Stacked projectile launcher system

Abstract

A stacked projectile launcher system is disclosed. The system includes: a first projectile engaged with a second projectile to define a projectile column having a central axis, the second projectile located at a distal end of the projectile column. A propulsion mechanism is connected to the first projectile or the second projectile, or to both projectiles, for sequentially propelling each projectile from the projectile column. A guide assembly provides directional guidance to the second projectile during launch, and the guide assembly comprises a guide surface of the first projectile and a guide surface of the second projectile, wherein the guide surface of the first projectile and the guide surface of the second projectile slidably engage each other and are parallel to the central axis. A controller operatively is connected to the propulsion mechanism.

Description

TITLESTACKED PROJECTILE LAUNCHER SYSTEMFIELD OF THE INVENTION

[0001] The present invention relates generally to a stacked projectile launcher, and in particular but not exclusively to a stacked projectile launcher that offers compatibility and versatility for a range of applications.BACKGROUND TO THE INVENTION

[0002] Projectile launch systems have long played a vital role in military operations, enabling the delivery of explosive ordnance to distant targets. The M7 rifle grenade launcher and the M17 fragmentation rifle grenade are notable examples among such systems.

[0003] The M7 rifle grenade launcher and M17 fragmentation rifle grenade combination gained significant prominence during World War II for its innovative design, utilising a rod and socket assembly. In this mechanism, the rod served as the launcher, while the projectile acted as the socket. Upon ignition, the expanding propellant filled the rifle barrel and entered the launcher rod, generating high pressure at the base of the socket. This propelled the rifle grenade for effective long-range deployment, achieving a range of approximately 200 meters with a barrel length of approximately 9-10 centimetres. To further extend the range, an auxiliary booster charge called the "Vitamin Pill" could be employed, providing an additional 90-135 meters of reach. However, despite these advantages, the effectiveness of the M7 launcher and M17 fragmentation grenade was ultimately limited by their reliance on the size of the rifle cartridge. This dependency imposed constraints on the overall power and range capabilities of the weapons, presenting challenges in certain operational scenarios. One significant disadvantage was the limitations it imposed on propellant loads. The reliance on the size of the rifle cartridge resulted in variations in the launch velocity and trajectory of projectiles, impacting their accuracy and consistency. Additionally, the limitedcapacity of the launcher to accommodate larger cartridges restricted the overall power and range potential of the weapons, limiting their effectiveness in situations that demanded greater firepower or extended range capabilities.

[0004] However, since World War II, the use of rifle grenades has declined, and standalone grenade launchers like the M79 and M203 have become more prevalent. Standalone launchers offer the advantage of simultaneous use of the rifle and grenade launcher without configuration changes. Furthermore, these launchers utilise dedicated grenade cartridges, eliminating limitations imposed by the propellant load of the rifle cartridge. Yet, compared to rife-mounted grenade launchers, standalone launchers are limited by their increased weight and bulkiness.

[0005] To address these limitations, attempts have been made to develop stacked projectile launcher systems. These systems arrange projectiles axially with propellant charges between them, allowing for high rates of fire through sequential ignition. However, existing stacked projectile systems suffer from several drawbacks. They often require the use of cumbersome and costly barrels, leading to the burden of carrying empty barrels post-firing. Also, the incorporation of inductive ignition, high voltage electronics, and batteries become necessary, and establishing direct electrical connections between projectiles presents several challenges. Moreover, the launch pressure exerted by one projectile can influence others, and these systems are not tailored for single-use scenarios. Inconsistent muzzle velocities further manifest as projectiles are discharged from various positions within the same barrel.

[0006] There is therefore a need for an improved stacked projectile launcher system that is simple in design and manufacturing, lightweight and costefficient.OBJECT OF THE INVENTION

[0007] It is an object of the present invention to overcome and / or alleviate one or more of the disadvantages of the prior art or provide the consumer with a useful alternative.SUMMARY OF THE INVENTION

[0008] In one form, although not necessarily the broadest form, the invention resides in a stacked projectile launcher system, comprising:A stacked projectile system comprising: a first projectile engaged with a second projectile to define a projectile column having a central axis, the second projectile located at a distal end of the projectile column; a propulsion mechanism connected to the first projectile or the second projectile, or to both projectiles, for sequentially propelling each projectile from the projectile column; a guide assembly for providing directional guidance to the second projectile during launch, the guide assembly comprising a guide surface of the first projectile and a guide surface of the second projectile, wherein the guide surface of the first projectile and the guide surface of the second projectile slidably engage each other and are parallel to the central axis; and a controller operatively connected to the propulsion mechanism.

[0009] Preferably, each projectile includes a main body and a modular insert secured within the main body.

[0010] Preferably, the modular insert includes a payload and a fuse or detonator to ignite the payload upon impact.

[0011] Preferably, the guide assembly includes a launch rod extending forward from a middle section of each projectile and a launch socket extending rearward from the middle section of each projectile, the launch rod of the first projectile being receivable in the launch socket of the second projectile to define a launch rod and socket assembly.

[0012] Preferably, an outer surface of the launch rod of the first projectile defines the guide surface of the first projectile, and an inner surface of thelaunch socket of the second projectile defines the guide surface of the second projectile.

[0013] Preferably, the launch socket of the first projectile is engageable with a launching device, the launching device having a forward extending launch rod receivable in the launch socket of the first projectile to define a launch rod and launch socket assembly.

[0014] Preferably, the first projectile is identical to the second projectile.

[0015] Preferably, an expandable cavity is defined by the launch rod and launch socket assembly.

[0016] Preferably, the expandable cavity forms a barrel-like enclosure.

[0017] In some embodiments, each projectile includes a rearward-mounted drag assembly extending radially outward from the main body.

[0018] In some embodiments, the rearward-mounted drag assembly comprises a circular fin encircling a series of radial fins, or an outer circumference on each launch rod has protruding rails engageable with corresponding grooves on the launch socket of the respective projectile is configured to spin the respective projectile for spin-stabilisation when propelled from the projectile column.

[0019] In some embodiments, the projectile column is supported by the launching device.

[0020] In some embodiments, the first projectile is releasably connectable to the second projectile to enable reload on a per column basis.

[0021] In some embodiments, the first projectile is releasably connectable to the second projectile to enable reload on an individual projectile basis.

[0022] In some embodiments, the first projectile includes a plug or other mechanical connection along an exterior circumference at a rear end of the launch socket of the first projectile configured to mate with a corresponding plug or other mechanical connection on the launch rod of the launching device, thereby mechanically and electrically connecting the launching device to the projectiles.

[0023] In some embodiments, the launching device includes a series of claws configured to engage a small channel in the exterior circumference of the first projectile for snap locking the projectile column to the launching device.

[0024] In some embodiments, the launching device includes rails and grooves for radially aligning the projectile column to the launching device.

[0025] In some embodiments, the propulsion mechanism includes a propellant and an electrical or mechanical trigger, the trigger configured to ignite the propellant charge and cause a combustion of the propellant that expands in the expandable cavity for applying a propelling force to the launch socket of the second projectile.

[0026] In some embodiments, the combustion of the propellant is contained within the expandable cavity.

[0027] In some embodiments, the propulsion mechanism further includes a barrier to seal the propellant charge from inadvertent ignition.

[0028] In some embodiments, the electrical or mechanical trigger is housed within a launching device.

[0029] In some embodiments, the second projectile further includes a tubular ignition cavity communicating a rearward face of the launch socket of the second projectile with the expandable cavity to allow the propellant to expand and propel the second projectile.

[0030] In some embodiments, each projectile further includes a number of tubular bypass cavities in its launch socket to enable the propellant to expand to other projectiles in the projectile column.

[0031] In some embodiments, each projectile further includes a guide rail in its launch rod and a corresponding groove in its launch socket to radially align the projectile column such that the ignition cavities and bypass cavities couple cooperatively.

[0032] In some embodiments, the propulsion mechanism communicates the expanding gases between each launch rod and launch socket assembly to enable launch via launch cavities in the launching device.

[0033] In some embodiments, the propulsion mechanism includes an induction coil circumferentially wound in each launch rod and launch socket assembly, the controller configured to initiate a current between each launch rod and launch socket assembly to generate opposing magnetic fields for applying a propelling force on the launch socket of each projectile.

[0034] In some embodiments, the poles of each magnetic field are in line with a radial centre of the projectile column.

[0035] In some embodiments, the propulsion mechanism includes a longitudinal spring assembly associated with an inner circumference of the launch socket on each projectile, the spring assembly configured to compress and expand for applying a propelling force on the launch socket of each projectile.

[0036] In some embodiments, the spring assembly includes a plurality of radially disposed springs configured to compress when the launch socket of each projectile is in engagement with the launch rod of a corresponding projectile.

[0037] In some embodiments the spring assembly further includes a clasp assembly to lock each launch rod and launch socket assembly in place when each projectile is in a compressed state in the projectile column.

[0038] In some embodiments, the system further comprises one or more additional projectiles in the projectile column.

[0039] In some embodiments, the system further comprises one or more additional projectile columns, the projectile columns engageable with a multi- column launching device.

[0040] In some embodiments, the projectile columns form an array of projectiles mechanically supported in three-dimensions.

[0041] In some embodiments, the projectiles have flattened edges to facilitate stacking of the projectile columns in three-dimensions.

[0042] In some embodiments, the guide assembly includes a rail and groove on each projectile.

[0043] In some embodiments, the projectiles include interlocking rails and grooves on top and bottom surfaces of the projectiles.

[0044] In some embodiments, wherein side surfaces of the projectiles further include interlocking rails and grooves to lock the projectiles together as a unit.

[0045] In some embodiments, the projectiles define a projectile array supported by a box-like enclosure for easy transport and to facilitate projectile launch.

[0046] In some embodiments, the box-like enclosure has inner surfaces including corresponding rails and grooves to support outer edges of the projectile array.

[0047] In some embodiments, the projectile array forms a pod configuration including a plurality of projectiles.

[0048] In some embodiments, the modular insert spans an axial length of a launch rod enabling mechanical or electrical connection between the projectiles through the modular insert.

[0049] In some embodiments, the modular insert forms an insert column for a series of frangibly connected inserts.

[0050] In some embodiments, each projectile includes a rotor and wings, and the propulsion mechanism is configured to provide remote-controlled propulsion to each projectile.

[0051] In some embodiments, the propulsion mechanism further includes a rocket motor.

[0052] In some embodiments, the projectile column is connected to the launching device via a rail.

[0053] In some embodiments, the projectiles comprise a size, shape and mass for desired flight characteristics.

[0054] In some embodiments, each projectile comprises a dual launch rod and launch socket defining a dual launch rod and socket assembly between projectiles and the launching device.

[0055] In some embodiments, each projectile further comprises a two-stage burner assembly for improving a combustion of gases that expand in the expandable cavity for applying a propelling force on the launch socket of each projectile.

[0056] In some embodiments, the two-stage burner assembly comprises a main burner body, a propellant cup for housing a propellant charge and to reduce inadvertent ignition of the propellant charge, and a burner exhaust engageable with the main burner body. The burner exhaust has one or more holes through which propellant charge can expand once the propellant charge has been ignited and the propellant cup has been ruptured.

[0057] In some embodiments, each projectile further comprises a printed circuit board and power source for receiving an electromagnetic signal from the controller to initiate launch of that projectile.

[0058] In some embodiments, the printed circuit board and power source each include an enclosure assembly.

[0059] In some embodiments, communication between the projectiles and the controller is encrypted.

[0060] Further forms and / or features of the present invention will become apparent from the following detailed description.BRIEF DESCRIPTION OF THE DRAWINGS

[0061] In order that the invention may be readily understood and put into practical effect, reference will now be made to preferred embodiments of the present invention with reference to the accompanying drawings, wherein like reference numbers refer to identical elements. The drawings are provided by way of example only, wherein:

[0062] FIG. 1 shows a schematic of a rifle grenade launcher and a fragmentation rifle grenade in a ready-to-fire position, as known from the prior art;

[0063] FIG. 2 shows a schematic of a stacked projectile system, according to an embodiment of the invention;

[0064] FIG. 3 shows a schematic of a projectile for use in the system of FIG. 2, according to an embodiment of the invention;

[0065] FIG. 4 shows a schematic of exemplary cross-sections and configurations of a projectile for use in a stacked projectile system, according to some embodiments of the invention;

[0066] FIGS. 5A and 5B show schematics of another projectile for use in a stacked projectile system, according to an embodiment of the invention;

[0067] FIG. 6A shows a schematic of another projectile for use in a stacked projectile system, according to an embodiment of the invention;

[0068] FIGS. 7A, 7B and 7C show schematics of various other projectiles for use in a stacked projectile system, according to some embodiments of the invention;

[0069] FIG. 8A shows a schematic of another projectile for use in a stacked projectile system, according to an embodiment of the invention;

[0070] FIG. 8B shows a schematic of another projectile for use in a stacked projectile system, according to an embodiment of the present invention;

[0071] FIG. 9 shows a schematic of another projectile for use in a stacked projectile system, according to an embodiment of the invention;

[0072] FIG. 10 shows a schematic of another projectile for use in a stacked projectile system, according to an embodiment of the invention;

[0073] FIGS. 11 A, 11 B, 11 C and 11 D show schematics of exemplary propulsion mechanisms for use in a stacked projectile system, according to some embodiments of the present invention;

[0074] FIG. 12A shows a schematic of another projectile, similar to the projectile of FIG. 3, for use in a stacked projectile system, according to an embodiment of the invention;

[0075] FIG. 12B and 12C show schematics of the internal components of the projectile of FIG. 12A, according to an embodiment of the invention;

[0076] FIG. 13 shows a schematic of another projectile, similar to the projectile of FIG. 12A, in a projectile column of two projectiles, according to an embodiment of the invention;

[0077] FIG. 14 shows a schematic of a stacked projectile system in a pod configuration, according to an embodiment of the invention;

[0078] FIGS. 15A, 15B and 15C show schematics of a stacked projectile system in various other pod configurations, according to some embodiments of the invention;

[0079] FIGS. 16A, 16B, 16C, 16D, 16E and 16F show schematics of various projectiles for use in a stacked projectile system, according to some embodiments of the invention;

[0080] FIGS. 17A, 17B and 17C show perspective views of a stacked projectile system in various pod configurations, according to some embodiments of the invention;

[0081] FIG. 17D shows a perspective view of two projectiles in a projectile column for use in a stacked projectile system, according to an embodiment of the invention;

[0082] FIG. 17E shows a perspective view of a stacked projectile system in an alternative pod configuration, according to another embodiments of the invention;

[0083] FIGS. 18A, 18B and 18C show perspective views of various other projectiles for use in a stacked projectile system, according to some embodiments of the invention;

[0084] FIG. 19 shows a schematic of a stacked projectile system utilising the projectiles of FIG. 18C in a pod configuration, according to an embodiment of the invention;

[0085] FIGS. 20A, 20B, 20C and 20D show various views of a stacked projectile system in pod configurations utilising the projectiles of FIGS. 18A, 18B or 18C, according to some embodiments of the invention;

[0086] FIGS. 21 A and 21 B show perspective views of various plane-drone projectiles for use in a stacked projectile system, according to some embodiments of the invention;

[0087] FIGS. 21 C and 21 D show perspective views of the projectiles of FIG. 21 A in a pod configuration, according to some embodiments of the invention;

[0088] FIG. 21 E shows a perspective view of the pod of FIG. 21 D on a vehicle, according to an embodiment of the invention;

[0089] FIGS. 22A and 22B show perspective views of other plane-drone projectiles for use in a stacked projectile system, according to some embodiments of the invention;

[0090] FIG. 23 shows a perspective view of a stacked projectile system utilising the projectiles of FIG. 22A or 22B in a pod configuration, according to some embodiments of the invention;

[0091] FIG. 24A shows a perspective view of another projectile for use in a stacked projectile system, according to an embodiment of the invention;

[0092] FIG. 24B shows a perspective view of a stacked projectile system utilising the projectiles of FIG. 24B in a pod configuration, according to an embodiment of the invention;

[0093] FIGS. 25A and 25B show perspective views of other plane-drone projectiles for use in a stacked projectile system, according to some embodiments of the invention;

[0094] FIGS. 25C and 25D show perspective views of stacked projectile system utilising the projectiles of FIG. 25B, according to some embodiments of the invention;

[0095] FIG. 25E shows a pod of projectiles from FIG. 25D on an aircraft, according to an embodiment of the invention;

[0096] FIGS. 26A and 26B show perspective views of various helicopter-drone like projectiles for use in a stacked projectile system, according to some embodiments of the invention;

[0097] FIGS. 26C and 26D show perspective views of the helicopter-drone like projectiles of FIGS. 26A or 26B in a pod configuration, according to some embodiments of the invention;

[0098] FIGS. 26E, 26F and 26G show perspective views of other helicopterdrone like projectiles for use in a stacked projectile system, according to some embodiments of the invention;

[0099] FIG. 26H shows a perspective view of the helicopter-drone projectiles of FIG. 26G in a projectile column for use in a stacked projectile system, according to an embodiment of the invention;

[0100] FIG. 27A shows a perspective view of another projectile for use in a stacked projectile system, according to an embodiment of the invention;

[0101] FIGS. 27B, 27C, 27D and 27E show perspective views of various stacked projectile systems, according to some embodiments of the invention;

[0102] FIGS. 28A, 28B, 28C, 28D, and 28E show perspective views of various missile-like projectiles for use in a stacked projectile system, according to some embodiments of the invention;

[0103] FIGS. 28F and 28G show views of the missile-like projectiles from either FIGS. 28A-E in various pod configurations, according to some embodiments of the invention; and

[0104] FIG. 28H shows a perspective view of the missile-projectiles from either FIGS. 28A-E arranged in another pod configuration, according to an embodiments of the invention.

[0105] Skilled addressees will appreciate that the drawings may be schematic and that elements in the drawings are illustrated for simplicity and clarity and have not necessarily been drawn to scale. For example, the relative dimensions of some of the elements in the drawings may be distorted to help improve understanding of embodiments of the present invention.DETAILED DESCRIPTION OF THE INVENTION

[0106] The present invention relates to a stacked projectile launcher system. Elements of the invention are illustrated in concise outline form in the drawings,showing only those specific details that are necessary to understand the embodiments of the present invention, but so as not to provide excessive detail that will be obvious to those of ordinary skill in the art in light of the present description.

[0107] In this specification, adjectives such as first and second, front and rear, inner and outer, and the like may be used solely to distinguish one element or action from another element or action without necessarily requiring or implying any actual such relationship or order. Words such as “propelling”, “firing”, “launching” and “ejecting” are intended to disclose a similar meaning; and words such as “comprises” or “includes” are intended to define a non-exclusive inclusion, such that the system or apparatus that comprises a list or elements does not necessarily include only those elements but may include other elements not expressly listed, including elements that are inherent to such a system or apparatus.

[0108] According to a first aspect, the present invention relates to a stacked projectile launcher system comprising: a first projectile engaged with a second projectile to define a projectile column having a central axis, the second projectile located at a distal end of the projectile column; a propulsion mechanism connected to the first projectile or the second projectile, or to both projectiles, for sequentially propelling each projectile from the projectile column; a guide assembly for providing directional guidance to the second projectile during launch, the guide assembly comprising a guide surface of the first projectile and a guide surface of the second projectile, wherein the guide surface of the first projectile and the guide surface of the second projectile slidably engage each other and are parallel to the central axis; and a controller operatively connected to the propulsion mechanism.

[0109] Various embodiments of the present invention can offer advantages that provide an effective solution for various applications, particularly military operations.[001 10] Particular advantages of some embodiments concern the removal of the need for a gun barrel, which can offer a lightweight and cost-effective solution to alternative systems. The removal of this requirement also renders the need for inductive ignition and associated high voltage electronics and batteries obsolete, enabling the system to be powered by, for example, a simple 9V battery in conjunction with a small controller in certain applications that synergistically achieve a less expensive system that is readily manufacturable. Further, embodiments help facilitate direct electrical connections between projectiles in a straightforward manner, which simplifies the design and manufacturing process.[001 11 ] Additionally, by obviating the necessity of gun barrels, projectiles of the present invention are unencumbered by the confines of barrels, offering increased versatility in terms of size and shape. For example, projectiles of the present invention can adopt unconventional geometries, such as plane-like forms for drones, without compromising the system’s performance. Such versatility can also contribute to favourable payload-to-system weight ratios, enhancing the system’s operational efficiency and performance.[001 12] Moreover, the absence of gun barrels ensures that projectiles do not need to withstand launch pressures beyond the launch apparatus, effectively preventing the risk of ‘blow-by’ ignition and contributing to enhanced operational safety and precise projectile launches.[001 13] Another advantage of some embodiments concerns the ability to independently launch projectiles within a projectile column with consistent launch velocity, improving accuracy, reliability and predictability during projectile launches.[001 14] Other advantages of some embodiments include the flexibility to reload on an individual basis, per column basis, or through integrated designs. This adaptability grants the system versatility in accommodating diverse operational requirements, particularly in military contexts, where the ability to replenishprojectiles promptly in accordance with specific mission objectives assumes paramount importance. Also, within the context of single-use integrated designs, the launch apparatus of the present invention only needs to withstand firing pressure once, possibly twice in some applications, which translates into a cost-effective manufacturing process compared to conventional systems which are built to endure multiple repeated firings throughout their lifetime.[001 15] Further advantages of some embodiments of the present invention offer a compact footprint and compatibility with a wide range of materials including plastics, making the system highly adaptable for applications with spatial constraints and stringent system design requirements.[001 16] It will be appreciated that not all embodiments of the present invention necessarily include all of the above-mentioned advantages.[001 17] FIG. 1 shows a schematic of a rifle grenade launcher 1 10 and a fragmentation rifle grenade 120 part way through launch, as known from the prior art. An example of such a system includes the M7 rifle grenade launcher and the M17 fragmentation grenade. In this configuration, the fragmentation rifle grenade 120 includes a rearwardly mounted launch socket 121 configured to cooperatively engage with a corresponding launch rod 1 11 on the rifle grenade launcher 1 10. This launch rod and socket assembly 1 1 1 , 121 forms a barrel-like enclosure 130 that contains the pressure generated during firing, thereby facilitating the launch of the fragmentation rifle grenade 120.[001 18] FIG. 2 shows a schematic of a stacked projectile system 200, according to an embodiment of the present invention. For the purposes of distinction in this description, projectiles 210 in this system 200 will be referred to as the first, second, third, and fourth projectiles; however, it should be understood that these projectiles are identical in structure and function, and thus will be denoted by using apostrophes (', ", andAdditionally, it should be noted that any number of projectiles can be implemented within the scope of the present invention, depending on the specific requirements of the system 200. Furthermore, as will be described hereinafter, the projectiles can be of various shapes and sizes, with the shape depicted in the schematic being merely illustrative and not limiting.[001 19] In this embodiment, the projectiles 210 are configured to cooperatively engage with each other in an axially stacked arrangement to define a projectile column 220. Specifically, the first projectile 210’ is located at a proximal end of the projectile column 220, the second projectile 210” and third projectile 210”’ are positioned sequentially within the projectile column 220, and the fourth projectile 210”” is located at a distal end of the projectile column 220. The projectile 210 at the distal end of the projectile column 220, which in this case is the fourth projectile 210””, is the first to be launched.

[0120] A propulsion mechanism (not shown) is connected to each projectile 210 for sequentially propelling the projectiles 210 from the projectile column 220. This propulsion mechanism may include, but is not limited to, a propellant charge, electromagnetic forces, electrical charges, linear actuators, springs, compressed air, or other suitable means for generating the necessary force to launch the projectiles 210. Embodiments of these propulsion mechanisms are disclosed hereinafter.

[0121] A guide assembly, or traveling guide assembly, is associated between adjacent projectiles 210 and includes surfaces oriented parallel to a central axis of the column 220 (which is parallel to the direction of travel of the projectiles 210 during launch), and provides directional guidance to the projectiles 210 during launch. For example, a traveling guide assembly is associated between the third projectile 210’” and fourth projectile 210”” such that, when the fourth projectile 210”” is propelled from the projectile column 220, the traveling guide assembly helps maintain alignment of the fourth projectile 210”” along a path parallel to the direction of travel. The same guiding principle applies to subsequent projectiles in the column as they are launched in sequence.

[0122] A controller is operatively connected to the propulsion mechanism for launching the projectiles. The controller is configured to manage the sequence of projectile launches, allowing for either simultaneous launch of all projectiles 210 or independent and sequential launching of individual projectiles 210 as desired. For example, the controller can be operated to launch only the fourth projectile 210”” from the projectile column 220 if such functionality is required. The controller is integrated into a launching device 230 that facilitates userinteraction with the system 200, providing control over the firing sequence and operational parameters of the propulsion mechanism.

[0123] FIG. 3 shows a schematic of a projectile 210 for use in the stacked projectile system 200, according to an embodiment of the present invention.

[0124] The projectile 210 has a main body that can be manufactured in various sizes, shapes, and materials, including, but not limited to, metals such as steel or aluminium, or plastics such as polycarbonate. This flexibility allows the projectile 210 to be tailored to specific operational requirements.

[0125] The main body includes a middle section 310, a launch rod 31 1 , and a launch socket 312. The launch rod 31 1 extends from the middle section 310 towards a front end 313 of the projectile 210, while the launch socket 312 extends from the middle section 310 towards a rear end 314 of the projectile 210. Notably, the middle section 310 of this embodiment is of zero length, such that the launch rod 311 and launch socket 312 span an entire length of the projectile 210. Specifically, the launch rod 31 1 spans a front section of the projectile 210, while the launch socket 312 spans a rear section of the projectile 210. This configuration may be advantageous in scenarios where high-speed launches and long-range accuracy are of importance. In other embodiments, which will be described hereinafter, the middle section 310 may have a nonzero length.

[0126] The arrangement of the launch rod 31 1 and launch socket 312 in this embodiment is configured to facilitate the axial stacking of projectiles 210 and the formation of a traveling guide assembly when used in the system 200. For example, the launch rod 311 of the first projectile 210’ is configured to be received in the launch socket 312 of the second projectile 210”; and the launch rod 311 of the second projectile 210” is similarly configured to be received in the launch socket 312 of the third projectile 21 O’”, and so forth. Additionally, the launch socket 312 of the first projectile 210’ is configured to fit over a corresponding launch rod 31 1 associated with the launching device 230.

[0127] The interaction between adjacent launch rods 311 and launch sockets 312 forms a 'barrel-like' enclosure that serves as the traveling guide assembly. For example, as the fourth projectile 210”” leaves the projectile column 220,the launch rod 311 of the third projectile 210”’ helps maintain alignment of the fourth projectile 210”” along the path defined by a length of the launch socket 312. During launch, an outer surface 313 of the launch rod 31 1 of the third projectile 210”’ defines a guide surface that slidably engages an inner surface 314 (defining another guide surface) of the launch socket 312 of the fourth projectile 210””. As shown, both surfaces 313, 314 are parallel to a central axis of the projectile column 220 and to the direction of travel at launch of the fourth projectile 210””.

[0128] Located at a front end 315 and a rear end 316 of the launch socket 312 is a mechanical connection assembly in the form of a spigot and socket type mechanical connection assembly. The spigot and socket type mechanical connection assembly comprises a spigot 321 extending rearward from the rear end of the launch socket 312 and a corresponding socket 322 at the rear end of the launch rod 311 . The spigot and socket may have various cross-sectional shapes, such as square, rectangular, or any other suitable configuration, depending on the design requirements.

[0129] The spigot and socket mechanical connection assembly in this embodiment is configured to mechanically lock or clip adjacent projectiles 210 to one another when used in the system 200. For example, the spigot 321 of the first projectile 210’ is configured to fit into the socket 322 of the second projectile 210”, and similarly, the spigot 321 of the second projectile 210” engages with the socket 322 of the third projectile 210’”, and so forth. This arrangement provides a robust mechanical connection that ensures the first, second, and third projectiles 210 remain securely attached to each other, even under the influence of forces generated when the fourth projectile 210”” is launched from the projectile column 210. Moreover, the spigot and socket connection assembly may act as a radial key between adjacent projectiles 210 to substantially minimise any rotational movement between the projectiles 210 under the influence of launch forces.

[0130] Also located at the front and rear end of the launch socket 312 are plugs 330 for accommodating wires and other electrical components to facilitate mechanical and electrical connections between the projectiles 210 when usedin the system 200. The plugs 330 can take many forms, including annular, magnetic or sliding / travelling configurations. Notably, annular magnetic electrical plugs 330 paired with a travelling mechanical connection assembly, such as the spigot and socket mechanical assembly described above, may be particularly advantageous for enabling secure and reliable electrical and mechanical connections between the projectiles 210 in the stacked projectile system 200.

[0131] As shown, the plugs 330 and the spigot and socket mechanical connection assembly are preferably positioned on opposing sides of the launch socket 312 to achieve optimal weight balance for enhanced stability and alignment. In other embodiments, however, this weight balance may also be achieved through an annular arrangement of these components around the launch socket 312.

[0132] While not shown, the main body may further include a modular insert configured to house a payload, such as an explosive charge that is designed to detonate upon impact with a target. The modular insert can be secured within the main body using a variety of mechanisms, including threaded rings, circlips, or other types of mechanical connections. Alternatively, adhesion techniques like gluing or crimping may be employed to secure the modular insert, thereby eliminating the need for additional mechanical fasteners.

[0133] FIG. 4 shows a schematic of exemplary cross-sections and configurations of a projectile 410 for use in a stacked projectile system, similar to the system 200, according to some embodiments of the present invention.

[0134] As shown, the launch rod 41 1 and launch socket 412 can alternatively assume various forms, including but not limited to cylindrical, star-shaped, elliptical or polygonal cross-sections. These different cross-sectional designs offer distinct advantages, such as optimising the aerodynamic properties of the projectile 410, enhancing structural integrity under different loading conditions, and improving compatibility with various launching devices.

[0135] Additionally, the projectile 410 may include more than one launch rod 41 1 and / or launch socket 412, which can provide several operational benefits. For example, distributing the mechanical load across multiple assembliesreduces wear and tear on individual components, thereby extending the system’s operational lifespan. This configuration is particularly advantageous in scenarios involving high-velocity launches or environments with significant lateral forces, where enhanced stability and structural integrity are critical. Moreover, in high-risk or military operations where redundancy is essential, having multiple launch rods 41 1 and / or launch sockets 412 may help maintain projectile stability and trajectory even if one assembly fails, thereby helping improve the overall reliability of the system.

[0136] FIGs. 5A and 5B show schematics of another projectile 500 for use in a stacked projectile system, according to an embodiment of the present invention.

[0137] In this embodiment, the launch rod 51 1 is configured to be collapsible within the launch socket 512. Specifically, the projectile 500 is configured such that as it is launched, the launch rod 51 1 collapses into the launch socket 512. This collapsible feature provides several advantages, particularly in springbased systems. For example, when the projectile 500 is loaded in the projectile column or onto the launching device, this design allows the launch rod 51 1 to be pushed into an extended position by the act of loading, compressing a spring on a latch. FIG. 5A shows the projectile 500 with the launch rod 51 1 in the extended position, and FIG. 5B shows the projectile 500 with the launch rod 51 1 in the collapsed position.

[0138] FIG. 6 shows a schematic of another projectile 600 for use in a stacked projectile system, according to an embodiment of the present invention.

[0139] In this embodiment, the middle section 610 has a non-zero size, and the launch rod 61 1 and launch socket 612 are relatively short compared to the length of the projectile 600. This design can be particularly advantageous for applications that require low launch velocities and high payload capacities, such as in the deployment of bombs. By having a shorter launch rod 61 1 and launch socket 612, the projectile 600 can accommodate larger payloads within a more compact structure, which is beneficial for maximising payload efficiency while maintaining operational effectiveness at lower launch velocities.

[0140] FIGS. 7A-B show schematics of various other projectiles for use in alternative stacked projectile systems, similar to the system 200, according to some embodiments of the present invention.

[0141] Referring to FIG. 7A, the projectile 700a may include a modular launch rod 711 and modular launch socket 712 that extend from the respective front and rear ends of a modular payload 710, which defines the middle section 710 of the projectile 700a. This modular configuration allows for any payload to be stacked and launched within the system. For instance, a system of FIG. 7A could be used to launch stacked bowling balls, toasters, frying pans, or, alternatively, life-rafts, buoys, drones, or satellites, depending on the specific requirements of the application.

[0142] Referring to FIG. 7B, the projectile 700b may include multiple modular launch rods 71 1 and modular launch sockets 712 attached to the modular payload 710, allowing for the accommodation of larger payloads, such as satellites. This setup can offer many advantages, including the ability to launch larger, more complex payloads while maintaining the modularity and adaptability of the system for different mission profiles.

[0143] Referring to FIG. 7C, a modular enclosure 720 can be configured to accommodate a conventional projectile in the system of FIG. 7A. This modular enclosure 720 enables conventional projectiles to be stacked according to the present invention without requiring modifications. The modular enclosure 720 can be configured to either remain with the projectile during flight or act as a sabot that is discarded immediately after launch.

[0144] FIG. 8A shows a schematic of another projectile 800a for use in a stacked projectile system, according to an embodiment of the present invention.

[0145] In this embodiment, the projectile 800a may be a conventional projectile with one or more full-length collapsible modular launch rods 81 1 and modular launch sockets 812. This allows the projectile 800a to be stacked in the system of the present invention. Upon launch, and / or during storage prior to launch, the modular launch rod 81 1 is configured to collapse into the modular launch socket 812.

[0146] FIG. 8B shows a schematic of another projectile 800b for use in a stacked projectile system, according to an embodiment of the present invention. In this embodiment, the modular launch rod 81 1 ’ is configured to be discarded from the projectile 800b upon launch, enabling a streamlined aerodynamic profile. This feature is particularly advantageous for larger modular systems, as it allows the modular launch socket 812’ - which may have structures such as wings extending from an exterior surface thereof - to occupy the entire length of the projectile 800b during flight.

[0147] FIG. 9 shows a schematic of a projectile 900 for use in yet another stacked projectile system, according to an embodiment of the present invention. In this embodiment, the projectile 900 is equipped with an inverse launch rod 91 1 and inverse launch socket 912. Specifically, for larger modular systems, it may be advantageous to use inversely stacked rod and sockets 91 1 , 912, where the inverse launch socket 912 extends from the middle section towards the front end of the projectile 900, and the inverse launch rod 91 1 extends from the middle section towards the rear end of the projectile 900.

[0148] While this configuration differs from other embodiments disclosed herein, which maintain a standard projectile shape optimised for flight, the inversely stacked arrangement provides increased flexibility in certain applications. For instance, although having the launch socket 912 pointing forward may not be ideal for aerodynamics, this can be mitigated by designing the launch rod and sockets 91 1 , 912 with discarding portions, or with flaps or similar features, that close over openings in the inverse launch socket 912 after launch. For instance, the inverse launch rod 91 1 can be discarded from the rear end of the projectile after launch, allowing the inverse launch socket 912 to remain intact and in flight.

[0149] FIG. 10 shows a schematic of another projectile 1000 for use in stacked projectile system, according to an embodiment of the present invention. In this embodiment, the launch rod includes one or more conventional tube-launchers 1010, which can deploy sub-munitions such as ‘Taser’-like projectiles, rubber balls, sponge rounds, capsicum burst rounds, flash-bang rounds, or conventional ammunition like bullets or shotgun shells. After launching its sub-munitions, the projectile 1000 can be ejected by igniting a small load of propellant 1020 or by puncturing a small compressed-air canister.

[0150] FIGS. 11 A-D show schematics of exemplary propulsion systems for use in a stacked projectile system, similar to the system 200, according to some embodiments of the present invention.

[0151] In FIG. 11 A, the projectiles utilise chemical propellant as the propulsion mechanism. Each projectile incorporates a two-stage burner 1 110 located within the middle section or launch rod. This two-stage burner 1 1 10 is ignited by an electric primer, which initiates the combustion process. Upon ignition, high-pressure gases are generated and released into the barrel-like enclosure formed by the launch rods and launch sockets between adjacent projectiles. For example, to launch the fourth projectile in the projectile column, the electric primer ignites the propellant in the two-stage burner 1 1 10. The resulting high- pressure gases are confined within the barrel-like enclosure between the third projectile and fourth projectile, creating sufficient force to propel the fourth projectile forward and away from the projectile column. This process can be sequentially repeated for subsequent projectiles in the projectile column.

[0152] In FIG. 11 B, the projectiles use electromagnetism as the propulsion mechanism. Coils of wire 1120 are wound inside both the launch rod and the launch socket of each projectile. The coils 1 120 in the launch rod are configured to generate a magnetic field with poles aligned along the longitudinal axis of the projectile column, while the coils 1 120 in the launch socket produce a magnetic field with opposing polarity.

[0153] For example, to launch the fourth projectile in the column, a current is applied to the coil 1 120 in the third and fourth projectile. This current generates a magnetic field with poles of reverse polarity aligned with a radial centre of the projectile column. The interaction between the opposing magnetic fields produces a force that propels the fourth projectile forward. This process can be sequentially repeated for subsequent projectiles in the projectile column, with the polarity of the magnetic poles switched in synchronisation with the launch sequence.

[0154] In FIG. 1 1 C, the projectiles utilise linear actuators as the propulsion mechanism. Specifically, each projectile is equipped with pyrotechnic linear actuators 1 130 configured to launch the projectiles sequentially. For instance, to launch the fourth projectile, the pyrotechnic linear actuator 1 130 generates a high-pressure force that pushes against the launch rod of the third projectile. A spigot of the actuator 1 130 engages with the forward end of the third projectile, and upon activation, it produces a force that drives the fourth projectile forward and away from the projectile column. This process can be sequentially repeated for subsequent projectiles in the projectile column.

[0155] In FIG. 11 D, the projectiles use springs as the propulsion mechanism. Each projectile is equipped with a spring assembly 1 140 housed within the launch socket and a clasp assembly located on a leading edge of an outer circumference of the launch socket.

[0156] During assembly, each projectile is positioned in the projectile column such that the launch rod of each subsequent projectile engages with the clasp assembly of the preceding one. This engagement compresses the spring assembly 1 140 within the launch socket of the preceding projectile, locking it in place.

[0157] For instance, in the case of the fourth projectile, the launch rod of the third projectile pushes the launch rod of the fourth projectile into an extended position. This action compresses the spring assembly 1 140 within the fourth projectile and engages its clasp assembly, securing it in the projectile column. When the clasp assembly is released, the compressed spring assembly in the fourth projectile expands, propelling the fourth projectile forward and away from the third projectile in the projectile column. This process can be sequentially repeated for subsequent projectiles in the projectile column.

[0158] FIGS. 12A-C show schematics of another projectile 1200 for use in a stacked projectile system, similar to the system 200, according to an embodiment of the present invention.

[0159] In this embodiment, the projectile 1200 utilises a chemical propulsion and is configured to be spin-stabilised. To achieve this, the launch socket includes internal rifling grooves 121 1 , while the launch rod includes externalrifling lands 1212. These rifling patterns, which may be conventional or polygonal, are configured to impart rotational spin on the projectile 1200 when launched from the system. For example, when the fourth projectile 1200 is launched from the projectile column, cooperative engagement between the rifling grooves 1211 in the launch socket of the fourth projectile 1200 and the rifling lands 1212 on the launch rod of the third projectile 1200 causes the fourth projectile 1200 to spin as it is propelled forward. This spin is generated as the fourth projectile 1200 moves along the launch rod of the third projectile 1200.

[0160] Referring to FIG. 12B, internal components of the projectile 1200 are shown. To facilitate electrical connectivity between projectiles in the system, the projectile 1200 includes an ignition wire channel 1220 located within an internal circumference of the launch socket. This ignition wire channel 1220 is configured to facilitate direct ignition of the electric primer 1241 via an electrical pulse of sufficient voltage and current. Wires are routed into the ignition wire channel 1220 and are securely fastened, for example, by gluing or using a suitable fastening method. The ignition wires may be encased in a common insulation shroud designed to fit into the channel 1220 and may be snapped or glued into place. Additionally, an ignition wire channel 1222 in an outer circumference of the launch socket is configured to establish an electrical connection between the ignition wires of each projectile 1200 and the controller.

[0161] Further, the two-stage burner 1 110 includes a burner cap 1231 that is threaded onto an external surface thereof. The burner cap 1231 includes a circular vent 1232 to allow for controlled propellant expansion, and also a screwdriver socket 1233 so that it can be securely screwed into the two-stage burner 1 1 10. The two-stage burner cap 1231 is typically made of metal, such as steel, to withstand the high-pressure environment created during combustion.

[0162] Before insertion into the two-stage burner 1 110, a propellant cup 1234, which is typically made of plastic such as acetal, is filled with propellant. The two-stage burner 1 1 10 itself is designed with a small hole 1235 along an outer circumference thereof to facilitate the passage of two small ignition wires - one ground and one positive. A small ingress 1236 on a front section of the two-stage burner 1 1 10 allows the ground wire to be soldered to the two-stage burner body 1 1 10, ensuring a secure electrical connection. The front section of the two-stage burner 1 1 10 also includes a primer ingress 1237, designed to accommodate the electric primer 1241 , such as an M52 or EtronX primer.

[0163] An inner rear surface of the front section of the two-stage burner 1 1 10 includes a screwdriver slot 1238, while an outer cylindrical surface is threaded, allowing the two-stage burner 11 10 to be screwed into the main body of the projectile 1200. A rear section of the inner circumferential surface 1239 of the two-stage burner is also threaded to receive the two-stage burner cap 1231 appropriately. The two-stage burner 1 1 10 is typically made of metal, such as steel, to ensure durability and reliability.

[0164] During assembly, the electric primer 1241 is inserted into the primer ingress 1237 of the two-stage burner 1 1 10. A primary separator 1242, typically made from plastic such as acetal, is used to electrically separate the two-stage burner 1 1 10 from a brass pin 1243. The primary separator 1242 has a central hole 1244 to allow passage of a spigot of the brass pin 1243 and another hole 1245 near an outer circumference thereof to facilitate passage of the positive ignition wire. An O-ring 1246 provides the brass pin 1243 with a sprung mount, ensuring a secure and flexible connection.

[0165] A secondary plastic separator 1247 houses both the brass pin 1243 and the O-ring 1246, ensuring that the brass pin 1243 is isolated from the main body. A small slot 1248 within the secondary separator 1247 allows for passage of the positive ignition wire around an outer circumference of the brass pin 1243 and the O-ring 1246.

[0166] This embodiment of the projectile 1200 is particularly designed for a stick reload system, and as such, it does not include plugs such as the plugs 330. In a stick reload system, projectiles 1200 are arranged in projectile columns rather than being individually loaded. These projectile columns or "sticks" are loaded or reloaded onto the launcher as units. Specifically, a rear end of each stick features a plug that facilitates electrical connection with the launcher, enabling efficient and rapid reloading during operation.

[0167] Referring to FIG. 12C, a top surface of the two-stage burner 1 110 includes two threaded holes 1251 designed to receive bolts. The primary separator 1242 also includes two corresponding holes 1252 to allow passage of the bolts, while the secondary separator 1247 has two additional holes 1253. The holes 1253 in the secondary separator 1247 are of a larger diameter towards a front surface thereof, providing a recessed area for heads of the bolt to seat securely.

[0168] During assembly, the electric primer 1241 is inserted into the primer ingress 1237, and the positive ignition wire is soldered to a centre of a front surface of the brass pin 1243. The positive ignition wire is then threaded through the O-ring 1246, which has an internal diameter and depth sufficient to accommodate the solder on the brass pin 1243.

[0169] With the secondary separator 1247 positioned on a flat surface, such as a table, the brass pin 1243 and O-ring 1246 are inserted into the secondary separator 1247 so that the positive ignition wire fits into the small slot 1248. The positive ignition wire is then threaded through the small hole 1245 in the primary separator 1242, which is subsequently placed atop the secondary separator 1247, ensuring that the spigot of the brass pin 1243 aligns with and is received by the hole 1244 at a centre of the primary separator 1242.

[0170] The two-stage burner 1 1 10, along with the assembly comprising the secondary separator 1247, brass pin 1243, O-ring 1246, and primary separator 1242, are then fastened together by screwing the bolts into the threaded holes 1251. The propellant cup 1234, filled with propellant, is inserted into the two- stage burner 1 1 10, and the two-stage burner cap 1231 is securely screwed onto the two-stage burner 1 1 10.

[0171] This assembled unit is then screwed into the main body of the projectile 1200, and the ignition wires are laid into the ignition wire channel 1220, where they are appropriately secured. The projectiles 1200 are then axially stacked in accordance with the present invention, and the ignition wires are connected to the controller in the launching device, either directly or via suitable plugs located at a rear end of the projectile column and a front surface of the launching device.

[0172] It is to be understood that this embodiment of the projectile 1200 is intentionally overbuilt to ensure safety. It is designed for production using inexpensive tools and materials, prioritising robustness and reliability over ease of assembly, lightweight construction, or compact size. As such, the internal components are deliberately made larger than strictly necessary.

[0173] FIG. 13 shows a schematic of another projectile 1200, similar to the projectile shown in FIGS. 12A-C, in a projectile column of two projectiles 1200, according to an embodiment of the present invention.

[0174] In this embodiment, the projectile 1200 is not spin-stabilised, as it does not incorporate rifling lands 1212 and rifling grooves 121 1. Instead, stabilisation is achieved through a rearward-mounted drag assembly in the form of drag fins 1310.

[0175] The projectile 1200 includes a cylindrical shroud 1320, typically made from a durable plastic material such as acetal. The shroud 1320 is equipped with plugs located toward its front and rear surfaces, which allow the projectiles 1200 in the system to be individually connected either to one another or directly to the launching device.

[0176] The ignition wire channel 1220 runs along the exterior circumference of the shroud 1320, providing a pathway that links the plugs at the front and rear surfaces. This channel 1220 enables the ignition wires of each projectile 1200 to be connected.

[0177] Although not shown in the figures, the projectile 1200 of this embodiment could also include a removable nose cap, allowing the main body to be constructed from tube-stock material, which could simplify manufacturing. Additionally, the internal components of the projectile 1200 could be made significantly smaller. This reduction in size could shift a centre of mass of the projectile 1200 forward, enhancing stability, or allow for an increased payload capacity.

[0178] Moreover, the internal components of the projectile 1200 may be replaced with a printed circuit board (PCB). A PCB could house a processor, enabling the projectile 1200 to support sophisticated features such as projectile coding, error reporting, and advanced safety mechanisms. Depending on thesize of the projectile 1200, the PCB could also support communication via radio frequency, GPS, remote control, and potentially even active flight surfaces, audio, and video capabilities.

[0179] FIG. 14 shows a schematic of a stacked projectile system in a pod 1410 configuration, according to another embodiment of the present invention. The pod 1410 is arranged as a battery of projectile columns in a two-dimensional 5x5 array, comprising 5 horizontal and 5 vertical projectile columns. Each projectile column includes three projectiles, forming a 5x5x3 configuration with three layers of projectiles within the pod 1410.

[0180] In this embodiment, the first layer comprises the third projectiles (i.e. lead projectile) from all the projectile columns within the pod 1410. Once the first layer is launched, the second layer of projectiles become the new lead projectiles, and this sequence continues with the third layer following suit. This arrangement allows for sequential launching of projectiles, layer by layer, from the pod 1410.

[0181] Notably, in this embodiment, the projectile columns are not in mechanical contact with one another, allowing for independent operation and launch of each column. The array size and the number of projectiles per column can be adjusted according to specific system requirements, providing flexibility in deployment and use based on mission parameters.

[0182] FIGS. 15A-C show schematics of a stacked projectile system in other pod configurations, according to some embodiments of the present invention. In these embodiments, a pod 1500 is arranged in a 3x3 array, comprising nine projectile columns.

[0183] In some embodiments, the projectile columns are configured to be in mechanical contact with each other, connected by bumpers, slide-rails, or wheels positioned on one or more surfaces of the projectiles (see FIG. 15A). These mechanical connections provide mutual support among the projectile columns, which is particularly beneficial for large or heavy projectiles. The nature of these connections can vary, including smooth connections 151 1 for minimal friction, grooved connections 1512 for enhanced guidance, interlocking mechanisms 1513 for secure attachment, slide-railed connections 1514 forcontrolled movement, or retractable mid-point slide-rails or bumpers 1515 that can be deployed as needed.

[0184] In such embodiments, the pod 1500 can be housed within a box-like enclosure 1520, which may provide additional structural integrity and protection during storage and transport.

[0185] In other embodiments, the projectile columns may only be in mechanical contact vertically (see FIGS. 15B-C). This configuration is advantageous when the sides of the projectiles include fragile or bulky structures, such as wings or antennas, as it reduces the risk of damage by minimising lateral contact.

[0186] FIGS. 16A-F show schematics of various projectiles for use in a stacked projectile system, according to some embodiments of the present invention. In these embodiments, the projectiles can have either a roundish or squarish cross-section. These projectiles are equipped with slide rails 1610 on their surfaces to facilitate stacking within projectile columns for a pod.

[0187] For example, FIGS. 16A and 16D show the projectiles 1600a, 1600d with slide rails 1610 on two adjacent surfaces, providing stability while allowing flexibility in assembly. FIGS. 16B and 16E show projectiles 1600b, 1600e with slide rails 1610 on all four surfaces, ensuring maximum stability within the column. FIGS. 16C and 16F show projectiles 1600c, 1600f with retractable slide rails 1610, which can be deployed or retracted as needed, offering versatility in stacking and ease of loading.

[0188] FIGS. 17A-C show a stacked projectile system in various pod configurations, according to some embodiments of the present invention.

[0189] FIG. 17A depicts a first prototype grenade pod 1700, configured in a 10x10x4 arrangement, holding 400 projectiles. Each projectile measures 200mm in length and 43mm in diameter (excluding components like drag fins), resulting in a pod dimension of approximately 55cm x 55cm x 50cm. The launching device is similarly sized to accommodate this arrangement.

[0190] FIG. 17B provides a front perspective view of the pod 1700 from FIG. 17A, illustrating the integration of launch rods, plugs, and mechanicalconnection assemblies within the launching device. Each of these components is configured to receive either individual projectiles or entire projectile columns.

[0191] FIG. 17C offers a rear perspective view of the launching device, which utilises direct ignition to launch the projectiles. This design supports the use of small, cost-effective batteries, making the system both efficient and economical.

[0192] FIG. 17D shows two projectiles 1710 for use in the stacked projectile system of FIGS. 17A-C, according to some embodiments of the present invention.

[0193] FIG. 17E shows a stacked projectile system in an alternative pod configuration, according to another embodiment of the present invention. In this embodiment, the pod 1700’ is designed to deploy plane-like drone projectiles.

[0194] FIGS. 18A-C show various other projectiles for use in a stacked projectile system, according to some embodiments of the present invention. In these embodiments, the projectiles are bomb-like projectiles.

[0195] Referring to FIGS. 18A-B, the projectile 1800a includes a rearwardmounted drag assembly that extends radially outward from the main body (see FIGS. 18A-B). Specifically, the projectile 1800a is equipped with four rearwardly mounted drag-fins 1310 and four sets of dual non-retractable mid-point sliderails 1810. These slide-rails 1810 are configured to provide mechanical connections between projectile columns in a pod configuration. In this way, the pod can form a solid-state unit that resists mechanical bumps and knocks. Additionally, as shown, the slide-rails 1810 are shorter than the launch rod of the projectile 1800a, allowing the slide-rails 1810 to disengage from operative contact before the launch rod and launch socket between projectiles 1800 during launch.

[0196] When the projectile 1800a of this embodiment is used in a pod configuration with a box enclosure, the box would also need retractable sliderails along interior surfaces thereof such that after the first layer of projectiles 1800a is launched, the first layer of box slide-rails would be retracted. This retraction would help ensure that the remaining projectiles 1800a in the pod can be smoothly and effectively launched without obstruction.

[0197] Referring to FIG. 18C, the projectile 1800c is equipped with retractable bumpers 1810’. These bumpers 1810’ provide a significant advantage by ensuring that the projectile columns are in operative mechanical contact before the launch of the projectiles 1800c. This contact helps the system withstand launch forces, absorb vibrations encountered during transport, and endure environmental impacts such as bumps and knocks.

[0198] Immediately prior to launch of the projectiles 1800c in this embodiment, the bumpers 1810’ of the projectile 1800c retract. This retraction helps ensure that when the projectile 1800c is launched, it disengages from mechanical contact with projectiles 1800c in adjacent projectile columns, maintaining contact only with the next projectile 1800c in the same column via the launch rod and socket assembly between projectiles 1800c.

[0199] During launch, only the launch rod and socket assembly between projectiles 1800c remains in contact with the lead projectile 1800c. As a result, directional guidance to the projectile 1800c is provided exclusively by the launch rod and socket assembly.

[0200] In this embodiment, the projectiles 1800c within a particular layer may be launched in any order.

[0201] FIG. 19 shows a schematic of a stacked projectile system utilising the projectiles 1800c from FIG. 18C in a pod configuration, according to an embodiment of the present invention.

[0202] As shown, the pod 1900 is housed within the box-like enclosure 1520, which serves dual purposes: providing environmental and mechanical protection for the projectiles 1800c inside and facilitating their launch. The boxlike enclosure 1520 includes retractable bumpers 1910 configured to engage with the projectiles 1800c to secure them within the pod 1900.

[0203] In this embodiment, interaction of the slide rails 1810’ between projectiles 1800c includes dual midpoint retractable bumpers 1810’ positioned on four opposing tangential surfaces of each projectile 1800c. These bumpers 1810’ establish mechanical connections at a midpoint between projectiles 1800c in adjacent projectile columns, ensuring stability within the pod 1900.

[0204] It will be appreciated that these bumpers 1810’ can vary in design, including single rails, longitudinally hollow rails, grooved rails, or interlocking surfaces. Preferably, the bumpers 1810’ are made of a slightly flexible and springy material, allowing for minor flexing to absorb shocks and vibrations during transportation and handling, while accommodating the rigid launch rod and launch socket between the projectiles 1800c.

[0205] Before the launch of individual projectiles 1800c, the corresponding box bumpers 1910 and the projectile’s own bumpers 1810’ are retracted. This retraction ensures that the projectile 1800c can launch smoothly, without any operative contact with surrounding bumpers 181 O’, allowing for an unobstructed departure from the box 1520.

[0206] FIGS. 20A-D show the stacked projectile system utilising the projectiles 1800a, 1800c from either FIG. 18A-C in various pod configurations, according to some embodiments of the present invention.

[0207] Referring to FIG. 20A, the box slide-rails 1910 of any previously launched layers of projectiles 1800a, 1800c are retracted, ensuring that the launch path for the remaining projectiles 1800a, 1800c is free from obstruction by the slide-rails 1810, 1810’ of layers that have already been launched.

[0208] If, before a projectile launches, both the box slide-rails (bumpers) 1910 surrounding the projectile and the projectile's own slide-rails (bumpers) are retracted, the stacked projectile system utilises the projectile configuration of FIG. 18C. Alternatively, if the slide-rails are non-retractable and the box sliderails 1910 are retracted only after a particular layer of projectiles has been launched, the stacked projectile system utilises the projectile configuration of FIGS. 18A-B.

[0209] This embodiment is particularly advantageous for launching large and heavy projectiles, as the retractable slide-rail and bumper mechanisms 1810’ provide robust support and stability during storage and transport while allowing for an unobstructed and controlled launch sequence.

[0210] Referring to FIG. 20B, this pod configuration contains 432 bomb-like projectiles 1800c arranged in a 12x12x3 array, each equipped with retractable slide-rails 1810’. Assuming each projectile 1800’ measures 300mm in lengthand 60mm in diameter - approximately the size of a conventional 60mm mortar round - and weighs around 1 .5kg, the total weight of the projectiles 1800c in the pod 2000, excluding the launching device and box 1520, would be approximately 648kg. Given that a B2 bomber has a munitions payload capacity of 18 tons, it could carry over 12,000 of these bomb-like projectiles 1800c.

[0211] It should be noted that the number and dimensions of the projectiles 1800c within this embodiment can vary widely depending on specific operational requirements. The design of the system is highly flexible, allowing it to accommodate different quantities and sizes of projectiles 1800c to meet the needs of various missions or delivery platforms.

[0212] Referring to FIG. 20C, this embodiment shows the same 12x12x3 pod configuration of FIG. 20B, oriented sideways and downward. Aircraft often release munitions at high velocities, and the optimal launch angle for projectiles 1800c may vary between sideways and downward depending on mission parameters. The retractable bumpers 1810’ offer flexibility, as they can be positioned at any point along the length of the projectile 1800c, without needing to disengage operative contact before the launch rod and launch socket between adjacent projectiles 1800c disengage.

[0213] In scenarios where the pod 2000 is launched horizontally, such as from an aircraft, it may be preferable to position the bumpers 1810’ further forward along the length of the projectile 1800c. This configuration supports the first layer of projectiles 1800c closer to a longitudinal midpoint, which is particularly beneficial for heavier projectiles 1800’. For very heavy bomb-like projectiles 1800c, such as projectiles 1800c of 120 mm diameter or larger, using two sets of retractable bumpers 1810’ per projectile 1800c ensures even weight distribution and enhanced stability during launch.

[0214] When launching pods of bomb-like projectiles 1800c horizontally, it is ideal to initiate the launch sequence with the bottom projectiles 1800c of each layer, followed by the next highest projectiles 1800c, and so on. This staggered approach prevents any projectile 1800c from needing to clear the projectile 1800c below it during launch, thereby streamlining the release process and minimising potential interference.

[0215] Referring to FIG. 20D, this embodiment illustrates the projectiles 1800a with non-retractable mid-point slide-rails 1810 in a pod configuration mid-way through launch. In this configuration, the non-retractable slide-rails 1810 are specifically designed to disengage from operative contact before the launch rod and launch socket between adjacent projectiles 1800 disengages. This design ensures that the slide-rails 1810 do not interfere with the separation of the projectiles 1800a during launch.

[0216] For systems utilising these types of projectiles 1800a with box-like enclosure pod configuration, the box-like enclosure 5120 would need to open to prevent the slide-rails 1810 of projectiles 1800a adjacent to the box 1520 from having to slide against the box 1520 during launch. This approach minimises friction and reduces the risk of potential damage to both the projectiles 1800a and the box 1520.

[0217] Alternatively, the box 1520 could be equipped with retractable sliderails 1910 that retract layer-by-layer as each layer of projectiles 1800a is launched. This configuration allows the launch process to proceed without requiring the box 1520 to open, thereby maintaining the structural integrity and environmental protection provided by the box-like enclosure 1520.

[0218] FIGS. 21 A-B show two alternative types of projectiles 2100a, 2100b for use in a stacked projectile system, according to some embodiments of the present invention. In these embodiments, the projectiles 2100a, 2100b take the form of plane-drone-like projectiles, and include, among other features described herein, an electronics and battery package 21 11 , a primer and propellant assembly 21 12, a solid rocket motor 2113, a metal rocket shroud 21 14 within the launch socket, vertical flaps 21 15, horizontal flaps 21 16, one or more propellors 21 17, wings 21 18, a slide rail assembly 2119 on each wing 21 18, and a dual slide rail assembly 2120 along a bottom surface of the main body. It will be appreciated that any propulsion mechanism can be used in this embodiment.

[0219] The rocket motor 21 13 is configured to vent through the rocket motor shroud 21 14 into a rocket plume. The rocket motor shroud 21 14 features numerous large holes in its surface to allow for efficient venting.

[0220] In these embodiments, the primer and propellant assembly 21 12 serves to launch the projectiles 2100a, 2100b and ignite the solid rocket motor 21 13. The system is configured so that the solid rocket motor 21 13 ignites as the projectiles 2100a, 2100b are being launched, ensuring continuous acceleration throughout its launch and into its initial upward rocket motor phase.

[0221] The rocket motor 2113 is configured to rapidly propel the projectiles 2100a, 2100b to its cruising altitude, after which the propellers 21 17 take over to enable cruising and subsequently dash or dive to the target. The rod assembly can be designed to include a shaped charge to puncture armour before the main payload is ignited. Alternatively, the projectiles 2100a, 2100b could be configured without a centrally mounted rocket motor 21 13, relying solely on propellers 21 17, or it could utilise dual wing-mounted rocket motors for propulsion.

[0222] Referring to the embodiment shown in FIG. 21 A, the plane-drone-like projectile 2100a includes a recess 2131 at the rear end thereof, configured specifically to induce drag. This recess 2131 creates a low-pressure area behind the projectile 2100a during flight, thereby increasing aerodynamic drag and helping to stabilise the projectile's trajectory.

[0223] Referring to the embodiment shown in FIG. 21 B, the projectile 2100b has an inwardly curving rear surface 2132. This curvature is configured to achieve a similar effect as the recess, by altering airflow patterns around the rear end of the projectile 2100b, further reducing drag and contributing to improved stability during flight. Both designs offer different approaches to managing drag while maintaining the same stacking length as other projectiles 2100b in the system.

[0224] FIG. 21 C shows a stacked projectile system utilising the plane-drone projectiles 2100a from FIG. 21 A arranged in a pod configuration, according to an embodiment of the present invention. In this embodiment, the slide-rails 2120 of the projectiles 2100a are configured to disengage from operative contact before the launch rod and launch socket between adjacent projectiles 2100a.

[0225] This sequential disengagement ensures that the projectiles 2100a maintain stability throughout the launch process. By having the slide-rails 2120 disengage first, any lateral forces that could destabilise the projectiles 2100a during the initial phase of the launch are minimised. Once the slide-rails 2120 are clear, the launch rod and launch socket can smoothly guide the projectile 2100a along its intended trajectory, ensuring a controlled and stable launch. This design reduces the likelihood of any misalignment or wobbling, providing a more precise and reliable launch sequence for the projectiles 2100a.

[0226] FIG. 21 D shows a stacked projectile system utilising the projectiles 2100a, 2100b from FIGS. 21 A or 21 B arranged in a pod configuration, according to another embodiment of the present invention. This embodiment features a 5x7x5 pod 2150, comprising 175 plane-drone projectiles 2100a, 2100b.

[0227] Assuming each projectile 2100a, 2100b measures 430mm in length, 305mm in width, and 60mm in height, and weighs 2 kilograms, the total size of the pod 2150 would be approximately 1 .5m x ,42m x 1 ,5m and the total weight of the pod 2150 in this configuration would be approximately 350kg.

[0228] The optimal launch sequence for this embodiment is as follows, with the sides and top of the box 1520 open:

[0229] This sequence can be repeated for each subsequent layer of projectiles 2100a, 2100b. Launching the projectiles 2100a, 2100b in this sequence ensures that each projectile 2100a, 2100b is launched with support from projectiles 2100a, 2100b either on either side and below it, or only below it, rather than having a projectile 2100a, 2100b on one side without acorresponding projectile 2100a, 2100b on the other side. However, the projectiles 2100a, 2100b in this embodiment can generally be launched in any order, starting with the first layer of projectiles 2100a, 2100b and proceeding sequentially through subsequent layers.

[0230] FIG. 21 E shows the stacked projectile system of FIG. 21 B on a U.S. military High Mobility Multipurpose Wheeled Vehicle (HMMWV) 2140. This figure exemplifies how the system can be deployed in combat and military operations. It will be appreciated that this system can similarly be adapted for use on other vehicles.

[0231] FIGS. 22A-B show two alternative types of projectiles for use in a stacked projectile system, according to some embodiments of the present invention. In this embodiment, the projectiles are a plane-drone projectile 2200.

[0232] The projectile 2200a may include dual vertical flaps 21 15, dual horizontal flaps 21 16, and dual propellers 21 17, as shown in FIG. 22A. Alternatively, as depicted in FIG. 22B, the projectile 2200b may be equipped with dual rocket motors 21 13 instead of propellers 21 17, offering a different propulsion option for various mission requirements.

[0233] FIG. 23 shows a stacked projectile system utilising the projectiles 2200a, 2200b of FIG. 22A or FIG. 22B in a pod configuration, according to some embodiments of the present invention.

[0234] As shown, the system is mounted on a large quad-copter drone 2310, specifically the Freefly Alta X, which has a payload capacity of 15kg. The DJI Flycart is another example that can be used herein and has a maximum payload of 30-40Kg.

[0235] The pod 2300 utilises the box-like enclosure 1520 that opens prior to launch. The box 1520 serves to environmentally protect the projectiles 2200a, 2200b while providing a rugged, solid-state, and sealed system until the moment of launch.

[0236] In this embodiment, the pod 2300 is a 3x15x5 configuration, comprising 225 plane-drone projectiles 2200a, 2200b. If each projectile 2200a, 2200b measures 140mm in length, 1 10mm in width, and 20mm in height, the pod 2300would have dimensions of approximately 350mm in width, 320mm in depth, and 420mm in height. If configured as a 3x15x3 pod 2300 with only three layers, the pod 2300 would measure approximately 350mm in width, 320mm in depth, and 280mm in height.

[0237] FIG. 24A shows another projectile 2400 for use in a stacked projectile system, according to an embodiment of the present invention.

[0238] In this embodiment, the projectile 2400 uses a linear actuator 2410 as the propulsion mechanism. The projectile 2400 includes four longitudinal grooves 2411 , which are positioned on an outer surface of the launch rod, along with four corresponding claws 2412 that define the launch socket. Specifically, these grooves 241 1 and claws 2412 are arranged such that the grooves 241 1 of the first projectile 2400 are configured to cooperatively receive the claws 2412 of the second projectile 2400, the grooves 241 1 of the second projectile 2400 are similarly configured to receive the claws 2412 of the third projectile 2400, and so on. This arrangement facilitates the axial stacking of the projectiles 2400 within the projectile column.

[0239] Additionally, the projectile 2400 includes four smooth column interaction surfaces 2420, which are radially offset by 45 degrees from the four longitudinal grooves 241 1 . This offset helps prevent the four claws 2412 from being obstructed by the projectile column interaction surfaces 2420 during launch, enabling a smooth disengagement process.

[0240] Moreover, the projectile 2400 is configured so that the projectile interaction surfaces 2420 disengage from operative contact before the launch rod and launch socket between adjacent projectiles disengage during launch. For enhanced functionality, the column interaction surfaces 2420 may also include two smaller slide-rails 2120 on two or all four surfaces thereof.

[0241] FIG. 24B shows a stacked projectile system utilising the projectiles 2400 of FIG. 24A in a pod configuration, according to some embodiments of the present invention.

[0242] In this embodiment, the pod 2430 is configured as an 8x8x3 array, comprising a total of 192 projectiles 2400. If each projectile 2400 measures 200mm in length, 40mm in width, and 40mm in depth, the overall dimensionsof the pod 2430’ would be approximately 320mm in width, 320mm in depth, and 400mm in height.

[0243] FIGS. 25A-B show various other plane-drone projectiles for use in a stacked projectile system, according to some embodiments of the present invention.

[0244] In the embodiment of FIG. 25A, the projectile 2500a is large and includes a dual-claw launch rod and launch socket designed for electromagnetic propulsion. The launch rod houses a coil or series of coils that generate a magnetic field aligned with the longitudinal axis of the projectile 2500a. The corresponding launch socket also includes a coil or series of coils that produce an opposing magnetic field, configured to facilitate the launch of the projectile 2500a through magnetic repulsion. The system may incorporate a mechanism for switching the polarity of the magnetic fields during launch to enable sequential launching of the projectiles 2500a. To assist with ground movement, the projectile 2500a may also include slide-rails 2120 on the bottom surface of the main body, or alternatively, a wheel assembly.

[0245] In the embodiment of FIG. 25B, the projectile 2500b includes a cylindrical hole extending from the front end to the rear end of the projectile 2500b, configured to receive the launch rod of the launching device. This design allows the projectiles in the system to axially stack on a long launch rod of the launching device, which spans a longitudinal length of the projectile column. In this embodiment, electromagnetic propulsion is utilised as the propulsion mechanism. Specifically, a coil or coils of wire in the launch rod of the launching device generate a magnetic field with poles aligned with the longitudinal axis of the rod assembly. A corresponding coil or coils of wire in the launch socket of the projectile 2500b generate a magnetic field with opposing polarity. This interaction launches the projectile 2500b with a velocity determined by the current in the coils. Following launch, the projectile 2500b may feature small flaps that cover the cylindrical hole at the front to maintain aerodynamic integrity.

[0246] FIG. 25C shows a schematic of the plane-drone projectiles 2500b of FIG. 25B in a projectile column, according to some embodiments of the present invention.

[0247] FIG. 25D shows a stacked projectile system utilising the plane-drone projectiles 2500a of FIG. 25A in a pod configuration, according to an embodiment of the present invention. In this embodiment, the wings 21 18 of the plane-drone projectiles 2500a do not include slide-rails 1219, as they are not in mechanical contact with one another. This configuration is suited for plane-drone projectiles 2150 with large or fragile wings 21 18. The pod 2510 is a 3x12x3 configuration and includes 108 projectiles 2500a. If each projectile 2500a measures 2m long, 1 m wide, and 15cm high, the 2510 would be 4m deep, 3m wide, and 1 .8m high.

[0248] FIG. 25E shows the pod 2510 of FIG. 25D inside an aircraft, according to an embodiment of the present invention. In this embodiment, the pod 2510 is used more as an ejection mechanism than a launching device, and the electrical requirements (voltage / current / capacity) are relatively low. The pod 2510 can draw power from the vehicle it is mounted on or contained within. For launching devices from or near a ground, where the pod 2510 is used as a launching device, the electrical requirements are higher, and mains power or vehicle batteries may be used accordingly.

[0249] FIGS. 26A-B show another projectile 2600a for use in a stacked projectile system, according to an embodiment of the present invention. In this embodiment, the projectile 2600a takes the form of a helicopter-drone projectiles 2600a.

[0250] The main body of the helicopter-drone projectile 2600a is elongated with a square-like cross section. The middle section of the projectile 2600a is substantial in size relative to the launch rod and launch socket, which are comparatively short. The launch rod includes a clip ingress 261 1 , while the launch socket is equipped with four clips 2612, facilitating the axial stacking of projectiles within the projectile column.

[0251] The middle section of the projectile 2600a features indents on all four surfaces, each designed to compactly receive an extendable rotor assembly2620. This rotor assembly 2620 comprises four rotors 2621 , which are designed to sit flush within the respective indents or recesses 2630 prior to launch. After the projectile 2600a is launched, the rotors 2621 are deployed, allowing the projectile 2600a to transform into a fully functional helicopter-drone.

[0252] In this embodiment, the propulsion mechanism is a pyrotechnic linear actuator 1 130 housed within the launch rod. FIG. 26A illustrates the helicopterdrone projectile 2600a with the rotors 2621 in a retracted position, compactly nestled within the indents or recesses 2630, as they would be prior to launch. FIG. 26B shows the helicopter-drone projectile 2600a with the rotors 2621 fully extended, illustrating the spigot of the pyrotechnic linear actuator in a launched position.

[0253] FIGS. 26C-D show the helicopter-drone projectile 2600a of FIGS-26A- B in a pod configuration, according to an embodiment of the present invention. In this embodiment, the pod 2610 features a 15x15x3 layout, accommodating 675 helicopter-drone projectiles 2600a. If each projectile 2600a measures 40mm in width, 40mm in depth, and 200mm in height, the pod 1610 dimensions would be approximately 60cm wide, 60cm deep, and 60cm high. This compact design facilitates the efficient storage and deployment of a large number of projectiles 2600a, making it suitable for mounting on a small delivery truck or similar vehicle for mobile launch operations.

[0254] FIGS. 26E-F show a helicopter-drone projectile 2600b, similar to the one depicted in FIGS. 26A-B, for use in a stacked projectile system, according to another embodiment of the present invention. In this embodiment, the main body of the projectile 2600b has a small, flat design with a square cross-section. Similar to the embodiment in FIGS. 26A-B, the rotors 2621 of this projectile 2600b are configured to extend immediately after launch. If the projectile 2600b measure 120mm in width, 120mm in depth, and 30mm in height, a 3x3x22 pod would be 66cm wide, 66cm deep, and 66cm high, accommodating 198 such projectiles 2600b. This flat design makes the projectile 2600b particularly well- suited for scenarios where low-profile deployment is necessary.

[0255] FIGS. 26G-H show another helicopter-drone projectile 2600c, which is similar to the embodiment shown in FIGS. 26A-B, for use in a stacked projectilesystem, according to an embodiment of the present invention. In this embodiment, the main body of the projectile 2600c is small and cylindrical. The launch socket includes a widened ingress 2640 at the rear end thereof, facilitating landing of projectiles 2600c on top of one another within the projectile column 2642.

[0256] The projectile 2600c utilises electromagnetic propulsion, wherein coils of wire in the launch rod and in the launch socket generate opposing magnetic fields. This interaction facilitates the launch of the projectile 2600c. One key advantage of this electromagnetic system is its ability to adjust the launch velocity based on operational conditions, allowing for adaptable deployment tailored to specific mission requirements.

[0257] The electromagnets within the launch rod and launch socket can generate an attractive force that gently pulls the landing projectile 2600c into position. This force is dynamically adjustable in real-time via the controller, ensuring a smooth and precise landing. The widened ingress 2640 in the launch socket further aids in aligning and securing the landing projectile 2600c.

[0258] In this embodiment, if the projectiles 2600c have a diameter of 30 cm (including the rotors 2621 ) and a height of 6 cm at the main body, a projectile column 2642 comprising 10 projectiles 2600c would measure 30cm in diameter and 60cm in height. This compact and efficient design makes the helicopterdrone projectile 2600c particularly well-suited for applications in the entertainment or commercial drone industry.

[0259] When stacked in the projectile column 2642, the projectiles 2600c are capable of communication and inductive recharging via the electromagnets in their launch rods and launch sockets. This feature enhances their operational endurance and allows for coordinated actions within the projectile column. The inductive charging capability ensures that the projectiles 2600c remain functional for extended periods, even during long-duration missions.

[0260] FIGS. 27A-B show another projectile 2700 for use in a stacked projectile system, according to an embodiment of the present invention. In this embodiment, the projectile 2700 takes the form of a taser-like device configured for deployment from a handheld taser-like pistol or similar launching device.The launch rod is rectangular in shape and includes dual taser-like probes 2710, along with associated wires housed within two small launch tubes 2720.

[0261] The projectile 2700 is designed to be roughly twice the size of a conventional taser cartridge, yet it stacks to the same overall dimensions for compatibility with existing taser systems. This design facilitates integration into current launching devices while offering enhanced functionality. The projectile's design can accommodate multiple small launch rods of varying sizes, enabling the launch of different sub-projectiles, such as sponge rounds, rubber balls, capsicum balls, small flash-bang rounds, or even small bullets or shotgun-like cartridges. This versatility allows users to tailor the type and sequence of projectiles 2700 to achieve specific tactical outcomes, making it adaptable to a wide range of scenarios.

[0262] With respect to the launching device, the pistol includes a projectile column capable of holding four projectiles, a fore-grip 2731 , a trigger 2741 with a guard assembly 2742, and a grip 2732 that houses the battery and controller. Upon activation, the taser probes from the lead projectile 2700 are ejected forward using the propulsion mechanism. These probes may include integrated batteries, allowing them to deliver a sustained charge to the target even after the projectile has been ejected from the pistol.

[0263] FIGS. 27C-E show various other projectiles for use in a stacked projectile system, according to some embodiments of the present invention. These embodiments exemplify various handheld launching devices for deploying different types of projectiles in accordance with the present invention.

[0264] For example, FIG. 27C depicts a small handheld grenade launcher. The projectile column in this embodiment can hold four grenade projectiles, each measuring 28mm in diameter and 120mm in length. The grenade projectiles may include rifling lands on their launch rods and corresponding rifling grooves in their launch sockets, enabling spin-stabilisation during flight. The launch rod of the grenade launcher also incorporates rifling grooves to match those of the projectiles. This compact and lightweight launcher is designed for a range of approximately 50-150 meters. It includes an uppersurface that can clip or attach to a rifle fore-grip via a Picatinny rail or similar attachment system.

[0265] FIG. 27D shows the small grenade launcher of FIG. 27C attached to an M4A1 rifle 2750, demonstrating the system’s compatibility with existing military equipment.

[0266] FIG. 27E shows the system utilising a handheld plane-drone launcher with plane-drone-like projectiles. In this embodiment, the plane-drone projectiles may be heat-seeking, laser-designated via a scope 2760, or remotely controlled by the user or from a distance. Both the handheld planedrone launcher and the projectiles can be constructed from plastic, offering a lightweight and cost-effective solution. The system is available in both reloadable and disposable versions, with options for reloading either by projectile column or by individual projectiles.

[0267] FIGS. 28A-E show various missile-like projectiles for use in a stacked projectile system, according to some embodiments of the present invention.

[0268] Referring to FIG. 28A, the missile-projectile 2800a can include fixed drag-fins 2810 and is configured to be stacked in upward-oriented projectile columns. This missile-projectile 2800a is approximately the size of a Javelin missile, a surface-to-air missile (SAM).

[0269] In FIGS. 28B-C, the missile-projectile 2800b is equipped with retractable drag-fins 2810’, which allow for close stacking in projectile columns without interfering with the launch process. This missile-projectile 2800b is roughly the size of a Pike missile and includes slide-rails 2820 on two adjacent surfaces. These slide-rails 2820 help ensure that the missile-projectile 2800b disengages from them before the launch rod and launch socket between projectiles 2800b separates. A squarish main body is preferred for this design. FIG. 28B shows the drag-fins 2810’ retracted, while FIG. 28C shows them extended.

[0270] In FIGS. 28D-E, the missile-projectile 2800c includes front and rear retractable bumpers 1610. FIG. 28D illustrates the missile 2800c with the bumpers 2820’ extended for storage, while FIG. 28E depicts the bumpers 2820’ retracted for deployment.

[0271] Referring to FIGS. 28F-G, the missile-projectiles of either FIGS. 28A-E are arranged in a pod configuration. The pod 2830 can be designed with a 20x20x3 configuration, accommodating 1 ,200 missile-projectiles. For missileprojectiles measuring 42mm wide x 42mm high x 420mm long, the pod dimensions would be 840mm wide x 840mm high x 900mm long, with an approximate weight of 924kg.

[0272] Referring to FIG. 21 H, the missile-projectiles of either FIGS. 28A-E are arranged in a single-layer pod configuration. The pod 2830’ is designed with a 10x10x1 configuration, accommodating 100 projectiles. If the projectiles of FIG. 28B are used, the pod 2830 would measure 40mm wide x 40mm high x 40mm long.

[0273] In this specification, the terms “comprise”, “comprises”, “comprising” or similar terms are intended to mean a non-exclusive inclusion, such that a system, method or apparatus that comprises a list of elements does not include those elements solely but may well include other elements not listed.

[0274] Similarly, it is to be noticed that the term attached, attachable or attachment, when used in the claims, should not be interpreted as being limited to direct attachments or permanent fixtures only.

[0275] It should also be understood that specific features from one embodiment may be combined with features from another embodiment, and such combinations are considered to be within the scope of the present invention.

Claims

CLAIMS1 . A stacked projectile launcher system comprising: a first projectile engaged with a second projectile to define a projectile column having a central axis, the second projectile located at a distal end of the projectile column; a propulsion mechanism connected to the first projectile or the second projectile, or to both projectiles, for sequentially propelling each projectile from the projectile column; a guide assembly for providing directional guidance to the second projectile during launch, the guide assembly comprising a guide surface of the first projectile and a guide surface of the second projectile, wherein the guide surface of the first projectile and the guide surface of the second projectile slidably engage each other and are parallel to the central axis; and a controller operatively connected to the propulsion mechanism.

2. The stacked projectile launcher system according to claim 1 , wherein each projectile includes a main body and a modular insert secured within the main body.

3. The stacked projectile launcher system according to claim 2, wherein the modular insert includes a payload and a fuse or detonator to ignite the payload upon impact.

4. The stacked projectile launcher system according to claim 1 , wherein the guide assembly includes a launch rod extending forward from a middle section of each projectile and a launch socket extending rearward from the middle section of each projectile, the launch rod of the first projectile being receivable in the launch socket of the second projectile to define a launch rod and socket assembly.

5. The stacked projectile launcher system according to claim 4, wherein an outer surface of the launch rod of the first projectile defines the guide surface of the first projectile, and an inner surface of the launch socketof the second projectile defines the guide surface of the second projectile.

6. The stacked projectile launcher system according to claim 5, wherein the launch socket of the first projectile is engageable with a launching device, the launching device having a forward extending launch rod receivable in the launch socket of the first projectile to define a launch rod and launch socket assembly.

7. The stacked projectile launcher system according to claim 1 , wherein the first projectile is identical to the second projectile.

8. The stacked projectile launcher system according to claim 5, wherein an expandable cavity is defined by the launch rod and launch socket assembly.

9. The stacked projectile launcher system according to claim87, wherein the expandable cavity forms a barrel-like enclosure.

10. The stacked projectile launcher system according to claim 1 , wherein each projectile includes a rearward-mounted drag assembly extending radially outward from the main body.1 1. The stacked projectile launcher system according to claim 10, wherein the rearward-mounted drag assembly comprises a circular fin encircling a series of radial fins, or an outer circumference on each launch rod has protruding rails engageable with corresponding grooves on the launch socket of the respective projectile is configured to spin the respective projectile for spin-stabilisation when propelled from the projectile column.

12. The stacked projectile launcher system according to claim 6, wherein the projectile column is supported by the launching device.

13. The stacked projectile launcher system according to claim 1 , wherein the first projectile is releasably connectable to the second projectile to enable reload on a per column basis.

14. The stacked projectile launcher system according to claim 1 , wherein the first projectile is releasably connectable to the second projectile to enable reload on an individual projectile basis.

15. The stacked projectile launcher system according to claim 6, wherein the first projectile includes a plug or other mechanical connection along an exterior circumference at a rear end of the launch socket of the first projectile configured to mate with a corresponding plug or other mechanical connection on the launch rod of the launching device, thereby mechanically and electrically connecting the launching device to the projectiles.

16. The stacked projectile launcher system according to claim 6, wherein the launching device includes a series of claws configured to engage a small channel in the exterior circumference of the first projectile for snap locking the projectile column to the launching device.

17. The stacked projectile launcher system according to claim 6, wherein the launching device includes rails and grooves for radially aligning the projectile column to the launching device.

18. The stacked projectile launcher system according to claim 8, wherein the propulsion mechanism includes a propellant and an electrical or mechanical trigger, the trigger configured to ignite the propellant charge and cause a combustion of the propellant that expands in the expandable cavity for applying a propelling force to the launch socket of the second projectile.

19. The stacked projectile launcher system according to claim 18, wherein the combustion of the propellant is contained within the expandable cavity.

20. The stacked projectile launcher system according to claim 18, wherein the propulsion mechanism further includes a barrier to seal the propellant charge from inadvertent ignition.21 .The stacked projectile launcher system according claim 18, wherein the electrical or mechanical trigger is housed within a launching device.

22. The stacked projectile launcher system according to claim 18, wherein the second projectile further includes a tubular ignition cavity communicating a rearward face of the launch socket of the secondprojectile with the expandable cavity to allow the propellant to expand and propel the second projectile.

23. The stacked projectile launcher system according to claim 22, wherein each projectile further includes a number of tubular bypass cavities in its launch socket to enable the propellant to expand to other projectiles in the projectile column.

24. The stacked projectile launcher system according to claim 23, wherein each projectile further includes a guide rail in its launch rod and a corresponding groove in its launch socket to radially align the projectile column such that the ignition cavities and bypass cavities couple cooperatively.

25. The stacked projectile launcher system according to claim 24, wherein the propulsion mechanism communicates the expanding gases between each launch rod and launch socket assembly to enable launch via launch cavities in the launching device.

26. The stacked projectile launcher system according to claim 6, wherein the propulsion mechanism includes an induction coil circumferentially wound in each launch rod and launch socket assembly, the controller configured to initiate a current between each launch rod and launch socket assembly to generate opposing magnetic fields for applying a propelling force on the launch socket of each projectile.

27. The stacked projectile launcher system according to claim 26, wherein the poles of each magnetic field are in line with a radial centre of the projectile column.

28. The stacked projectile launcher system according to claim 4 wherein the propulsion mechanism includes a longitudinal spring assembly associated with an inner circumference of the launch socket on each projectile, the spring assembly configured to compress and expand for applying a propelling force on the launch socket of each projectile.

29. The stacked projectile launcher system according to claim 28, wherein the spring assembly includes a plurality of radially disposed springsconfigured to compress when the launch socket of each projectile is in engagement with the launch rod of a corresponding projectile.

30. The stacked projectile launcher system according to claim 29, wherein the spring assembly further includes a clasp assembly to lock each launch rod and launch socket assembly in place when each projectile is in a compressed state in the projectile column.

31. The stacked projectile launcher system according to claim 1 , further comprising one or more additional projectiles in the projectile column.

32. The stacked projectile launcher system according to claim 1 , further comprising one or more additional projectile columns, the projectile columns engageable with a multi-column launching device.

33. The stacked projectile launcher system according to claim 32, wherein the projectile columns form an array of projectiles mechanically supported in three-dimensions.

34. The stacked projectile launcher system according to claim 32, wherein the projectiles have flattened edges to facilitate stacking of the projectile columns in three-dimensions.

35. The stacked projectile launcher system according to claim 1 , wherein the guide assembly includes a rail and groove on each projectile.

36. The stacked projectile launcher system according to claim 35, wherein the projectiles include interlocking rails and grooves on top and bottom surfaces of the projectiles.

37. The stacked projectile launcher system according to claim 38, wherein side surfaces of the projectiles further include interlocking rails and grooves to lock the projectiles together as a unit.

38. The stacked projectile launcher system according to claim 1 , wherein the projectiles define a projectile array supported by a box-like enclosure for easy transport and to facilitate projectile launch.

39. The stacked projectile launcher system according to claim 38, wherein the box-like enclosure has inner surfaces including corresponding rails and grooves to support outer edges of the projectile array.

40. The stacked projectile launcher system according to claim 38 wherein the projectile array forms a pod configuration including a plurality of projectiles.41 .The stacked projectile launcher system according to claim 2, wherein the modular insert spans an axial length of a launch rod enabling mechanical or electrical connection between the projectiles through the modular insert.

42. The stacked projectile launcher system according to claim 41 , wherein the modular insert forms an insert column for a series of frangibly connected inserts.

43. The stacked projectile launcher system according to claim 1 , wherein each projectile includes a rotor and wings, and the propulsion mechanism is configured to provide remote-controlled propulsion to each projectile.

44. The stacked projectile launcher system according to claim 1 , wherein the propulsion mechanism further includes a rocket motor.

45. The stacked projectile launcher system according to claim 6, wherein the projectile column is connected to the launching device via a rail.

46. The stacked projectile launcher system according to claim 1 , wherein the projectiles comprise a size, shape and mass for desired flight characteristics.

47. The stacked projectile launcher system according to claim 6, wherein each projectile comprises a dual launch rod and launch socket defining a dual launch rod and socket assembly between projectiles and the launching device.

48. The stacked projectile launcher system according to claim 8, wherein each projectile further comprises a two-stage burner assembly forimproving a combustion of gases that expand in the expandable cavity for applying a propelling force on the launch socket of each projectile.

49. The stacked projectile launcher system according to claim 48, wherein the two-stage burner assembly comprises: a main burner body; a propellant cup for housing a propellant charge and to reduce inadvertent ignition of the propellant charge; and a burner exhaust engageable with the main burner body, the burner exhaust having one or more holes through which propellant charge can expand once the propellant charge has been ignited and the propellant cup has been ruptured.

50. The stacked projectile launcher system according to claim 1 , wherein each projectile further comprises a printed circuit board and power source for receiving an electromagnetic signal from the controller to initiate launch of that projectile.

51. The stacked projectile launcher system according to claim 50, wherein the printed circuit board and power source each include an enclosure assembly.

52. The stacked projectile launcher system according to claim 50, wherein communication between the projectiles and the controller is encrypted.

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