connection 26.

Figure 2 shows that part of the multiple launcher associated with the lockable bearing 1 5. The basis of the bearing 1 5 is a generally U-shaped hinge 30 comprising two upright plates 31, 41, rising from a platform 32. The two halves of the crossbeam 1 4 are rotatably attached to the hinge 30 by means of spindles 33 received in corresponding holes 34 provided in the upright plates 31, 41.

Each half of the crossbeam 1 4 has an annular collar 35, 36 located adjacent the upright plates 31, 41 respectively, one of which collars 36 is provided with a recess 37.

Rotatably attached to the underside of the platform 32 is the yoke 1 6 comprising the two arms 1 7 and 18 conjoined by an annular bearing plate 38 located adjacent the platform 32. The bearing plate 38 is provided with a recess 39.

Mounted on the upper surface of the platform 32 in a frame 42 is a pivot pin 44.

Located on the pin is a bell crank lever 45 having two arms 46 and 47 disposed substantially at 90 one to the other. Attached to the end of each of the arms 46, 47 via springs 48 are pins 49, 50 which are received in holes 51, 52 in the upright plate 41 and bearing plate 38 respectively. Movement of the pivot pin 44 and bell crank lever 45 is governed by the trigger 1 9 which is connected thereto by means of a sheathed cable 53, attached at 54 to a lever 55.

In use an operator grips the yoke 1 6 by means of the two triggers 1 9 and 25 and views the intended target through the optical sight 22. The trigger 1 9 is in its relaxed position and the bell crank lever 45 is in a position such that the pins 49, 50 engage in the recesses 37, 39 in the collar 36 and bearing plate 38 respectively. In this condition the pins 49, 50 lock the hinge 30 firmly to both the yoke 1 6 and crossbeam 14 preventing relative movement therebetween. The aiming unit is thus firmly locked to the support member 8 in a predetermined relative orientation. The arrangement is such that the direction of view as seen through the optical sight 22 corresponds substantially to the direction in which the guided missile canisters 10 are aimed.

While the aiming unit is thus locked to the support member 8, movement of the aiming unit to maintain the target in the field of view of the sight 22 will therefore track the target with the guided missiles. Movement of the aiming unit in azimuth causes the frame 1 to pivot on the spindle 3 to effect azimuthal adjustment of the direction of the missiles.

Similarly movement of the aiming unit in elevation causes the support member 8 to pivot between the two upright arms 5 to effect elevational adjustment of the direction of the missiles.

When the operator wishes to fire a missile he depresses trigger 25 which actuates the firing control unit 11 to initiate a firing sequence and launch a missile from one of the canisters 1 0. When firing of the missile has been accomplished the operator depresses trigger 1 9 causing the rocker member 45 to be rotated, withdrawing pins 49, 50 from their respective recesses 37, 39. This permits the yoke 1 6 to rotate with respect to the hinge 30 in order to facilitate azimuthal movement of the aiming unit without corresponding movement of the frame 1 or support member 8. Similarly the hinge 30 is now free to rotate with respect to the collars 35, 36 and the crossbeam 14, permitting movement of the aiming unit in elevation without corresponding movement of the support member 8.

It will be readily apparent that by a combination of movements in elevation and azimuth, the aiming unit 21 may be be oriented in any direction without the necessity for movement of the support member 8 and missiles. The operator maintains both the target and the receding missile in the field of view of sight 22 and adjusts the direction of flight of the missile with movement of the joystick 24. Movement of the joystick causes the transmitter 23 to transmit radio signals to the missile in flight via an aerial (not shown) present in the canister 10 that previously contained the missile. Alternatively an aerial may be provided as part of the aiming unit.

The radio signals are received by a corresponding aerial on the missile and control a missile guidance mechanism which adjusts the course of the missile.

In order for the operator to effectively guide the missile, the target and missile must be maintained within the field of view of sight 22 and it may well be necessary to employ rapid movements of the aiming unit to keep a quickly moving target in view. With the trigger 1 9 depressed the aiming unit is free to rotate independently of the support member 8 and is therefore more easily and rapidly moved Following engagement of the target it is desirable to reconnect the aiming unit 21 to the support member 8 so that a second target may be tracked and engaged. To achieve this the operator merely releases trigger 1 9 which causes the bell crank lever 45 to be returned to its original position urging pins 49, 50 against the collar 36 and bearing plate 38 respectively.The operator then returns the aiming unit to an orientation in alignment with the missile canisters 10 wherein the pins 49, 50 engage in the recesses 37, 39 locking the aiming unit in the correct position. Further movement of the aiming unit 21 causes the support member and missile canisters to be correspondingly moved.

It is conceivable that the aiming unit could be biased so as to return to the desired locking position when released by the operator. This would further reduce time between engagements as the operator need merely release the aiming unit and let it automatically orient itself and lock on to the support member. The operator is again able to grip the aiming unit and engage a target.

Fig. 3 shows part of an alternative embodiment of multiple launcher according to the invention. In the embodiment of Fig. 3, the crossbeam 14 is in two halves each of rectangular cross section and separated by a space 50. At the end of each half of the crossbeam 14 is attached a U-shaped cradle 51. The Ushaped crades 51 define rectangular recesses 52, 53 in each of which is received an arm 54, 55, the arms extending laterally from a saddle 20 constituting means for mounting an aiming unit (not shown). Ball catches 56 are provided on the U-shaped cradles 51 to retain the arms 54, 55 in the recesses 52, 53.

In use an aiming unit 21 is mounted on the saddle 20 and manoeuvred to track a target with the sight 22. Rotation of the aiming unit in azimuth or in elevation causes the arms 54, 55 to transfer the movement to the crossbeam 14 causing corresponding movement of the support member and missiles. After the missile has been launched as previously described, the aiming unit is lifted by the operator forcing the arms 54, 55 upwardly past the ball catches 56 and out of the recesses 52, 53. No longer constrained by the cradles 51, the aiming unit may be easily oriented by the operator to keep the target within the field of view of the optical sight 22, to guide the missile thereto with movements of the joystick 24.

When the engagement of the target is completed the aiming unit may be replaced in the cradles 51 with the arms 54, 55 'snapping' back past the 56 and into the recesses 52, 53. The aiming unit 21 is again firmly linked to the support member 8 in the desired predetermined orientation therewith.

It will be appreciated that either of the above described embodiments of multiple launcher may be easily adapted to employ an inertial control guidance system. The aiming unit 21 does not have a joystick 24 but is instead provided with a gyroscope (not shown). A similar gyroscope is present in each missile and the aiming unit 21 has a process ing unit to compare the orientation of the gyroscope in the missile in flight with that of the gyroscope in the aiming unit. Signals from the processing unit determine the directional instructions transmitted to the missile in flight by the transmitter 23.

It will be apparent to those skilled in the art that a variety of alternative arrangements may be employed without departing from the scope of the present invention. Indeed a selection of hinges, pivots or catches may all conceivably be employed.

Claims (14)

1. A multiple launcher for guided missiles comprising a frame including a support member adapted to support a plurality of guided missiles each aligned in a predetermined direction with respect to the support member, the support member being adjustable in the frame to vary the absolute direction of aiming of the missiles; means for firing the guided missiles one at a time; and means for mounting and positively locating an aiming unit in a predetermined orientation with respect to the support member, the aiming unit being releasable so as to be moveable with respect thereto.

2. A multiple launcher according to claim 1 including an aiming unit adapted to control guidance of the missiles when in flight.

3. A multiple launcher according to claim 2 wherein the aiming unit includes a transmitter for transmitting guidance signals to the missiles when in flight.

4. A multiple launcher according to any one of claims 1 to 3 wherein the means for firing the missiles comprises a firing control unit adapted to control sequential firing of the missiles.

5. A multiple launcher according to claim 4 wherein dependent on claim 2 wherein the firing control unit is integral with the aiming unit.

6. A multiple launcher according to any one of claims 2 to 5 wherein the aiming unit includes a joystick, movement of which controls the guidance of the missiles.

7. A multiple launcher according to any one of claims 2 to 5 wherein the orientation of the aiming unit controls the guidance of the missiles.

8. A multiple launcher according to any one of claims 2 to 7 wherein the aiming unit is mounted so as to be pivotable with respect to the support member about at least one of its axes, and there is provided means for locking the aiming unit and support member one to the other in mutually fixed, predetermined relative orientation.

9. A multiple launcher according to claim 8 wherein the aiming unit is mounted so as to be pivotable relative to the support member about two mutually perpendicular axes.

1 0. A multiple launcher according to claim 8 or claim 9 wherein the support member and the means for mounting the aiming unit are provided one with one or more recesses and the other with one or more retractable pins, the pins being actuable to move into the one or more recesses to lock the aiming unit and support member one to the other.

11. A multiple launcher according to any one of claims 1 to 7 wherein the means for mounting the aiming unit is such that the aiming unit is removable from the support member.

1 2. A multiple launcher according to claim 11 wherein the means for mounting the aiming unit comprises a cradle provided on the support member and adapted to receive and positively locate the aiming unit.

1 3. A multiple launcher according to claim 1 2 wherein the means for mounting the aiming unit includes one or more arms of shaped cross section, and the cradle is of complementary shape positively to locate the arms and restrain the aiming unit.

14. A multiple launcher according to claim 1 3 wherein the one or more arms are integral with the aiming unit.

1 5. A multiple launcher according to any preceding claim and including one or more guided missiles supported by the support member.

1 6. A multiple launcher substantially as herein described with reference to Figs. 1 and 2 or Fig. 3 of the accompanying drawings.

1 7. A vehicle incorporating a multiple launcher according to any preceding claim.