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 two projectiles, for sequentially propelling each projectile from the projectile column. A guide assembly provides directional guidance to the second projectile during firing, and the guide assembly includes a guide surface of the first projectile and a guide surface of the second projectile, where 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 is operably connected to the propulsion mechanism.

Description

Technical Field

[0001] The present invention generally relates to a stacked projectile launcher, and particularly, but not exclusively, to a stacked projectile launcher that provides compatibility and versatility for a range of applications. Background Technology

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

[0003] During World War II, the M7 rifle grenade launcher and the M17 fragmentation rifle grenade launcher combination gained significant prominence due to their innovative design utilizing a rod and spigot assembly. In this mechanism, the rod acts as the launcher, while the projectile acts as the spigot. Upon ignition, expanded propellant fills the rifle barrel and enters the launcher rod, generating high pressure at the base of the spigot. This enables effective long-range deployment of the rifle grenade, achieving a range of approximately 200 m and a barrel length of approximately 9 to 10 cm. To further extend the range, an auxiliary range-extending charge, known as a "vitamin pellet," can be used to provide an additional 90 to 135 meters of range. However, despite these advantages, the effectiveness of the M7 launcher and the M17 fragmentation grenade was ultimately limited by their dependence on the size of the rifle bullet. This dependence imposed constraints on the overall power and range of the weapon, posing challenges in certain operational scenarios. A significant drawback was the limitation imposed on the propellant load. Dependence on rifle bullet size leads to variations in projectile velocity and trajectory, thus affecting accuracy and consistency. Furthermore, the limited capacity of a launcher to accommodate larger cartridges restricts the weapon's overall power and range potential, thereby limiting its effectiveness in situations requiring greater firepower or range.

[0004] However, since World War II, the use of rifle grenades has declined, and independent grenade launchers like the M79 and M203 have become more common. Independent launchers offer the advantage of using both rifle and grenade launchers simultaneously without changing configuration. Furthermore, these launchers utilize dedicated grenade cartridges, eliminating the limitations imposed by the propellant load of rifle cartridges. However, compared to commonly installed grenade launchers, independent launchers are limited by their increased weight and larger size.

[0005] To address these limitations, attempts have been made to develop stacked projectile launcher systems. These systems arrange projectiles axially with propellant between them to achieve high rates of fire through sequential ignition. However, existing stacked projectile systems suffer from several drawbacks. They typically require bulky and expensive tubes, resulting in the burden of carrying empty tubes after firing. Furthermore, the integration of induction ignition, high-voltage electronics, and batteries becomes necessary, and establishing direct electrical connections between projectiles presents several challenges. Additionally, the launch pressure exerted by one projectile can affect other projectiles, and these systems are not tailored for single-use scenarios. Inconsistent muzzle velocities become even more apparent when projectiles are fired from various positions within the same tube.

[0006] Therefore, there is a need for an improved stacked projectile launcher system that is simple to design and manufacture, lightweight, and cost-effective. Purpose of the invention

[0007] The purpose of this invention is to overcome and / or mitigate one or more disadvantages of the prior art, or to provide consumers with a useful alternative. Summary of the Invention

[0008] In one form, though not necessarily the most widespread, the invention relates to a stacked projectile launcher system comprising: A stacked projectile system comprising: A first projectile, which engages with a second projectile to define a projectile column having a central axis, the second projectile being located at the distal end of the projectile column; A propulsion mechanism, which is connected to the first projectile or the second projectile, or to both projectiles, for sequentially propelling each projectile from the projectile column; A guidance assembly for providing directional guidance to a second projectile during launch, the guidance assembly including a guidance surface of a first projectile and a guidance surface of a second projectile, wherein the guidance surfaces of the first and second projectiles are slidably engaged with each other and parallel to a central axis; and A controller that is operatively connected to the propulsion mechanism.

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

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

[0011] Preferably, the guiding assembly includes a launch rod extending forward from the middle section of each projectile and a launch port extending rearward from the middle section of each projectile, wherein the launch rod of the first projectile can be received in the launch port of the second projectile to define the launch rod and launch port assembly.

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

[0013] Preferably, the launch port of the first projectile can be engaged with a launching device having a forward-extending launch rod capable of being received in the launch port of the first projectile, thereby defining the launch rod and launch port assembly.

[0014] Preferably, the first projectile is the same as the second projectile.

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

[0016] Preferably, the cavity can be expanded to form a tubular outer shell.

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

[0018] In some embodiments, the rear-mounted drag assembly includes a circular wing surrounding a series of radial wings, or a protruding guide rail on the outer periphery of each launch bar that is capable of engaging with a corresponding groove on the launch port of the corresponding projectile and is configured to rotate the corresponding projectile for rotational stabilization as it is advanced from the projectile column.

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

[0020] In some embodiments, the first projectile can be releasably connected to the second projectile to enable reloading on a per-projectile basis.

[0021] In some embodiments, the first projectile is releasably connected to the second projectile, enabling reloading on a single projectile basis.

[0022] In some embodiments, the first projectile includes a plug or other mechanical connection along the outer periphery of the rear end of the first projectile's launch port, the plug or other mechanical connection being configured to engage 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 projectile.

[0023] In some embodiments, the launching device includes a series of claws configured to engage small channels in the outer periphery of the first projectile for locking the projectile post to the launching device.

[0024] In some embodiments, the launching device includes a guide rail and a groove for radially aligning the projectile column with the launching device.

[0025] In some embodiments, the propulsion mechanism includes a propellant and an electrical or mechanical trigger configured to ignite the propellant charge and cause combustion of the propellant expanding in an expandable cavity to apply propulsion to the launch port of the second projectile.

[0026] In some embodiments, propellant combustion is confined within an expandable cavity.

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

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

[0029] In some embodiments, the second projectile further includes a tubular ignition cavity that connects the rearward face of the second projectile's launch port to an expandable cavity to allow propellant to expand and propel the second projectile.

[0030] In some embodiments, each projectile also includes multiple tubular bypass cavities in its launch port to allow propellant to extend into 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 port for radial alignment of the projectile post, such that the ignition cavity and the bypass cavity are cooperatively connected.

[0032] In some embodiments, the propulsion mechanism enables the expansion gas to communicate between each launch bar and launch port assembly, thereby enabling launch via a launch cavity in the launch device.

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

[0034] In some embodiments, the magnetic poles of each magnetic field are aligned with the radial center of the projectile column.

[0035] In some embodiments, the propulsion mechanism includes a longitudinal spring assembly associated with the inner periphery of the launch port on each projectile, the spring assembly being configured to be compressible and expandable to apply a propulsive force to the launch port of each projectile.

[0036] In some embodiments, the spring assembly includes a plurality of radially arranged springs configured to compress when the launch port of each projectile engages with the launch rod of the corresponding projectile.

[0037] In some embodiments, the spring assembly further includes a hook assembly to lock each launch rod in place with the launch port assembly when each projectile is compressed in the projectile column.

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

[0039] In some embodiments, the system further includes one or more additional projectiles that can be engaged with a multi-projectile launching device.

[0040] In some embodiments, the projectile column forms a projectile array supported by three-dimensional mechanical means.

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

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

[0043] In some embodiments, the projectile includes interlocking guides and grooves on the top and bottom surfaces of the projectile.

[0044] In some embodiments, the side surface of the projectile also includes interlocking rails and grooves to lock the projectiles together as units.

[0045] In some embodiments, the projectiles define a projectile array supported by a box-shaped housing to facilitate transport and projectile launch.

[0046] In some embodiments, the box-shaped housing has an inner surface including corresponding guide rails and grooves to support the outer edge of the projectile array.

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

[0048] In some embodiments, the modular insert spans the axial length of the launch rod to enable mechanical or electrical connections between projectiles via the modular insert.

[0049] In some embodiments, the modular insert forms an insert post for a series of vulnerable connection inserts.

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

[0051] In some embodiments, the propulsion mechanism also includes a rocket engine.

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

[0053] In some embodiments, the projectile includes size, shape, and mass for desired flight characteristics.

[0054] In some embodiments, each projectile includes dual launch rods and a launch port to define a dual launch rod and launch port assembly between the projectile and the launching device.

[0055] In some embodiments, each projectile further includes a two-stage burner assembly to improve combustion of gases expanding in an expandable cavity to apply propulsion at the launch port of each projectile.

[0056] In some embodiments, the two-stage burner assembly includes a main burner body, a propellant cup for receiving propellant charge and reducing accidental ignition of the propellant charge, and a burner exhaust port that engages with the main burner body. The burner exhaust port has one or more orifices through which the propellant charge can expand once the propellant charge is ignited and the propellant cup ruptures.

[0057] In some embodiments, each projectile further includes a printed circuit board and a power supply for receiving electromagnetic signals from a controller to initiate the launch of the projectile.

[0058] In some embodiments, the printed circuit board and the power supply each include a housing assembly.

[0059] In one embodiment, communication between the projectile and the controller is encrypted.

[0060] Other forms and / or features of the invention will become apparent from the following detailed description. Attached Figure Description

[0061] To facilitate understanding and practice of the invention, preferred embodiments of the invention will now be referred to with reference to the accompanying drawings, wherein like reference numerals denote like elements. The drawings are provided by way of example only, in which: Figure 1 A schematic diagram is shown of a rifle grenade launcher and a fragmentation rifle grenade in a ready-to-fire position, as known from the prior art. Figure 2 A schematic diagram of a stacked projectile system according to an embodiment of the present invention is shown; Figure 3 An embodiment of the invention is shown for use Figure 2 A schematic diagram of the projectiles in the system; Figure 4 A schematic diagram of an exemplary cross-section and configuration of a projectile in a stacked projectile system according to some embodiments of the present invention is shown; Figure 5A and Figure 5BA schematic diagram of another projectile for a stacked projectile system according to an embodiment of the present invention is shown; Figure 6 A shows a schematic diagram of another projectile in a stacked projectile system according to an embodiment of the present invention; Figure 7A , Figure 7B and Figure 7C Schematic diagrams of various other projectiles for a stacked projectile system according to some embodiments of the present invention are shown; Figure 8A A schematic diagram of another projectile for a stacked projectile system according to an embodiment of the present invention is shown; Figure 8B A schematic diagram of another projectile for a stacked projectile system according to an embodiment of the present invention is shown; Figure 9 A schematic diagram of another projectile for a stacked projectile system according to an embodiment of the present invention is shown; Figure 10 A schematic diagram of another projectile for a stacked projectile system according to an embodiment of the present invention is shown; Figure 11A , Figure 11B , Figure 11C and Figure 11D A schematic diagram of an exemplary propulsion mechanism for a stacked projectile system is shown according to some embodiments of the present invention; Figure 12A An embodiment of the invention is shown that is similar to Figure 3 A schematic diagram of another projectile used in a projectile stacking system; Figure 12B and Figure 12C An embodiment according to the present invention is shown. Figure 12A A schematic diagram of the internal components of a projectile; Figure 13 An embodiment of the invention is shown that is similar to Figure 12A A schematic diagram of another projectile in the projectile column of two projectiles; Figure 14 A schematic diagram of a stacked projectile system with a cabin configuration according to an embodiment of the present invention is shown; Figure 15A , Figure 15B and Figure 15C A schematic diagram of a stacked projectile system employing various other hull configurations is shown according to some embodiments of the present invention; Figure 16A , Figure 16B , Figure 16C , Figure 16D , Figure 16E and Figure 16FSchematic diagrams of various projectiles for a stacked projectile system according to some embodiments of the present invention are shown; Figure 17A , Figure 17B and Figure 17C A perspective view of a stacked projectile system employing various hull configurations according to some embodiments of the present invention is shown; Figure 17D A perspective view of two projectiles in a projectile column for a stacked projectile system according to an embodiment of the present invention is shown; Figure 17E A perspective view of a stacked projectile system in an alternative hull configuration according to another embodiment of the invention is shown; Figure 18A , Figure 18B and Figure 18C Perspective views of various other projectiles for a stacked projectile system according to some embodiments of the present invention are shown; Figure 19 The use of a cabin configuration according to an embodiment of the present invention is illustrated. Figure 18C A schematic diagram of a stacked projectile system; Figure 20A , Figure 20B , Figure 20C and Figure 20D The invention illustrates the use of some embodiments thereof. Figure 18A , Figure 18B or Figure 18C Various views of a stacked projectile system with a hull configuration for projectiles; Figure 21A and Figure 21B A perspective view of various aircraft-unmanned aerial vehicle (UAV) projectiles for a stacked projectile system according to some embodiments of the present invention is shown; Figure 21C and Figure 21D The illustration shows a cabin configuration according to some embodiments of the present invention. Figure 21A A perspective view of the projectile; Figure 21E A vehicle according to an embodiment of the present invention is shown. Figure 21D A perspective view of the cabin; Figure 22A and Figure 22B A perspective view of other aircraft-UAV projectiles for a stacked projectile system according to some embodiments of the present invention is shown; Figure 23 The use of a cabin configuration according to some embodiments of the present invention is illustrated. Figure 22A or Figure 22B A perspective view of a stacked projectile system; Figure 24AA perspective view of another projectile in a stacked projectile system according to an embodiment of the present invention is shown; Figure 24B The use of a cabin configuration according to an embodiment of the present invention is illustrated. Figure 24B A perspective view of a stacked projectile system; Figure 25A and Figure 25B A perspective view of other aircraft-UAV projectiles for a stacked projectile system according to some embodiments of the present invention is shown; Figure 25C and Figure 25D The invention illustrates the use of some embodiments thereof. Figure 25B A perspective view of a stacked projectile system; Figure 25E An aircraft according to an embodiment of the present invention is shown. Figure 25D The hull of the projectile; Figure 26A and Figure 26B A perspective view of various helicopter-unmanned aerial vehicles (UAVs) for a stacked projectile system according to some embodiments of the present invention is shown; Figure 26C and Figure 26D The illustration shows a cabin configuration according to some embodiments of the present invention. Figure 26A or Figure 26B A perspective view of a helicopter-drone-shaped projectile; Figure 26E , Figure 26F and Figure 26G A perspective view of a projectile for a similar helicopter in a stacked projectile system according to some embodiments of the present invention is shown; Figure 26H An example of a projectile column in a stacked projectile system according to an embodiment of the present invention is shown. Figure 26G A perspective view of a helicopter-drone projectile; Figure 27A A perspective view of another projectile in a stacked projectile system according to an embodiment of the present invention is shown; Figure 27B , Figure 27C , Figure 27D and Figure 27E Perspective views of various stacked projectile systems according to some embodiments of the present invention are shown; Figure 28A , Figure 28B , Figure 28C , Figure 28D and Figure 28E Perspective views of various missile-shaped projectiles for a stacked projectile system according to some embodiments of the present invention are shown; Figure 28F and Figure 28G The following illustrations show various cabin configurations based on embodiments of the invention. Figures 28A to 28E A view of a missile-shaped projectile; and Figure 28H An embodiment of the invention is shown, employing a different hull configuration. Figures 28A to 28E A perspective view of a missile launch.

[0062] Those skilled in the art will understand that the accompanying drawings are schematic, and the elements in the drawings are illustrated for simplicity and clarity and are not necessarily drawn to scale. For example, the relative dimensions of some elements in the drawings may be distorted to aid in understanding the embodiments of the invention. Detailed Implementation

[0063] This invention relates to a stacked projectile launcher system. The elements of the invention are illustrated in simplified outline form in the accompanying drawings, showing only those specific details necessary for understanding embodiments of the invention, but therefore not providing excessive details that would be obvious to those skilled in the art according to this specification.

[0064] In this specification, adjectives such as first and second, front and back, inside and outside may be used only to distinguish one element or action from another, without necessarily requiring or implying any actual such relationship or order. Words such as “propelled,” “fired,” “launched,” and “ejected” are intended to disclose similar meanings; and words such as “comprising” or “including” are intended to define a non-exclusive inclusion, such that a system or apparatus that includes a list or elements does not necessarily include only those elements, but may include other elements not expressly listed, including elements inherent to such a system or apparatus.

[0065] According to a first aspect, the present invention relates to a stacked projectile launcher system comprising: A first projectile, which engages with a second projectile to define a projectile column having a central axis, the second projectile being located at the distal end of the projectile column; A propulsion mechanism, which is connected to the first projectile or the second projectile, or to both projectiles, for sequentially propelling each projectile from the projectile column; A guidance assembly for providing directional guidance to a second projectile during launch, the guidance assembly including a guidance surface of a first projectile and a guidance surface of a second projectile, wherein the guidance surfaces of the first and second projectiles are slidably engaged with each other and parallel to a central axis; and A controller that is operatively connected to the propulsion mechanism.

[0066] Various embodiments of the present invention can provide the advantage of offering effective solutions for a variety of applications, particularly military operations.

[0067] Specific advantages of some embodiments involve eliminating the need for a barrel, which provides a lightweight and cost-effective solution for alternative systems. This elimination also eliminates the need for induction ignition and associated high-voltage electronics and batteries, allowing the system to be powered, for example, by a simple 9V battery combined with a small controller in some applications. This synergistically enables the realization of a cheaper system that is easy to manufacture. Furthermore, the embodiments facilitate direct electrical connection between projectiles in a straightforward manner, simplifying the design and manufacturing process.

[0068] Furthermore, by eliminating the need for a barrel, the projectile of the present invention is not constrained by a tube, thereby providing increased versatility in terms of size and shape. For example, the projectile of the present invention can adopt unconventional geometries, such as those used for unmanned aerial vehicles, without compromising system performance. Such versatility can also contribute to a favorable high payload-to-weight ratio, thereby enhancing the system's operational efficiency and performance.

[0069] Furthermore, the absence of a gun barrel ensures that the projectile does not need to withstand launch pressure outside the launching device, effectively preventing the risk of "leakage" ignition and contributing to enhanced operational safety and accurate projectile launch.

[0070] Another advantage of some embodiments involves the ability to launch projectiles independently within the projectile column at a consistent rate of fire, thereby improving accuracy, reliability, and predictability during projectile launch.

[0071] Other advantages of some embodiments include flexibility in reloading on a standalone basis, on a per-pillar basis, or through an integrated design. This adaptability grants the system versatility to accommodate varying operational requirements, particularly in military contexts where the ability to replenish projectiles in a timely manner according to specific mission objectives is crucial. Furthermore, in the context of a single-use integrated design, the launcher of the present invention only needs to withstand one firing pressure, and in some applications two, which translates into a cost-effective manufacturing process compared to conventional systems configured to withstand multiple repeated firings throughout their lifespan.

[0072] Other advantages of some embodiments of the invention provide a compact footprint and compatibility with a variety of materials, including plastics, making the system highly adaptable to applications with space constraints and stringent system design requirements.

[0073] It will be understood that not all embodiments of the present invention must include all the advantages described above.

[0074] Figure 1A schematic diagram is shown of a fragmentation rifle grenade 120 and a rifle grenade launcher 110 in the process of firing, as known from the prior art. Examples of such systems include the M7 rifle grenade launcher and the M17 fragmentation grenade. In this configuration, the fragmentation rifle grenade 120 includes a rearwardly mounted firing port 121 configured to engage cooperatively with a corresponding firing rod 111 on the rifle grenade launcher 110. This firing rod and the port assemblies 111, 121 form a tubular housing 130 that accommodates the pressure generated during firing, thereby facilitating the firing of the fragmentation rifle grenade 120.

[0075] Figure 2 A schematic diagram of a stacked projectile system 200 according to an embodiment of the present invention is shown. For the purpose of distinction in this specification, the projectiles 210 in this system 200 will be referred to as the first projectile, the second projectile, the third projectile, and the fourth projectile; however, it should be understood that these projectiles are identical in structure and function, and will therefore be indicated by the use of apostrophes (', '', ''', and ''''). Additionally, it should be noted that any number of projectiles can be implemented within the scope of the invention, depending on the specific requirements of the system 200. Furthermore, as will be described below, projectiles can have various shapes and sizes, wherein the shapes depicted in the schematic diagrams are illustrative only and not limiting.

[0076] In this embodiment, the projectiles 210 are configured to engage with each other in a axially stacked manner to define the projectile column 220. Specifically, the first projectile 210' is positioned at the proximal end of the projectile column 220, the second projectile 210'' and the third projectile 210''' are sequentially positioned within the projectile column 220, and the fourth projectile 210'''' is positioned at the distal end of the projectile column 220. The projectile 210 at the distal end of the projectile column 220 (in this case, the fourth projectile 210'''') is launched first.

[0077] A propulsion mechanism (not shown) is connected to each projectile 210 for sequentially advancing the projectile 210 from the projectile post 220. This propulsion mechanism may include, but is not limited to, propellant charge, electromagnetic force, electric charge, linear actuator, spring, compressed air, or other suitable devices for generating the force required to launch the projectile 210. Embodiments of these propulsion mechanisms are disclosed below.

[0078] A guidance assembly or travel guidance assembly is associated between adjacent projectiles 210 and includes a surface oriented parallel to the central axis of the column 220 (which is parallel to the travel orientation of the projectiles 210 during launch), and provides directional guidance to the projectiles 210 during launch. For example, a travel guidance assembly is associated between a third projectile 210''' and a fourth projectile 210'''', such that as the fourth projectile 210'''' is advanced from the projectile column 220, the travel guidance assembly helps maintain the fourth projectile 210''''' aligned along a path parallel to the direction of travel. The same guidance principle applies to subsequent projectiles in the column, as subsequent projectiles are launched sequentially.

[0079] The controller is operatively connected to the propulsion mechanism for launching projectiles. The controller is configured to manage the sequence of projectile launches, allowing for the simultaneous launch of all projectiles 210 as desired, or the independent and sequential launch of each projectile 210. For example, if such functionality is required, the controller can be operated to launch only the fourth projectile 210'' from the projectile launcher 220. The controller is integrated into the launching device 230, facilitating user interaction with the system 200 to provide control over the firing sequence and operating parameters of the propulsion mechanism.

[0080] Figure 3 A schematic diagram of a projectile 210 for a stacked projectile system 200 according to an embodiment of the present invention is shown.

[0081] The projectile 210 has a body that can be manufactured in various sizes, shapes, and materials, including but not limited to metals such as steel or aluminum, or plastics such as polycarbonate. This flexibility allows the projectile 210 to be customized to specific operational requirements.

[0082] The main body includes a middle section 310, a launch rod 311, and a launch port 312. The launch rod 311 extends from the middle section 310 toward the front end 313 of the projectile 210, while the launch port 312 extends from the middle section 310 toward the rear end 314 of the projectile 210. Notably, in this embodiment, the length of the middle section 310 is zero, such that the launch rod 311 and the launch port 312 span the entire length of the projectile 210. Specifically, the launch rod 311 spans the front section of the projectile 210, while the launch port 312 spans the rear section of the projectile 210. This configuration may be advantageous in scenarios where high-speed firing and long-range accuracy are critical. In other embodiments described below, the middle section 310 may have a non-zero length.

[0083] In this embodiment, the arrangement of the launch rod 311 and launch port 312 is configured to facilitate the axial stacking of projectiles 210 and the formation of the travel guidance assembly when used in system 200. For example, the launch rod 311 of the first projectile 210' is configured to be received in the launch port 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 port 312 of the third projectile 210''', etc. In addition, the launch port 312 of the first projectile 210' is configured to be adapted to a corresponding launch rod 311 associated with the launching device 230.

[0084] The interaction between adjacent launch rods 311 and launch ports 312 forms a "tubular" housing that serves to propel the guiding assembly. For example, as the fourth projectile 210 exits 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 the length of the launch port 312. During launch, the outer surface 313 of the launch rod 311 of the third projectile 210 defines a guiding surface that slidably engages the inner surface 314 of the launch port 312 of the fourth projectile 210 (defining another guiding surface). As shown, the two surfaces 313, 314 are parallel to the central axis of the projectile column 220 and parallel to the direction of travel of the fourth projectile 210 upon launch.

[0085] Located at the front end 315 and rear end 316 of the launch socket 312 are mechanical connection components in the form of a spigot and a socket-type mechanical connection assembly. The spigot and socket-type mechanical connection assembly includes 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. Depending on design requirements, the spigot and socket can have various cross-sectional shapes such as square, rectangular, or any other suitable configuration.

[0086] In this embodiment, the pin and socket mechanical connection assembly is configured to mechanically lock or clamp adjacent projectiles 210 together when used in system 200. For example, the pin 321 of the first projectile 210' is configured to fit into the socket 322 of the second projectile 210'', and similarly, the pin 321 of the second projectile 210'' engages with the socket 322 of the third projectile 210''', etc. This arrangement provides a robust mechanical attachment, ensuring that the first, second, and third projectiles 210 remain securely attached to each other even under the influence of the force generated when the fourth projectile 210'''' is launched from the projectile post 210. Furthermore, the pin and socket connection assembly can act as a radial key between adjacent projectiles 210 to substantially minimize any rotational movement between projectiles 210 under the influence of the launch force.

[0087] Also located at the front and rear ends of the launch port 312 are plugs 330 for accommodating wires and other electrical components to facilitate mechanical and electrical connections between projectiles 210 when used in system 200. Plugs 330 can take various forms, including annular, magnetic, or sliding / traveling configurations. Notably, annular magnetic plugs 330 paired with moving mechanical connection components (such as the plug-and-port mechanical components described above) may be particularly advantageous for achieving fixed and reliable electrical and mechanical connections between projectiles 210 in the stacked projectile system 200.

[0088] As shown in the figure, the plug 330 and the pin and socket mechanical connection assembly are preferably positioned on opposite sides of the firing socket 312 to achieve optimal weight balance for enhanced stability and alignment. However, in other embodiments, this weight balance can also be achieved through a circumferential arrangement of these components around the firing socket 312.

[0089] Although not shown, the body may also include modular inserts configured to accommodate payloads, such as those designed to detonate upon impact with a target. The modular inserts can be secured within the body using various mechanisms, including threaded rings, spring rings, or other types of mechanical connections. Alternatively, adhesive techniques such as gluing or press-fitting can be used to secure the modular inserts, eliminating the need for additional mechanical fasteners.

[0090] Figure 4 A schematic diagram of an exemplary cross-section and configuration of a projectile 410 in a stacked projectile system similar to System 200, according to some embodiments of the present invention, is shown.

[0091] As shown in the figure, the launch rod 411 and launch port 412 can alternatively take various forms, including but not limited to cylindrical, star-shaped, elliptical, or polygonal cross-sections. Such diverse cross-sectional designs offer various advantages, such as optimizing the aerodynamic characteristics of the projectile 410, thereby enhancing structural integrity under various load conditions and improving compatibility with various launching devices.

[0092] Additionally, the projectile 410 may include more than one launch lever 411 and / or launch port 412, which can provide several operational benefits. For example, distributing mechanical loads across multiple components can reduce wear and tear on individual components, thereby extending the system's operational life. This configuration is particularly advantageous in scenarios involving high-speed launch or environments with significant lateral forces, where enhanced stability and configuration integrity are critical. Furthermore, in high-risk or military operations where redundancy is necessary, having multiple launch levers 411 and / or launch ports 412 can help maintain the projectile's stability and trajectory even if one component fails, thereby helping to improve the overall reliability of the system.

[0093] Figure 5A and Figure 5B A schematic diagram of another projectile 500 for a stacked projectile system according to an embodiment of the present invention is shown.

[0094] In this embodiment, the launch lever 511 is configured to be retractable within the launch socket 512. Specifically, the projectile 500 is configured such that when it is launched, the launch lever 511 is retracted into the launch socket 512. This retractable feature provides several advantages, particularly in spring-based systems. For example, when the projectile 500 is loaded into the projectile column or launching device, this design allows the launch lever 511 to be pushed into an extended position by the loading action to compress the spring on the latch. Figure 5A The projectile 500 is shown with the launch lever 511 in the extended position, and Figure 5B The projectile 500 is shown with the launch lever 511 in the retracted position.

[0095] Figure 6 A schematic diagram of another projectile 600 for a stacked projectile system according to an embodiment of the present invention is shown.

[0096] In this embodiment, the intermediate segment 610 has a non-zero dimension, and the launch rod 611 and launch port 612 are relatively short compared to the length of the projectile 600. This design is particularly advantageous for applications requiring low launch rates and high payload capacity, such as in bomb deployment. By having shorter launch rods 611 and launch ports 612, the projectile 600 can accommodate a larger, more efficient payload in a more compact structure, which helps maximize payload efficiency while maintaining operational effectiveness at lower launch rates.

[0097] Figures 7A to 7B Schematic diagrams are shown of various other projectiles for an alternative stacked projectile system similar to System 200, according to some embodiments of the present invention.

[0098] refer to Figure 7A The projectile 700a may include a modular launch rod 711 and a modular launch port 712 extending from the front and rear ends of a modular payload 710, respectively, which defines the middle section 710 of the projectile 700a. This modular configuration allows any payload to be stacked and launched within the system. For example, depending on the specific requirements of the application, Figure 7A The system can be used to launch stacked bowling balls, toasters, frying pans, or alternatively, life rafts, buoys, drones, or satellites.

[0099] refer to Figure 7BThe projectile 700b may include multiple modular launch rods 711 and modular launch ports 712, which are attached to a modular payload 710 to allow for the accommodation of larger payloads such as satellites. This configuration can provide many advantages, including the ability to launch larger and more complex payloads while maintaining the modularity and adaptability of the system to different mission profiles.

[0100] refer to Figure 7C The modular housing 720 can be configured to accommodate Figure 7A The modular housing 720 allows conventional projectiles to be stacked according to the invention without modification. The modular housing 720 can be configured to remain with the projectile during flight or act as a ejector cartridge case immediately after launch.

[0101] Figure 8A A schematic diagram of another projectile 800a for a stacked projectile system according to an embodiment of the present invention is shown.

[0102] In this embodiment, the projectile 800a may be a conventional projectile having one or more full-length retractable modular launch rods 811 and modular launch ports 812. This allows the projectile 800a to be stacked in the system of the present invention. During launch and / or during storage before launch, the modular launch rods 811 are configured to be retracted into the modular launch ports 812.

[0103] Figure 8B A schematic diagram of another projectile 800b for a stacked projectile system according to an embodiment of the invention is shown. In this embodiment, a modular launch bar 811' is configured to be ejected from the projectile 800b upon launch, enabling a streamlined aerodynamic profile. This feature is particularly advantageous for larger modular systems because it allows a modular launch port 812'—which can have a wing-like structure extending from its outer surface—to occupy the entire length of the projectile 800b during flight.

[0104] Figure 9 A schematic diagram of a projectile 900 for another stacked projectile system according to an embodiment of the invention is shown. In this embodiment, the projectile 900 is equipped with a reverse-launch rod 911 and a reverse-launch socket 912. In particular, for larger modular systems, it may be advantageous to use reverse-stacked rods and sockets 911, 912, in which the reverse-launch socket 912 extends from the middle section of the projectile 900 toward the front end and the reverse-launch rod 911 extends from the middle section of the projectile 900 toward the rear end.

[0105] While this configuration differs from other embodiments disclosed herein that maintain a standard projectile shape optimized for flight, the reverse-stacked arrangement offers increased flexibility in certain applications. For example, although pointing the launch port 912 forward may not be aerodynamically ideal, this can be mitigated by designing the launch rod and ports 911, 912 with discard portions, or with baffles or similar features that close the opening in the reverse-launch port 912 after launch. For instance, the reverse-launch rod 911 can be discarded from the rear end of the projectile after launch to allow the reverse-launch port 912 to remain intact and in flight.

[0106] Figure 10 A schematic diagram of another projectile 1000 for a stacked projectile system according to an embodiment of the present invention is shown. In this embodiment, the launching rod includes one or more conventional tube launchers 1010, which can deploy submunitions such as Taser-like projectiles, rubber balls, sponge bullets, pepper spray bullets, flashbangs, or conventional ammunition like bullets or shotgun shells. After firing its submunitions, the projectile 1000 can be ejected by igniting a small amount of propellant 1020 or by piercing a small compressed air canister.

[0107] Figures 11A to 11D A schematic diagram of an exemplary propulsion system for a stacked projectile system similar to System 200 is shown according to some embodiments of the present invention.

[0108] exist Figure 11A In this design, the projectiles utilize chemical propellant as their propulsion mechanism. Each projectile is coupled with a two-stage burner 1110 located within the middle section or launch rod. This two-stage burner 1110 is ignited by an electric detonator, initiating the combustion process. After ignition, high-pressure gas is generated and released into a tubular outer shell formed by the launch port between the launch rod and the adjacent projectile. For example, to launch the fourth projectile in the projectile column, the electric detonator ignites the propellant in the two-stage burner 1110. The resulting high-pressure gas is confined within the tubular outer shell between the third and fourth projectiles, thereby generating sufficient force to propel the fourth projectile forward and away from the projectile column. This process can be repeated sequentially for subsequent projectiles in the projectile column.

[0109] exist Figure 11B In this design, the projectile uses electromagnetism as its propulsion mechanism. A coil 1120 is wound within both the launch rod and the launch port of each projectile. The coil 1120 in the launch rod is configured to generate a magnetic field with its poles aligned along the longitudinal axis of the projectile, while the coil 1120 in the launch port generates a magnetic field of opposite polarity.

[0110] For example, to launch the fourth projectile in the column, an electric current is applied to coils 1120 in the third and fourth projectiles. This current generates a magnetic field in which oppositely polarized magnetic poles are aligned with the radial center of the projectile column. The interaction between the opposite magnetic fields generates a force that propels the fourth projectile forward. This process can be repeated sequentially for subsequent projectiles in the column, with the polarity of the magnetic poles switching synchronously with the launch sequence.

[0111] exist Figure 11C In this design, projectiles utilize linear actuators as propulsion mechanisms. Specifically, each projectile is equipped with a pyrotechnic linear actuator 1130 configured to launch projectiles sequentially. For example, to launch a fourth projectile, the pyrotechnic linear actuator 1130 generates high pressure against the launch rod of the third projectile. The pin of the actuator 1130 engages with the front end of the third projectile, and upon activation, the actuator generates a force that drives the fourth projectile forward and away from the projectile column. This process can be repeated sequentially for subsequent projectiles in the projectile column.

[0112] exist Figure 11D In this design, the projectile uses a spring as its propulsion mechanism. Each projectile is equipped with a spring assembly 1140 housed within the launch port and a hook assembly located on the leading edge of the launch port's outer periphery.

[0113] During assembly, each projectile is positioned within the projectile post such that the launch rod of each subsequent projectile engages with the latch assembly of the preceding projectile. This engagement compresses the spring assembly 1140 within the launch port of the preceding projectile, locking it in place.

[0114] For example, in the case of the fourth projectile, the launch rod of the third projectile pushes the launch rod of the fourth projectile into the extended position. This action compresses the spring assembly 1140 within the fourth projectile and engages the latch assembly of the fourth projectile to secure it within the projectile column. When the latch assembly is released, the compressed spring assembly within the fourth projectile expands, propelling the fourth projectile forward and away from the third projectile in the projectile column. This process can be repeated sequentially for subsequent projectiles in the projectile column.

[0115] Figures 12A to 12C A schematic diagram of another projectile 1200 for a stacked projectile system similar to system 200, according to an embodiment of the present invention, is shown.

[0116] In this embodiment, the projectile 1200 utilizes chemical propulsion and is configured for spin stability. To achieve this, the launch port includes internal rifling grooves 1211, while the launch rod includes external rifling ridges 1212. These rifling patterns can be conventional or polygonal and are configured to impart rotational rotation to the projectile 1200 upon firing from the system. For example, when the fourth projectile 1200 is fired from the projectile column, the cooperative engagement between the rifling grooves 1211 in the launch port of the fourth projectile 1200 and the rifling ridges 1212 on the launch rod of the third projectile 1200 causes the fourth projectile 1200 to rotate as it propels forward. This rotation is generated as the fourth projectile 1200 moves along the launch rod of the third projectile 1200.

[0117] refer to Figure 12B The internal components of projectile 1200 are shown. To facilitate electrical connections between projectiles in the system, projectile 1200 includes an ignition wire channel 1220 located within the inner periphery of the launch port. This ignition wire channel 1220 is configured to facilitate direct ignition of the electric detonator 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 adhesive or using a suitable fastening method. The ignition wires may be encapsulated in a common insulating sheath designed to fit into the channel 1220 and may be snapped or glued into place. Additionally, an ignition wire channel 1222 in the outer periphery of the launch port is configured to establish an electrical connection between the ignition wire of each projectile 1200 and the controller.

[0118] In addition, the two-stage burner 1110 includes a burner cap 1231 screwed onto its outer surface. The burner cap 1231 includes a circular vent 1232 to allow controlled propellant expansion and a screwdriver slot 1233 so that it can be securely screwed into the two-stage burner 1110. The two-stage burner cap 1231 is typically made of a metal such as steel to withstand the high-pressure environment generated during combustion.

[0119] Before the two-stage burner 1110 is inserted, the propellant cup 1234 is filled with propellant, and the propellant cup 1234 is typically made of a plastic such as acetal. The two-stage burner 1110 itself is designed with small holes 1235 along its outer periphery to allow two small ignition wires (one ground and one positive) to pass through. Small inlets 1236 on the front section of the two-stage burner 1110 allow the ground wire to be soldered to the two-stage burner body 1110 to ensure a reliable electrical connection. The front section of the two-stage burner 1110 also includes an inlet 1237, which is designed to accommodate an electric detonator 1241 such as an M52 or EtronX detonator.

[0120] The inner rear surface of the front section of the two-stage burner 1110 includes a screwdriver slot 1238, while the outer cylindrical surface is threaded to allow the two-stage burner 1110 to be screwed into the body of the projectile 1200. The rear section of the inner circumferential surface 1239 of the two-stage burner is also threaded to properly receive the two-stage burner cap 1231. The two-stage burner 1110 is typically made of a metal such as steel to ensure durability and reliability.

[0121] During assembly, the electric detonator 1241 is inserted into the detonator inlet 1237 of the two-stage burner 1110. A primary separator 1242, typically made of a plastic such as acetal, is used to electrically disconnect the two-stage burner 1110 from the brass pin 1243. The primary separator 1242 has a central hole 1244 and another hole 1245 near its outer periphery; the central hole 1244 allows the pin of the brass pin 1243 to pass through, and the other hole 1245 facilitates the passage of the positive ignition wire. An O-ring 1246 provides a flexible mounting for the brass pin 1243, ensuring a secure yet flexible connection.

[0122] The 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 the positive ignition wire to pass around the outer periphery of the brass pin 1243 and the O-ring 1246.

[0123] This embodiment of the projectile 1200 is specifically designed for a projectile rod reloading system, whereby the projectile does not include a plug such as plug 330. In the projectile rod reloading system, the projectile 1200 is arranged as projectile rods rather than loaded individually. These projectile rods, or "rods," are loaded or reloaded onto the launcher as units. In particular, the rear end of each rod has a plug that facilitates electrical connection to the launcher, enabling efficient and rapid reloading during operation.

[0124] refer to Figure 12C The top surface of the two-stage burner 1110 includes two threaded holes 1251 designed to receive bolts. The primary separator 1242 also includes two corresponding holes 1252 to allow bolts to pass through, while the secondary separator 1247 has two additional holes 1253. The holes 1253 in the secondary separator 1247 have a larger diameter facing its front surface to provide a recessed area for the bolt head to sit securely.

[0125] During assembly, the electric detonator 1241 is inserted into the detonator inlet 1237, and the positive ignition wire is soldered to the center of the front surface of the brass pin 1243. The positive ignition wire is then passed through an O-ring 1246, which has an inner diameter and depth sufficient to accommodate the solder on the brass pin 1243.

[0126] When the secondary splitter 1247 is positioned on a flat surface such as a table, brass pin 1243 and O-ring 1246 are inserted into the secondary splitter 1247 so that the positive ignition wire is fitted into the slot 1248. The positive ignition wire then passes through the hole 1245 in the primary splitter 1242, which is then placed on top of the secondary splitter 1247, ensuring that the pin of the brass pin 1243 is aligned with and received by the hole 1244 in the center of the primary splitter 1242.

[0127] Then, the two-stage burner 1110, together with the assembly including the secondary separator 1247, brass pin 1243, O-ring 1246, and primary separator 1242, is fastened together by screwing bolts into threaded holes 1251. A propellant cup 1234 filled with propellant is inserted into the two-stage burner 1110, and the two-stage burner cap 1231 is securely screwed onto the two-stage burner 1110.

[0128] The assembled unit is then screwed into the body of the projectile 1200, and the ignition wire is placed in the ignition wire channel 1220, where it is properly secured. The projectiles 1200 according to the invention are then stacked axially, and the ignition wire is connected directly or via suitable plugs located at the rear end of the projectile column and the front surface of the launching device to the controller in the launching device.

[0129] It should be understood that this embodiment of the Projectile 1200 was intentionally overbuilt to ensure safety. It was designed for production using inexpensive tools and materials, prioritizing robustness and reliability over ease of assembly, lightweight construction, or compact size. Therefore, internal components were deliberately made larger than strictly required.

[0130] Figure 13 A schematic diagram of another projectile 1200 according to an embodiment of the present invention is shown, which is similar to Figures 12A to 12C The projectile shown is in two projectile columns of 1200.

[0131] In this embodiment, because the projectile 1200 does not include the rifling ridges 1212 and the rifling grooves 1211, the projectile 1200 is not rotationally stable. Instead, stabilization is achieved by a rearwardly mounted drag assembly in the form of drag fins 1310.

[0132] The projectile 1200 includes a cylindrical shield 1320 typically made of a durable plastic material such as acetal. The shield 1320 is equipped with plugs positioned toward its front and rear surfaces, which allows the projectiles 1200 in the system to be connected to each other individually or directly to the launching device.

[0133] The ignition wire channel 1220 extends along the outer periphery of the shield 1320 to provide a path for connecting the plugs at the front and rear surfaces. This channel 1220 allows the ignition wires of each projectile 1200 to be connected.

[0134] Although not shown in the figures, the projectile 1200 of this embodiment may also include a removable nose cap to allow the body to be constructed from tubular material, which simplifies manufacturing. Additionally, the internal components of the projectile 1200 can be made significantly smaller. This reduction in size can shift the center of gravity of the projectile 1200 forward to enhance stability or allow for increased payload capacity.

[0135] Furthermore, the internal components of the projectile 1200 can be replaced with printed circuit boards (PCBs). The PCB can house a processor, enabling the projectile 1200 to support complex features such as projectile coding, error reporting, and advanced safety mechanisms. Depending on the size of the projectile 1200, the PCB can also support communication via radio frequency, GPS, remote control, and even potentially support active flight surfaces, audio, and video capabilities.

[0136] Figure 14 A schematic diagram of a stacked projectile system using a pod 1410 configuration according to another embodiment of the present invention is shown. The pod 1410 is arranged as a series of projectile columns comprising a two-dimensional 5×5 array of five horizontal projectile columns and five vertical projectile columns. Each projectile column includes three projectiles, forming a 5×5×3 configuration with three layers of projectiles within the pod 1410.

[0137] In this embodiment, the first layer includes a third projectile (i.e., a lead-in projectile) from all projectile columns within the hull 1410. Once the first layer is launched, the second layer of projectiles becomes the new lead-in projectile, and this sequence continues, with the third layer following immediately afterward. This arrangement allows projectiles to be launched sequentially from the hull 1410, layer by layer.

[0138] It is worth noting that in this embodiment, the projectile columns do not mechanically contact each other, allowing each column to operate and launch independently. The array size and the number of projectiles per column can be adjusted according to specific system requirements to provide deployment and usage flexibility based on mission parameters.

[0139] Figures 15A to 15C A schematic diagram of a stacked projectile system employing other hull configurations according to some embodiments of the present invention is shown. In these embodiments, the hull 1500 is arranged in a 3×3 array comprising nine projectile columns.

[0140] In some embodiments, the projectile columns are configured to be in mechanical contact with each other, connected by buffers, rails, or wheels positioned on one or more surfaces of the projectile (see [link to relevant documentation]). Figure 15AThese mechanical connections provide mutual support between the projectile columns, which is particularly beneficial for large or heavy projectiles. The nature of these connections can vary, including smooth connections 1511 for minimal friction, grooved connections 1512 for enhanced guidance, interlocking mechanisms 1513 for secure attachment, slide rail connections 1514 for controlled movement, or retractable midpoint slide rails or buffers 1515 that can be deployed as needed.

[0141] In such embodiments, the cabin 1500 can be housed within a box-shaped outer shell 1520, which can provide additional structural integrity and protection during storage and transport.

[0142] In other embodiments, the projectile column may make only vertical mechanical contact (see...). Figures 15B to 15C This configuration is advantageous when the sides of the projectile include fragile or large parts such as wings or antennas, as it reduces the risk of damage by minimizing lateral contact.

[0143] Figures 16A to 16F Schematic diagrams of various projectiles for a stacked projectile system according to some embodiments of the present invention are shown. In these embodiments, the projectiles may have a circular or square cross-section. These projectiles are equipped with rails 1610 on their surfaces to facilitate stacking within projectile columns for a hull.

[0144] For example, Figure 16A and Figure 16D Projectiles 1600a and 1600d with slide rails 1610 on two adjacent surfaces are shown, providing stability while allowing for assembly flexibility. Figure 16B and Figure 16E Projectiles 1600b and 1600e with slide rails 1610 on all four surfaces are shown to ensure maximum stability within the column. Figure 16C and Figure 16F Projectiles 1600c and 1600f are shown, which have retractable slide rails 1610 that allow for deployment or retraction as needed to supply stacks and facilitate loading.

[0145] Figures 17A to 17C Stacked projectile systems employing various hull configurations are illustrated according to some embodiments of the present invention.

[0146] Figure 17A A first prototype grenade launcher 1700 is depicted in a 10×10×4 arrangement to hold 400 projectiles. Each projectile is 200 mm long and 43 mm in diameter (excluding components such as drag fins), resulting in a hull size of approximately 55 cm × 55 cm × 50 cm. The launching device is similarly designed to accommodate this arrangement.

[0147] Figure 17B Provided Figure 17A A frontal perspective view of the hull at 1700, illustrating the integration of the launch rod, plug, and mechanical connection assemblies within the launching system. Each of these components is configured to receive individual projectiles or the entire projectile launcher.

[0148] Figure 17C A rear perspective view of a launching device that uses direct ignition to launch projectiles is provided. This design supports the use of small, cost-effective batteries, making the system efficient and economical.

[0149] Figure 17D The invention illustrates its use in some embodiments. Figures 17A to 17C The two projectiles 1710 in the stacked projectile system.

[0150] Figure 17E A stacked projectile system in an alternative hull configuration according to another embodiment of the invention is shown. In this embodiment, hull 1700' is designed to deploy aircraft-shaped unmanned aerial vehicle projectiles.

[0151] Figures 18A to 18C Various other projectiles for stacked projectile systems according to some embodiments of the invention are shown. In these embodiments, the projectiles are bomb-like projectiles.

[0152] refer to Figures 18A to 18B The projectile 1800a includes a rearwardly mounted drag assembly extending radially outward from the body (see...). Figures 18A to 18B Specifically, the projectile 1800a is equipped with four rearward-mounted drag fins 1310 and four sets of double non-retractable midpoint rails 1810. These rails 1810 are configured to provide a mechanical connection between the projectile rods in a hull configuration. In this way, the hull can form a solid unit resistant to mechanical impacts and collisions. Additionally, as shown, the rails 1810 are shorter than the launch rod of the projectile 1800a, allowing the rails 1810 to disengage during launch before the launch rod between the projectiles 1800a disengages from the launch port.

[0153] When the projectile 1800a of this embodiment is used in a hull configuration with a housing, the housing also requires a retractable slide rail along its inner surface, such that after the first layer of projectile 1800a is launched, the first layer of the slide rail is retracted. This retraction helps ensure that the remaining projectiles 1800a in the hull can be launched smoothly and efficiently without obstruction.

[0154] refer to Figure 18CThe projectile 1800c is equipped with retractable buffers 1810'. These buffers 1810' provide significant advantages by ensuring that the projectile column is in operational mechanical contact before the projectile 1800c is launched. Such contact helps the system withstand launch forces, absorb vibrations encountered during transport, and withstand environmental effects such as collisions and impacts.

[0155] In this embodiment, the buffer 1810' of projectile 1800c retracts just before the projectile 1800c is launched. This retraction helps ensure that when projectile 1800c is launched, it disengages from mechanical contact with projectiles 1800c in adjacent projectile columns, and maintains contact with the next projectile 1800c in the same column only via the launch rod and socket assembly between projectiles 1800c.

[0156] During launch, only the launch rod and socket assembly between the projectiles 1800c remain in contact with the guide projectile 1800c. Therefore, directional guidance of the projectile 1800c is provided solely by the launch rod and socket assembly.

[0157] In this embodiment, the projectiles 1800c within a specific layer can be launched in any order.

[0158] Figure 19 An embodiment of the invention is shown utilizing a cabin configuration Figure 18C A schematic diagram of the stacked projectile system of the 1800c projectile.

[0159] As shown, the hull 1900 is housed within a box-shaped outer casing 1520, which serves a dual purpose: providing environmental and mechanical protection for the internal projectiles 1800c and facilitating their launch. The box-shaped outer casing 1520 includes a retractable buffer 1910 configured to engage with the projectiles 1800c to secure them within the hull 1900.

[0160] In this embodiment, the interaction of the rails 1810' between the projectiles 1800c includes a double-midpoint retractable buffer 1810' positioned on four opposing tangential surfaces of each projectile 1800c. These buffers 1810' establish a mechanical connection at the midpoint between the projectiles 1800c in adjacent projectile columns to ensure stability within the hull 1900.

[0161] It will be understood that the design of these buffers 1810' can vary, including a single guide rail, a longitudinally hollow guide rail, a grooved guide rail, or an interlocking surface. Preferably, the buffer 1810' is made of a slightly soft and resilient material to allow slight bending to absorb shocks and vibrations during transport and handling, while accommodating a rigid launch rod and launch port between the projectiles 1800c.

[0162] Before launching a single projectile 1800c, the corresponding box buffer 1910 and the projectile's own buffer 1810' retract. This retraction ensures that the projectile 1800c can be launched smoothly without any operational contact with the surrounding buffer 1810', allowing it to exit the box 1520 unimpeded.

[0163] Figures 20A to 20D The invention illustrates the use of various cabin configurations based on some embodiments of the invention. Figures 18A to 18C The 1800a and 1800c stacked projectile systems.

[0164] refer to Figure 20A The slide rail 1910 of any previously launched layer of projectiles 1800a and 1800c retracts to ensure that the launch paths of the remaining projectiles 1800a and 1800c are not obstructed by the slide rails 1810 and 1810' of the already launched layers.

[0165] If both the box rail (buffer) 1910 surrounding the projectile and the projectile's own rail (buffer) retract before launch, then the stacked projectile system utilizes Figure 18C The projectile configuration. Alternatively, if the slide rail is non-retractable, and the box slide rail 1910 only retracts after the projectiles of a particular layer have been fired, the stacked projectile system utilizes... Figures 18A to 18B Projectile configuration.

[0166] This embodiment is particularly advantageous for launching large and heavy projectiles because the retractable rail and buffer mechanism 1810' provides robust support and stability during storage and transport, while allowing for unobstructed and controlled launch sequences.

[0167] refer to Figure 20B This hull configuration includes 432 bomb-shaped projectiles 1800c, each equipped with a retractable slide rail 1810' arranged in a 12×12×3 array. Assuming each projectile 1800' is 300 mm long, 60 mm in diameter (roughly the size of a conventional 60 mm mortar projectile), and weighs approximately 1.5 kg, the total weight of the projectiles 1800c within the hull 2000, excluding the launching equipment and housing 1520, would be approximately 648 kg. Given the B-2 bomber's 18-ton payload capacity, it can carry over 12,000 of these bomb-shaped projectiles 1800c.

[0168] It should be noted that the number and size of the projectiles 1800c in this embodiment can be widely varied according to specific operational requirements. The system is designed to be highly flexible, allowing it to accommodate a wide range of numbers and sizes of projectiles 1800c to meet the needs of various missions or delivery platforms.

[0169] refer to Figure 20C This embodiment illustrates a laterally and downwardly oriented [structure / object]. Figure 20B The same 12×12×3 hull configuration. The aircraft frequently releases munitions at high speeds, and depending on mission parameters, the optimal launch angle for projectile 1800c can vary between lateral and downward. The retractable buffer 1810' provides flexibility, as it can be positioned anywhere along the length of projectile 1800c without disengaging from operational contact before the launch rod and launch port between adjacent projectiles 1800c disengage.

[0170] In scenarios where the hull 2000 is launched horizontally from an aircraft, it may be preferable to position the buffer 1810' further forward along the length of the projectile 1800c. This configuration supports the first layer of the projectile 1800c closer to the longitudinal midpoint, which is particularly advantageous for heavier projectiles 1800'. For very heavy, bomb-like projectiles 1800c, such as those with a diameter of 120 mm or greater, using two sets of retractable buffers 1810' for each projectile 1800c ensures uniform weight distribution and enhanced stability during launch.

[0171] When launching a bomb-shaped projectile 1800c horizontally, it is ideal to initiate the launch sequence with the bottom projectile 1800c of each layer, followed by the next highest projectile 1800c, and so on. This staggered approach prevents any projectile 1800c from needing to clear projectiles 1800c below it during launch, thus streamlining the release process and minimizing potential interference.

[0172] refer to Figure 20D This embodiment illustrates a projectile 1800a in a launch process, employing a hull configuration and featuring a non-retractable midpoint rail 1810. In this configuration, the non-retractable rail 1810 is specifically designed to disengage from operational contact before the launch rod between adjacent projectiles 1800a disengages from the launch port. This design ensures that the rail 1810 does not interfere with the separation of the projectile 1800a during launch.

[0173] For systems utilizing these types of projectiles 1800a with a box-shaped housing configuration, the box-shaped housing 5120 would need to be opened to prevent the rails 1810 of the adjacent box 1520 of the projectile 1800a from sliding relative to the box 1520 during launch. This solution minimizes friction and reduces the risk of potential damage to both the projectile 1800a and the box 1520.

[0174] Alternatively, the box 1520 may be equipped with a retractable rail 1910 that retracts layer by layer when each layer of projectile 1800a is fired. This configuration allows the firing process to be carried out without opening the box 1520, thereby maintaining the configuration integrity and environmental protection provided by the box-shaped housing 1520.

[0175] Figures 21A to 21B Two alternative types of projectiles 2100a and 2100b for a stacked projectile system according to some embodiments of the invention are shown. In these embodiments, projectiles 2100a and 2100b take the form of aircraft-unmanned aerial vehicle-like projectiles and, in addition to other features described herein, include an electronics and battery pack 2111, a detonator and propellant assembly 2112, a solid rocket motor 2113, a metal rocket shield 2114 within a launch port, vertical flaps 2115, horizontal flaps 2116, one or more thrusters 2117, wings 2118, a rail assembly 2119 on each wing 2118, and a double rail assembly 2120 along the bottom surface of the body. It will be understood that any propulsion mechanism can be used in this embodiment.

[0176] The rocket engine 2113 is configured to discharge into the rocket jet through the rocket engine shroud 2114. The rocket engine shroud 2114 has numerous large perforations on its surface to allow for efficient ventilation.

[0177] In these embodiments, the detonator and propellant assembly 2112 is used to launch projectiles 2100a and 2100b and ignite the solid rocket motor 2113. The system is configured such that the solid rocket motor 2113 ignites when projectiles 2100a and 2100b are launched to ensure continuous acceleration throughout the launch process and entry into its initial upward rocket motor phase.

[0178] Rocket motor 2113 is configured to rapidly propel projectiles 2100a and 2100b to their cruising altitude, after which thruster 2117 takes over to enable cruising and subsequent slamming or diving toward the target. The boom assembly may be designed to include shaped charge to penetrate armor before the main payload is ignited. Alternatively, projectiles 2100a and 2100b may be configured without a centrally mounted rocket motor 2113, relying solely on thruster 2117; or the projectiles may utilize biplane-mounted rocket motors for propulsion.

[0179] refer to Figure 21A In the embodiment shown, the aircraft-unmanned aerial vehicle-shaped projectile 2100a includes a recess 2131 at its rear end, which is specifically configured to generate drag. This recess 2131 creates a low-pressure region behind the projectile 2100a during flight, thereby increasing aerodynamic drag and helping to stabilize the projectile's trajectory.

[0180] refer to Figure 21B In the embodiment shown, projectile 2100b has an inwardly curved rear surface 2132. This curvature is configured to achieve a similar effect to a recess by altering the airflow pattern around the rear end of projectile 2100b, further reducing drag and contributing to improved stability during flight. The two designs provide different approaches to managing drag while maintaining the same stack length as other projectiles 2100b in the system.

[0181] Figure 21C An embodiment of the invention illustrates the use of a cabin configuration arrangement from [source missing]. Figure 21A The aircraft-to-unmanned aerial vehicle (UAV) projectile 2100a is a stacked projectile system. In this embodiment, the slide rail 2120 of the projectile 2100a is configured to disengage from operational contact before the launch bar and launch port between adjacent projectiles 2100a.

[0182] This sequential disengagement ensures that the projectile 2100a remains stable throughout the firing process. By disengaging the slide rail 2120 first, any lateral forces that could cause instability in the projectile 2100a during the initial phase of firing are minimized. Once the slide rail 2120 is cleared, the launch rod and launch port can smoothly guide the projectile 2100a along its predetermined trajectory to ensure controlled and stable firing. This design reduces the possibility of any misalignment or wobbling, providing a more precise and reliable firing sequence for the projectile 2100a.

[0183] Figure 21D This illustrates a cabin configuration arrangement based on another embodiment of the invention, utilizing... Figure 21A or Figure 21B The system comprises a stacked projectile system of projectiles 2100a and 2100b. This embodiment is characterized by a 5×7×5 hull 2150 including 175 aircraft-unmanned aerial vehicle projectiles 2100a and 2100b.

[0184] Assuming each 2100a and 2100b projectile is 430 mm long, 305 mm wide, and 60 mm high, and weighs 2 kg, then the overall dimensions of the hull 2150 are approximately 1.5 m × 42 m × 1.5 m, and the total weight of the hull 2150 in this configuration is approximately 350 kg.

[0185] The optimal launch sequence for this embodiment is as follows, wherein the sides and top of cartridge 1520 are open:

[0186] This sequence can be repeated for each subsequent layer of projectiles 2100a and 2100b. Firing projectiles 2100a and 2100b in this manner ensures that each projectile 2100a and 2100b is launched with support from projectiles 2100a and 2100b, with the support projectiles 2100a and 2100b located either to the side and below, or only below, the launched projectiles 2100a and 2100b, rather than having a supported projectile 2100a and 2100b on one side and no corresponding supported projectile 2100a and 2100b on the other side. However, in this embodiment, projectiles 2100a and 2100b can generally be launched in any order, starting from the first layer of projectiles 2100a and 2100b and proceeding sequentially to subsequent layers.

[0187] Figure 21E Shown on the U.S. military High Mobility Multipurpose Wheeled Vehicle (HMMWV) 2140 Figure 21B This is a stacked projectile system. The accompanying diagram illustrates how the system can be deployed in combat and military operations. It should be understood that this system can be similarly adapted for use on other vehicles.

[0188] Figures 22A to 22B Two alternative types of projectiles for a stacked projectile system are illustrated according to some embodiments of the invention. In this embodiment, the projectile is an aircraft-unmanned aerial vehicle projectile 2200.

[0189] like Figure 22A As shown, the projectile 2200a may include twin vertical flaps 2115, twin horizontal flaps 2116, and twin thrusters 2117. Alternatively, as Figure 22B As shown, the projectile 2200b can be equipped with dual rocket engines 2113 instead of thrusters 2117 to provide various propulsion options for various mission requirements.

[0190] Figure 23 The use of a cabin configuration according to some embodiments of the present invention is illustrated. Figure 22A or Figure 22B The 2200a and 2200b stacked projectile systems.

[0191] As shown, the system is mounted on the Freefly Alta X, a large quadcopter drone with a payload capacity of 15 kg. The DJI Flycart is another example that can be used in this paper and has a maximum payload of 30 kg to 40 kg.

[0192] The hull 2300 utilizes a box-shaped outer shell 1520 that opens before launch. The box 1520 is used to protect the environment of the projectiles 2200a and 2200b before launch while providing a robust, solid, and sealed system.

[0193] In this embodiment, the hull 2300 is a 3×15×5 configuration comprising 225 aircraft-UAV projectiles 2200a and 2200b. If each projectile 2200a and 2200b has a length of 140 mm, a width of 110 mm, and a height of 20 mm, then the hull 2300 will have dimensions of approximately 350 mm wide, 320 mm deep, and 420 mm high. If configured as a 3×15×3 hull 2300 with only three layers, the hull 2300 will have dimensions of approximately 350 mm wide, 320 mm deep, and 280 mm high.

[0194] Figure 24A Another projectile 2400 for a stacked projectile system according to an embodiment of the present invention is shown.

[0195] In this embodiment, the projectile 2400 uses a linear actuator 2410 as a propulsion mechanism. The projectile 2400 includes four longitudinal grooves 2411 positioned on the outer surface of the launch rod, along with four corresponding claws 2412 defining a launch port. Specifically, these grooves 2411 and claws 2412 are arranged such that the groove 2411 of the first projectile 2400 is configured to cooperatively receive the claw 2412 of the second projectile 2400, the groove 2411 of the second projectile 2400 is similarly configured to receive the claw 2412 of the third projectile 2400, and so on. This arrangement facilitates the axial stacking of the projectiles 2400 within the projectile column.

[0196] Additionally, the projectile 2400 includes four smooth columnar interaction surfaces 2420 that are radially offset by 45 degrees from the four longitudinal grooves 2411. This offset helps prevent the four claws 2412 from being obstructed by the projectile columnar interaction surfaces 2420 during launch, thus enabling a smooth release process.

[0197] Furthermore, the projectile 2400 is configured such that the projectile interaction surface 2420 disengages from operational contact before the launch rod between adjacent projectiles disengages from the launch port during launch. For enhanced functionality, the projectile interaction surface 2420 may also include two smaller guide rails 2120 on two or all four of its surfaces.

[0198] Figure 24B The use of a cabin configuration according to some embodiments of the present invention is illustrated. Figure 24A The 2400-projectile stacked projectile system.

[0199] In this embodiment, the hull 2430 is configured as an 8×8×3 array comprising a total of 192 projectiles 2400. If each projectile 2400 has a length of 200 mm, a width of 40 mm, and a depth of 40 mm, then the total dimensions of the hull 2430' will be approximately 320 mm wide, 320 mm deep, and 400 mm high.

[0200] Figures 25A to 25B Various other aircraft-unmanned aerial vehicle (UAV) projectiles for use in a stacked projectile system according to some embodiments of the present invention are shown.

[0201] exist Figure 25A In one embodiment, the projectile 2500a is large and includes a dual-claw launch bar and a launch port designed for electromagnetic propulsion. The launch bar houses a coil or a series of coils that generate a magnetic field aligned with the longitudinal axis of the projectile 2500a. The corresponding launch port also includes a coil or a series of coils that generate an opposing magnetic field configured to facilitate the launch of the projectile 2500a by magnetic repulsion. The system can be combined with a mechanism for switching the magnetic field polarity during launch so that the projectiles 2500a can be launched sequentially. To assist ground movement, the projectile 2500a may also include a rail 2120 on the bottom surface of the body, or alternatively, a wheel assembly.

[0202] exist Figure 25B In one embodiment, projectile 2500b includes a cylindrical aperture extending from the front end to the rear end of projectile 2500b, configured to receive the launch rod of a launching device. This design allows projectiles in the system to be axially stacked on a long launch rod of the launching device spanning the longitudinal length of the projectile column. In this embodiment, electromagnetic propulsion is used as the propulsion mechanism. Specifically, one or more coils of wire in the launch rod of the launching device generate a magnetic field, the poles of which are aligned with the longitudinal axis of the rod assembly. One or more coils of corresponding wire in the launch port of projectile 2500b generate magnetic fields of opposite polarity. This interaction launches projectile 2500b at a velocity determined by the current in the coils. After launch, projectile 2500b may have a small flap feature that covers the cylindrical aperture at the front to maintain aerodynamic integrity.

[0203] Figure 25C The projectile column shown in some embodiments according to the present invention is an example of a projectile column. Figure 25B A schematic diagram of the aircraft-drone missile 2500b.

[0204] Figure 25D The use of embodiments of the present invention is illustrated. Figure 25AThe system employs a hull configuration for stacked projectile systems of aircraft-UAV projectiles 2500a. In this embodiment, the wings 2118 of the aircraft-UAV projectiles 2500a do not include rails 1219 because they do not mechanically contact each other. This configuration is suitable for aircraft-UAV projectiles 2150 with large or fragile wings 2118. The hull 2510 is a 3×12×3 configuration and includes 108 projectiles 2500a. If each projectile 2500a is 2 m long, 1 m wide, and 15 cm high, then 2510 will be 4 m deep, 3 m wide, and 1.8 m high.

[0205] Figure 25E The interior of an aircraft according to an embodiment of the present invention is shown. Figure 25D The hull 2510. In this embodiment, the hull 2510 is used more as a catapult mechanism than a launching device, and its electrical requirements (voltage / current / capacity) are relatively low. The hull 2510 can obtain energy from the vehicle on which it is mounted or housed. For a ground-based or near-ground launching device where the hull 2510 is used, the electrical requirements are higher, and therefore a mains power supply or a vehicle battery can be used accordingly.

[0206] Figures 26A to 26B Another projectile 2600a for a stacked projectile system according to an embodiment of the present invention is shown. In this embodiment, the projectile 2600a takes the form of a helicopter-unmanned aerial vehicle projectile 2600a.

[0207] The main body of the helicopter-UAV projectile 2600a is elongated with a square cross-section. The middle section of the projectile 2600a is considerably large relative to its relatively short launch bar and launch port. The launch bar includes a clamping inlet 2611, while the launch port is equipped with four clamps 2612 to facilitate axial stacking of the projectile within the projectile column.

[0208] The central section of the projectile 2600a features notches on all four surfaces, each notch designed to compactly accommodate an extendable rotor assembly 2620. This rotor assembly 2620 includes four rotor blades 2621 designed to sit flush within a corresponding notch or recess 2630 prior to launch. After launch, the rotor blades 2621 are deployed, allowing the projectile 2600a to transform into a fully functional helicopter-unmanned aerial vehicle (UAV).

[0209] In this embodiment, the propulsion mechanism is a pyrotechnic linear actuator 1130 housed within the launch bar. Figure 26A The illustration shows a helicopter projectile 2600a with rotor 2621 in the retracted position, the rotor being tightly nested within a notch or recess 2630 as it would be before launch. Figure 26BThe illustration shows the helicopter-UAV projectile 2600a with the rotor 2621 fully extended, and the pin of the pyrotechnic linear actuator in the launch position.

[0210] Figures 26C to 26D An embodiment of the invention is shown employing a cabin configuration. Figures 26A to 26B The helicopter-to-unmanned aerial vehicle (UAV) projectile 2600a is described. In this embodiment, the hull 2610 features a 15×15×3 layout to accommodate 675 helicopter-to-unmanned aerial vehicle (UAV) projectiles 2600a. If each projectile 2600a is 40 mm wide, 40 mm deep, and 200 mm high, then the hull 1610 would be approximately 60 cm wide, 60 cm deep, and 60 cm high. This compact design facilitates the efficient storage and deployment of large numbers of projectiles 2600a, making it suitable for mounting on small delivery trucks or similar vehicles for mobile launch operations.

[0211] Figures 26E to 26F A helicopter-unmanned aerial vehicle (UAV) projectile 2600b according to another embodiment of the invention is shown, which is used in a stacked projectile system, similar to... Figures 26A to 26B The projectile depicted in the image. In this embodiment, the body of projectile 2600b has a small, flat design with a square cross-section. Similar to... Figures 26A to 26B In the embodiment described, the rotor 2621 of the projectile 2600b is configured to extend immediately after launch. If the projectile 2600b has dimensions of 120 mm in width, 120 mm in depth, and 30 mm in height, then a 3×3×22 hull would be 66 cm wide, 66 cm deep, and 66 cm high to accommodate 198 such projectiles 2600b. This flat design makes the projectile 2600b particularly well-suited for scenarios requiring low-altitude deployment.

[0212] Figures 26G to 26H Another helicopter-unmanned aerial vehicle (UAV) projectile 2600c according to an embodiment of the present invention is shown, which is used in a stacked projectile system similar to Figures 26A to 26B The embodiment shown is illustrated below. In this embodiment, the body of the projectile 2600c is small and cylindrical. The launch port includes a widened inlet 2640 at its rear end to facilitate the landing of the projectile 2600c on top of each other within the projectile column 2642.

[0213] The 2600c projectile utilizes electromagnetic propulsion, where coils in the launch rod and launch port generate opposing magnetic fields. This interaction facilitates the launch of the 2600c projectile. A key advantage of this electromagnetic system is its ability to adjust the launch rate based on operating conditions, allowing for adaptable deployment tailored to specific mission requirements.

[0214] Electromagnets within the launch bar and launch port generate an attractive force that gently pulls the landing projectile 2600c into position. This force can be dynamically adjusted in real time via a controller to ensure a smooth and precise landing. A widened inlet 2640 in the launch port further aids in aligning and securing the landing projectile 2600c.

[0215] In this embodiment, if the projectile 2600c has a diameter of 30cm (including the rotor 2621) and a height of 6cm at the main body, then the projectile column 2642, comprising 10 projectiles 2600c, will have a diameter of 30cm and a height of 60cm. This compact and efficient design makes the helicopter drone projectile 2600c particularly well-suited for applications in the recreational or commercial drone industry.

[0216] When stacked within projectile column 2642, projectiles 2600c are able to communicate and inductively charge via electromagnets in their launch rods and launch ports. This feature enhances their operational durability and allows for coordinated action within the projectile column. The inductive charging capability ensures that projectiles 2600c remain functional over extended periods, even during long-duration missions.

[0217] Figures 27A to 27B Another projectile 2700 for a stacked projectile system according to an embodiment of the invention is shown. 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 firing device. The firing rod is rectangular in shape and includes dual Taser-like probes 2710, along with associated lines housed within two small firing tubes 2720.

[0218] The Projectile 2700 is designed to be roughly twice the size of a standard Taser cartridge; however, it is stacked to the same overall size for compatibility with existing Taser systems. This design facilitates integration into current firing devices while providing enhanced functionality. The projectile is designed to accommodate multiple small firing rods of different sizes, enabling the firing of various sub-projectiles such as sponge grenades, rubber balls, pepper balls, small flashbangs, or even small bullets or shotgun-like cartridges. This versatility allows users to customize the type and sequence of the Projectile 2700 to achieve specific tactical results, making it adaptable to a wide range of scenarios.

[0219] Regarding the firing mechanism, the pistol includes a projectile column capable of holding four rounds, a foregrip 2731, a trigger 2741 with a protective component 2742, and a grip 2732 housing a battery and controller. Upon activation, Taser probes from the guided projectile 2700 are ejected forward using a propulsion mechanism. These probes may include integrated batteries to allow them to deliver a continuous charge to the target even after the projectile has been fired from the pistol.

[0220] Figures 27C to 27E Various other projectiles for stacked projectile systems are illustrated according to some embodiments of the invention. These embodiments illustrate various handheld launching devices according to the invention for deploying various types of projectiles.

[0221] For example, Figure 27C A small, handheld grenade launcher is depicted. In this embodiment, the projectile column can hold four grenade projectiles, each measuring 28 mm in diameter and 120 mm in length. Each grenade projectile may include rifling grooves on its launch bar and corresponding rifling grooves in its launch port to allow for spin stabilization during flight. The launch bar 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 to 150 meters. It includes an upper surface that can be clamped or attached to a rifle foregrip via a Picatinny rail or similar attachment system.

[0222] Figure 27D It shows Figure 27C A small grenade launcher was attached to the M4A1 rifle 2750 to demonstrate the system's compatibility with existing military equipment.

[0223] Figure 27E A system utilizing a handheld aircraft-drone launcher with an aircraft-drone-shaped projectile is illustrated. In this embodiment, the aircraft-drone projectile can be thermally tracked, designated via a laser sight 2760, or remotely controlled by the user or from a distance. Both the handheld drone launcher and the projectile can be made of plastic, providing a lightweight and cost-effective solution. The system is available in both reloadable and disposable versions, with options for reloading via a projectile column or by a single projectile.

[0224] Figures 28A to 28E Various missile-shaped projectiles for a stacked projectile system are shown according to some embodiments of the present invention.

[0225] refer to Figure 28A The missile projectile 2800a may include fixed drag fins 2810 and is configured to be stacked in an upward-oriented projectile column. This missile projectile 2800a is roughly the size of a Javelin missile, a surface-to-air missile (SAM).

[0226] exist Figures 28B to 28CIn this design, the missile projectile 2800b is equipped with retractable drag fins 2810' that allow for close stacking within the projectile column without interfering with the launch process. This missile projectile 2800b is roughly the size of a long-range missile and includes rails 2820 on two adjacent surfaces. These rails 2820 help ensure that the missile projectile 2800b disengages from the rails before the launch rod separates from the launch port between the projectiles 2800b. A square body is preferred for this design. Figure 28B The retractable drag wing 2810' is shown, while Figure 28C An extended drag wing is shown.

[0227] exist Figures 28D to 28E In the middle, the missile projectile 2800c includes front and rear retractable buffers 1610. Figure 28D The illustration shows the buffer 2820' extended for storing missile 2800c, while Figure 28E The buffer 2820' is depicted retracting for deployment.

[0228] refer to Figures 28F to 28G , Figures 28A to 28E Each missile launcher is arranged in a hull configuration. Hull 2830 can be designed in a 20×20×3 configuration to accommodate 1,200 missile launchers. For a missile launcher with dimensions of 42 mm wide × 42 mm high × 420 mm long, the hull dimensions would be 840 mm wide × 840 mm high × 900 mm long, and the weight would be approximately 924 kg.

[0229] Referring to Figure 21H, Figures 28A to 28E Each missile is arranged in a single-layer hull configuration. Hull 2830' is designed with a 10×10×1 configuration to accommodate 100 missiles. If used Figure 28B The dimensions of the hull 2830 for the projectile will be 40 mm wide × 40 mm high × 40 mm long.

[0230] 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 includes a list of elements may include not only those elements but also other elements not listed.

[0231] Similarly, it should be noted that when used in the claims, the terms attached, attachable, or attachable should not be construed as limited to direct attachment or permanent fixation.

[0232] It should also be understood that a particular feature from one embodiment may be combined with a feature from another embodiment, and such combinations are considered to be within the scope of the invention.

Claims

1. 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 being at a distal end of the projectile column; a propulsion mechanism connected to the first projectile or the second projectile, or both the first projectile and the second projectile, 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 including 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 one another and are parallel to the central axis; and a controller operably connected to the propulsion mechanism.

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

3. The stacked projectile launcher system of claim 2, wherein the modular insert includes a payload and a fuze or initiator for igniting the payload upon impact.

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

5. The stacked projectile launcher system of 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 socket of the second projectile defines the guide surface of the second projectile.

6. The stacked projectile launcher system of claim 5, wherein the launch socket of the first projectile is engageable with a launch device having a forwardly 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 of claim 1, wherein the first projectile is identical to the second projectile.

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

9. The stacked projectile launcher system of claim 87, wherein the expandable cavity forms a tubular casing.

10. The stacked projectile launcher system of claim 1, wherein each projectile includes a rearwardly mounted drag assembly extending radially outward from the body.

11. The stacked projectile launcher system of claim 10, wherein the rearwardly mounted drag assembly includes a circular wing encircling a series of radial wings, or an outer periphery on each launch rod has a protruding rail engageable with a corresponding groove on a launch socket of a corresponding projectile configured to rotate the corresponding projectile for spin stabilization as propelled from the projectile column.

12. The stacked projectile launcher system of claim 6, wherein the projectile column is supported by the launch device. ​ 13. The stacked projectile launcher system of claim 1, wherein the first projectile is releasably connected to the second projectile to enable reloading on a per-pillar basis.

14. The stacked projectile launcher system of claim 1, wherein the first projectile is releasably connected to the second projectile to enable reloading on a single projectile basis.

15. The stacked projectile launcher system of claim 6, wherein the first projectile includes a plug or other mechanical connection along the outer periphery of the rear end of the launch port of the first projectile, the plug or other mechanical connection being configured to engage 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 projectile.

16. The stacked projectile launcher system of claim 6, wherein the launching device includes a series of claws configured to engage small channels in the outer periphery of the first projectile for snap-locking the projectile post to the launching device.

17. The stacked projectile launcher system of claim 6, wherein the launching device includes a guide rail and a groove for radially aligning the projectile column with the launching device.

18. The stacked projectile launcher system of claim 8, wherein the propulsion mechanism comprises a propellant and an electrical or mechanical trigger configured to ignite the propellant charge and cause combustion of the propellant extending in the expandable cavity to apply a propulsion force to the launch port of the second projectile.

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

20. The stacked projectile launcher system of claim 18, wherein the propulsion mechanism further includes a barrier to seal the propellant charge to prevent accidental ignition.

21. The stacked projectile launcher system of claim 18, wherein the electrical or mechanical trigger is housed within the launching device.

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

23. The stacked projectile launcher system of claim 22, wherein each projectile further comprises a plurality of tubular bypass cavities in its launch port to allow the propellant to extend into other projectiles in the projectile column.

24. The stacked projectile launcher system of claim 23, wherein each projectile further includes a guide rail in its launch rod and a corresponding groove in its launch port for radial alignment of the projectile post, such that the ignition cavity and the bypass cavity are cooperatively connected.

25. The stacked projectile launcher system of claim 24, wherein the propulsion mechanism enables communication of the expansion gas between each launch bar and launch port assembly to enable launch via a launch cavity in the launch device.

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

27. The stacked projectile launcher system of claim 26, wherein the magnetic poles of each magnetic field are aligned with the radial center of the projectile column.

28. The stacked projectile launcher system of claim 4, wherein the propulsion mechanism includes a longitudinal spring assembly associated with the inner periphery of the launch port on each projectile, the spring assembly being configured to compress and expand to apply a propulsive force on the launch port of each projectile.

29. The stacked projectile launcher system of claim 28, wherein the spring assembly comprises a plurality of radially arranged springs configured to compress when the launch port of each projectile engages with the launch rod of the corresponding projectile.

30. The stacked projectile launcher system of claim 29, wherein the spring assembly further includes a hook assembly to lock each launch bar in place with the launch port assembly when each projectile is compressed in the projectile column.

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

32. The stacked projectile launcher system of claim 1, further comprising one or more additional projectile columns capable of engaging with a multi-column launcher.

33. The stacked projectile launcher system of claim 32, wherein the projectile columns form a projectile array supported by three-dimensional mechanical means.

34. The stacked projectile launcher system of claim 32, wherein the projectiles have flat edges to facilitate three-dimensional stacking of the projectile columns.

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

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

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

38. The stacked projectile launcher system of claim 1, wherein the projectiles define a projectile array supported by a box-shaped housing for ease of transport and for easy projectile launch.

39. The stacked projectile launcher system of claim 38, wherein the box-shaped housing has an inner surface including corresponding guide rails and grooves to support the outer edge of the projectile array.

40. The stacked projectile launcher system of claim 38, wherein the projectile array forms a hull configuration, the hull configuration comprising a plurality of projectiles.

41. The stacked projectile launcher system of claim 2, wherein the modular insert spans the axial length of the launch rod to enable mechanical or electrical connection between the projectiles via the modular insert.

42. The stacked projectile launcher system of claim 41, wherein the modular insert forms an insert post for a series of vulnerable connecting inserts.

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

44. The stacked projectile launcher system of claim 1, wherein the propulsion mechanism further comprises a rocket engine.

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

46. ​​The stacked projectile launcher system of claim 1, wherein the projectile includes dimensions, shape, and mass for desired flight characteristics.

47. The stacked projectile launcher system of claim 6, wherein each projectile includes dual launch rods and a launch port to define a dual launch rod and port assembly between the projectile and the launching device.

48. The stacked projectile launcher system of claim 8, wherein each projectile further comprises a two-stage burner assembly for improving combustion of gases extending in the expandable cavity to apply propulsion at the launch port of each projectile.

49. The stacked projectile launcher system of claim 48, wherein the two-stage burner assembly comprises: Main burner body; A propellant cup, used to contain the propellant charge and reduce accidental ignition of the propellant charge; as well as A burner exhaust device, which can engage with the main burner body, has one or more orifices through which the propellant charge expands once the propellant charge is ignited and the propellant cup ruptures.

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

51. The stacked projectile launcher system of claim 50, wherein the printed circuit board and the power supply each include a housing assembly.

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

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