Flywheel turbo-vane stack of pellets and ammunition for electromagnetic defense systems

Abstract

The application discloses a flywheel vortex paddle laminated canister for an electromagnetic defense system and ammunition, and belongs to the technical field of short-range defense weapon systems. The canister comprises a core, a center rod and a shell, and the core is composed of multiple flywheel vortex paddle plates which are coaxially laminated on the center rod. The paddle plates form a parameterized sequence, in which at least one parameter of the blade installation angle and the mass eccentricity changes in a preset gradient in the sequence. After being launched, the core rotates under the driving of the airflow, and the paddle plates generate differential axial tension and precession drift due to the above-mentioned gradient difference, so that two-dimensional controllable diffusion is realized in the airspace in a programmed manner, and high-efficiency interception of the barrage is formed in a predetermined shape and density. The application combines the low-cost advantage of electromagnetic emission, avoids the bottleneck of serious ablation and expensive guidance, overcomes the defect of disordered dispersion of traditional canisters, and realizes "super-saturation counterattack" on high-performance-price-ratio targets such as unmanned aerial vehicle swarms.

Description

Technical Field

[0001] This invention relates to the field of ammunition technology and close-in weapon systems, specifically to a shotgun shell and its projectile structure suitable for electromagnetic launch platforms, particularly a flywheel turboprop stacked shotgun shell capable of achieving controlled fragmentation. Technical Background

[0002] Currently, low-cost, intelligent aerial threats, represented by drones and loitering munitions, are posing a severe challenge to traditional air defense systems with their two core advantages: "saturation attacks" and "ultra-low cost." Defenders face the dilemma of difficulty in detecting "low, slow, and small" targets, as well as the "cost-effectiveness inversion" caused by using expensive interceptor missiles to deal with low-cost targets.

[0003] Existing main interception methods each have their limitations: traditional kinetic energy interception systems (such as anti-aircraft guns and missiles) are too expensive or have insufficient firepower density; directed energy weapons are constrained by the environment and energy; and although traditional shotgun shells have the concept of area kill, their spherical or cylindrical fragments are scattered disorderly and their density decays rapidly after leaving the barrel, resulting in poor interception range and controllability, making it difficult to effectively destroy high-speed, dispersed cluster targets.

[0004] Electromagnetic launch technology is considered a key breakthrough, theoretically capable of delivering large-mass payloads over long distances at extremely low cost. However, its practical application faces two inherent bottlenecks: the pursuit of ultra-high speeds leads to severe ablation and short lifespan of the launch devices, and the ultra-high-speed projectile guidance technology required for precision strikes is complex and costly.

[0005] In summary, a key contradiction exists in the current technological ecosystem: electromagnetic launch technology, which combines low cost and wide-area kill potential, is hampered by engineering durability and guidance costs; while traditional shotgun munitions, which possess area-effect capabilities, are limited by the poor performance of their destructive elements. Therefore, the industry urgently needs a new type of highly efficient interceptor munition that can integrate the low-cost advantages of electromagnetic launch while completely circumventing its engineering bottlenecks, and achieve wide-area, high-density, and controllable diffusion patterns. Summary of the Invention

[0006] 3.1 Technical problems to be solved

[0007] This invention aims to solve the following problems existing in the prior art:

[0008] 3.1.1. When facing a saturation attack from a swarm of drones / loitering munitions, traditional defense methods suffer from an imbalance between cost-effectiveness and insufficient interception density;

[0009] 3.1.2. Existing shotgun shells suffer from technical defects such as uncontrollable fragmentation, small effective coverage area, and limited power and range;

[0010] 3.1.3. In the engineering of electromagnetic launch technology, there are two major bottlenecks: severe ablation of the launch device due to the pursuit of ultra-high speed, and high cost of precision guidance of ultra-high speed projectiles.

[0011] 3.2 Technical Solution

[0012] To overcome the aforementioned technical problems, this invention provides a flywheel-turboprop stacked fragmentation shot and ammunition for electromagnetic defense systems. Its core design concept is to abandon the pursuit of "longer range, greater accuracy, and greater power" for individual projectiles, and instead utilize the cost and projectile payload advantages of electromagnetic launch to launch a "stacked" pre-fragmented warhead programmed with precise aerodynamic and mass parameters, forming a high-density, large-volume lethal barrage with controllable diffusion in the target airspace.

[0013] 3.2.1 The technical solution of the present invention is achieved through the following structure:

[0014] A flywheel-turboprop stacked shotgun shell and ammunition for an electromagnetic defense system includes a core, a center rod, and a cartridge case. The core is composed of multiple coaxially stacked flywheel-turboprop discs mounted on the center rod; the cartridge case is used to cover and secure the core before firing.

[0015] The flywheel turboprop disk is a key innovative component, which is a thin metal disk with a central hole, characterized by comprising:

[0016] Outer ring flywheel: It has a circular structure and its outer edge may be serrated to enhance the cutting effect when it collides with an incoming projectile.

[0017] The central blades are a number of blades evenly distributed around the circumference. Their airfoils can adopt or draw inspiration from the blades of aircraft turbofan engines, as well as the airfoils of aircraft propellers (such as the NACA series). The blades have specific twist angles and curvatures to generate predetermined aerodynamic forces in the airflow.

[0018] Inner ring center plate: The center has a precision round hole that mates with the center rod; the center plate has a non-continuous annular through groove, which can be selected to protrude forward, be in the shape of a rectifier cap, or remain in a flat shape.

[0019] Stabilizer bar: Vertically mounted on the through slot, it serves to stabilize the tail fin. The mass distribution of the disc can be precisely adjusted by designing its installation position, quantity, or by adding counterweights.

[0020] The front end of the central rod is equipped with a rectifier cap, and the rear end may be equipped with a friction section or a spiral guide section, which are used to control the timing and state of the disk separating from the central rod after launch.

[0021] The cartridge case can be assembled from multi-lobed composite material units using hoops. The inner wall has protrusions that mate with the recesses of the stacked discs, used to lock the relative positions of the discs within the chamber and prevent relative rotation. After firing, the cartridge case detaches in a predetermined manner, releasing the cartridge core.

[0022] 3.2.2 Working principle and controllable diffusion mechanism of the present invention:

[0023] After the projectile leaves the barrel, the cartridge case separates, exposing the projectile core to the airflow. At this point, two key parameters begin to work together to achieve the "two-dimensional controllable dispersion" of the barrage:

[0024] 3.2.2.1. Axial Spreading (Longitudinal Stretching): By pre-setting different blade installation angles (torsion angles) for each disc in the sequence, discs with larger installation angles have higher aerodynamic efficiency, greater axial thrust, and higher flight speed; discs with smaller installation angles have slower speeds. This causes the stacked disc sequence to gradually stretch axially during flight, forming a continuous "leap chain".

[0025] 3.2.2.2. Radial Spread (Lateral Diffusion): By presetting different mass eccentricities for each disc in the sequence (achieved through embedding counterweights in specific blades and / or asymmetrically arranging stabilizing rods), the mass eccentricity will cause the discs to precess, i.e., to drift in a cone shape around the flight direction, under high-speed rotation. By programmatically setting the magnitude and direction of the eccentricity of each disc, its drift radius and phase can be controlled, allowing the entire missile belt to spread synchronously in the lateral direction, forming a continuously expanding dynamic spiral cone-shaped kill curtain.

[0026] By precisely programming the gradient changes of the two parameters mentioned above in the stacked sequence, various controllable bullet screen patterns, ranging from dense to sparse and from linear to three-dimensional, can be formed in a preset airspace, achieving "oversaturated" coverage of incoming cluster targets.

[0027] 3.3 Beneficial Effects

[0028] Compared with the prior art, the present invention has the following significant advantages:

[0029] 3.3.1. Disruptive cost-effectiveness: Combining the low cost per shot of electromagnetic launch with the simple structure and mass production characteristics of this munition, the defender can intercept the incoming target at a cost far lower than that of the target, fundamentally reversing the advantage of "low-cost saturation attack" relied upon by drone "swarms" and realizing the strategic countermeasure of "oversaturation counterattack".

[0030] 3.3.2. Superior interception performance: The unique "flywheel turboprop stacked" design, through precise programming of aerodynamic and mass parameters, enables controllable fragmentation range, density and morphology, completely overcoming the shortcomings of traditional shotguns with random dispersion and small effective area. A single shot can form a large-volume uniform damage zone, greatly improving the interception probability of small high-speed cluster targets.

[0031] 3.3.3. Ingeniously avoiding technical bottlenecks: This invention does not pursue extreme initial velocity, which significantly reduces electrothermal ablation during launch and extends the life of the launch platform; at the same time, the ammunition itself is an unguided intelligent structure, and its destructive power can be derived from the overall parameterized design, which completely avoids the problem of integrating expensive guidance systems on ultra-high speed projectiles, making it possible for low-cost electromagnetic close-in weapon systems to be put into practical use.

[0032] 3.3.4. High controllability and flexibility: By adjusting the parameter gradient of the disk sequence, barrages of different shapes (such as cylinders, cones, and inverted cones), densities, and diffusion rates can be generated in advance to adapt to the needs of different defense scenarios, resulting in extremely high tactical flexibility.

[0033] 3.3.5. The shotgun structure of the present invention has good platform adaptability. It can be used not only in new concept electromagnetic defense systems, but also integrated into existing traditional artillery, missiles (rockets) and other platforms, providing an efficient and low-cost anti-swarm upgrade solution for existing air defense systems, greatly expanding its application prospects and market value. Attached Figure Description

[0034] The embodiments of the present invention will now be described with reference to the accompanying drawings. It should be noted that the drawings are for illustrative purposes only, and the proportional relationships between the components are not limitations imposed during actual manufacturing.

[0035] Figure 1 This is an exploded view of the overall structure of the flywheel turboprop stacked shotgun provided in the first embodiment of the present invention.

[0036] Figure 2 for Figure 1 The side view of the overall structure shown illustrates the relative positions of the core, center rod, and cartridge case.

[0037] Figure 3 for Figure 1 A frontal 3D structural schematic diagram of a key component—a single flywheel turboprop disk.

[0038] Figure 4 for Figure 3 The diagram shows a rear-view 3D structural schematic of the flywheel turboprop disk.

[0039] Figure 5 for Figure 3 The image shows a front view of the flywheel turboprop disk.

[0040] Figure 6 for Figure 3 The rear view of the flywheel turboprop disc shown.

[0041] Figure 7 for Figure 3 The side view of the flywheel turboprop disk shown.

[0042] Figure 8 for Figure 3 The top view of the flywheel turboprop disk shown.

[0043] Figure 9 For along Figure 8 The cross-sectional view obtained by cutting with section line AA shown in the figure.

[0044] Figure 10 The diagrams show a comparison of two different stabilizer bar structures; (a) is the standard stabilizer bar and its exploded view, and (b) is the stabilizer bar with a counterweight added to the tail and its exploded view.

[0045] Figure 11 The diagrams show a comparison of two different structural forms of the center rod; (a) is a center rod with a friction section at the tail and its exploded view, and (b) is a center rod with a helical guide rail section at the tail and its exploded view.

[0046] Figure 12 A schematic diagram illustrating the process of sequentially stacking and assembling multiple flywheel turboprop discs along a central rod.

[0047] Figure 13 for Figure 12 The side view of the stacked assembly shown highlights the staggered arrangement of the stabilizer bars on the front and rear discs.

[0048] Figure 14 The diagrams show two flywheel turboprop disks with different blade installation angles to illustrate the differences in installation angle parameters. (a) The disk blade installation angle is 60°, and (b) The disk blade installation angle is 75°.

[0049] Figure 15 for Figure 14 The diagram shows a rear-view 3D comparison of the two types of discs.

[0050] Figure 16 A comparative schematic diagram of a complete core formed by stacking multiple flywheel turboprop discs and a single disc.

[0051] Figure 17 This is a front-view three-dimensional schematic diagram of the shotgun assembly of the first embodiment.

[0052] Figure 18 for Figure 17 The image shows a rear-view 3D schematic diagram of a shotgun shell.

[0053] Figure 19 This is a front-view three-dimensional schematic diagram of the time-delay cartridge case used in a selected embodiment of the present invention.

[0054] Figure 20 for Figure 19 The diagram shows a rear-view 3D schematic of the time-delay cartridge case.

[0055] Figure 21 This is a front-view three-dimensional structural diagram of a turboprop disk (without an outer ring flywheel) provided in the second embodiment of the present invention.

[0056] Figure 22 for Figure 21 The diagram shows a rear-view three-dimensional structural schematic of the turboprop disk.

[0057] Figure 23 A schematic diagram comparing a core formed by stacking multiple turboprop disks with a single disk.

[0058] Figure 24 An exploded view of the overall structure of the shotgun provided in the second embodiment.

[0059] Figure 25 This is a front-view three-dimensional schematic diagram of the shotgun after assembly according to the second embodiment.

[0060] Figure 26 for Figure 25 The image shows a rear-view 3D schematic diagram of a shotgun shell.

[0061] Figure 27 This is a family tree diagram of the various possible airfoils and configurations of the disk structure described in this invention.

[0062] The meanings of the labels in the attached diagram are as follows:

[0063] 100: Flywheel turboprop disc (core unit), 110: Flywheel, 111: Flywheel outer edge serrations, 112: Flywheel and propeller blade connection.

[0064] 120: Blade; 121: Connection between blade and center disk; 122: Eccentric counterweight of blade.

[0065] 130: Center plate, 131: Center hole, 132: Through groove, 133: Forward protrusion of the plate body.

[0066] 140: Stabilizer bar; 141: Standard bar; 141b: Type B bar; 142: End cap (butt cap); 143: Snap ring; 144: Counterweight sleeve (for Type B stabilizer bar).

[0067] 200: Center rod, 210: Standard center rod, 210b: Type B center rod, 220: Rectifier cap, 230: Friction section rubber sleeve, 230b: Helical guide section (for Type B center rod).

[0068] 300: Cartridge case assembly; 310: Cartridge case splitting unit; 320: Hoop ring; 330: Cartridge case groove; 340: Hoop ring cut-off position.

[0069] 400: Delayed cartridge case; 410: Delayed cartridge case split unit; 420: Longitudinal fuse; 430: Circular fuse; 440: Primer.

[0070] 1120: Blade of the second embodiment; 1121: Connecting part of the second embodiment; 1122: Eccentric counterweight of the second embodiment.

[0071] 3300: Second embodiment cartridge case; 3310: Second embodiment cartridge case segment; 3320: Second embodiment clamp; 3330: Second embodiment casing groove; 3340: Second embodiment clamp cut-off position. Detailed Implementation

[0072] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be described in detail below with reference to the accompanying drawings and examples. The following description is exemplary and not restrictive, and those skilled in the art can make modifications and variations within the spirit of the present invention.

[0073] In this invention, unless otherwise expressly defined, the term "flywheel turboprop disc" refers to a thin disc having a central disc and circumferential blade structure, which may or may not include an outer flywheel structure.

[0074] 5.1 Example 1

[0075] This embodiment provides a flywheel turboprop stacked shotgun shell for an electromagnetic defense system, the overall structure of which is as follows: Figure 1 , Figure 2 , Figure 17 and Figure 18 As shown. The shotgun shell is mainly composed of three parts: a flywheel turboprop disc (100), a center rod (200), and a cartridge case (300).

[0076] 5.1.1. Structural Composition

[0077] 5.1.1.1 Composition of Flywheel Turbine Disc (100) and Sponge Core

[0078] The flywheel turboprop disk (100) is the core damage unit of this invention, and its specific structure is as follows: Figures 3 to 9As shown. In this embodiment, 100 discs are coaxially stacked along the axial direction and jointly inserted onto the central rod (200) to form the core of the shot. The disc material is preferably 60Mn spring steel, with a single disc thickness of 2mm and a diameter of 100mm. The manufacturing of each disc includes two main steps: first, a thin metal blank is obtained through a stamping process; then, the blades (120) of the blank are precisely twisted and bent using special tooling to form an aerodynamic shape that meets the preset installation angle (torsion angle) gradient requirements. The finished disc specifically includes the following structural parts:

[0079] Flywheel (110): The outermost ring of the disc, with serrations (111) on its outer edge to enhance cutting ability.

[0080] The inner edge of the flywheel (110) is connected to the tips of each blade (120) through a connecting block (112), which strengthens the overall structure.

[0081] Blade (120): 12 blades evenly distributed circumferentially. Blade (120) has a specific twist angle (i.e., installation angle) and curvature, and its airfoil can be derived from the airfoil of the NACA series of aircraft propellers. At a specific radial position on at least one blade, a counterweight (122) is embedded to provide a controllable mass eccentricity for the disc.

[0082] Center disk (130): Located in the center of the disk, it has a circular hole (131) at its center that precisely matches the center rod (200) (tolerance range: +0.0 mm to +0.1 mm). The center disk (130) has a non-continuous annular through groove (132). In particular, the disk body of the center disk (130) protrudes forward as a whole (133) to form a counterweight structure, which is used to balance the eccentric torque generated by the rearward extension of the stabilizer rod (140) in the axial direction, and to ensure the dynamic stability of the disk in flight.

[0083] Because the change in the installation angle of adjacent blades is small, it is difficult to observe this change; therefore... Figure 14 , Figure 15 The changes of two disks with significantly different installation angles were compared. (a) The installation angle of the disk blade (120a) is 60°, and (b) The installation angle of the disk blade (120b) is 75°. Their changes can be seen intuitively.

[0084] Stabilizer bar (140): such as Figure 10 As shown, the stabilizer bar is vertically installed on the through slot (132) of the center plate (130). It can be fixed by the end cap (142) and the retaining ring (143). The installation position, number (e.g., 1-2 bars) of the stabilizer bar (140) and whether to add a counterweight (144) (which can be used to fine-tune the mass distribution of the plate) depend on the specific working conditions.

[0085] 5.1.1.2 Center rod (200)

[0086] The structure of the center rod (200) is as follows Figure 11 As shown, it mainly includes:

[0087] Central rod (210): Main rod.

[0088] Optimizer cap (220): Located at the front end, used to reduce flight drag.

[0089] Tail section: This embodiment provides two options. One is a friction section (230), which is made of a friction-resistant rubber sleeve and is used to provide resistance after launch to delay the disk from detaching; the other is a spiral guide section (240), which has a spiral guide on its outer surface and can interact with the center hole (131) of the disk to give the disk an initial rotation state.

[0090] 5.1.1.3 Cartridge casings (300)

[0091] The cartridge case (300) is used to fix the cartridge core inside the chamber, and its structure is as follows: Figure 1 , Figure 17 , Figure 18 As shown. It is composed of four-lobed composite material cartridge case units (310) assembled together and secured externally by a hoop (320). The inner wall of the cartridge case has longitudinal grooves (330) that engage with the flywheel (110) of the disc to prevent the cartridge core from rotating inside the case before firing. During firing, the external mechanism acts on the hoop cut-off point (340) to cause the hoop (320) to break inside the barrel and be ejected by the extraction mechanism; after the cartridge body leaves the barrel, the four-lobed cartridge case unit (310), which has lost the constraint of the hoop, quickly separates from the cartridge core under the action of airflow, releasing the cartridge core.

[0092] 5.1.2. Working Principle and Process

[0093] The core of this embodiment lies in achieving "two-dimensional controllable dispersion" of the projectile core after it leaves the barrel through preset gradient parameters, thereby forming a large-scale, high-density interception barrage.

[0094] 5.1.2.1 Parametric Sequence Design

[0095] The 100 disks in this invention are not identical, but rather constitute a parameterized sequence. There are two key control parameters:

[0096] Blade installation angle gradient (controlling axial spread): From the 1st blade (adjacent to the fairing cap) to the 100th blade, the blade installation angle (torsion angle) of each blade decreases linearly with a very small difference (e.g., 0.1° to 0.5°). This results in "faster blades" with larger installation angles having greater axial aerodynamic thrust and higher speed, while "slower blades" with smaller installation angles have lower speed. After a period of flight, the fast and slow blades naturally separate axially, forming a longitudinally distributed "leap chain," which is "one-dimensional spread."

[0097] Mass eccentricity gradient (controlling radial dispersion): By systematically changing the radial position, mass, and / or asymmetrical arrangement of the counterweights (122) and stabilizers (140) on each disc, a small, directionally controllable mass eccentricity is preset for each disc. According to the principles of dynamics, a high-speed rotating eccentric body will generate precession, which manifests as a conical drift of the disc around the flight direction. By programming and setting the magnitude and directional gradient of the eccentricity, different discs can generate precession drifts with different radii and phases. Thus, the entire missile belt spreads synchronously in the lateral direction, forming a dynamically expanding conical kill zone, which is "radial dispersion".

[0098] The combination of axial and radial dispersion achieves "two-dimensional dispersion," ultimately forming a massive, controllable three-dimensional interception barrage in the preset airspace.

[0099] 5.1.2.2 Workflow

[0100] The workflow of this embodiment includes five stages in sequence: launch preparation, missile casing separation, missile core activation, programmed dispersion, and final interception.

[0101] a. Launch preparation stage: The assembled missile core (i.e., 100 parameterized discs inserted on the central rod) is encapsulated in the missile casing (300) and loaded into the electromagnetic launch device as a whole.

[0102] b. Cartridge case separation stage: During the chambering process, the external linkage mechanism acts on the circumference cut-off point (340) of the cartridge case, causing the circumference (320) to break and be ejected; after the cartridge body leaves the chamber, under the action of aerodynamic resistance, the four-lobed cartridge case unit (310) that has lost the constraint of the circumference quickly separates from the cartridge core, completing the release of the cartridge core.

[0103] c. Core Launch Phase: After release, the core flies forward at an initial velocity V0. A strong oncoming airflow acts on the blades (120) of each disk, driving the entire disk stack to begin high-speed rotation. At this time, all disks still function as a single unit.

[0104] d. Disc Separation and Programmed Dispersion: During flight, the discs rotate and consume some kinetic energy, causing their axial velocity to gradually decrease below that of the central rod. Their relative motion is clearly manifested as follows: the discs rotate at high speed while sliding along the central rod towards the tail. At the same time, the friction section (230) or the helical guide section (240) at the tail of the central rod further adjusts the separation dynamics, causing the discs to slip off the central rod in sequence.

[0105] e. Two-dimensional dispersion: After being freed from constraints, the gradients of aerodynamic and mass parameters pre-set in the disk sequence immediately dominate its motion trajectory:

[0106] - Axial stretching (one-dimensional spread): Based on the installation angle gradient, different disks generate differentiated axial aerodynamic thrust, resulting in flight speed differentiation, thus stretching the whole in the longitudinal direction into a long "spring chain".

[0107] - Radial diffusion (two-dimensional spread): Based on the mass eccentricity gradient, each high-speed rotating disk generates a specific phase and radius precession, causing the entire chain of missiles to expand laterally in sync, ultimately forming a dynamically expanding three-dimensional conical kill zone.

[0108] f. Terminal Interception Phase: After dispersal, a high-density interception screen composed of hundreds of high-hardness, high-speed rotating, intelligently distributed discs is formed. Any "low, slow, and small" target entering this airspace will face an extremely high probability of damage to its airframe, power system, or control system, thus achieving efficient and low-cost area air defense.

[0109] 5.1.3. Implementation Results

[0110] The shotgun of this embodiment can effectively cover the core short-range air defense zone from 500 to 3000 meters. If a delayed-action cartridge case (400) is used, it can be extended to deal with threats from 3000 to 10000 meters. It does not rely on precision guidance to a single target, but intercepts cluster targets with a very high probability by delivering supersaturated, intelligently dispersed damage elements along key flight paths. Its single-shot cost is extremely low, successfully achieving a strategic countermeasure of "saturation attack" with "supersaturation counterattack", with a significant cost-effectiveness advantage.

[0111] 5.2 Example 2:

[0112] This embodiment provides another implementation of the flywheel turboprop stacked shotgun shell of the present invention, the overall structure of which is as follows: Figure 24 , Figure 25 and Figure 26 As shown. The shot also consists of a core, a center rod (200), and a cartridge case (3300).

[0113] 5.2.1 Structural Composition

[0114] The core is composed of multiple turboprop discs (1100) stacked coaxially along the axis and threaded through the central rod (200).

[0115] The turboprop disk (1100) is the core feature of this embodiment. It is a thin, integrally formed metal part, mainly comprising:

[0116] - Blade (1120): Several blades evenly distributed circumferentially, having an installation angle (torsion angle) that varies according to a preset gradient, and a counterweight (1122) is provided on at least one blade.

[0117] - Center plate: Similar to the structure of Embodiment 1, it has a central opening and may be provided with a forward protrusion and a through groove for mounting the stabilizer bar (140).

[0118] The key difference from Embodiment 1 is that the disc in this embodiment does not have an outer ring flywheel structure, and the blade root of the blade (1120) is directly connected to the outer edge of the central disc.

[0119] The structure and function of the central rod (200) (such as the front rectifier cap, the rear friction section, or the spiral guide section) are the same as in Embodiment 1.

[0120] The cartridge case (3300) also adopts a multi-lobed composite structure, which is fastened by a hoop (3320), and the inner wall is provided with a groove (3330) to fit with the disc.

[0121] 5.2.2 Working Principle and Process

[0122] The working principle, parameterized sequence design concept (installation angle gradient and mass eccentricity gradient), and workflow (launch, separation, and dispersion) of this embodiment are consistent with those described in Embodiment 1 (Section 5.1.2), and will not be repeated here.

[0123] This configuration is primarily designed for smaller caliber ammunition platforms (e.g., electromagnetic defense systems that launch projectiles with diameters from 30mm to 60mm). In this application scenario, omitting the outer flywheel is a better choice: firstly, it simplifies the manufacturing process and reduces mass production costs; secondly, it maximizes the aerodynamic area of ​​the blades within a limited radial dimension, ensuring sufficient axial thrust and rotational torque; and thirdly, it allows for a lighter projectile core, which is beneficial for increasing muzzle velocity or ammunition capacity.

[0124] 5.2.3 Implementation Results

[0125] This embodiment fully realizes the tactical effects of "two-dimensional controllable dispersion" and "supersaturation counterattack" described in this invention. At the same time, its structure is more compact and lightweight, and its manufacturing cost is lower. It provides an economical "consumable" interception munition solution for dealing with large-scale, low-cost drone swarm attacks, and complements the function of Embodiment 1.

[0126] It should be noted that the foregoing embodiments only demonstrate two typical configurations of the flywheel turboprop disk (100) or turboprop disk (1100) of the present invention. Those skilled in the art will understand that the specific shape of the disk for realizing the core principle of the present invention is not limited thereto.

[0127] like Figure 27 As shown in the schematic diagram of the turboprop type family, the blade portion of the disk can adopt various aerodynamic or structural forms in specific implementations. For example, its shape can be similar to a fan blade, propeller, windmill blade, or other general blade configurations; it can have an outer ring connection to enhance rigidity (as in Embodiment 1), or it can be without an outer ring (as in Embodiment 2); the edge of the blade can be set to be smooth, or it can have serrations or other structures to enhance damage capability.

[0128] Similarly, the central disc can take multiple forms. It can be forward protrusion (133) as in Examples 1 and 2, or it can be a flat plate, or it can be a form that protrudes forward and then convex backward.

[0129] These specific shape variations, as long as they are manufactured into a thin disc sequence that can be programmed by preset gradient parameters (installation angle, eccentricity) and threaded onto the central rod to form a spring core, all belong to the equivalent transformations or simple variations of the "flywheel turboprop stacked disc" concept of this invention, and should be covered within the protection scope of this invention.

[0130] 5.3 Application Area Expansion

[0131] It should be noted that the "flywheel turboprop stacked shotgun" provided by this invention, as an innovative controllable dispersion surface lethal projectile, has its core value in its core structure and working principle, rather than relying on a specific launching or delivery platform. Based on the disclosed embodiments, those skilled in the art can adapt it to various defense scenarios.

[0132] 5.3.1 Application of Traditional Artillery Platforms

[0133] The shotgun shells of this invention are adaptable to conventional chemical energy (gunpowder) driven artillery. Specifically, a complete shotgun shell (including a core, center rod, and compatible casing) as described in Embodiment 1 or 2 can be integrated as a warhead into a fixed or separate-loading projectile, which includes a casing, propellant, and primer. When fired by conventional artillery, the working principle and effect of casing separation, core activation, and programmed two-dimensional dispersion are exactly the same as those in the aforementioned electromagnetic launch embodiment, thus providing an efficient and low-cost upgrade solution for anti-drone / loitering munitions for existing artillery systems.

[0134] 5.3.2 Application of Missile / Rocket Dispensers

[0135] The shotgun shells of this invention are also suitable as submunitions, carried and dispersed by platforms such as missiles, rockets, or drones. In this application mode, multiple flywheel-turboprop stacked shotgun shells (typically with their disposable cartridge cases removed or using lightweight maneuvers) as described in any of the foregoing embodiments can be bundled and encapsulated within a single mother warhead (dispenser), equipped with a corresponding dispersing mechanism (such as a center-dispensing charge) and a fuze (such as a timed, proximity, or command fuze). When the vehicle reaches the target area airspace, the fuze triggers the dispersing mechanism, uniformly launching a large number of disc submunitions into the air. Subsequently, each disc rapidly unfolds in the air based on its preset installation angle gradient and mass eccentricity gradient, forming a continuous intercepting barrage (i.e., a "metal cloud") with a very wide range and extremely high density. This mode achieves "area defense" or "area denial" of critical airspace, directly hitting the target without guided munitions, and is particularly suitable for intercepting large-scale swarm targets or protecting high-value areas.

[0136] It should be understood that the above-described embodiments are merely specific examples of the present invention, used to illustrate the technical solutions of the present invention, and are not intended to limit the present invention. Within the scope of the core concept disclosed in the present invention, those skilled in the art can modify the above embodiments or make equivalent substitutions for some of the technical features. These modifications or substitutions should all be considered to be included within the protection scope of the present invention.

Claims

1. A flywheel turboprop stacked shotgun shell for use in an electromagnetic defense system, characterized in that, Includes the cartridge core, center rod, and cartridge case; The core is formed by stacking multiple flywheel turboprop discs coaxially sleeved on the central rod along the axial direction. The flywheel turboprop disk is a thin disk, including a central disk with a central hole, and several blades with aerodynamic airfoils distributed circumferentially on the outer side of the central disk. The multiple flywheel turboprop discs form a parameterized sequence, wherein at least one aerodynamic or mass parameter affecting the disc motion changes with a preset gradient in the sequence, so that the discs can programmatically generate two-dimensional spatial diffusion after the projectile core is launched.

2. The flywheel turboprop stacked shotgun shell according to claim 1, characterized in that, The parameter that varies in gradient is the blade installation angle.

3. The flywheel turboprop stacked shotgun shell according to claim 1 or 2, characterized in that, The gradient-changing parameter is the mass eccentricity of the disk.

4. The flywheel turboprop stacked shotgun shell according to claim 3, characterized in that, The mass eccentricity is provided by embedding a counterweight on at least one blade of each disc.

5. The flywheel turboprop stacked shotgun shell according to claim 3, characterized in that, The mass eccentricity is provided or adjusted by placing at least one stabilizing bar on the center plate of each disk.

6. The flywheel turboprop stacked shotgun shell according to claim 1, characterized in that, The flywheel turboprop disk also includes an outer ring flywheel connecting the tips of each of the propeller blades.

7. The flywheel turboprop stacked shotgun shell according to claim 6, characterized in that, The flywheel has serrations on its outer edge.

8. The flywheel turboprop stacked shotgun shell according to claim 1, characterized in that, The tail section of the central rod is provided with a functional structure for adjusting the timing of disk disengagement. The functional structure is a friction section or a spiral guide section.

9. The flywheel turboprop stacked shotgun shell according to claim 1, characterized in that, The cartridge case has a multi-lobed composite structure, and its inner wall is provided with a positioning structure that fits into the stacked disc blades.

10. A type of ammunition, characterized in that, Includes the flywheel turboprop stacked shotgun as described in any one of claims 1 to 9.

11. The ammunition according to claim 10, characterized in that, The ammunition is suitable for firing from conventional artillery or firearms, and the propellant charge is a gunpowder charge.

12. The ammunition according to claim 10, characterized in that, The munition is the warhead of a missile or rocket; the warhead includes a dispersing device configured to disperse the flywheel turboprop stacked shot in a predetermined airspace.

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