GB2539691A - Launching devices from a submerged launch platform - Google Patents

Abstract

A launch canister apparatus 100 is configured for ejection from a submerged launch platform. The launch canister apparatus is configured for carrying a plurality of aerial devices 102 from the submerged launch platform to surface. A floating and stabilized launch platform is provided by the canister apparatus 100 for the plurality of aerial devices 102 subsequent to surfacing of the launch canister apparatus 100.

Description

Launching devices from a submerged launch platform

FIELD OF THE INVENTION

This disclosure relates to launch of devices from a submerged launch platform.

BACKGROUND

Submerged vessels such as submarines have various uses, in particular by naval forces. A submarine may not have sufficiently effective counter measure to an aerial or small surface craft attack, for example attacks by anti-submarine warfare (ASW) capable helicopters. In particular, if ASW helicopter threat is in the immediate location of a submarine the only option available for the submarine may be evasion. Similarly, a surface vessel such as a ship can become vulnerable to a Fast Incoming Attack Craft (FIAC) or Fast Attack Craft (FAC) threat in a situation where an escorting submarine could be used to provide covert anti-FIAC/FAC to protect the surface vessel. However, FIACs and FACs typically comprise small fast moving surface crafts, and a submarine may not have effective enough weaponry or other equipment to counter this threat.

A submarine can try to counter-attack such threats e.g. by means of torpedoes and/or aerial weaponry such as missiles or other unmanned aerial devices launched into air. Torpedoes however may not always be effective against fast moving objects. Also, torpedoes are costly. A sub-surface to air missile capability would provide the submarine with an offensive capability to neutralise an anti-submarine warfare (ASW) threat. However launch of e.g. a missile from a submarine has certain difficulties as conventional launch solutions that could be used on land, on ships or other non-submerged platforms cannot be used as such. The conventional launch platforms and systems are not well suited for use on submerged platforms already because they are designed to launch aerial devices such as e.g. missiles into clear air, not through a layer of water. Also, deployment of these against multiple threats may not be possible.

Therefore improved launch of devices from a submerged launch platform would be desired.

SUMMARY

According to an aspect there is provided a launch canister apparatus, the launch canister apparatus being configured to be ejected from a submerged launch platform, carry a plurality of aerial devices from the submerged launch platform to surface, and provide a floating and stabilized launch platform for the plurality of aerial devices subsequent to surfacing of the launch container apparatus.

According to another aspect there is provided a method for launching aerial devices, comprising carrying by a launch canister apparatus ejected from a submerged launch platform a plurality of aerial devices, subsequent to surfacing of the launch canister apparatus, providing by the launch canister apparatus a floating and stabilized launch platform for the plurality of aerial devices, and launching the plurality of aerial devices from the floating and stabilized launch canister apparatus.

According to a more detailed aspect the aerial devices comprise surface to air missiles, surface to surface missiles and/or anti-aircraft missiles.

A control apparatus can be provided, the control apparatus being configured to, subsequent to launch of at least one of the aerial devices from the launch canister apparatus, control on-air operation of the at least one aerial device independently from controls of the submerged launch platform. The aerial devices may comprise missiles, each missile comprising control apparatus configured to acquire a target and guide the missile to the target. The control device can be adapted to switch between primary and secondary targets. Coordination of on-air operation of the aerial devices may also be provided. A staggered launch of the aerial devices can also be provided. Sensor apparatus for determining surfacing of the canister apparatus and configured to provide a surfacing signal to the control apparatus may also be provided. In response to determining surfacing, a buoyancy and stabilization device of the canister apparatus can be activated to provide buoyancy and stabilization for the launch of the aerial devices. A nose cap of the canister apparatus can be released and launch of at least one aerial device from the canister apparatus can be initiated immediately in response to the signal.

A launch canister apparatus may comprise buoyancy and stabilization petals and a petal drive mechanism configured to move the petals from a folded position to an expanded position to provide buoyancy and stabilization for the launch container apparatus. This can be provided in response to a surfacing signal. The petal drive mechanism may be configured to drive the petals to the expanded position for providing a weapon stabilisation platform for launch of a plurality of missiles from the launch container apparatus. Each petal may be provided with a flotation device. An inflatable flotation device may be provided at each petal.

According to yet another aspect of the present invention there is provided a computer program comprising code means adapted to perform, when run on processor apparatus, any of the herein described methods.

DESCRIPTION OF THE DRAWINGS

The present invention will now be described by way of example with reference to the accompanying drawings, in which: Figure 1 is a schematic diagram of a launch arrangement in accordance with an embodiment, Figure 2 is a schematic diagram of a launch canister apparatus in accordance with an embodiment, Figures 3 and 4 show sectioned views of two launch canister arrangements, Figures 5A -5D show an exemplifying launch sequence and a buoyancy and stabilisation device of launch canister apparatus, Figure 6 shows an example of control apparatus, Figure 7 is a flowchart for launch operation in accordance with an embodiment, and Figure 8 is an example of a possible submerged launch platform.

DETAILED DESCRIPTION OF THE DRAWINGS

The following description presents certain examples for launching a plurality of aerial devices, and more particularly launch of missiles such as anti-aircraft missiles (AAM) or anti-aircraft / surface missiles (AASM) and equipment for launch thereof from a submerged platform to enable person skilled in the art to make and use the invention, and is provided in the context of particular applications. Such devices are typically unmanned aerial devices. Examples of unmanned aerial devices/systems include unmanned aerial vehicles (UAVs) and various airborne intelligence, surveillance, targeting, defensive and reconnaissance systems. It is noted that in this disclosure the terms unmanned aerial device, anti-aircraft missiles (AAM), and anti-aircraft/surface missile (AASM) are used interchangeably, where appropriate.

A description of a possible launch apparatus construction is given with reference to Figures 1 -8 showing examples of various aspects of apparatuses for launching multiple antiaircraft / surface missiles (AASM) from a submerged platform or structure. The missiles can be for example dual capable anti-aircraft and anti-FIAC/FAC missiles. The dual capability refers to a sub-surface to air and at least a limited sub-surface to surface capability of a missile launched whilst the submarine remains submerged. The submarine can be considerably deep underwater. A plurality of missiles can be housed inside a launch container, referred herein as canister apparatus.

The canister apparatus enclosing a multiple of missiles can be launched e.g. from a torpedo tube. This is illustrated schematically in Figure 1 where canister apparatus 100 enclosing a multiple of missiles 102 is shown within a torpedo tube 404 of a submarine 401 (only a relevant part of the hull of the submarine shown). A torpedo launch version of the launch container apparatus can utilize launch rails currently used for missile launch from a helicopter but attached to the inside of the launch canister. In accordance with a non-limiting example, a 533 mm diameter canister can be configured to carry three or four missiles. A torpedo launch canister may be, for example, approximately 2.5 meters to 3 meters in length and can use the same mechanical and electrical interface that is currently used by torpedo tube launched weapons.

According to a possibility a multi-missile launch canister is housed within a under casing launcher (UCL) that is permanently fitted to the submarines pressure hull on under casing launcher cells. UCLs are launch devices provided outside the pressure hull of a submarine and configured to eject a payload from a launch tube adapted to withstand the dive pressures experienced by a submarine hull. Other exemplifying possibilities for providing a launch structure for the canister include ejector openings such as submerged signal ejector (SSE), casing holes, garbage ejectors and the like.

Figure 2 shows in more detail canister apparatus 100 configured to carry a multiple of AASMs 102a and 102b. For example, the canister apparatus may be adapted to carry three or four surface to air or dual mode (surface to air and surface to surface) missiles. Multiple missiles such as AASMs 102a and 102b can be carried in an enclosure of the canister 100. The canister is adapted for ejection through water for delivery of the AASMs into the airspace above the submerged launch platform. The launch canister can be adapted for ejection from any kind of underwater launch apparatus. The examples given herein assume the launch platform be a submarine, but the launch platform could equally be any other type of submerged platform or structure. The submerged platform can thus be e.g. a submerged delivery structure, or a submerged unmanned autonomous vehicle.

The canister launch structure provides a watertight launcher enclosure 121 adapted to carry the canister 100 and therein enclosed AASMs. The canister 100 is of sufficient size to house and store the multiple aerial devices. The launcher enclosure can have a circumferential shape. Other sizes, shapes and types of enclosures are also possible, for example to provide improved manoeuvrability, more efficient use of storage space and/or to accommodate particular shapes and/or properties of the launch platform and/or the canister apparatus.

The launch enclosure 121 is open ended at one end to facilitate exit of the launch canister 100. Depending on the application, a watertight nose cap at the open end 128 can be provided to prevent water ingress into the launcher enclosure.

The launch apparatus can include a drive module for ejecting the launch canister 100 from the enclosure and an end piece having an electrical connector for connection to the submarine by means of which power and/or data can be provided to the launch canister and/or the missiles enclosed therein. Launch canister 100 can be connected via an electrical connector arrangement for connection to the submarine. In this manner the devices within the canister can be charged and/or initialisation and combat system data uploaded to the devices. Figure 1 shows a data umbilical type connector 113 for the connection between the launch canister 100 and the launch platform.

The data umbilical can be used to exchange, for example, AASM initialisation data between the AASMs and the host platform combat system. Additionally, as shown by Figure 2, a data umbilical type connector 117 is fitted for connection between the launcher apparatus and the AASMs 102a and 102b in the self-contained launch canister 100. Additionally or alternatively, during the deployment of the launch canister 100, the data umbilical 113 can be disconnected from the self-contained launch canister and host platform during the launch canister deployment. According to a possibility it can remain attached to allow operators to pass over data to the AASMs from the host platform while in the enclosure 121 and before launch.

The launch can be aided by a drive module 122 arranged to drive the launch canister 100 out of the enclosure 121 through a launch opening 128. The drive module can be any suitable kind of mechanism for launching the device, including a mechanical device (e.g. a catapult or other sprung mechanism), a pyrotechnic device, or a compressed gas charge, or a combination of these.

In accordance with a possibility the missiles are ejected out of the canister after surfacing by their own booster motors. A booster motor of a missile can be initiated by the on-board control system of the canister. The operation can be triggered by a surfacing signal.

The launch canister 100 may also comprise a drive module 104 that is arranged to assist the operation of driving the devices 102a and 102b out of the launch canister 100 through opening 108. The drive module 104 can be used to deploy a buoyancy and stabilization device, for example stabilisation petals, and a missile efflux vents by any suitable type of drive mechanism.

Figures 3 and 4 show schematic examples of how three or four missiles can be arranged within canister apparatus 100. In Figure 3 example three missiles 162 are supported by a structure 160 attached on the internal side wall 164 of the launch canister 100. The structure can be provided e.g. by a launch railings or the like. Figure 4 shows an example where a launch block 170 with missile receiving apertures 174 is inserted in the launch canister 100 and attached to the internal structure the canister.

The launch canister apparatus can comprise a buoyancy and stabilisation device. A buoyancy and stabilisation device can also comprise a mechanism operable between different operational states and positions. In accordance with an embodiment the buoyancy and stabilisation device comprises moveable petals that can be opened after the canister has surfaced. The arrangement can be such that after the submarine's control system initiates the deployment of the launch canister into the sea surface and after the launch canister apparatus has exited the submarines launch apparatus the missile launch canister apparatus can float to the surface aided by flotation devices attached to the launch canister buoyancy and stabilisation petals.

Figures 5A -5D show a more detailed example of buoyancy and stabilisation petals 109 and flotation devices 112 configured to assist ascent of a launch canister 100 to the surface, post discharge from the submerged platform or structure, and flotation of the canister 100 on the surface. The petal and flotation device arrangement is also configured to stabilise motion and orientation of the container during the launch of the aerial devices from the canister. Figures 5A -5D illustrate a launch sequence of the canister 100 provided with five deployable stabiliser and buoyancy petals 109 in accordance with an embodiment.

In Figure 5A the canister 100 has been launched from opening 301 of a submarine 401 in water 402. A canister adapted for launching multiple missiles is advantageously launched from a torpedo tube, and thus Figure 5A depicts the canister 100 exiting from a torpedo tube 404 at front of submarine 401.

In the next stage shown in Figure 5B flotation devices 112 are deployed from the petals 109 that are yet folded against the sides of a launch canister 100 as the canister is still submerged in water 402. The device is now in ascent and floatation position.

In Figure 5C the flotation devices 112 and the top cone of the canister 100 have surfaced from water 402. At this stage the petals are moved to opened position. Figure 5D then shows the petals 109 and floatation devices 112 in a fully expanded position, or buoyancy position on the water 402. When the petals 109 and flotation devices 112 are in a fully expanded position the canister missile efflux vents can be opened prior to launch to enable venting of gases from the launch. An AASM 102 is shown to be exiting the canister.

As shown by Figure 5D, the petals on the launch canister 100 can be moveably attached at 105 to the canister 100. In Figure 5D the point of pivotal attachment is shown to be at the bottom of the canister but this is not the sole possibility.

The petals can have at least two different operating positions. A drive module 104 is provided to deploy the stabilisation and buoyancy petals 109 during launch initiation sequence. The drive module can also be used to open the launch canister efflux vents prior to the deployment of the AASMs from the launch canister 100 through the open ended section of the launch canister. The operation of the drive module, the actuator and other possible elements of the container apparatus 100 can be controlled by an on-board control apparatus 106. A schematic presentation of an example for possible control apparatus is illustrated in Figure 6.

In operation, when the launch canister 100 has exited the submerged host platform the launch canister ascends to the surface aided by the launch canister petal flotation devices. Each petal may be provided with a flotation device112.

On discharge from the host platform the flotation devices 112 can provide buoyancy aids for aiding ascent of the canister to the surface. The flotation devices can be flotation bags, collars or any other type of flotation aids.

The tip portion 110 of at least some of the petals 109 can be arranged to cover the nose cap of the canister when the petals are in the folded launch position. The flotation devices can thus provide a protective closure for the cap and/or formed such as to provide improved hydrodynamic properties of the canister apparatus. For example, when closed the flotation devices can cover the cap end of the canister and form an appropriate shaped cone at the front end of the apparatus.

On exit from the submerged launch platform, e.g., a torpedo tube, the petal flotation devices 112 can be deployed from the ends of the petals. When the nose of the canister has surfaced a surfacing sensor can detect that the nose cap is no longer submerged. The launch canister 100 can comprise a surfacing sensor 107 (Fig. 2) for detecting when the nose cap 103 or another predefined part of the container 100 broaches the surface of the water. The surfacing sensor may be any kind of suitable sensor capable of detecting surfacing of the canister.

For example, a hydrostatic switch, a pressure switch or an electronic or electro-optical sensor for detecting the transition from water to air can be provided. In accordance with a possibility a positioning system receiver provides a surfacing information signal in response to acquiring a signal from at least one positioning satellite. In response to a signal from the sensor that the canister has broached, the drive module can deploy the stabiliser and buoyancy petals 109, with floatation devices 112, to a fully deployed position of Figure 5D. At this position these stabiliser and buoyancy petals with flotation devices maintain buoyancy and orientation of the launch canister relative to the wave motion.

In Figure 8 example a flotation collar 308 is arranged around the launch canister 100. The flotation collar can be provided from any appropriate material.

The collar 308 can be arranged around the circumference of the canister so as to aid and guide the motion of the canister to the surface. Once surfaced, the collar improves the buoyancy of the canister and stabilises the canister for the launch of the missile.

The system can be provided with a variety of sensors. For example, position, movement and/or orientation determining apparatus can be provided. Some or all of such determining apparatus can be located at the antiaircraft/surface missile (AASM) 102. For example, an AASM can be provided with a radar seeker and/or other targeting capability by entity 115. An AASM can also comprise control apparatus 116. The signalling connection 117 can be used for data communications between the control electronics 106 of the canister apparatus 100 and/or the control electronics of the submarine and control electronics 116 of the AASM 102. The connection can be based on wired or wireless communication technology. The connection between the controllers or the AASM and the container can be adapted for use as long as the AASM is still located within the container and/or is in close vicinity thereof.

In accordance with a possibility a launch canister 100 may have an on-board fitted Inertial Measurement Unit (IMU) 114 to detect the motion of the launch canister 100. The IMU can signal canister motion data to the control electronics 116 to assist in the discharge initiation sequence. Furthermore, a positioning system unit may also be provided in the AASM and/or in the canister itself. For example, the AASM may comprise a Global Positioning System (GPS) or an enhanced Long Range Navigation (eLORAN) receiver. The canister motion data along with the GPS receiver acquiring a GPS satellite lock or the eLORAN receiver acquiring an eLORAN position can be used to determine when the aerial device is ready for the on-board control system electronics to initiate a discharge sequence from the enclosure.

Figure 6 shows an example of a control apparatus 70 for an aerial device and/or for the launch container apparatus. The control apparatus can be configured to provide control functions in association with the herein described launch operations. For this purpose the control apparatus comprises at least one memory 71, 72, at least one data processing unit 73, 74, and an input/output interface 75. Via the interface the control apparatus can be coupled to at least one external sensor and at least one other control apparatus. The control apparatus can be configured to execute an appropriate software code to provide the control functions. The required data processing apparatus and functions may be provided by means of one or more data processors. The data processors may be of any type suitable to the local technical environment, and may include one or more of general purpose computers, special purpose computers, microprocessors, digital signal processors (DSPs), application specific integrated circuits (ASIC), gate level circuits and processors based on multi core processor architecture, as non-limiting examples. The data processing may be distributed across several data processing modules. A data processor may be provided by means of, for example, at least one chip. The memory or memories may be of any type suitable to the local technical environment and may be implemented using any suitable data storage technology, such as semiconductor based memory devices, magnetic memory devices and systems, optical memory devices and systems, fixed memory and removable memory.

Figure 7 is a flowchart for operation for launching multiple of missile, for example, AASMs in accordance with an embodiment. A launch canister apparatus carrying multiple aerial devices such as AASMs is ejected from a submerged launch platform. The launch canister apparatus ejected from a submerged launch platform then carriers a plurality of aerial devices at 200 to the surface. At 202, subsequent to surfacing, the launch canister apparatus provides a floating and stabilized launch platform for the plurality of aerial devices. The plurality of aerial devices can then be launched at 204 from the floating and stabilized launch canister apparatus.

On-air operation of the at least one AASM can be controlled at 206 independently from controls of the submerged launch platform. The control can be provided entirely by the respective AASM.

Aerial devices can be launched from the canister one at the time.

Alternatively, at last two devise can be launched substantially at the same time. A staggered launch sequence out of the canister can be provided for the multiple devices. Each device can have its own target. Alternatively, a multiple of devices can be launched against a single target.

Each missile can be allocated a primary target by a control system of the launch platform whilst the missile is in the launch canister and prior to the deployment of the launch canister from the platform. The on-board targeting system of the missile can be capable of switching to a secondary target of interest if a primary target of the missile can no longer be acquired.

The targeting and/or initial coordination of the operation of the multiple of aerial devices can be provided by a combat system of a submarine via launcher control units. Target data can be sent from the submarine's combat management system (CMS) via the launch controllers to the missiles via the data/power connectors and umbilical or via a wireless communications system. The firing sequence can be initiated from the submarine's CMS via the launch controller which sends a fire pulse to appropriate launch apparatus of the submarine. The firing pulse initiates launch canister discharge procedure which will launch the canister into the sea. On exit the canister petal flotation devices are deployed to aid the canisters ascent to the surface. Once the canister nose has broached a broach sensor and a switch will initiate the first stage of the launch sequence which will fully deploy the stabilization and buoyancy petals. In response to the sensor, a nose cap of the canister can be released.

In accordance with an example of operation, when the launch canister broaches water surface a pressure switch initiates the first stage of a AASM launch sequence. This stage fully deploys the buoyancy and stabilization petals or other flotation device to provide the launch canister with a stable launch platform. The petals can be opened for example to an angle of 90 degrees or substantially close thereto to the vertical. This is believed to provide a stable weapon platform for the missile to be launched in sea states up to four as a threshold requirement and sea states six as an objective requirement. Once the petals are in the weapon stabilization position second stage is initiated which is the deployment of the nose cap. A lower section sleeve on the canister can also open up to provide a vent path for the missile booster rocket blast when a missile is launched into the air. The missiles can be launched vertically into the air and once launched will transition to flight and commence acquisition of the target. The missile radar seeker will acquire, track and engage the target independent of the submarine. Thus, once airborne a missile can independently use its radar seeker and acquire and attack the target without any need for communication with the combat control system of the submarine. Thus an anti-aircraft capability can be provided when the submarine is in depth and has no communications capability with the missile.

Once all missiles have been launched the canister can self-scuttle.

Provision of dual capable missiles provides a submarine with an effective, covert and secondary anti FIAC capability in addition to anti-aircraft capability. Examples of missiles that can be used as a dual capable sub-surface to air and subsurface to surface missile include HellfireTM, LongbowTM and DAGRTM by the applicant Lockheed Martin Corporation. These missile types are examples of suitable missiles that can be can be adapted in particular for a submarine launched fire and forget missile operation described herein. For example, the Hellfire TM can utilize a millimetric wave radar which, once launched, relies on its own radar seeker to acquire, track and engage the target. Of these two missiles DAGRTM has a smaller diameter and weighs less than Hellfire TM or Longbow TM. Multi-missile apparatus can be particularly useful in countering e.g. multiple FIAC or aerial attacks. In accordance with an advantageous embodiment a launch canister apparatus adapted for torpedo tube launch is provided. A torpedo tube launched version can be developed that uses a standard torpedo shape launch canister containing e.g. four DAGRTM or three Hellfire TM missiles. Communications between the submarine's CMS and the launch canister can be via a standard "A" link umbilical which is connected to the submarine's fire control system and will pass over initialization and targeting data between the missile and the CMS. Communications between the launch canister and the missiles can be via the standard data links already used on helicopter based launchers. The launch canister can be discharged like a normal torpedo, this meaning that the whole launch canister is discharged from the torpedo tube where after it will deploy launch canister petal flotation devices and ascend to the surface.

Figure 8 shows a submarine 401 beneath the water surface 407 and comprising a canister launcher. Launch canister 100 is ejected from the launcher at phase (a) with its subsequent motion in phase (b) through water 402 to the surface being guided by a launch canister flotation device, for example flotation devices shown in Figure 5D and/or a flotation collar 308. The flotation device can be activated on launch of the canister (e.g. by means of a hydrostatic switch). At phase (c) the launch canister broaches the surface 407 and in response a surface sensor causes petals or other stabilization means to be deployed and nose cap 103 to be jettisoned. Further in response to broaching the surface of water 402, devices such as AASMs 102 are launched from the canister and hence driven into the air where the devices enter a flight mode and power away to complete their mission. At this stage self-seeking guiding and targeting systems of the respective aerial devices switched on. Thus, e.g., each missile can lock itself to one of the targets 410. In case of multiple targets, coordination can be provided, e.g. by CMS of a submarine, between the devices so that all targets, or as many as possible, are targeted in optimal manner and/or to enable switching between primary and secondary targets.

A launch container apparatus described herein can be launched from various depths, for example from at approximately periscope depth to very deep dive. Because no launch mast is needed the submarine can remain entirely submerged. The missile can operate independently from the submarine once the missile is airborne and therefore no communication link between the submarine and the unmanned aerial device is needed. The examples can provide a cost effective and effective anti-aircraft and/or anti-FIAC/FAC capability to either counter a singleton or swarm attacks. A dual capable and flexible missile system can be provided as opposed to just an anti-aircraft system.

Various modifications to the disclosed embodiments will be readily apparent to those skilled in the art. Thus the general principles described herein may be applied to other embodiments and applications without departing from the spirit and scope of the present invention and the present invention is not intended to be limited by the embodiments shown, but is to be accorded the 13 widest scope consistent with the principles and features disclosed herein.

The applicant hereby discloses in isolation each individual feature described herein and any combination of two or more such features, to the extent that such features or combinations are capable of being carried out based on the present specification as a whole in the light of the common general knowledge of a person skilled in the art, irrespective of whether such features or combinations of features solve any problems disclosed herein, and without limitation to the scope of the claims. The applicant indicates that aspects of the present invention may consist of any such individual feature or combination of features. In view of the foregoing description it will be evident to a person skilled in the art that various modifications may be made within the scope of the invention.

Claims (21)

1. CLAIMS1. A launch canister apparatus, the launch canister apparatus being configured to be ejected from a submerged launch platform, carry a plurality of aerial devices from the submerged launch platform to surface, and provide a floating and stabilized launch platform for the plurality of aerial devices subsequent to surfacing of the launch container apparatus.
2. 2. A launch canister apparatus as claimed in claim 1, wherein the aerial devices comprise surface to air missiles, surface to surface missiles and/or antiaircraft missiles.
3. 3. A launch canister apparatus as claimed in claim 1 or 2, comprising control apparatus configured to, subsequent to launch of at least one of the aerial devices from the launch canister apparatus, control on-air operation of the at least one aerial device independently from controls of the submerged launch platform.
4. 4. A launch canister apparatus as claimed in claim 3, wherein the aerial devices comprise missiles, each missile comprising control apparatus configured to acquire a target and guide the missile to the target.
5. 5. A launch canister apparatus as claimed in any preceding claim, comprising control apparatus configured to coordinate on-air operation of the aerial devices.
6. 6. A launch canister apparatus as claimed in any preceding claim, configured for staggered launch of the aerial devices.
7. 7. A launch canister apparatus as claimed in any preceding claim comprising buoyancy and stabilization petals and a petal drive mechanism configured to move the petals from a folded position to an expanded position to provide buoyancy and stabilization for the launch container apparatus in response to a surfacing signal.
8. 8. A launch canister apparatus as claimed in claim 7, wherein the petal drive mechanism is configured to drive the petals to the expanded position for providing a weapon stabilisation platform for launch of a plurality of missiles from the launch container apparatus.
9. 9. A launch canister apparatus as claimed in claim 7 or 8, wherein each petal is provided with a flotation device.
10. 10. A launch canister apparatus as claimed in any preceding claim, comprising an inflatable flotation device.
11. 11. A launch canister apparatus as claimed in any preceding claim adapted for launch from a submerged torpedo tube, signal ejector tube, or an under casing launcher.
12. 12. A launch canister apparatus as claimed in any preceding claim, wherein the submerged launch platform is one of a submarine, a submerged swimmer delivery vehicle, a submerged delivery structure, and a submerged unmanned autonomous vehicle.
13. 13. A method for launching aerial devices, comprising carrying by a launch canister apparatus ejected from a submerged launch platform a plurality of aerial devices, subsequent to surfacing of the launch canister apparatus, providing by the launch canister apparatus a floating and stabilized launch platform for the plurality of aerial devices, and launching the plurality of aerial devices from the floating and stabilized launch canister apparatus
14. 14. A method as claimed in claim 13, wherein the aerial devices comprise at least one of surface to air missiles, surface to surface missiles and anti-aircraft missiles.
15. 15. A method as claimed in claim 13 or 14, comprising controlling on-air operation of each of the aerial device independently from controls of the submerged launch platform.
16. 16. A method as claimed in any of claims 13 to 15, comprising coordinating the on-air operation of at least two aerial devices.
17. 17. A method as claimed in any of claims 13 to 16, comprising switching between primary and secondary targets of at least one aerial device.
18. 18. A method as claimed in any of claims 13 to 17, wherein the aerial devices comprise missiles and the method comprises each missile independently acquiring a target and guiding the missile to the target by control apparatus provided at the missile.
19. 19. A method as claimed in any of claims 13 to 18, comprising determining surfacing of the canister apparatus, and in response to the determining of the surfacing, driving petals of a buoyancy and stabilization device of the canister apparatus to an expanded position to provide buoyancy and stabilization for the launch of the aerial devices from the canister apparatus, opening a nose cap of the canister apparatus, and initiating launch of at least one aerial device from the canister apparatus.
20. 20. A computer program comprising code means adapted to perform, when run on processor apparatus, a method in accordance with any of claims 13 -19.
21. 21. A launch apparatus for an unmanned aerial device substantially as described herein with reference to any of figures 1 to 8.