Launcher systems and deployable entities

Abstract

Examples relate to launcher systems for launching a deployable entity. For instance, a launcher system comprises: a set of telescopic elongate members for receiving a first fluid; the set of telescopic elongate members comprising a static member and a moveable member; the moveable member being arranged to actuate the deployable entity; the set of elongate members being expandable between a contracted state and an expanded state to launch the deployable entity in response to ingress of the first fluid.

Description

LAUNCHER SYSTEMS AND DEPLOYABLE ENTITIES TECHNICAL FIELD

[0001] The present application relates launcher systems and associated entities such as effectors and aircraft.BACKGROUND

[0001] Surface-to-Air missile (SAM) systems and deep strike missiles are crucial to providing ground-based defences to incoming airborne threats as well as providing ground based offensive initiatives. The Storm Shadow missile, which is air launched from, for example, a Euro-fighter, is an example of a deep strike missile. However, the Storm Shadow missile can only be air-launched by at least a Mach 0.8 manned asset. The cost of a Storm Shadow missile is a significant seven-figure sum.

[0002] Furthermore, present ground-based missiles and air launched missiles have significant thermal and / or acoustic signatures that render them eminently detectable and trackable, which clearly puts the assets and any operational crew at a disadvantage.

[0003] Still further, launch systems can be complex, in terms of needing a bespoke coupling to a fighter jet and / or needing a carriage with 16m rails in the case of some ground-based missiles. Furthermore, many missile systems have a significant nonrecurring engineering cost. For example, such costs for a bespoke 40 kg effector of this class can be of the order of about £1 m, and the recurring cost per cartridge fired is about £80,000.BRIEF DESCRIPTION OF THE DRAWINGS

[0002] Examples of launcher systems and associated deployable entities such as, for example, aircraft, effectors, projectiles, missiles and the like will now be described, by way of example only, with reference to the accompanying drawings, in which:

[0003] Figure 1A shows a view 100 of a launcher system according to examples;

[0004] Figure 1 B illustrates a view of a further launcher system according to examples;

[0005] Figure 1C depicts a still further launcher system according to examples;

[0006] Figure 1D shows a view of a yet further launcher system according to examples;

[0007] Figure 2 depicts a pair of views of stanchion or elongate members of the above launcher systems;

[0008] Figure 3 depicts a further pair of views of the stanchion or the elongate members of the launcher system;

[0009] Figure 4A illustrates an example of the launcher system of figure 1A on a carrier vehicle according to examples;

[0010] Figure 4B illustrates an example of the launcher system of figure 1C on a carrier vehicle according to examples

[0011] Figure 5 shows a deployable entity according to examples;

[0012] Figure 6 illustrates a pair of engine arrangements of a deployable entity according to examples;

[0013] Figure 7 depicts a deployable entity according to examples;

[0014] Figure 8 shows a launcher system according to examples;

[0015] Figure 9 illustrates a cross-sectional view of an elongate member of the launcher system of figure 8 according to examples;

[0016] Figure 10 shows the cross-sectional view of the elongate member of figure 9 in a partially expanded state;

[0017] Figure 11 depicts the cross-sectional view of the elongate member of figure 9 in a further expanded state;

[0018] Figure 12 shows the cross-sectional view of the elongate member in a postlaunch state;

[0019] Figure 13A illustrates a recoil system according to examples;

[0020] Figure 13B shows in greater detail the recoil system coupled to part of a fluidic fed system and a retardation system;

[0021] Figure 14 depicts further details of the recoil system according to example;

[0022] Figure 15 illustrates an alternative arrangement of the elongate members according to examples;

[0023] Figure 16 depicts a control system according to examples; and

[0024] Figure 17 shows a pair of relationships between various components of the launchers and deployable entities according to examples.DETAILED DESCRIPTION

[0025] Figure 1A shows a view 100A of a launcher system 102 according to examples. The launcher system 102 comprises a set of elongate members. In the example depicted, the set of elongate members comprises four elongate members 104 to 110. Although the example shown in figure 1 comprises four elongate members 104 to 110, examples are not limited to such an arrangement. Examples can be realised in which the set of elongate members comprises some other number of members such as, for instance, one, two or three elongate members or some other plurality of elongate members. Each elongate member 104 to 110 is an example of a telescopic elongate member. Each elongate member is extendible, that is, the overall length of the elongate member can be changed.

[0026] Each elongate member 104 to 110 is telescopic, that is, each can be extended. The telescopic nature of each elongate member 104 to 110 will be described in greater detail with reference to figures 2 and 3.

[0027] Each elongate member 104 to 110 can be actuated, that is, moved between a contracted state and an extended state in response to receiving an actuation fluid. The actuation fluid can be a gas such as, for example, compressed air. The actuation fluid is an example of a first fluid. The actuation fluid can be stored in a set of tanks. In the example shown in figure 1, the set of tanks comprises eight tanks 112 to 124. The gas can be stored in a gaseous or liquid phase. For gas that is stored in the liquid phase, to support rapid expansion at the pressures required, examples can be realised that use a heater to heat the liquid phase gas.

[0028] The launcher system 102 comprises an upright planar body 126. The upright planar body 126 bears or otherwise carries the set of elongate members 104 to 110. The upright planar body 126 also carries a deflector 127 having profiled surface to deflect any exhaust gas from the set of elongate members 104 to 110 sideways relative to a longitudinal axis (not shown in figure 1) of each member 104 to 110.

[0029] The upright planar body 126 is pivotable relative to a base 128. The base 128 comprises a void 130 for housing the set of tanks 112 to 124. The void 130 also houses an actuation assembly for controlling the angle of elevation of the upright planar body 126 and, therefore, the angle of elevation of the set of elongate members 104 to 110. The actuation assembly comprises an elongate planar body 132 that is pivotably coupled to base 128. The body 132 carries the upright planar body 126 suchthat an overall L-shaped structure is formed. The actuation assembly comprises a set of pistons. In the example shown in figure 1A, the set of pistons comprises first 134 and second 136 pistons. The set of pistons is controllable to raise and lower the elongate planar body 132 according to a desire elevation or launch angle.

[0030] The void 130 also houses a power supply 138 for operating the pistons.

[0031] The set of elongate members 104 to 110 is arranged to receive a deployable entity (not shown) that is described herein with reference to figures 2 to 6.

[0032] Examples described herein will be given with reference to the deployable entity being at least one or more than one of the following taken jointly and severally in any and all permutations: an effector, a one-way effector, an unmanned air vehicle, ordnance, a missile and the like.

[0033] Referring to figure 1B, there is shown a view 100B of a further launcher system 102B according to examples. Reference numerals used in figure 1A, with the suffix B when used in figure 1B refer to the same or comparable entities as in figure 1A when used with the suffix A. It can be appreciated that rather than a set of elongate members comprising four members as indicated above with respect to figure 1A, a set of elongate members in the example shown in figure 1B comprises three elongate members 104B to 108B. I n the launcher system 102B of figure 1 B, two sets of elongate members are provided to carry and launch respective deployable entities. A first set of elongate members comprises three elongate members 104B to 108B. A second set of elongate members also comprises three elongate members 104B’ to 108B’. Launcher systems can be realised that comprise a plurality of sets of elongate members. For instance, examples can be realised that comprise four sets of elongate members for carrying and launching respective deployable entities.

[0034] The upright planar body 126B is pivotable coupled to the base 128B. The base 128B comprises a void 130B for housing a set of tanks (not shown). The set of tanks is an example of the above-described set of tanks 112 to 124. The void 130B can also house an actuation assembly for controlling the angle of elevation of the upright planar body 126B and, therefore, the angle of elevation of the sets of elongate members 104B to 108B and 104B’ to 108B’. The actuation assembly comprises first 132B and second 132B’ elongate planar bodies that are coupled to the upright planar body 126B. The actuation assembly comprises a set of pistons. In the example shown in figure 1 B, the set of pistons comprises first 134B and second 136B pistons. The set of pistons iscontrollable to raise and lower the elongate planar body 132B’ according to a desire elevation or launch angle.

[0035] Referring to figure 1 C, there is shown a view 100C of a launcher system 102C. Reference numerals common to figure 1A, but for the suffix A being replaced by the suffix C, refer the same or common elements. It can be seen that the launcher system 102C comprises a set of three elongate members 104C to 108C. The launcher system 102C also comprises a deflector 127C.

[0036] Referring to figure 1 D, there is shown a view 100D of a launcher system 102D. Reference numerals common to figures 1A to 1C, but for the suffixes A, B, C being replaced by the suffix D, refer the same or common elements. It can be seen that the launcher system 102D is shown as hosting a salvo of deployable entities 105D. In the present example, the salvo comprises two deployable entities. However, examples can be realised in which some other number of deployable entities are provided. For example, examples can be realised that provide one, two, three or four deployable entities or some other plurality of deployable entities.

[0037] The entities 132, 132A-D are handling structures arranged to allow a salvo of deployable entities to be loaded onto a mobile vehicle as shown below and described with reference to figures 4A and 4B.

[0038] Figure 2 depicts a pair of sectional views 200A and 200B of an elongate member 200 of the launcher system 102. The elongate member 200 is shown hosting a female member 202 of a deployable entity (not shown). The elongate member 200 is an example of any of the above-described elongate members 104A-C to 110A-C. The elongate member 200 comprises an inner elongate hollow member 204. The inner elongate hollow member 204 is an example of a static member of a telescopic elongate member. Examples can be realised in which the inner elongate hollow member 204 is an inner hollow cylindrical tube 204. The elongate member 200 also comprises a female, outer, orfemale sheath, elongate member 206, which will be referred to simply as a female outer elongate member 206 herein. The female outer elongate member 206 is an example of a moveable member of a telescopic elongate member. Examples can be realised in which the female outer elongate member 206, the inner and outer elongate members 204 and 206 are arranged in a longitudinally sliding or slidable relationship.

[0039] The inner and outer 204 and 206 members each comprises respective stops 208 and 210. The respective stops 208 and 210 limit the extension or longitudinal movement of the inner 204 and outer 206 elongate member relative to one another. Examples can be realised in which the respective stops 208 and 210 are optional. Examples can be realised in which the respective stops 208 and 210 form a gas tight seal such that the gas contained therein compresses to rapidly decelerate any longitudinal movement of the elongate member in a manner that avoids excessive impulses forces that might follow from collision or other contact between the stops 208 and 210.

[0040] The elongate member 200 also comprises a frangible or compressible member 212. The frangible or compressible member 212 can be realised in the form of an annular body. The frangible or compressible member 212 can be resiliently deformable. Such a resiliently deformable member 212 can be used multiple times. Alternatively, the frangible or compressible member 212 can be realised in the form of a single use body such as, for example, carbon body. Examples can be realised in which the frangible or compressible member 212 can be realised in the form of a foraminate member bearing foraminations. The foraminations can be realised in the form of through vias. Accordingly, examples can be realised in which the frangible or compressible member 212 is realised as a frangible cardon annular body bearing a plurality of through vias. The frangible or compressible member 212 is arranged to influence, that is, reduce, the impulse force between the two stops 208 and 210 when the inner 204 and outer 206 elongate members are accelerated, or otherwise moved, relative to one another.

[0041] The inner elongate hollow member 204 has an actuation fluid ingress aperture 214. The inner elongate hollow member 204 has a first actuation fluid egress aperture 216. A source of actuation fluid is stored in a tank 218. The actuation fluid is an example of a first fluid. The tank 218 is an example of one or more of the abovedescribed tanks 112 to 124. The actuation fluid is coupled to the interior volume or hollow of the inner elongate member 204 via respective pipework 220 and a valve 222. Examples can be realised in which the valve 222 can be opened within a predetermined period of time. The predetermined period of time is a relatively short period of time. The relatively short period of time can be of the order of milliseconds. Examples can be realised in which the valve 222 uses a frangible acrylic sheet (not shown) but is not limited thereto; other types of fast acting valves can be used. Thefrangible acrylic sheet can be broken using an actuator (not shown). The acrylic valve will be subjected to significant pressure since the actuation fluid is stored at a predetermined gauge pressure. Examples can be realised in which the gauge pressure is less than 30 bar G, optionally, substantially 20-24 bar G. The pressure will assist in breaking the frangible acrylic sheet. Examples can be realised in which the gas is realised into the inner elongate hollow member 204 to ensure there is an isobaric behaviour of the released actuation fluid. The volume of actuation fluid used to actuate the launcher system is a predetermined multiple of the extended volume of the inner elongate hollow member 204 and the outer female elongate member 206. Examples can be realised in which the ratio of the volume of actuation fluid released to the extended volume is 6:1. However, other examples can be realised that use other ratios such as, for instance, 10: 1 , or some other ratio. Preferred ratios are in the range of 4: 1 to 2:1 such as, for example, 3:1 or 2.5:1.

[0042] The immediately preceding paragraph can be applicable to all examples described herein.

[0043] Still referring to figure 2, there is shown a view 200B of the elongate member 200 in a partially extended state. The partially extended state arises from supplying the actuation fluid from the source 218 to the interior of the inner elongate hollow member 204 via the ingress aperture 214. The pressure within the inner elongate hollow member 204 will increase and, in turn, will bear on the female elongate member 202. The stiction between the female elongate member 202 and the female outer elongate member 206 causes the latter to slide longitudinally. The female outer elongate member 206 slides longitudinally until the stops 208, 210 and the frangible or compressible member 212 arrest any longitudinal movement.

[0044] The arresting longitudinal movement is sufficient to overcome the stiction between the female outer elongate member 206 and the female elongate member 202 such that the latter continues, in response to the pressure created by the actuation fluid, the longitudinal direction. When the stops 208, 210 and frangible or compressible member 212 arrest further longitudinal movement, the elongate male member 200 is in a fully expanded state.

[0045] The inner hollow elongate member 204 also comprises an exhaust aperture 224.

[0046] Figure 3 depicts a further pair of sectional views 300A and 300B of the elongate member 200 of the launcher system 102. In the first view 300A, the female elongate member 202, which is part of the deployable entity (not shown), has continued accelerating to the instant at which the female elongate member 202 of the deployable entity is at the point of separation from the elongate male member 200. In the second view 300B, the female elongate member 202 has continued moving longitudinally to the point that the female elongate member 202 of the deployable entity has separated from the elongate male member 200. Although the female elongate member 202 has been described as part of the deployable entity, as will be appreciated with reference to figure 17, the female elongate member 202 can be a cartridge or other vessel that, in turn, hosts or otherwise accommodates the deployable entity.

[0047] Figure 4A illustrates a view 400A of the launcher system 102 on a carrier vehicle 402A together with a deployable entity 404A according to examples. In the example shown, the deployable entity is an effector 404A in the form of an electric propulsion missile. The connection or exhaust apertures 224 of three elongate hollow members 204 are visible as protruding from the rear face of the upright member 126. The connection or exhaust apertures 224 allow a manifold for delivering the actuation fluid to be connected to associated respective the inner elongate hollow members 204. Therefore, examples can be realised in which the apertures can be used to either exhaust actuation fluid or supply actuation fluid.

[0048] Figure 4B illustrates a view 400B of the launcher system 102 on a carrier vehicle 402B together with a deployable entity 404B according to examples. In the example shown, the deployable entity is an effector 404B in the form of the electric propulsion missile. The connection or exhaust apertures 224 of three elongate hollow members 204 are visible as protruding from the rear face of the upright member 126. The connection or exhaust apertures 224 allow a manifold for delivering the actuation fluid to be connected to associated respective the inner elongate hollow members 204.

[0049] Figure 5 shows a view 500 of a number of views of a deployable entity 502 according to examples. The deployable entity 502 is shown in plan view 504, front view 506, rear view 508, bottom view 510 and side view 512.

[0050] Referring to the plan view 504, it can be appreciated that the deployable entity 502 comprises an elongate fuselage 514. Examples can be realised in which the fuselage 514 has a substantially square or rectangular cross-section. The fuselage514 has a nose cone 516, a first or fore engine section 518 that has first air intakes 520 and first air outlets or air exhausts 522. The fuselage 514 comprises a pair of wings 524. Examples can be realised in which the wings 524 have a predetermined surface area. The predetermined surface area can be set according to desired performance characteristics such as, for example, lift. Examples can be realised in which the predetermined surface area is 1.7mA2 per wing. The wings 524 comprise respective flaps 526. The fuselage 514 continues to a second or aft engine section 528 that has second air intakes 530 and second air outlets or air exhausts 532. The rear of the fuselage 514 bears an inverted-V tailplane bearing left 534 and right 536 stabilisers. The left 534 and right 536 stabilisers have respective elevators 538 and 540.

[0051] The rear view 508 shows a set of female apertures for receiving the elongate male members such as, for instance, members 104A-C to 110A-C of any of the launch systems described and / or illustrated herein. In the example depicted, the set of female apertures comprises four apertures 542.

[0052] The remaining views are labelled as indicated above such that corresponding reference numerals refer to the same element or feature.

[0053] Referring to figure 6, there is shown a pair of views 602 and 604 of arrangements of first 606 and second 608 sets of thrust producers. The first set of thrust producers 606 comprises a plurality of thrust producers. In the example depicted in view 602, the first set of thrust producers comprises 10 thrust producers. The set of thrust producers are arranged in an alternating manner with the centres of thrust producers of one column, in set 606, or one row, in set 608, being offset relative to the centres of thrust producers of an adjacent column or row respectively. This arrangement assists in reducing the cross-sectional area of the fuselage body 514 needed to accommodate the thrust producers. Examples can be realised in which the thrust producers are electric engines driving respective fans.

[0054] Although examples have been described in which the sets of thrust producers each comprise 10 thrust producers, examples are not limited thereto. Examples can be realised in which at least one, or more than one, set of thrust producers comprises some other number of thrust producers. For instance, examples can be realised in which a set of thrust producers comprises two or more thrust producers. Examplescan be realised in which a set of thrust producers comprises a plurality of thrust producers.

[0055] Figure 7 depicts a view 700 of a deployable entity 702. The deployable entity 702 comprises an elongate body 704. The elongate body 704 has a substantially square cross-section. The deployable entity 702 has a nose cone 706. The node cone leads to mutually perpendicularly disposed sets of air intakes comprising a set of fore air intakes 708 and set of aft air intakes 710. Each set of air intakes comprises a pair of air intakes disposed on opposite sides of the body 704.

[0056] The set of fore air intakes 708 leads to exhaust outlets (not shown) that feed respective exhaust channels disposed on opposite sides of the body; only the left-hand exhaust channel 712 is visible in figure 7.

[0057] The set of aft air intakes 710 is fed by air intake feed channels disposed on opposite sides of the body; only the upper air intake feed channel 714 is visible in figure 7.

[0058] The deployable entity 702 comprises a set of wings with control surfaces; only the left wing 716 is visible, and a set of horizontal stabilisers with control surfaces; again, only the left stabiliser 718 is visible.

[0059] The deployable entity 702 further comprises at least one tail with or without a control surface or control surfaces. In the example depicted, the deployable entity 702 comprises two such tails 720 and 722 arranged in a V configuration.

[0060] Referring to figure 8, there is shown a view 800 of a launch system 802 according to examples. The launch system 802 comprises a set of elongate male members. In the example depicted the set comprises four elongate male members 804 to 810. Each elongate member 804 to 810 is an example of a telescopic elongate member. Each male member 804 to 810 comprises an outer female sheath such as sheathes 812 and 814 mounted on respective inner elongate male members; two such male members 816 and 818 are clearly visible in figure 8. Each inner elongate male member is an example of a static member of a telescopic elongate member. Each outer female sheath is an example of a moveable member of such a telescopic elongate member.

[0061] Figure 8 shows the set of elongate male members 804 to 810 arranged in a first configuration. The first configuration is a substantially square or rectangular arrangement. As will be described later, other configurations can be realised.

[0062] Each male member 804 to 810 is coupled to a respective support 820 and 822. A set of recoil compensation systems is coupled to the supports. In the example depicted, the set of recoil compensation systems comprises four recoil compensation systems 824 to 830. Each recoil compensation system 824 to 830 is arranged to compensate for any recoil generated by launching an effector or other deployable entity using a respective set of elongate male members 804 to 810. Examples can be realised in which such a respective set comprises a single elongate male member. Examples can be realised in which such a respective set comprises a plurality of elongate male members. For instance, examples can be realised in which such a respective set comprises one, two, three or four elongate male members. The number of elongate male members in such a respective set can be related to the mass of the effector to be launched; the greater the mass, the greater the number of male members within the respective set.

[0063] The launch system 802 comprises a rail 832. Examples can be realised in which the rail 832 is a unitary structure or in which the rail is extendible via two or more cooperating structures such as the pair of rails 834 and 836 shown. The rail 832 comprises a set of rollers (not shown). The rollers assist in supporting movement of an effector when being loaded or mounted onto the tubes 804 to 810 or when being launched.

[0064] The launch system 802 also comprises a set of tanks containing pressurised air. In the example shown, the set comprises four tanks 838 to 844. Each tank contains sufficient pressurised air to launch at least one effector of a set of possible effectors. The set of possible effectors can comprise effectors of respective weights. The respective weights can comprise 125 kg to 1000 kg effectors or aircraft such as, for example, the effectors 105D, 404A and 404B described above with reference to figures 1 D, 4A and 4B respectively.

[0065] The elongate male members 804 to 810 are extendible, or otherwise telescopic, as a consequence of the female sheaths, such as sheaths 812 and 814, being in sliding engagement with the inner male members, such as members 816 and 818.

[0066] In the example shown in figure 8, the tanks 838 to 844 are coupled to the rail 832. The rail 832 is pivotally coupled to a supporting frame 846 to vary the angle of inclination of the male members and, hence, the launch angle. The assemblycomprising the tubes 804 to 810, the recoil systems 824 and 830, the tanks 838 to 844 and the supports 820 and 822 can be coupled to, and be pivotable with, the rail 832 about the pivot point 848. Examples can be realised, however, as with the above examples, in which the tanks are not coupled to, and pivotable with, the rail 832.

[0067] Figure 9 shows a cross-sectional view 900 of an elongate member 902, a recoil system 904 and a fluidic feed system 906. The elongate member 902 is an example of the above-described elongate male members 810 to 810. The elongate member 902 is an example of a telescopic elongate member. The recoil system 904 is an example of the above-described recoil compensation systems 824 to 830. The fluidic feed system 906 comprises an inlet 908, a first outlet 910 and a second outlet 912. The inlet 908 can be coupled to a respective tank of the plurality of tanks 838 to 844 to feed pressurised air into the launch system.

[0068] The elongate member 902 comprises an outer female sheath 914. The outer female sheath 914 accommodates a hollow inner elongate male member or tube 916. The outer female sheath 914 is arranged to bear the projectile 918. Examples can be realised in which the outer female sheath is an example of a moveable member of a telescopic elongate member. The hollow inner elongate male member 916 is an example of a static member of a telescopic elongate member.

[0069] The first outlet 910 is arranged to feed pressurised air into the elongate member 902, in particular into the hollow inner elongate tube 916.

[0070] The fluidic fed system 906 comprises a centrally disposed outlet feed 911. The outlet feed 911 comprises a set of holes (three of which are shown but not labelled for clarity) to allow the passage of pressurised air from the inlet to the second outlet 912. Examples of the outlet feed 911 can be realised in the form of a foraminate cylinder. The second outlet 912 is arranged to feed pressurised air into the recoil system 904.

[0071] The female outer sheath 914 has a distal end plate 920. The end plate 920 bears a set of apertures; only two apertures 922 and 924 are visible in the cross-sectional view 900. Feeding pressurised air into the hollow inner elongate male member 916 allows pressure and, therefore, force to be exerted on an inner distal surface 926 of the projectile 918. Examples can be realised in which the projectile 918 forms part of a deployable entity or is an example of a cartridge or vessel for cooperating with a deployable entity as will be described with reference to and / or as illustrated in figure 17.

[0072] The projectile 918 is coupled to the female sheath 914. The coupling can be realised using a frangible linkage 928 such as, for example, a mechanical fuse. The frangible linkage 928 is designed to fail at a predetermined load. In the example shown, the frangible linkage 928 is shown as coupling the ends of the female sheath 914 and the projectile 918. However, other examples can be realised in which the frangible linkage 928 can be realised using a mechanical (waisted) bolt (not shown) that couples the projectile 918 to the end plate 920 through a via (not shown) in the projectile.

[0073] Although examples have been described that use a frangible linkage 928 to couple the projectile 928 and the female sheath 914, examples are not limited to such an arrangement. Examples can be realised in which at least one, or both, of: stiction and frictional are used to couple the projectile 918 and the female sheath 914.

[0074] The female sheath 914 is arranged to be in sliding engagement with the hollow inner tube 916. Due to the internal pressure and the frangible linkage 928 between the female sheath 914 and the hollow inner elongate male member 916 both the projectile 918 and the female sheath 914 start accelerating. The acceleration of both entities continues until the load on the frangible linkage 928 reaches the predetermined load at which point the frangible linkage 928 is designed to fail.

[0075] The elongate male member 902 comprises a retardation system 930. The retardation system 930 comprises a piston. The retardation system 930 is an example of a retardation assembly. The piston is formed using a partially foraminate bore 932 comprising a set of holes 934 at a proximal end and a hole-free region at a distal end or retardation region 936. The set of holes 934 at the proximal end is an example of a perforated region. The hole-free region at a distal end is an example of an unperforated region. The piston also comprises a crown 938. The crown 938 is coupled to the end plate 920 via a shaft 940.

[0076] In operation, as the pressurised air is released into the hollow inner tube 916, the piston is actuated. The piston can be actuated by at least one, or both, of: the air driving the piston by acting on the crown or the shaft 940 dragging the piston as the female sheath moves distally. The crown 938 moves freely whilst in the foraminate region 934. However, once the crown 938 enters the retardation region 936, the distal surface 942 of the crown 938 starts to compress the air within the retardation region 936. As the crown 938 progresses further into the retardation region 936, the air willbe increasingly compressed, which will, in turn, generate a rapid or impulse deceleration force acting against the motion of the crown 938. The volume of air within the retardation region is such that the magnitude of the impulse force associated with the rapid deceleration exceeds the predetermined failure load of the frangible linkage 928 before the crown 928 reaches an end stop 944 of the piston.

[0077] The retardation system 930 can be coupled to the fluidic feed system 906. Examples can be realised in which the retardation system 930 is couped to the fluidic feed system 906 via an articulation joint 945.

[0078] The fluidic feed system 906 also comprises a metering plate 946. The metering plate 946 is arranged to control the rate of flow of pressurised air into the hollow inner tube 916, which also generates sufficient pressure within the fluidic feed system 906 to ensure that pressurised air is fed into the recoil system 904.

[0079] The recoil system 904 comprises a piston 948 having a crown 950 within an internal volume of the piston 948. The piston 948 has distal volume 952 and a proximal volume 954. The distal volume 952, in use, is arranged to house a fluid. Examples can be realised in which the fluid is water. The distal volume 952 is fluidically coupled to an exhaust 956. In the example shown, the exhaust 956 is realised using an exhaust nozzle. The exhaust 956 is sealed with a seal 958. Examples can use a bung as the seal 958 to seal the exhaust 956. The seal can be an adjustable seal that allows the pressure or force needed to release the seal to be set. The proximal volume 954 is arranged to bear pressurised air from the second outlet 912. The pressured air drives the crown 950 that, in turn, causes the pressure within the distal volume 952 to overcome the sealing effect of the seal 958. The water provides a reaction mass to balance or otherwise counteract the accelerating masses in or associated with the elongate member 902 and projectile 918.

[0080] Initially, the distal volume 952 will be at a maximum and the proximal volume 954 will be at a minimum. Examples can be realised in which the initial, that is, prelaunch or primed, proximal volume will be substantially zero. This allows the reaction mass of the water in the piston to be maximised. The proximal volume 954 has been shown other than as minimised for purposes of explanation.

[0081] Referring to figure 10, there is shown a view 1000 of the cross-section described with reference to figure 9. Reference numerals common to figures 9 and 10 refer to the same entity. It can be appreciated that the projectile 918 and the femalesheath 916 have moved distally, that is, to the right, relative to an initial state and, similarly, the seal 958 has been broken or otherwise ejected by the crown 950 of the piston having also moved distally in the opposite direction, that is, to the left, which also results in water efflux 1002 leaving the nozzle 956. The crown 938 has also entered the retardation region 936 and, therefore, will start to load or rapidly decelerate the female sheath 914 with an impulse force.

[0082] Figure 11 shows a view 1100 of the launch system in which the forward acceleration of the projectile 918 and the female sheath 914, in cooperation with the retardation impulse force exerted by the retardation system, have been sufficient to retard the female sheath 914 relative to the projectile 918, which has resulted in the frangible linkage 928 being broken.

[0083] The pressurised air is still being fed into the expanding volume created by the female sheath 914, interior of the hollow inner tube 916 and the interior volume of the projectile 918. At this stage the expansion is due to progression of the projectile 918. It can be seen that the recoil system 904 has exhausted or otherwise ejected more water from the distal volume 952.

[0084] Referring to figure 12, there is shown a view 1200 of the launch system in a fully expanded state in which the projectile 918 has reached the end of the female sheath 914. The projectile 918 and the female sheath are shown as being separated for purposes of illustration. The female sheath and the hollow inner member have a predetermined total expanded length. Examples can be realised in which the predetermined expanded length is of the order of 2.5m to 3.5m, optionally 3.2m. Examples can be realised in which the length of the interior volume of the projectile that is filled with pressurised air during launch can be between 4m to 6m, optionally 5m.

[0085] Referring to figure 13A, there is shown a detailed view 1300A of a recoil system 1302. The recoil system 1302 is an example of any of the recoil systems described herein such as, for instance, recoil system 904. Also shown is part of a fluidic feed system 1304. The fluidic feed system 1304 is an example of any of the fluidic feed systems described herein such as, for instance, fluid feed system 906.

[0086] The recoil system 1302 comprises a fluid storage tank 1306 having an inlet 1308 and an outlet 1310. The tank 1306 houses a piston comprising a crown 1312. The crown 1312 can be stabilised via a respective rod 1314 and spider 1316. Thespider 1315 is aforaminated slidable disc or plate housed in a neck 1318 that fluidically couples pressurised air from the fluidic feed system 1304 to the tank 1306. The neck 1318 can be supported by a collar or a set of collars 1320. An outer sheath 1322 encases the neck 1318 and collar 1320. The outer sheath 1322 extends from the fluidic feed system 1304 to a base plate or surface 1324 of the tank 1306. The outer sheath 1322 is arranged at a distal end to contact the base plate or surface 1324 of the tank 1306 without being affixed thereto. The outer sheath 1322 forms a sufficient air-tight seal with the fluidic feed system 1304 and allows a sliding movement, such as a reciprocating sliding movement, of the neck 1318 within the outer sheath 1322 and the outer casing 1332 of the fluidic feed system 1304. The reciprocating sliding movement accommodates reciprocal movement of the tank 1306.

[0087] A set of biasing members 1326 is circumferentially disposed around the outer sheath 1322. The set of biasing members 1326 are arranged to urge the tank 1306 into contact with the distal end of the outer sheath 1322. The distal ends of the biasing members 1326 are coupled to the base plate or surface 1324 of the tank while the proximal ends of the biasing members 1326 are coupled to an anchor collar 1330. The anchor collar 1330 is coupled to the fluidic feed system 1304. Examples can be realised in which the proximal ends of the biasing members 1326 are coupled to an anchor ring 1334 of the fluidic fed system housing 1332 as opposed to being coupled to the anchor collar 1330.

[0088] The outlet 1310 in the depicted example can be realised as a convergent-divergent nozzle having a narrow throat. Alternatively, the outlet 1310 can be realised as a simple aperture. The cross-sectional area of the outlet 1310 can be changed to accommodate at least one, or both, of: projectiles of different masses and different magnitudes of recoil reaction.

[0089] Referring to figure 13B, there is shown a view 1300B of the recoil system 1302, the fluidic fed system 1304 comprising a centrally disposed outlet feed 1334, a retardation system 1336, a hollow inner tube 1338, a female sheath 1340. The retardation system 1336 is an example of the above-described retardation system 930. The hollow inner tube 1338 is an example of the above-described hollow inner tube 916. The female sheath 1340 is an example of the above-described female sheath 914. The recoil system 1302, the centrally disposed outlet feed 1334 and the retardation system 1336 are coupled and movable in unison.

[0090] Referring to figure 14, there is shown a detailed view 1400 of the elongate members 804 to 810 and respective recoil systems 824 to 830 in a first configuration in which the supports 820 and 822 are vertically disposed. The first configuration has the advantage of allowing a projectile (not shown) to be actuated using all elongate members or a subset of the elongate members. Such a subset of elongate members could comprise one, two or three elongate members.

[0091] Referring to figure 15, there is shown a view 1500 of the elongate members 804 to 810 and respective recoil systems 824 to 830 in a second configuration in which the supports 820 and 822 are horizontally disposed. The second configuration has the advantage of allowing a projectile (not shown) to be actuated using all elongate members or a subset of the elongate members. Such a subset of elongate members could comprise one, two or three elongate members. Where multiple elongate members are used to actuate a projectile, the elongate members can be adjacently disposed or non-adjacently disposed. For instance, a projectile can be actuated using two immediately adjacent elongate members such as first and second elongate members 804 and 808, or the centrally disposed pair of elongate members 808 and 810, or spaced apart elongate members such as, for instance, the outer most elongate members 804 and 806, or a pair of adjacent but one elongate members such as, for instance, elongate members 804 and 810 or elongate members 808 and 806.

[0092] In both the first and second configurations, up to four effectors or other deployable entities can be launched.

[0093] Referring to figure 16, there is shown a view 1600 of a control system 1602 for controlling the launcher system. The control system 1602 can comprise a primary control interface 1604. Optionally, a second, or remote, control interface 1606 can be provided. The second control interface 1606 can be coupled to the primary control interface 1604 for communication therebetween. The second control interface is intended to allow the launcher system to be operated at a safe distance. The safe distance can be, for instance, up to 100 m.

[0094] The primary control interface 1604 can issue commands to control the states of a set of valves used in the launcher system. The set of values is shown as comprising one or more than one of the following taken jointly and severally in any and all permutations: a fire valve 1608, an arming valve 1610, a pressure dump value 1612,a vent valve 1614, a fill valve 1616, a first pressure regulated valve 1618 and a second pressure regulated valve 1620.

[0095] The arming valve 1610 can comprise a normally closed pneumatically driven ball valve. The fire valve 1608 can comprise a pneumatically opened and closed ball valve.

[0096] The primary control interface 1604 can also receive sensor data from a set of sensors. The set of sensors can comprise at least one, or both, of: a first pressure sensor 1622, a second pressure sensor 1624. Using two pressure sensors provides a level of redundancy. Other sensors such as a temperature sensor can be included. The set of sensors can be used to monitor the pressure within a tank 1626. The tank 1626 is an example of above-described tanks 838 to 844.

[0097] The fire valve 1608 can be realised as a pneumatically driven ball valve. Examples can be realised in which the fire value opens within a predetermined period of time such as, for instance, between 0.08s to 0.12s, optionally 0.1s. The transition from the contracted state, shown in figure 10, to the fully expanded state, shown in figure 12, takes a predetermined period of time. Examples can be realised in which the predetermined period of time is of the order of 0.2s to 0.5s such as, for instance, 0.3s to achieve a desired launch speed for a respective mass of projectile. For instance, the projectile mass can be of the order of preferably 80kg to 300 kg, preferably 250 kg per member of the set of elongate members 804 to 810. Examples can be realised in which the launch speed is between 25 m / s and 60 m / s, optionally 55 m / s.

[0098] The arming valve 1610 controls the flow of pressurised air from the main tank 1626 to the fire valve 1608.

[0099] The fire valve 1608 and the arming valve 1610 are actuated by a pressure source. The pressure source can comprise an actuation tank 1628 containing a pressurised fluid such as air for actuating at least one, or both, of: the fire valve 1608 and the arming valve 1610. The pressure within the actuation tank 1628 can be controlled by the pressure regulator valve 1620.

[0100] The dump valve 1612 is arranged to rapidly reduce pressure within the tank 1626 such as might be beneficial in an emergency.

[0101] The pressure regulated valve 1618 is arranged to prevent the pressure in the tank 1626 from rising above a maximum predetermined limit.

[0102] The vent valve 1614 is arranged to allow controlled or progressive venting of pressure from the tank 1626.

[0103] The fill valve 1616 is arranged to allow the tank 1626 to be pressurised with air from an external source.

[0104] The fire valve can be controlled by solenoid valves opening and closing a respective air feed from the actuation tank.

[0105] The state table below reflects the states that can be adopted by the control system.

[0106] Using air pressure as an initial launch propellant has the advantage that it has a minimal heat signature in contrast to, for example, a rocket propellant typically associated with missiles. Using water as the reaction mass has the advantage that is leaves no lasting evidence at the launch site.

[0107] An effector is an example of a deployable entity. A deployable entity comprises at least one, or both, of: an effector and aircraft. An aircraft can comprise an Unmanned Air Vehicle. An effector can be a missile with a warhead.

[0108] Referring to figure 17, there is shown a view 1700 of first 1702 and second 1704 arrangements or relationships between the various components of the elongate members of the launcher systems described herein and the deployable entities.

[0109] Referring to the first arrangement 1702, there is provided a telescopic or extendible elongate member comprising an inner elongate hollow member 1706, a female member 1708 and a further female member 1710. The inner elongate hollow member 1706 hosts, or is received by, the female member 1708. The female member 1708 hosts, or is received by, the further female member 1710.

[0110] Examples can be realised in which the further female member 1710 forms part of a deployable entity. In this way, the deployable entity is mounted directly onto the overall telescopic or extendible elongate member of the launcher system.

[0111] Referring to the second arrangement 1704, there is provided a telescopic or extendible elongate member comprising the inner elongate hollow member 1706, the female member 1708, the further female member 1710 and a still further female member 1712. The elongate hollow member 1706 hosts, or is received by, the female member 1708. The female member 1708 hosts, or is received by, the further female member 1710. The further female member 1710 hosts, or is received by, the still further female member 1712.

[0112] Examples can be realised in which the still further female member 1712 forms part of a deployable entity. In this way, the deployable entity is mounted onto the overall telescopic or extendible elongate member of the launcher system via the intermediary the further female member 1710. Examples can be realised in which the further female member 1710 is a cartridge that is ejected from the launcher as part of launching the deployable entity. The cartridge or vessel separates from the deployable entity after, or during, launch. The cartridge or vessel can be recovered and re-used for respective launches of respective deployable entities.

[0113] It can be appreciated that the above-described inner elongate hollow member 204 can be, oris, an example of such an inner elongate hollow member 1706, that the above-described female, outer, or female sheath, elongate member 206 can be, or is, an example of such a female member 1708, and that the female member 202 can be, or is, an example of the above-described further female member 1710. In the examples described with reference to figure 2, the female member 202 can form part of the deployable entity. However, examples can be realised in which the female member 202 can be, or is, an example of the further female member 1710 that, in turn, hosts or otherwise cooperates with a respective or complementary formation of thedeployable entity such as, for example, an instance of the still further female member 1712 of the deployable entity.

[0114] Examples of launcher systems can be realised in which the first 1702 and second 1704 arrangements shown in and / or described with reference to figure 17 are applicable all launcher systems described and / or claimed herein.

[0115] Storing the gas in a liquid or gaseous phase, as has been described with reference to figures 1A-D. However, such storage can be applied to any of the examples described herein.

[0116] The deflectors in the above examples have been described with reference to having profiled surface to deflect any exhaust gas from the elongate members. However, examples can be realised in which the deflectors deflect exhaust airflows from propulsion systems of the deployable entities instead of deflecting exhaust gas from the elongate members.

[0117] Although examples have been described herein in which the volume of actuation fluid used to actuate the launcher system is a predetermined multiple of the extended volume of the inner elongate hollow member 204 and the outer female elongate member 206, that is, the extended volume of respective static and moveable member pairs, examples are not limited thereto. Examples can be realised in which the extended volume to be accommodate or otherwise used in accelerating a deployable entity comprises the volume of such a static member, the volume of such a moveable member and the volume of a cartridge or other vessel for cooperating with the deployable entity as described with reference to and / or as illustrated in figure 17. Furthermore, examples can be realised in which the total volume for accelerating a deployable entity can comprise the volume of such a static member, the volume of such a moveable member and the volume of a deployable entity provided to host such a moveable member.

[0118] Although the example described herein provide a recoil system, examples can be realised in any of launcher systems are realised without such a recoil system.

[0119] Even though the examples described herein can be realised using electric engines as thrust producers on the deployable entities, examples can be realised that use other types of thrust producers. Examples can be realised in which the thrust producers of the deployable entities are turbofans or turbojets.

[0120] Within the present application the terms proximal and distal are used relative to a movement datum such as the movement datum indicated in, for instance, figures 9, 10, 11 or 12.

[0121] Examples can be realised according to the following clauses:

[0122] Clause 1 : A launcher system for launching a deployable entity; the launcher system comprising:

[0123] a set of elongate hollow male members for bearing a fluid; the set of elongate hollow male members comprising at least one elongate hollow male member comprising a fluid ingress aperture and a fluid egress aperture. An actuation fluid is an example of such a fluid.

[0124] Clause 2: The launcher system of any preceding clause, further comprising an elongate hollow sheath member in a longitudinally sliding relationship with the at least one elongate hollow male member.

[0125] Clause 3: The launcher system of clause 2, comprising an impact attenuator, or crumple zone entity, to influence (restrict or slow down) longitudinal movement of the at least one elongate hollow sheath member, optionally, the impact attenuator is arranged to reduce the impulse force between a stop associated with the at least one elongate hollow male member and a stop associated with the at least one elongate hollow sheath member.

[0126] Clause 4: The launcher system of any preceding clause, in which the set of elongate hollow male members comprises at least three elongate hollow male members, optionally, the at least three elongate hollow male members are distributed in a triangular arrangement.

[0127] Clause 5: The launcher system of any preceding clause, in which the set of elongate hollow male members comprises at least four elongate hollow male members, optionally, the at least four elongate male members are distributed in a rectangular or square arrangement.

[0128] Clause 6: The launcher system of any preceding clause, in which the at least one elongate hollow male member has a predetermined length, optionally, the predetermined length is 5m.

[0129] Clause 7: A launcher system for launching a deployable entity; the launcher system comprising:

[0130] at least one elongate male member for insertion into a complementary elongate female member of the deployable entity; the at least one elongate male member being telescopically extendible between a contracted state and an extended state in response to:

[0131] an actuating fluid supplied by an actuating fluid ingress aperture of the at least one elongate male member, and

[0132] a coupling (striction) between the at least one elongate male member and the complementary elongate female member;

[0133] to launch the deployable entity.

[0134] Clause 8: The launcher system of clause 7, in which the at least one elongate male member comprises an inner elongate hollow member for receiving the actuating fluid and a female outer, or female sheath, elongate member in a longitudinally slidable relationship with the inner elongate hollow member; the female outer, or female sheath, elongate member concentrically housing the inner elongate hollow member.

[0135] Clause 9: The launcher system of clause 8, in which the inner elongate hollow member and the female outer, or female sheath, elongate member have respective stops to limit the extension, or relative longitudinal sliding, of the inner elongate male member and the female outer, or female sheath, elongate member.

[0136] Clause 10: The launcher system of clause 9, in which a frangible member is disposed between the stops to limit the impulse force arising from limiting the extension.

[0137] Clause 11: The launcher system of clause 10, in which the frangible member is a frangible annulus.

[0138] Clause 12: The launcher system of clause 11, in which the frangible member comprises a frangible foraminate member, optionally, the frangible foraminate member comprises a carbon annular member bearing a plurality of through vias.

[0139] Clause 13: The launcher system of any preceding clause comprising an actuatable platform to orientate the deployable entity at a launch angle, or elevation angle.

[0140] Clause 14: The launcher system of clause 13, in which the actuatable platform is L-shaped; the L-shaped platform comprising a first planar body bearing the at least one elongate male member.

[0141] Clause 15: The launcher system of clause 14, in which the first planar body comprises a profiled surface arranged to deflect any exhaust fluid ejected from an exhaust port of the at least one elongate member.

[0142] Clause 16: A deployable entity for use with a launcher system of any preceding clause; the deployable entity comprising a female member for accommodating a complementary male member of the launcher system; the female member providing a reaction interface between the actuation fluid of the launcher system and the deployable entity to launch the deployable entity.

[0143] Clause 17: The deployable entity of clause 16, in which the deployable entity comprises an aircraft or ordnance.

[0144] Clause 18: The deployable entity of either of clauses 18 or 19 comprising an elongate body bearing thrust producers for providing thrust to the deployable entity.

[0145] Clause 19: The deployable entity of clause 18, in which the thrust producers are electric thrust producers.

[0146] Clause 20: The deployable entity of either of clauses 18 or 19, in which the thrust producers comprise at least a first set of thrust producers; the first set of thrust producers being disposed in an aft location of the deployable entity.

[0147] Clause 21: The deployable entity of any of clauses 18 to 20, in which the thrust producers comprise at least a second set of thrust producers; the second set of thrust producers being disposed in a fore location of the deployable entity.

[0148] Clause22: The deployable entity of clause 21, in which the first and second sets of thrust producers are arranged in a tandem arrangement.

[0149] Clause 23: The deployable entity of clause 22, in which

[0150] the first set of thrust producers comprises a first respective set of air inlets and a first respective set of air outlets, and

[0151] the second set of thrust producers comprises a second respective set of air inlets and a second respective set of air outlets.

[0152] Clause 24: The deployable entity of clause 23, in which the first and second sets of air inlets and air outlets are perpendicularly disposed relative to one another.

[0153] Clause 25: The deployable entity of any of clauses 16 to 24, comprising a set of wings to generate lift during flight of the deployable entity.

[0154] Clause 26: The deployable entity of clause 25, in which air exhaust from the second respective set of air outlets is arranged to flow over an upper surface of at least one wing of the set of wings.

Claims

CLAIMS1. A launcher system for launching a deployable entity; the launcher system comprising:a. a set of telescopic elongate members for receiving a first fluid; the set of telescopic elongate members comprising a static member and a moveable member; the moveable member being arranged to actuate the deployable entity; the set of elongate members being expandable between a contracted state and an expanded state to launch the deployable entity in response to ingress of the first fluid.

2. The launcher system of claim 1 , in which the moveable member is in a longitudinally sliding relationship with the static member.

3. The launcher system as claimed in claim 2, comprising a retardation assembly arranged to decelerate or stop longitudinal movement of the moveable member.

4. The launcher system as claimed in claim 3, in which the retardation assembly comprises a piston having a crown moveable within bore; the bore having a perforated region and unperforated region; the unperforated region being arranged to progressively increase pressure within the piston in response to movement of the crown.

5. The launcher system as claimed in any preceding claim, further comprising a set of recoil systems; the set of recoil systems comprising one recoil system per elongate member of the set of telescopic elongate members; each recoil system being arranged to balance reaction forces associated with expanding a respective elongate member of the set of telescopic elongate members from the contracted state to the expanded state.

6. The launcher system as claimed in claim 5, in which each recoil system comprises a tank, bearing a second fluid, housing a piston; the piston being moveable in response to ingress of the first fluid to eject the second fluid from the tank.

7. The launcher system as claimed in any preceding claim, comprising a plurality of sets of telescopic elongate members; optionally, the plurality of sets of telescopic elongate members comprises at least three sets of telescopic elongate members, optionally, the at least three sets of telescopic elongate members are distributed in a triangular arrangement.

8. The launcher system as claimed in claim 7, in which the plurality of sets of telescopic elongate members comprises at least four set of telescopic elongate members, optionally, the at least four set of telescopic members are distributed in a rectangular or square arrangement.

9. The launcher system as claimed in either of claims 7 or 8, in which the plurality of sets of telescopic elongate members are configurable in a number of layouts.

10. The launcher system as claimed in claim 9, in which the number of layouts comprises a plurality of adjacent linearly disposed sets of telescopic elongate members.

11. The launcher system as claimed in any preceding claim comprising a frangible mechanical coupling for coupling the deployable entity to the moveable elongate member.

12. A deployable entity for use with a launcher system as claimed in any preceding claim; the deployable entity comprising a female member for accommodating a complementary male member of the launcher system; the female member providing a reaction interface between the first fluid of the launcher system and the deployable entity to launch the deployable entity.

13. The deployable entity as claimed in claim 12, in which the deployable entity comprises a missile or a drone.

14. The deployable entity as claimed in claim comprising an elongate body bearing thrust producers for providing thrust to the deployable entity.

15. The deployable entity as claimed in claim 14, in which the thrust producers are electric thrust producers.

16. The deployable entity as claimed in either of claims 14 or 15, in which the thrust producers comprise at least a first set of thrust producers; the first set of thrust producers being disposed in an aft location of the deployable entity.

17. The deployable entity as claimed in any of claims 14 to 16, in which the thrust producers comprise at least a second set of thrust producers; the second set of thrust producers being disposed in a fore location of the deployable entity.

18. The deployable entity of claim 17, in which the first and second sets of thrust producers are arranged in a tandem arrangement.

19. The deployable entity as claimed in claim 18, in whicha. the first set of thrust producers comprises a first respective set of air inlets and a first respective set of air outlets, andb. the second set of thrust producers comprises a second respective set of air inlets and a second respective set of air outlets.

20. The deployable entity of claim 19, in which the first and second sets of air inlets and air outlets are perpendicularly disposed relative to one another.

21. The deployable entity of any of claims 12 to 20, comprising a set of wings to generate lift during flight of the deployable entity.

22. The deployable entity of claim 21 , in which air exhaust from the second respective set of air outlets is arranged to flow over an upper surface of at least one wing of the set of wings.

23. The deployable entity as claimed in any of claims 12 to 22, comprising means to accommodate a frangible linkage between the deployable entity and a moveable member of the launcher system.

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