A Multi-Wound Coil Reconnection Gun Structure and Its Electromagnetic Launch System Design Method

Abstract

This application belongs to the field of ultra-high-speed electromagnetic launch design analysis, specifically disclosing a multi-wound coil reconnection gun structure and its electromagnetic launch system design method. The multi-wound coil reconnection gun structure includes an excitation source, multiple sets of drive coils, and a launcher armature for launching the load. The launcher armature is disposed within a launch track formed by the multiple sets of drive coils. Each set of drive coils is connected to the excitation source and generates electromagnetic force under the excitation of the excitation source to drive the launcher armature to launch the load. The launcher armature includes a connecting mold and multiple self-closing multilayer metal coil disks, wherein the self-closing multilayer metal coil disks are arranged collinearly at equal distances and fixed together by the connecting mold. This application can significantly reduce the acceleration distance and the length of the launch track.

Description

Technical Field

[0001] This application belongs to the field of ultra-high-speed electromagnetic launch design analysis, and more specifically, relates to a multi-wound coil reconnection gun structure and its electromagnetic launch system design method. Background Technology

[0002] Traditional launch methods using gunpowder as the energy source suffer from a series of drawbacks, including low efficiency, high noise, strong vibration, and a theoretical speed limit. Electromagnetic launch technology emerged to address these challenges. This technology directly converts electromagnetic energy into the kinetic energy of the launch vehicle, offering high efficiency, low noise, high controllability, and freedom from the limitations of the speed of sound, making it a promising field for ultra-high-speed launches.

[0003] In traditional wound-type multi-stage reconnection electromagnetic launcher systems, the launcher armature uses a single wound self-closing metal coil. However, because no electromagnetic thrust is generated before the axis of the single wound metal coil moves to the position of the drive coil axis, the launcher has an inter-stage thrust gap, resulting in wasted acceleration distance and an excessively long launch trajectory, making it unsuitable for applications with strict requirements on launch trajectory length.

[0004] Therefore, how to better realize the structural design of the coiled reconnector and improve its performance has become a technical problem that the industry urgently needs to solve. Summary of the Invention

[0005] In view of the shortcomings of the existing technology, the purpose of this application is to better design the winding reconnector gun structure and improve the performance of the winding reconnector gun. It aims to solve the problems of wasted acceleration distance and excessively long launch trajectory in the existing winding multi-stage reconnector gun electromagnetic launch system.

[0006] To achieve the above objectives, in a first aspect, this application provides a multi-wound coil reconnection gun structure, comprising: An excitation source, multiple sets of drive coils, and a transmitter; the transmitter armature is disposed within a transmitter track formed by the multiple sets of drive coils; Each set of driving coils is connected to the excitation source to generate electromagnetic force under the excitation of the excitation source, so as to drive the transmitter armature to emit; the transmitter armature includes a connecting mold and multiple self-closing multilayer metal coil disks, wherein each of the self-closing multilayer metal coil disks is arranged collinearly at equal distances and is fixed together by the connecting mold.

[0007] Secondly, this application provides a design method for an electromagnetic launching system applied to any of the aforementioned multi-wound coil reconnection gun structures, comprising: The system launch efficiency was analyzed using the thrust model of the wound electromagnetic launch system, and the first selection strategy for the geometric configuration of the drive coil and the launcher armature coil was determined. The system thrust, capacitor discharge in the excitation source, and changes in pulse power device current are analyzed to determine a second selection strategy for the number of turns of the drive coil and the number of turns of the transmitter armature coil. Based on the thrust model, the electromagnetic performance of the electromagnetic thrust generated between adjacent self-closing multilayer metal coil disks is analyzed to determine the third selection strategy for the capacitor in the excitation source of the electromagnetic launch system. A parameter selection analysis is performed on the repetitive peak voltage, pulse peak current, critical rate of rise of on-state current, and current pulse width of the excitation source to determine the fourth selection strategy for pulse power devices in the excitation source. The electromagnetic launch system is designed according to the first selection strategy, the second selection strategy, the third selection strategy, and the fourth selection strategy.

[0008] Overall, the technical solutions conceived in this application have the following beneficial effects compared with the prior art: This application provides a multi-wound coil reconnection gun structure and its electromagnetic launch system design method. By addressing the drawback of inter-stage thrust gaps in traditional wound-type multi-stage electromagnetic launch systems, a launcher armature structure is designed, consisting of multiple self-closing multi-layer metal coil disks arranged equidistantly and collinearly, and fixed together by a connecting mold. This allows the self-closing multi-layer metal coil disks to work together during launch, thereby filling the inter-stage thrust gaps. This significantly reduces acceleration distance and launch trajectory length, while also substantially reducing the cost of external circuit power devices and thrust pulsation. It is well-suited for applications such as electromagnetic catapults that carry large mass loads and have strict requirements on launch trajectory length. The electromagnetic system structure and design method of this application are applicable to induction-type electromagnetic guns such as multi-wound coil guns and multi-wound coil reconnection guns. Attached Figure Description

[0009] Figure 1 This is one of the structural schematic diagrams of the multi-wound coil reconnection gun structure provided in the embodiments of this application; Figure 2 This is the second schematic diagram of the multi-wound coil reconnection gun structure provided in the embodiments of this application; Figure 3 (a) is the structure of a conventional wound-type multi-stage reconnection gun electromagnetic launch system provided in the embodiments of this application, and (b) is a schematic diagram of the thrust pulse data distribution of a conventional wound-type multi-stage reconnection gun electromagnetic launch system. Figure 4 This is a schematic diagram illustrating the principle of multi-stage coordinated acceleration of the multi-wound coil reconnection gun structure provided in the embodiments of this application; Figure 5(a) is a schematic diagram of the thrust pulse curve of the multi-wound coil reconnected gun electromagnetic launch system provided in the embodiment of this application, and (b) is a schematic diagram of the combined electromagnetic thrust curve of the launcher armature of the multi-wound coil reconnected gun electromagnetic launch system provided in the embodiment of this application. Figure 6 This is a flowchart illustrating the design method of an electromagnetic launch system with a multi-wound coil reconnection gun structure provided in the embodiments of this application; Figure 7 (a) is a schematic diagram of the calculation of electromagnetic coupling curves by finite element method and program method under geometric parameter multiples of 1-4 provided in the embodiments of this application; (b) is a schematic diagram of the calculation of electromagnetic coupling curves by finite element method and program method under geometric parameter multiples of 5-7; (c) is a schematic diagram of the calculation of electromagnetic coupling curves by finite element method and program method under geometric parameter multiples of 8-10. Figure 8 (a) is a schematic diagram of electromagnetic thrust with different geometric parameter multiples provided in the embodiments of this application; (b) is a graph of electromagnetic coupling with different geometric parameter multiples; and (c) is a graph of electromagnetic coupling with different geometric parameter multiples. The curve (d) represents multiples of different geometric parameters. The curve (e) represents multiples of different geometric parameters. Curve graph; (f) represents multiples of different geometric parameters. Line graph; Figure 9 (a) in this application is provided by an embodiment. Schematic diagrams of finite element method and program method calculations, (b) is a schematic diagram of the change in velocity of the launcher under different geometric parameter multiples; (c) is a schematic diagram of the efficiency of a single launch of the launcher under different geometric parameter multiples. Figure 10 This is a schematic diagram of the dual-slider reconnection system provided in the embodiments of this application; Figure 11 This is a schematic diagram illustrating the accuracy of the capacitor selection model provided in the embodiments of this application; Figure 12 (a) is a circuit diagram of a type I PFN in a single-stage transmission process, and (b) is a circuit diagram of a type II PFN in a single-stage transmission process. Figure 13 This is a circuit diagram of the capacitor reverse voltage discharge stage provided in an embodiment of this application; Figure 14 This is a circuit diagram of the type I PFN excitation of the multi-wound coil electromagnetic launch system provided in the embodiments of this application; Figure 15 This is a circuit structure diagram of the Type II PFN excitation system with multi-wound coil electromagnetic launch system provided in the embodiments of this application; Figure 16(a) is a simulation diagram of the finite element method and procedural method provided in the embodiments of this application, and (b) is a schematic diagram of the reduction of the track length of the multi-wound coil electromagnetic launch system; Figure 17 (a) is a simulation diagram of the highest temperature of the armature coil of the transmitter in the multi-wound coil electromagnetic transmitter system provided in the embodiments of this application, and (b) is a schematic diagram of the temperature distribution of the armature coil of the transmitter in the multi-wound coil electromagnetic transmitter system. Figure 18 This is a schematic diagram of the thermal stress distribution of the armature of the transmitter in a multi-wound coil electromagnetic launch system provided in this application embodiment; Figure 19 (a) is a stress distribution diagram of the drive coil structure provided in the embodiment of this application, (b) is a stress distribution diagram of the structure of the self-closing emitter armature coil, and (c) is a distribution diagram of the absolute total gas pressure of the emitter armature at an ultra-high speed of 680 m / s. Detailed Implementation

[0010] To make the objectives, technical solutions, and advantages of this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application.

[0011] The terms "first" and "second," etc., used in the specification and claims of this application are used to distinguish different objects, not to describe a specific order of objects. For example, "first selection strategy" and "second selection strategy," etc., are used to distinguish different selection strategies, not to describe a specific order of selection strategies.

[0012] In the embodiments of this application, the terms "exemplary" or "for example" are used to indicate that something is an example, illustration, or description. Any embodiment or design that is described as "exemplary" or "for example" in the embodiments of this application should not be construed as being more preferred or advantageous than other embodiments or design. Specifically, the use of the terms "exemplary" or "for example" is intended to present the relevant concepts in a specific manner.

[0013] In the description of the embodiments of this application, unless otherwise stated, "multiple" means two or more, for example, multiple processing units means two or more processing units, multiple elements means two or more elements, etc.

[0014] The embodiments of this application are described below with reference to the accompanying drawings.

[0015] Figure 1 This is one of the structural schematic diagrams of the multi-wound coil reconnection gun structure provided in the embodiments of this application, such as... Figure 1 As shown, it includes: The system includes an excitation source 1, multiple sets of drive coils 2, and a transmitter armature 3 for the transmitting load; the transmitter armature 3 is disposed within a transmitting track composed of multiple sets of drive coils 2. Each set of drive coils 2 is connected to the excitation source 1 and is used to generate electromagnetic force under the excitation of the excitation source 1 to drive the transmitter armature 3 to drive the load to emit; the transmitter armature 3 includes a connecting mold 31 and multiple self-closing multilayer metal coil disks 32, wherein each self-closing multilayer metal coil disk 32 is arranged collinearly at equal distances and is fixed together by the connecting mold 31.

[0016] Specifically, in the embodiments of this application, a wound-type launcher re-attachment structure is constructed by employing an excitation source, multiple sets of drive coils, and a launcher armature, wherein the launcher armature comprises multiple self-closing multilayer metal coil disks. The load to be launched can be mounted on the launcher armature, together forming the launcher. Here, each set of drive coils is connected to an excitation source, which provides high-power pulse energy to excite electromagnetic coupling between the drive coils and the launcher armature, thereby generating electromagnetic force that drives the launcher armature to move at high speed, thus driving the load mounted on it to launch.

[0017] Among them, the self-closing multilayer metal coil disc refers to a disc-shaped structure formed by multiple tightly packed coils spirally wound from a single metal wire, with the ends of the metal wire connected to form a closed loop, so that the coil can form a closed circuit. It can also be simply described as a "wound metal coil".

[0018] The drive coil can be a hollow coil disk arranged on the top and bottom, and each hollow coil disk is formed by multiple layers of tightly attached hollow multi-turn coils.

[0019] The excitation source can be a pulse forming network (PFN) circuit, including a type I PFN pulse circuit or a type II PFN pulse circuit. Both types of PFN excitation sources are typically composed of pulse capacitors. C ,diode D、 thyristor TH and freewheeling resistor composition.

[0020] Based on the above embodiments, as an optional embodiment, multiple sets of drive coils are arranged collinearly at equal distances along the horizontal direction, and each set of drive coils includes two hollow coil disks connected in series or in parallel and arranged coaxially to form a launch track; each closed multilayer metal coil disk is arranged in parallel within the launch track.

[0021] Specifically, in the embodiments of this application, multiple sets of drive coils are arranged collinearly at equal distances along the horizontal direction, and each set of drive coils may include two hollow metal coil discs connected in series or in parallel and arranged coaxially to form a launch track, with the wound metal coils arranged parallel to the launch track. In this way, by coaxially arranging the drive coils, it can be ensured that the axial repulsive forces on the launcher armature coils cancel each other out, and the forces on the launcher armature coils in the axial direction are balanced, so that the launcher armature can move more stably on the launch track in the middle of the drive coils, thereby improving the firing performance of the re-launch gun.

[0022] The two hollow metal coil disks in each group of drive coils can have rectangular, square, or circular shapes, etc., and this application does not impose any specific limitations on their shape. Similarly, the various wound metal coils in the transmitter armature can also have rectangular, square, or circular shapes, etc., and this application does not impose any specific limitations on their shape.

[0023] It should be noted here that the series or parallel connection method refers to the connection method of the two hollow metal coil disks in the excitation source circuit. When the sequential series connection is selected, the same-name ends and opposite-name ends of the two hollow metal coil disks are connected in series and then connected to the excitation source circuit. When the sequential parallel connection is selected, the same-name ends of the two hollow metal coil disks are connected in parallel and then connected to the excitation source circuit.

[0024] Furthermore, the two hollow metal coil discs, which are coaxially arranged, can be connected in series or in parallel according to actual design requirements, thus meeting more reconnection requirements.

[0025] Based on the above embodiments, as an optional embodiment, the axial arrangement distance between two adjacent self-closing multilayer metal coil disks is determined based on the number of self-closing multilayer metal coil disks and the axial arrangement distance between adjacent two-stage drive coils.

[0026] Specifically, in the embodiments of this application, the transmitter armature employs multiple wound self-closing metal coils arranged at equal intervals, and these multiple wound self-closing metal coils are connected by a connecting mold. Assuming the distance between the axial centers of two adjacent drive coil stages is D, and the number of wound metal coils is N, the transmitter armature moves... If a thrust acceleration is triggered at a distance of 2D-D / N, then the axial arrangement distance between two adjacent wound metal coils is 2D-D / N.

[0027] In one specific embodiment of this application, the axial distance between two adjacent drive coils is D=160mm, and five self-closing wound metal coils are used, meaning that a thrust acceleration is triggered every 32mm of movement. Therefore, the axial distance between two adjacent wound metal coils is 288mm. Figure 2 As shown.

[0028] like Figure 3 As shown in (a), in a traditional wound-type multi-stage electromagnetic launch system, the armature of the launcher is composed of a single wound metal coil. The coil is driven to discharge stage by stage, thus producing a staged acceleration effect. For example... Figure 3 As shown in (b), it demonstrates that the conventional launch structure produced large thrust pulsations and had interstage thrust gaps, wasting acceleration distance and resulting in an excessively long launch trajectory.

[0029] The design concept of the multi-wound coil reconnection gun in this application embodiment stems from filling the thrust gap between stages, saving acceleration distance, and greatly reducing the launch trajectory length. For example... Figure 4 As shown, under the working conditions that satisfy the above five winding metal coil arrangement methods, the position directly opposite is the position where the axis of the emitter coil coincides with that of the drive coil. When the first winding metal coil is directly opposite the first row of drive coils, the drive coil discharges, and the resulting thrust F=F1; when it moves... After the trigger distance, the second wound metal coil is directly aligned with the third drive coil, causing the drive coil to discharge. The resulting thrust is F = F1 + F2; after moving the same distance... Then, the third winding coil generates electromagnetic thrust, and so on. When the fifth winding coil generates thrust against the ninth row of drive coils, it moves the same distance. Then, the first winding coil re-aligns with the second row of drive coils, generating a thrust F = F1 + F2 + F3 + F4 + F5, thus producing a periodic acceleration effect. The thrust pulse curve during this process is shown below. Figure 5 As shown in (a) above, the schematic diagram of the combined electromagnetic thrust of the transmitter armature is as follows: Figure 5 As shown in (b), the armature of the launcher is propelled by multiple wound coils, which fill the interstage thrust gaps within the same spatial scale and greatly shorten the launch track length. Considering the propulsion of large-mass loads such as electromagnetic catapults, high-speed maglev transportation, and aerospace electromagnetic launches, the impact of adding lightweight metal wound coils on the total mass of the launcher is negligible, thus greatly reducing the acceleration distance.

[0030] The multi-wound coil reconnection gun structure provided in this application addresses the issue of thrust gaps between stages in traditional wound multi-stage electromagnetic launch systems. It designs a launcher armature structure consisting of multiple self-closing, multi-layered metal coil disks arranged equidistantly and collinearly, and fixed together by a connecting mold. This allows for coordinated driving between the self-closing multi-layered metal coil disks during launch, thereby filling the thrust gaps between stages. This significantly reduces acceleration distance and launch trajectory length, while also substantially reducing the cost of external circuit power devices and thrust pulsation. It is well-suited for applications such as electromagnetic catapults that carry large mass loads and have strict requirements for launch trajectory length.

[0031] The electromagnetic launch system design method of the multi-wound coil reconnection gun structure provided in this application is described below. The electromagnetic launch system design method of the multi-wound coil reconnection gun structure described below can be referred to in correspondence with the multi-wound coil reconnection gun structure described above.

[0032] Figure 6 This is a flowchart illustrating the design method of an electromagnetic launch system for a multi-wound coil reconnection gun structure provided in this application embodiment. It is understood that this method can be applied to any of the aforementioned multi-wound coil reconnection gun structures, such as... Figure 6 As shown, it includes: Step S1: Analyze the system launch efficiency using the thrust model of the wound electromagnetic launch system to determine the first selection strategy for the geometric configuration of the drive coil and the launcher armature coil. Step S2: Analyze the changes in system thrust, capacitor discharge in the excitation source, and pulse power device current to determine the second selection strategy for the number of turns of the drive coil and the number of turns of the transmitter armature coil; Step S3: Based on the thrust model, perform electromagnetic performance analysis on the electromagnetic thrust generated between adjacent self-closing multilayer metal coil disks to determine the third selection strategy for the capacitor in the excitation source of the electromagnetic launch system. Step S4: Perform parameter selection analysis on the repetitive peak voltage, pulse peak current, critical rate of rise of on-state current, and current pulse width of the excitation source to determine the fourth selection strategy for pulse power devices in the excitation source. Step S5: Design the electromagnetic launch system according to the first selection strategy, the second selection strategy, the third selection strategy, and the fourth selection strategy.

[0033] Specifically, in the embodiments of this application, the series structure of the driving coil is used as an example. The design method of the parallel structure electromagnetic system can be derived with reference to this application.

[0034] More specifically, in the embodiments of this application, in step S1, the electromagnetic coupling efficiency is calculated and the system launch efficiency is analyzed using the thrust model of the wound electromagnetic launch system, and a first selection strategy for the geometric configuration of the drive coil and the launcher armature coil is determined.

[0035] Based on the above embodiments, as an optional embodiment, step S1 involves using a thrust model to analyze the system launch efficiency and determine a first selection strategy for the geometric configuration of the drive coil and the launcher armature coil, including: Based on the thrust model, determine the electromagnetic coupling curve model of the system; The system inductance model is determined, and the system emission efficiency-size ratio model is determined based on the system electromagnetic coupling curve model and the system inductance model. The first selection strategy for determining the geometric configuration of the drive coil and the transmitter armature coil is to use the system emission efficiency-size ratio model to maximize the model output.

[0036] Specifically, in the embodiments of this application, based on the electromagnetic thrust data model in the mathematical analysis foundation of the wound electromagnetic launch system, the electromagnetic thrust and... The expression with the greatest relation is: The expression for the system's inductance is: (1); in, Peak thrust; The mutual inductance corresponding to the optimal electromagnetic coupling point of the system. This represents the mutual inductance gradient corresponding to the optimal electromagnetic coupling point of the system. This represents the pulse capacitance value in the excitation source. The initial voltage of the pulse capacitor. and These are the self-inductance of the transmitter armature coil and the self-inductance of the drive coil, respectively. For the mutual inductance between the drive coil and the emitter armature coil, The optimal electromagnetic coupling point can be defined as the mutual inductance gradient between the drive coil and the armature coil of the transmitter in the electromagnetic system. At the maximum position, and These represent the number of turns of the upper drive coil 1 and the lower drive coil 2, respectively; and These represent the flux linkage areas of drive coil 1 and drive coil 2, respectively. and These represent the flux linkage path lengths of drive coil 1 and drive coil 2, respectively. Represents the magnetic permeability of air; The magnetic flux linkage area represents the area of ​​the linkage driving coil 1 and driving coil 2; This represents the flux linkage path length between drive coil 1 and drive coil 2. Represents the number of turns in the armature coil of the transmitter; The magnetic flux linkage area represents the armature coil area of ​​the transmitter; Represents the flux linkage path length of the armature coil of the transmitter; and These represent the flux linkage areas of the linkage drive coil 1 and the emitter armature coil, and the flux linkage areas of the drive coil 2 and the emitter armature coil, respectively. and These represent the flux linkage path lengths of the linkage drive coil 1 and the emitter armature coil, and the drive coil 2 and the emitter armature coil, respectively. and These represent the self-inductance of drive coil 1 and drive coil 2, respectively; and This represents the mutual inductance between drive coil 1, drive coil 2, and the armature coil of the emitter, respectively. This represents the mutual inductance between drive coil 1 and drive coil 2.

[0037] Here, in order to balance the repulsive force along the axis of the transmitter armature coil, the transmitter armature coil is positioned in the middle of the drive coil for emission, and the number of turns, size, and shape of drive coil 1 and drive coil 2 are exactly the same.

[0038] Substituting the system inductance model expression (1), we can obtain The expression depends only on the coil geometry and is independent of the number of turns. Based on the electromagnetic thrust data model for the three discharge stages in the mathematical analysis fundamentals of wound electromagnetic launch systems, the expression most closely related to the coil geometry can be derived as follows: As shown in the above formula (1), the peak thrust... The peak thrust depends only on the initial energy of the capacitor and the value of the expression for the optimal electromagnetic coupling point.

[0039] Directly By independently decoupling from the electromagnetic thrust formula, and using this expression to represent the important factors affecting the coil geometry's influence on electromagnetic launch performance, this curve can be defined as the electromagnetic coupling curve, thus obtaining the system's electromagnetic coupling curve model. .

[0040] Furthermore, the inductance model of the electromagnetic system is calculated using a numerical calculation method based on coil mutual inductance, and the inductance is calculated. definite integral of the curve model with respect to the x-coordinate of position Determine the design objectives for the coil geometry.

[0041] According to the virtual work displacement theorem in the mathematical analysis foundation of wound electromagnetic launch systems, namely: (2); in, This represents the current in the drive coil. When the number of turns in the drive coil is designed to be large, the current duration in the system increases, and the current decay rate slows down significantly. It is assumed that the current hardly decays during the diode commutation stage and the diode freewheeling stage. According to formula (2), the decay of the electromagnetic thrust depends only on the structural parameters of the coil body. That is, the definite integral of the electromagnetic coupling curve and the horizontal axis of the position. A higher value indicates a higher definite integral of thrust and position, representing a higher converted productive quantity, and thus a higher electromagnetic launch efficiency under the same excitation conditions. Generally, the upper limit of the definite integral can be taken as a specific value at a relatively long distance. , It should be determined based on the actual coil geometry parameters. At this position, the electromagnetic coupling curve approaches 0, meaning that electromagnetic coupling is considered non-existent. The lower limit of 0 represents the position where the armature coil axis of the emitter coincides with the drive coil axis, i.e.: (3); The finite element method (FEM) for deriving electromagnetic coupling curves for different coil geometries is time-consuming and inefficient. This paper proposes a procedural method to calculate the mutual inductance of a disc-shaped coil using numerical integration of Bessel and Struve functions. The Gauss-Laguerre quadrature formula with 34 quadrature nodes is used to approximate infinite numerical integration, significantly reducing computation time. This method offers high accuracy, simple inductance calculation, and short computation time, greatly improving the design efficiency of disc-shaped coil geometries. However, this method is only applicable to disc-shaped coils, and their use is recommended. For coils with rectangular or other geometries, inductance calculation manuals can be consulted, but these methods have lower accuracy and more complex calculation expressions.

[0042] Table 1

[0043] Taking Table 1 as the original parameters as an example, the outer diameter, inner diameter, and thickness geometric parameters of the transmitter armature winding metal coil and the drive coil are proportionally increased to 1-4 times the original parameters, respectively. The simulation results of their electromagnetic coupling curves are as follows: Figure 7 As shown in (a) above; the electromagnetic coupling curve simulation results are as follows: the parameters are scaled up to 5-7 times the original parameters. Figure 7 As shown in (b) of the figure; and with parameters scaled up to 8-10 times the original parameters, the simulation results of their electromagnetic coupling curves are as follows. Figure 7As shown in (c) in the diagram. Electromagnetic launch systems have strict requirements for the air gap, and the distance between a single drive coil and the armature coil of the launcher remains constant at 20mm. This is considered for launches of large-mass loads such as electromagnetic catapult fighter jets, electromagnetic projectiles carrying large-mass armor-piercing guided missiles, ultra-high-speed maglev transportation, and aerospace electromagnetic launches. In these cases, the mass of the wound metal coil has almost no effect on the total mass of the launcher, so the total mass of the launcher remains unchanged, the capacitor energy is adjusted to 1250kJ, and the total mass of the launcher is set to 100kg.

[0044] The accuracy of this procedure is as follows: Figure 7 As shown in (a), (b), and (c), it can be seen that the procedural method and the finite element method have small errors and meet the engineering accuracy requirements.

[0045] Referring to the second selection strategy for the number of coil turns described below, while meeting the requirements of the pulse width for pulsed power devices, the number of turns in the drive coil should be as large as possible. Under the same power supply energy excitation and optimal electromagnetic coupling conditions, when the transmitter is launched to different positions, the definite integral value of the electromagnetic thrust with respect to the horizontal axis of the position represents the kinetic energy gained by the transmitter. The higher the definite integral value, the higher the launch efficiency. Figure 8 The electromagnetic thrust curve shown in (a) is similar to that shown in Figure 1. Figure 8 The electromagnetic coupling curves shown in (b) exhibit a very high degree of consistency in their changing trends; for example... Figure 8 The curve shown in (c) ,like Figure 8 The curve shown in (d) ,like Figure 8 The curve shown in (e) ,like Figure 8 The curve shown in (f) With Figure 9 The electromagnetic thrust curves shown in (a) are not consistent. Therefore, the peak value of the electromagnetic coupling curve determines the peak thrust, and the width of the electromagnetic coupling curve determines the range of electromagnetic coupling, thus determining the thrust width; both together determine the thrust. .

[0046] When in the capacitor discharge phase Monotonically increasing to 1, when the capacitor discharge ends. If at this time the armature coil of the transmitter is in the electromagnetic system At the maximum position, the transmitter armature coil can obtain the highest thrust peak, and at this time the transmitter armature coil reaches the optimal electromagnetic coupling condition.

[0047] Through such Figure 9 The calculation in (a) ,as well as Figure 9The launch efficiency calculated in (c) shows that the trends of the two processes are highly consistent. Figure 9 Figure (b) shows the velocity variation under different geometric parameter multiples under the same condition of optimal electromagnetic coupling, which proves that... High precision characterization of electromagnetic emission efficiency.

[0048] Here, the electromagnetic coupling curve is only related to the coil geometry and not to the number of turns. Regardless of whether the wound electromagnetic launch system uses a rectangular or other geometrically shaped coil, the electromagnetic coupling curve should be used as the design target. The electromagnetic coupling curve characterizes the influence of the wound electromagnetic launch system's structure on the electromagnetic launch system.

[0049] For applications such as electromagnetic catapult-launched fighter jets and electromagnetic guns, where acceleration distance is strictly limited, launch efficiency should not be a primary concern. The efficiency-size ratio model should be considered. The track length is The length of a single transmitter drive coil along the transmission direction is , This includes the length of the drive coil and the spacing between stages. If the coil uses a disc-shaped configuration and there are no gaps between the drive coils of different stages, To determine the outer diameter of the driving coil, under optimal electromagnetic coupling, the energy constraint of a single-stage power supply is considered as follows: The total kinetic energy increase of a single wound metal coil in the transmitter armature is The relationship between it and the efficiency-size ratio is as follows: (4); Given a limited launch trajectory length, to ensure sufficient launch kinetic energy, an efficiency-to-size ratio should be selected. The most important parameters are the coil geometry, and efficiency should not be the primary focus. The first selection strategy, namely the index, is to use the system emission efficiency-size ratio model to perform model output maximization analysis and determine the corresponding geometric configuration of the drive coil and the transmitter armature coil.

[0050] Optionally, provided that the kinetic energy of the launcher meets the engineering objectives, the energy storage selection for a single launch stage power supply can be... When fixed, the cost of a single transmitter stage is The ratio of the two is basically fixed and constant. The total cost of the electromagnetic launch system Estimated as (5); This allows for the selection of coil geometry parameters with higher transmission efficiency, thereby reducing the energy storage requirements for a single transmitter stage. This reduces the cost of electromagnetic launch systems.

[0051] Different design parameters should be applied to the electromagnetic coupling curve under different engineering objectives, with the engineering objectives taking precedence.

[0052] In the embodiments of this application, a coil geometry optimization design method based on a four-dimensional particle swarm optimization algorithm is also proposed, which greatly improves the design efficiency and accuracy of coil configuration and perfects the design principles of wound electromagnetic launch systems.

[0053] In the design process of a wound electromagnetic launch system, the coil geometry should be determined first based on the actual engineering dimensional requirements. Electromagnetic launch systems are highly sensitive to air gap requirements; a smaller air gap can increase the degree of electromagnetic coupling, increase the peak value of the electromagnetic coupling curve, thereby increasing the peak thrust and improving electromagnetic launch performance. However, considering the vibration that occurs during electromagnetic launch, the air gap should not be too small; otherwise, the launcher armature coil may easily collide with the drive coil, compromising the safety of the electromagnetic launch system. Taking an open-type reconnection gun system as an example, a double-slider design and clamps can be used to fix the wound launcher armature coil in the middle of the drive coil for launch, reducing launcher vibration and increasing the stability of the launch system. This allows for further reduction of the air gap and improved electromagnetic launch performance. Figure 10 As shown. Optionally, the guide rail structure can also use other structures, as long as the function can be achieved.

[0054] like Figure 10 As shown, the red arrows represent the direction of electromagnetic thrust, and the blue squares represent the load. The coilgun, with its open structure, can handle a wide range of loads and has many applications. Examples include electromagnetic catapult fighter jets, ultra-high-speed maglev systems, aerospace electromagnetic launches, and applications such as electromagnetic guns and electromagnetic railguns. In contrast, the coilgun, with its closed structure, is almost exclusively used for electromagnetic guns or electromagnetic railguns.

[0055] The essence of a magnetic field is excited by an electric current. Only when the excitation current is large enough can the magnetic field be strong enough, and thus the electromagnetic thrust generated by the interaction between the current and the magnetic field can be large enough.

[0056] Traditional linear motor drive devices use devices such as insulated gate bipolar transistors (IGBTs) for driving. IGBTs are subject to saturation due to conductivity modulation effects, preventing further increases in current density. The maximum peak current that this transistor can withstand is only a few hundred A. Typically, the air gap magnetic field strength of a motor-type solution reaches saturation at 1.6 T.

[0057] The drive devices for both the reconnector and coilgun employ pulsed power devices. Pulse thyristors exhibit regenerative feedback and plasma propagation effects, while pulsed diodes demonstrate full-area bipolar conduction. Both can withstand pulsed peak currents of tens to hundreds of megaamperes and extremely high critical current rise rates, easily exceeding 10T in air gap magnetic field strength. Essentially, this generates electromagnetic thrust ranging from tens to hundreds of meganewtons, far surpassing the thrust limit of linear motor-based solutions.

[0058] Traditional electromagnetic launch devices use solid metal plates or cylinders as the launcher armature, lacking a mathematical analytical foundation. They can only be designed using the finite element method, requiring hundreds of launch stages for acceleration to ultra-high speeds. Even high-performance computers require months to complete the design, resulting in low efficiency and making engineering virtually impossible. In contrast, the wound-type electromagnetic launch system has a clear mathematical analytical foundation and design principles. A high-performance electromagnetic system can be designed in just minutes, offering extremely high design efficiency and accuracy. It can accommodate large-mass loads, opening up vast new prospects in the field of high-thrust, ultra-high-speed electromagnetic launch vehicles.

[0059] In the embodiments of this application, the drive coil should be designed to be relatively thin, while the transmitter armature coil should be designed to be relatively thick, resulting in a small equivalent air gap. The distance between the upper and lower drive coils should be relatively close, while maintaining a small air gap. This results in a high degree of electromagnetic coupling. The thickness and air gap parameters need to be designed according to the actual engineering site size limitations. Taking a disc-shaped coil as an example, the design parameters have four dimensions, including the outer diameter of the drive coil, the outer diameter of the transmitter armature coil, the inner diameter of the drive coil, and the inner diameter of the transmitter armature coil.

[0060] In one specific embodiment of this application, the optimization and selection time can be greatly shortened by using a four-dimensional parameter heuristic optimization algorithm based on particle swarm optimization. The thickness and air gap geometric parameters are shown in Table 1. The coil outer diameter is 32mm-640mm, while the inner diameters of the drive coil and the emitter armature coil can be arbitrarily designed, considering an application scenario with limited acceleration distance. The efficiency-to-size ratio model is used as the design objective, i.e., selecting... The selection of the largest geometric configuration parameters, along with the parallel computation of electromagnetic coupling curves at different locations using 56 threads on the workstation, can almost determine the globally optimal solution in just 10 minutes. Geometric configuration parameters: drive coil outer diameter 295mm, emitter armature coil outer diameter 328mm, emitter armature coil inner diameter 68mm, drive coil inner diameter 56.8mm. The value is 1.2313, which conforms to the engineering convention that the outer diameter of the armature in an electromagnetic launch system is often slightly larger than the outer diameter of the drive coil.

[0061] If an enumeration method is used for simulation, 20 values ​​are uniformly sampled for each dimension of data, and 56 threads are used in parallel to calculate the values ​​for each geometric parameter. It would take at least 80 days. If the finite element method is used for parametric scanning design, a high-performance calculator would need at least several years to calculate, resulting in low design efficiency and making it almost impossible to proceed.

[0062] The four-dimensional particle swarm optimization heuristic algorithm iterates through the four dimensions of the particle simultaneously in each iteration, thus optimizing concurrently. The computation time remains constant regardless of the number of dimensions in the design parameters. Even with five dimensions and 56 threads working in parallel, the five-dimensional particle swarm optimization algorithm can almost reach the global optimum in just 10 minutes. The enumeration method simulates sequential loop calculations, and the calculation time varies with the number of design parameter dimensions. When the design parameter dimensions are five-dimensional, 20 values ​​are uniformly sampled for each dimension, and 56 threads are used for parallel calculation, it will take at least 1600 days to complete the calculation.

[0063] In applications of electromagnetic railguns and guns, the central hole in the armature coil of the launcher can be used to fill explosives. A high-mass, high-density armor-piercing warhead is mounted at the front end of the armature coil, making it ideal for armor-piercing high-explosive projectiles. After penetrating the armor, the warhead detonates with a time-delay fuse. The launcher simultaneously functions as both a kinetic energy projectile and an explosive projectile. The explosive portion is isolated from the armor-piercing projectile body, which, compared to traditional armor-piercing high-explosive projectiles, does not affect the length and mass of the projectile core or the penetration depth, thus further increasing its destructive power.

[0064] Furthermore, in the embodiments of this application, in step S2, based on the mathematical analysis of the wound electromagnetic launch system, the changes in system thrust, capacitor discharge in the excitation source, and pulse power device current are analyzed, and a second selection strategy for the number of turns of the drive coil and the number of turns of the launcher armature coil can be derived.

[0065] Based on the above embodiments, as an optional embodiment, step S2 involves analyzing the changes in system thrust, capacitor discharge in the excitation source, and pulse power device current to determine a second selection strategy for the number of turns in the drive coil and the number of turns in the transmitter armature coil, including: Determine the system inductance model; Determine the peak thrust model of the transmitter armature, the time model of the capacitor discharge stage in the excitation source, and the peak pulse current model of the thyristor under the optimal electromagnetic coupling condition; Using the system inductance model, the peak thrust model of the transmitter armature, the time model of the capacitor discharge stage, and the peak current model of the thyristor pulse, we analyze the changes in system thrust, capacitor discharge in the system excitation source, and pulse power device current. Based on the analysis results, a second selection strategy was determined for the number of turns in the drive coil and the number of turns in the emitter armature coil.

[0066] Specifically, in the embodiments of this application, it is first necessary to determine the inductance model (1) of the electromagnetic launch system based on the circuit structure of the wound electromagnetic launch system, and under the condition of optimal electromagnetic coupling, determine the peak thrust model of the launcher, the time model of the capacitor discharge stage, and the peak pulse current model of the thyristor. Then, using the inductance model of the electromagnetic launch system, the peak thrust model of the launcher, the time model of the capacitor discharge stage, and the peak pulse current model of the thyristor, the changes in system thrust, capacitor discharge in the system excitation source, and pulse power device current are analyzed.

[0067] More specifically, substituting the definition of the electromagnetic system inductance model in equation (1) into equation (1) Number of turns of the drive coil and and the number of turns of the transmitter armature coil Complete elimination means that neither the number of turns in the drive coil nor the number of turns in the emitter armature coil will affect the peak thrust of the system.

[0068] Under optimal electromagnetic coupling conditions, a time model of the capacitor discharge stage in the system's excitation source is provided. for (6); Substituting the electromagnetic system inductance model in equation (1) into equation (6), increasing the number of turns in the drive coil will prolong the capacitor discharge phase time. Therefore, by adjusting to a smaller peak capacitance, the emitter can be moved to the optimal electromagnetic coupling point at the end of the capacitor discharge phase, thereby achieving the optimal electromagnetic coupling condition of the system.

[0069] Furthermore, based on the mathematical analysis of the wound electromagnetic launch system, and under the condition of optimal electromagnetic coupling, the pulse peak current model of the thyristor, the pulse power device in the system's excitation source, is determined. Specifically, the peak pulse current through the thyristor and the rate of rise of the on-state critical current It can be determined as follows: (7); in, In the derivation process, since the mutual inductance is small in magnitude and changes slowly with time, it can be treated as a constant. This indicates the mutual inductance of the system when the axis of the transmitter armature coil coincides with the axis of the drive coil.

[0070] Based on the aforementioned capacitor discharge phase time model, under optimal electromagnetic coupling conditions, when the emitter reaches ultra-high speed, the velocity change is relatively small compared to the incident velocity at high speeds. Therefore, without considering the velocity change, the duration of the capacitor discharge phase is... If the voltage withstand capability of the driving coil in this transmitter stage is lower than the initial voltage of the pulse capacitor, it is insufficient to guarantee the safety of the system. Substituting the definition of the inductance model of the above electromagnetic launch system into the time model of the capacitor discharge stage, through derivation, it is necessary to maintain... Remain unchanged, refer to the third selection strategy for excitation source capacitor selection below, and at the same time, satisfy the capacitor energy constraint to maintain... If the voltage remains unchanged, the initial voltage of the pulse capacitor can be determined. Proportional to the number of turns of drive coil 1 ,Right now ...

[0071] Taking the series structure of the driving coil as an example, the inductance model definition of the electromagnetic launch system is substituted into the initial voltage in the capacitor selection formula (13) below. It can be deduced that: ; in, - All are algebraic variables with no physical meaning, and their values ​​are all values ​​of the electromagnetic optimal coupling point.

[0072] Therefore, a second selection strategy for determining the number of turns in the drive coil also includes: under the condition of optimal electromagnetic coupling, taking five wound metal coils connected to form the emitter armature as an example, through insulation layer thickness design and special stator winding settings, the inter-turn withstand voltage of the coil must be much greater than that of the drive coil. Substituting the inductance expression (1) above into (7), under the premise of satisfying the pulse width of the pulse power device, the number of turns of the final selected drive coil should be as large as possible to reduce the peak pulse current and the rate of rise of the on-state critical current of the pulse power device, thereby reducing the specifications and cost of the pulse power device; increasing the number of coil turns helps to slow down the decay rate of the current, expand the thrust width, improve the transmission performance, and make the final withstand voltage greater than the maximum initial voltage of each stage of the pulse capacitor.

[0073] Specifically, when designing the drive coil, through the design of the wire insulation layer thickness and a specific wire winding method, the inter-turn withstand voltage of the drive coil must be much greater than [the required value]. To meet the pulse width requirements of pulsed power devices, the number of turns should be selected as large as possible, ensuring the final withstand voltage of the drive coil is greater than the initial voltage of all emitter stages. Currently, the inter-turn withstand voltage of triple-insulated circuits can reach 7000V, and the initial number of turns was chosen accordingly. Then, by using the following iterative selection method for the highest thrust peak capacitor, the system's withstand voltage requirements can be met relatively easily, with almost no need for redesign.

[0074] Furthermore, based on the mathematical analysis of wound electromagnetic launch systems and the aforementioned analysis results, the second selection strategy for determining the number of turns in the launcher's armature coil also includes: the number of turns in the launcher's coil. If the effect is completely eliminated, the number of turns of the transmitter armature coil will have almost no impact on the electromagnetic characteristics and parameter selection. However, the number of turns of the transmitter armature coil should be as large as possible, and the cross-sectional radius of the transmitter armature coil conductor should be much smaller than the eddy current skin depth to ignore the influence of the eddy current skin effect and meet the prerequisites for the wound electromagnetic launch system.

[0075] More specifically, based on the design launcher's maximum speed Taking the estimation of eddy current skin depth as an example, the emitter current is equivalent to a sinusoidal alternating current, based on the equivalence relation ,in, For the armature coil current of the transmitter, when electromagnetic coupling is optimal, the transmitter does not move a very long distance, and the mutual inductance... With minimal attenuation, the drive coil current and the emitter armature coil current rise from 0 to their peak values ​​almost simultaneously, at which point it is equivalent to 1 / 4 cycle. Using uniform motion for estimation yields high accuracy. This process can be represented as: (9); in, The distance from the optimal electromagnetic coupling point to the axis of the drive coil. , These represent the equivalent alternating frequency and alternating period, respectively. Indicates the skin depth of the eddy current; and These represent the magnetic permeability and electrical conductivity of the metal material of the armature coil of the transmitter, respectively.

[0076] Therefore, the selection strategy for the transmitter armature coil also includes: the diameter of the metallic conductor only needs to be much smaller than... The conductor diameter can be selected as follows: The effects of eddy skin effect and proximity effect can be almost ignored; the Litz line can also be used to further reduce the influence of proximity effect.

[0077] Further, in step S3, the electromagnetic performance of the electromagnetic thrust generated between adjacent self-closing multilayer metal coil disks is analyzed based on the thrust model of the wound electromagnetic launch system. Specifically, based on the mathematical analysis fundamentals of the wound electromagnetic launch system, the simulated thrust model can be expressed as: (10); in, This refers to the system uptime.

[0078] Based on the above embodiments, as an optional embodiment, step S3 involves performing electromagnetic performance analysis on the electromagnetic thrust generated between adjacent self-closing multilayer metal coil disks according to the thrust model of the wound electromagnetic launch system, and determining a third selection strategy for the capacitor in the excitation source of the electromagnetic launch system, including: Based on the thrust model, determine the target thrust model for the electromagnetic thrust generated between adjacent self-closing multilayer metal coil disks; The target thrust model is integrated according to the impulse theorem to obtain the armature velocity model of the launcher. With the goal of achieving optimal electromagnetic coupling conditions for the launcher armature coil, the capacitor selection model under the maximum thrust peak is determined by extrapolation and analysis based on the launcher armature velocity model. The third selection strategy is determined based on the capacitor selection model.

[0079] Specifically, in the embodiments of this application, the electromagnetic performance of the electromagnetic thrust generated between adjacent self-closing multilayer metal coil disks is analyzed based on the thrust model of the wound electromagnetic launch system. By observing the thrust pulse shape, the thrust pulse can be directly equivalent to a simulated thrust function with symmetry. It has high precision and is relatively easy to operate.

[0080] For example, assuming the distance between the axes of the interstage drive coils is 160mm, the optimal electromagnetic coupling point is 32mm from the axis, and five wound metal coils are connected as the armature of the transmitter, with each 32mm movement triggering one wound metal coil to generate electromagnetic thrust, when the electromagnetic thrust of the previous wound metal coil rises to its peak, the electromagnetic thrust of the next wound metal coil starts to rise from 0. The electromagnetic thrust of the next wound metal coil lags behind the electromagnetic thrust of the previous wound coil by the capacitor discharge stage time. When selecting this stage of capacitor, the acceleration effect generated by the electromagnetic thrust of both wound coils needs to be considered simultaneously, respectively... and This represents the electromagnetic thrust of the upper-level winding coil and the electromagnetic thrust of the current-level winding coil. This represents the incident velocity of the stage. Based on the thrust model, the target thrust model for the electromagnetic thrust generated between adjacent self-closing multilayer metal coil disks is determined. By integrating the target thrust model according to the impulse theorem, the armature velocity model of the launcher is obtained. This process can be represented as: (11); Here, if the number of self-closing metal coils wound is not equal to Then, the thrust function needs to be equivalent to a simulated thrust function, and the velocity expression is obtained by integrating the thrust of multiple wound coils according to different lag times.

[0081] Furthermore, with the goal of achieving optimal electromagnetic coupling conditions for the transmitter armature coil, the transmitter armature velocity model is combined with the time model of the capacitor discharge stage for extrapolation and analysis, which leads to the derivation of the capacitor selection model under the highest thrust peak.

[0082] Based on the above embodiments, as an optional embodiment, with the goal of achieving optimal electromagnetic coupling conditions for the transmitter armature coil, a capacitor selection model is determined by performing a deduction and analysis based on the transmitter armature velocity model, including: Determine the time model of the capacitor discharge stage in the excitation source when the armature coil of the transmitter reaches the optimal electromagnetic coupling condition; The transmitter armature velocity model is integrated based on the capacitor discharge stage time model to obtain the transmitter armature displacement model. Based on the capacitor discharge stage time model and the emitter armature displacement model, the capacitor selection model under the highest thrust peak is determined.

[0083] In the embodiments of this application, based on the mathematical analysis of the wound electromagnetic launch system, the time model of the capacitor discharge stage in the excitation source when the armature coil of the launcher reaches the optimal electromagnetic coupling condition can be determined as described above (6).

[0084] Furthermore, by integrating the aforementioned transmitter armature velocity model, the corresponding transmitter armature displacement model expression is obtained, ensuring that at the end of the capacitor discharge phase, the transmitter is precisely at the optimal electromagnetic coupling point. Thus, the optimal electromagnetic coupling condition is achieved, taking into account capacitor energy constraints.

[0085] (12); Therefore, based on the capacitor discharge stage time model and the emitter armature displacement model, the capacitor selection model under the highest thrust peak value in this case is obtained, and its formula can be expressed as: (13); In the formula = , = , = , = , = , = ， = .

[0086] It should be noted that simplification of this formula to decimal places is not recommended. If simplification is performed, due to the issue of retaining significant figures, the formula is highly prone to non-convergence and incorrect solutions under high-speed operating conditions. Considering that the pulse capacitor material, process, usage conditions, size, space, and cost are subject to certain engineering constraints, and the energy of the pulse capacitor is the same, the pulse capacitor in the excitation source can be made as a large capacitor with a small voltage, or a small capacitor with a large voltage. From the peak thrust formula... (14); Considering the capacitor energy constraint, the peak thrust depends only on the initial capacitor energy and the coil geometry. The peak thrust is basically aligned with the peak thrust line, such as... Figure 5 As shown in (a) in the figure; thrust pulsation is significantly reduced to 10%, as Figure 5 As shown in (b) of the diagram. By verifying the motion displacement of the first, second, and third wound metal coils, the optimal electromagnetic coupling point distance is 32 mm. When the emitter armature moves to 32 mm, 64 mm, and 96 mm respectively, the corresponding thyristor current rises to its peak value. The model satisfies the optimal electromagnetic coupling condition, verifying its high engineering accuracy. Figure 11 As shown.

[0087] Furthermore, in the embodiments of this application, based on the above capacitor selection model, the selection strategy for the pulse capacitor in the system excitation source can be determined, that is, the preset operating parameters of the design can be substituted into the above capacitor selection model to calculate the corresponding optimal capacitor.

[0088] Furthermore, in the embodiments of this application, in step S4, parameter selection analysis can be performed on the repetitive peak voltage, pulse peak current, critical rate of rise of on-state current, and current pulse width of the excitation source according to different types of system excitation sources, thereby determining the fourth selection strategy for pulse power devices in different system excitation sources.

[0089] Furthermore, in the embodiments of this application, in step S5, based on the aforementioned first selection strategy, second selection strategy, third selection strategy and fourth selection strategy, the capacitance parameters of the system excitation source pulse capacitor, the geometric configuration parameters and coil turn parameters of the transmitter armature coil and drive coil under the highest thrust peak, and the selection parameters of the power devices in the system excitation source can be determined. Then, the wound electromagnetic launch system can be designed and simulated based on these determined parameter information.

[0090] The electromagnetic launch system design method of this application, based on the mathematical analysis of the wound electromagnetic launch system, further explores the influence of the capacitor in the system excitation source on the system thrust, the influence of the geometric configuration of the system drive coil and the launcher armature coil on the system launch efficiency, the influence of the number of turns of the system drive coil and the launcher armature coil on the system thrust, the capacitor discharge in the system excitation source and the pulse power device current, and the selection model of the pulse power device in the system excitation source to meet its requirements for repetitive peak voltage, pulse peak current, critical rise rate of on-state current and current pulse width. It constructs a selection model or strategy for the number of turns of the system drive coil, the number of turns of the launcher armature coil, the geometric configuration of the drive coil and the launcher armature coil, and the capacitor and pulse power device in the system excitation source, so as to achieve the performance conditions of optimal electromagnetic coupling of the system. It can realize the design of wound electromagnetic launch systems with high efficiency and high precision, and is suitable for the design application scenarios of induction electromagnetic guns such as multi-wound coil coil guns and multi-wound coil reconnection guns.

[0091] Based on the above embodiments, as an optional embodiment, step S4, the pulse power device includes a thyristor; parameter selection analysis is performed on the repetitive peak voltage, pulse peak current, critical rate of rise of on-state current, and current pulse width of the excitation source to determine a fourth selection strategy for the pulse power device in the excitation source, including: Based on the capacitance value and initial voltage of the excitation source, the self-inductance of the emitter armature coil, the self-inductance of the drive coil, and the mutual inductance between the drive coil and the emitter armature coil, a selection model is determined for the forward repetitive peak voltage, pulse peak current, and critical rate of rise of the on-state current of the thyristor. Based on the self-inductance of the drive coil, the capacitance and freewheeling resistance in the system excitation source, a current pulse width selection model for the thyristor is determined. Based on the selection model of thyristor's forward repetitive peak voltage, pulse peak current and critical rise rate of on-state current, as well as the selection model of thyristor's current pulse width, the selection strategy of thyristor is determined; the fourth selection strategy includes the selection strategy of thyristor.

[0092] Specifically, in the embodiments of this application, based on the mathematical analysis of the wound electromagnetic launch system, during a single-stage launch process, the selection of the thyristor in the system's excitation source mainly depends on four indicators: forward repetitive peak voltage. Pulse peak current Critical rate of rise of on-state current and current pulse width Furthermore, based on the capacitance value and initial voltage of the capacitor in the system's excitation source... Self-inductance of the armature coil of the emitter Self-inductance of the drive coil And the mutual inductance between the drive coil and the emitter armature coil Determine the forward repetitive peak voltage of the thyristor. Pulse peak current and the critical rate of rise of the on-state current Given the constraints, the process can be expressed as follows: (15); in, This represents the system mutual inductance at the end of the capacitor discharge phase.

[0093] It should be noted that regardless of the emitter's position at the end of capacitor discharge, the corresponding system mutual inductance should ensure the safety of the thyristor. Therefore, the forward repetitive peak voltage of the thyristor can ultimately be derived. Pulse peak current and the critical rate of rise of the on-state current The selection model formula is: (16); Furthermore, based on the self-inductance of the drive coil, the capacitance in the system excitation source, and the freewheeling resistance, a current pulse width selection model for the thyristor is determined.

[0094] Based on the above embodiments, as an optional embodiment, a current pulse width selection model for the thyristor is determined based on the self-inductance of the drive coil, the capacitance in the system excitation source, and the freewheeling resistor, including: When the system excitation source is a type I PFN excitation source or a type II PFN excitation source, such as Figure 12 (a) is the circuit structure diagram of a Type I PFN in a single-stage transmission process. Figure 12 (b) shows the circuit structure of a Type II PFN in a single-stage emission process. Based on the relationship between the first parameter and the self-inductance of the drive coil, the current pulse width selection model of the thyristor is determined using the self-inductance of the drive coil, the capacitance in the system excitation source, and the freewheeling resistor; the first parameter is determined based on the capacitance and freewheeling resistor in the system excitation source.

[0095] Specifically, taking PFN excitation as an example, the selection of thyristor current pulse width requires consideration of Type I and Type II PFN excitation sources, as well as... and The working conditions are classified and discussed.

[0096] It should be noted that in engineering, the thyristor current pulse width is generally defined as the time required for the current to rise to 10% of the pulse peak value and then fall back to 10% of the pulse peak value. However, in practical applications, considering the need to set a certain safety margin, and considering that the transcendental function has no symbolic analytical solution and the equation becomes too high-degree after Taylor expansion, making it difficult to solve, for ease of solution, the thyristor current pulse width can be further defined as the time required for the current to rise to 10% of the pulse peak value and then fall back to 0.

[0097] Furthermore, in the embodiments of this application, when the system excitation source is a Type I PFN excitation source or a Type II PFN excitation source, based on the first parameter... With the self-inductance of the drive coil The magnitude relationships between them will be discussed separately, utilizing the self-inductance of the driving coil. Capacitors in the system excitation source C and freewheeling resistor Ultimately, the current pulse width selection model for thyristors can be determined.

[0098] More specifically, when the system excitation source is a type I PFN excitation source and the operating condition is... In the case of the parameters in Table 1 above, taking them as an example, the following conditions must be met: To simulate the current function Using the actual current in place of the calculation results in higher accuracy; this process can be represented as:

[0099] (17); Furthermore, considering that regardless of the emitter's position at the end of capacitor discharge, the corresponding system mutual inductance should guarantee the thyristor's safety, the thyristor current pulse width under this operating condition can be derived. The selection model is as follows: (18); Similarly, the number of turns in a single drive coil can be adjusted to 10 turns, the capacitance to 3mF, and the remaining parameters as shown in Table 1, to satisfy the first parameter. Through derivation, the thyristor current pulse width under this operating condition can be obtained. The selection model is as follows: (19); Furthermore, in the embodiments of this application, when the system excitation source is a type II PFN excitation source, according to the mathematical analysis basis of wound electromagnetic systems, when the operating condition is... The diode commutation stage ends at [time]. When the converter phase ends, the launcher has already traveled a certain distance. As an approximation, the process can be represented as: (20); in, This represents the current flowing through the thyristor. Similarly, the final thyristor current pulse width can be obtained. The selection model is as follows: (twenty one); Furthermore, when the operating condition is The diode commutation stage ends at [time]. , can be represented as: (twenty two); in, There is no solution; theoretically, the thyristor's turn-off time is infinite, meaning it will never turn off. Since transcendental functions have no symbolic analytical solutions, and the Taylor expansion results in equations of too high a degree, solving them is difficult. Therefore, with a type II PFN excitation source and operating condition... In such cases, it is recommended to use actual data verified by engineering simulation to select the thyristor current pulse width.

[0100] It should also be noted that when selecting thyristors for actual engineering projects, a certain safety margin factor still needs to be multiplied by the thyristor selection model formula.

[0101] Therefore, based on the selection models of the thyristor's forward repetitive peak voltage, pulse peak current, and critical rise rate of on-state current, as well as the selection model of the thyristor's current pulse width, the selection strategy of the thyristor can be determined, thereby realizing the selection and design of the thyristor in the excitation source.

[0102] Based on the above embodiments, as an optional embodiment, in step S4, the pulse power device includes a diode; a parameter selection analysis is performed on the repetitive peak voltage, pulse peak current, critical rate of rise of on-state current, and current pulse width of the excitation source to determine a fourth selection strategy for the pulse power device in the excitation source, including: Based on the self-inductance of the emitter armature coil, the self-inductance of the drive coil, the mutual inductance between the drive coil and the emitter armature coil, as well as the freewheeling resistance, capacitance value and initial voltage of the capacitor in the system excitation source, a selection model is determined for the reverse repetitive peak voltage, pulse peak current and critical rate of rise of the on-state current of the diode. Based on the self-inductance of the drive coil, the capacitance and freewheeling resistance in the system excitation source, a current pulse width selection model for the diode is determined. Based on the diode selection model of reverse repetitive peak voltage, pulse peak current and critical rise rate of on-state current, as well as the diode current pulse width selection model, the diode selection strategy is determined; the fourth selection strategy includes the diode selection strategy.

[0103] Specifically, in the embodiments of this application, during the single-stage emission process, based on the mathematical analysis of the wound electromagnetic emission system, the selection of the diode mainly depends on four indicators: reverse repetitive peak voltage. Pulse peak current Critical rate of rise of on-state current and current pulse width .

[0104] More specifically, when in Under normal operating conditions, whether driven by a type I or type II PFN, the diode receives the peak pulse current when the capacitor branch current crosses zero. The critical rate of rise of the on-state current is obtained at the initial moment of the diode commutation stage. Therefore, for reverse repetitive peak voltage Pulse peak current Critical rate of rise of on-state current The selection only needs to be divided into and We will discuss both scenarios, without needing to differentiate between the types of incentive sources.

[0105] Furthermore, when in Under the operating condition, based on the self-inductance of the transmitter armature coil Self-inductance of the drive coil Mutual inductance between the drive coil and the emitter armature coil and the freewheeling resistor in the system excitation source. capacitance value C and its capacitor initial voltage Determine the reverse repetitive peak voltage of the diode. Pulse peak current and the critical rate of rise of the on-state current The selection model can be represented as follows: (twenty three); in, This refers to the diode branch current during the diode commutation stage. The commutation stage time of the diode under type I PFN excitation; It is an algebraic variable and has no physical meaning.

[0106] Similarly, considering that regardless of the emitter's position at the end of capacitor discharge, the corresponding system mutual inductance should guarantee the diode's safety. Ultimately, the relevant reverse repetitive peak voltage can be derived. Pulse peak current Critical rate of rise of on-state current The selection model is as follows: (twenty four); Similarly, when in the position Under normal operating conditions, whether driven by a type I or type II PFN, the diode receives the peak pulse current when the capacitor branch current crosses zero. The critical rate of rise of the on-state current is obtained at the initial moment of the diode commutation stage. This process can be represented as: (25); in, These are algebraic variables with no physical meaning. Similarly, considering that regardless of the emitter's position at the end of capacitor discharge, its corresponding system mutual inductance should guarantee the diode's safety. Ultimately, the relevant reverse repetitive peak voltage can be derived. Pulse peak current Critical rate of rise of on-state current The selection model is as follows: (26); In the embodiments of this application, the number of turns of a single drive coil is adjusted to 10 turns, the capacitance is 3mF, and the other parameters are shown in Table 1, to satisfy the requirements. .

[0107] Furthermore, in the embodiments of this application, the selection of the diode current pulse width requires consideration of Type I PFN excitation and Type II PFN excitation, as well as... and The working conditions are classified and discussed.

[0108] When the system excitation source is a type I PFN excitation source, the operating condition is... In engineering practice, the diode current pulse width is generally defined as the time required for the current to rise to 10% of the pulse peak value and then fall back to 10% of the pulse peak value. However, since transcendental functions lack a signed analytical solution, and the Taylor expansion results in an equation of too high a degree, making it difficult to solve, this method is defined here as the time required for the diode current pulse width to rise from 0 to fall back to 10% of the pulse peak value, to allow for a certain safety margin.

[0109] Furthermore, in embodiments of this application, based on the self-inductance of the driving coil Capacitors in the system excitation source Cand freewheeling resistor This determines the diode current pulse width selection model. Specifically, taking the parameters in Table 1 as an example, it satisfies... Under operating conditions, during the diode freewheeling phase, the emitter has traveled a considerable distance. The solution process can be performed by referring to the mathematical analysis fundamentals of wound electromagnetic launch systems, and can be represented as follows:

[0110] (27); Furthermore, the diode current pulse width under this operating condition can be derived. The selection model is as follows: (28); Similarly, adjust the number of turns of a single drive coil to 10 turns, the capacitance to 3mF, and the other parameters as shown in Table 1 to meet the requirements. Under the same operating conditions, the diode current pulse width under those conditions can be derived similarly. The selection model is as follows: (29); Furthermore, in the embodiments of this application, when the system excitation source adopts a type II PFN excitation source, in Under operating conditions, it is necessary to analyze the circuit stages after the thyristor is turned off. This stage is defined as the capacitor reverse discharge stage, where the emitter has already traveled a considerable distance. The solution is performed, and its circuit structure diagram is as follows: Figure 13 As shown.

[0111] The loop equation for this stage can be expressed as: (30); Solving for the given information yields: (31); in, This indicates the current flowing through the freewheeling resistor. This represents the voltage across the capacitor.

[0112] During this stage, the thyristor is turned off, does not output energy, and does not generate electromagnetic thrust. Therefore, it can be deduced that: (32); The diode current pulse width under this operating condition can be solved. The selection model is as follows: (33); Furthermore, in the embodiments of this application, when the operating condition is... The diode commutation stage ends at [time]. It can be represented as: (34); in, There is no solution; theoretically, the thyristor's turn-off time is infinite, meaning it will never turn off. Since transcendental functions have no symbolic analytical solutions, and the Taylor expansion results in equations of too high a degree, solving them is difficult. Therefore, with a type II PFN excitation source and operating condition... In such cases, it is recommended to use actual data verified by engineering simulation to select the diode current pulse width.

[0113] Similarly, when selecting diodes for actual engineering projects, a certain safety margin factor still needs to be multiplied by the diode selection model formula.

[0114] Optionally, when selecting pulse power devices for practical engineering applications, it is not necessary to strictly follow the definitions of the four indicators mentioned above. Engineering conventions can still be used to select devices based on these four indicators. By deriving selection formulas for different engineering conventions from the mathematical analysis foundation of wound electromagnetic launch systems, pulse power device selection can be performed.

[0115] As can be seen from the mathematical analysis of wound electromagnetic launch systems, a higher freewheeling resistance helps reduce the critical rise rate of the pulse peak current and on-state current of pulsed power devices. When the pulsed power device is difficult to manufacture, the freewheeling resistance can be adjusted. This ensures that the selection of pulse power devices meets current manufacturing specifications. Increasing the freewheeling resistor accelerates energy consumption in the circuit, reduces the device's requirement for current pulse width, and lowers the cost of pulse power devices. However, it reduces the thrust width and degrades transmission performance. Therefore, the selection of the freewheeling resistor must be based on a trade-off between cost and transmission performance according to actual requirements.

[0116] Here, as Figure 14 As shown, when the external circuit of the multi-wound coil is reconnected to the gun and the excitation is a type I PFN, and the armature of the launcher is composed of five wound self-closing metal coils, a diode branch is shared. The following program method, which combines current wire and finite element inductance data, is used to iterate five sets of diode reverse repetitive peak voltages. Pulse peak current Critical rate of rise of on-state current Current pulse width In practical diode selection, the largest specification value should be chosen from five sets of iterative data to prevent breakdown or burnout failure due to insufficient voltage withstand capability, excessive on-state current, excessively rapid current rise rate, or excessive heating time. For thyristor selection, simply iterate through the above selection formula to obtain five sets of specifications. The selection can be performed directly; for pulse capacitor selection, simply iterate through the above selection formula (13) to obtain five sets of pulse capacitor values. and initial voltage Simply select the appropriate type. When using a Type I PFN excitation, the cost of pulse power devices can be significantly reduced because the diode branch is shared.

[0117] like Figure 15 When the external circuit is a type II PFN excitation, the selection of pulse power devices follows the single-stage emitter selection formula derived above, satisfying the requirements for 5 sets of repetitive peak voltages. Pulse peak current Critical rate of rise of on-state current Current pulse width and capacitor The requirements are met. When a Type II PFN circuit is excited, it cannot share a diode branch like a Type I PFN circuit, resulting in a higher cost.

[0118] Based on the above embodiments, as an optional embodiment, step S5 involves designing the wound electromagnetic launch system according to the first selection strategy, the second selection strategy, the third selection strategy, and the fourth selection strategy, including: Based on the first selection strategy, determine the geometric configuration parameters of the drive coil and the emitter armature coil; Based on the second selection strategy, determine the coil turns parameters of the drive coil and the transmitter armature; According to the third selection strategy, the capacitor parameters under the highest thrust peak are determined by using the preset launcher armature incident velocity and the capacitor energy of the system excitation source for parameter iterative calculation. Based on the fourth selection strategy, determine the selection parameters for the thyristor, diode, and freewheeling resistor of the system excitation source; The electromagnetic launch system is designed based on the selection parameters of thyristors, diodes, and freewheeling resistors, the capacitance parameters at the highest thrust peak, the geometric configuration parameters, and the number of coil turns. Specifically, in the embodiments of this application, firstly, based on the first selection strategy and engineering requirements, the design goals of the coil geometry are determined, and the parameters of the coil geometry are designed. Based on the engineering requirements, the design goals are determined, and corresponding index processing is performed on the electromagnetic coupling curve model. Heuristic algorithms such as four-dimensional particle swarm optimization can be used to design the three-dimensional geometric parameters of the driving coil and the wound metal coil.

[0119] In the embodiments of this application, the number of turns of the drive coil and the initial energy of the pulse capacitor in the excitation source are then selected based on the second selection strategy, as well as existing space size constraints, conductor current carrying density, inter-turn withstand voltage capability, etc. E .

[0120] Specifically, for the structure of a multi-stage reconnection electromagnetic launcher system, the launcher is accelerated to ultra-high speed through progressive acceleration. This is based on the required launcher mass. Acceleration distance Final velocity and initial velocity Derive the equivalent thrust It can be represented as: (35); Multi-wound coil electromagnetic launch systems, by filling interstage thrust gaps, exhibit high thrust continuity and minimal thrust fluctuation. The number of self-closing coils is [number missing]. The series of thrust pulses from a multi-stage reconnection gun is equivalent to a constant thrust. Both are equivalent in terms of energy input to the launcher. Observing the shape of the thrust pulses, equating it to an axisymmetric trigonometric function graph provides high accuracy and a relatively simple computational model. Under optimal electromagnetic coupling conditions, i.e., simulating thrust in spatial dimensions... Replacing thrust pulses for calculations offers higher accuracy. With closely spaced drive coils, the distance between the centers of adjacent stages in a multi-stage reconnected gun is equal to the outer diameter D of the drive coil, and the optimal electromagnetic coupling point is... .

[0121] (36); Regarding the selection method for the number of self-closing coils, when engineering problems such as high processing difficulty of the power supply occur, multiple winding coils can be used to form an armature, which increases the thrust amplitude, reduces the structural stress borne by a single winding coil, greatly reduces thrust pulsation, reduces emitter vibration, and thus allows for a smaller air gap and improved emitter efficiency. Compared with the method of increasing power supply energy, this method has higher engineering feasibility, is more suitable for ultra-high speed operation, and can significantly reduce the cost of external circuits. It is recommended to select as many self-closing winding coils as possible.

[0122] Given a fixed initial coil geometry and the number of self-closing coils, the design process for a multi-wound coil electromagnetic launch system is as follows: First, the initial energy of the pulse capacitor should be selected. Number of turns of the drive coil .

[0123] ; Based on the mathematical analysis of wound electromagnetic systems, the peak value of the driving coil current... for: (38); Regardless of the position of the emitter at the end of the capacitor discharge phase, the safety of the system should be ensured. The mutual inductance when the emitter is in the facing position should be used as an estimate, at which point the current peak is the largest.

[0124] (39); Based on the second selection strategy, the coil turns parameters of the drive coil and the emitter armature are determined. Here, the number of turns of the drive coil... The more turns, the better, as it helps improve transmission performance and reduce external circuit costs. When selecting the number of stator turns, engineering parameters such as the thickness of the insulating varnish and the final withstand voltage of the coil being greater than the initial voltage of all transmitter stages must still be considered.

[0125] Optionally, the current density limit of the electromagnetic launch system It can be designed to With sufficient margin, usually That is, the cross-sectional spatial dimensions It depends only on the actual engineering size limitations, so the coil configuration can be determined in the early stages of design.

[0126] Furthermore, once the number of turns and the geometry of the driving coil are determined, the inductance data can be determined. Here, the inductance data can be obtained from the finite element method and used for parameter iteration of the multi-wound electromagnetic launch system.

[0127] Furthermore, following the third selection strategy, based on the finite element inductance data, the initial energy of the pulse capacitor, the incident velocity, and the load mass, the inductance data is imported into the current wire program. The capacitance parameters and initial voltage of the multi-wound coil electromagnetic launch system can be iterated using formula (13) as the iterative formula. Taking the parameters in Table 1 as an example, it only takes 2 minutes to iterate the capacitance and initial voltage of the highest thrust peak of level 127, so that the launcher can be accelerated from 72m / s to 680m / s.

[0128] Here, if a solid metal plate is used to form the transmitter armature, only parameter scanning design based on the finite element method can be employed. Because the coordination of interstage capacitors needs to be considered, the dimension of the scanning parameter table is greatly increased. It would require a high-performance computer and at least several years to derive the optimal capacitors for hundreds of stages, making it practically impossible in engineering. If fixed capacitors and initial voltages are used, the peak thrust decays rapidly, resulting in large reaction forces and significant thrust fluctuations, making it unsuitable for engineering applications. Compared to the finite element parameter scanning design method, this method offers extremely high engineering efficiency and accuracy, greatly improving the design efficiency of multi-wound coil electromagnetic launch systems, such as... Figure 16 As shown in (a), a 10kg load can be accelerated from 72m / s to 680m / s with only a 4m acceleration distance. Figure 16As shown in (b), under the same acceleration conditions, a traditional multi-stage wound electromagnetic launch system requires a track length of 20.38m. When the launcher armature is composed of 5 wound metal self-closing coils, the acceleration distance is only 1 / 5 of that of the traditional multi-stage electromagnetic launch system, and the track length is shortened by 80%. Under the same power supply energy, using N self-closing wound coils increases the equivalent thrust by N times, and shortens the length to 1 / N.

[0129] Depend on Figure 5 As shown in (a), after selecting the optimal thrust peak capacitance at level 127, finite element simulations show that the thrust peak value is almost aligned with the thrust peak line, and there is no attenuation of the thrust peak value with increasing velocity. Furthermore, the thrust fluctuation is significantly reduced to 10%. Figure 5 As shown in (b) above. According to After selecting the capacitor with the highest thrust peak, the thrust peak depends only on the coil geometry and the initial capacitor energy. The alignment of the thrust peak with the side of the thrust line confirms the high accuracy of the analytical formula.

[0130] Furthermore, in the embodiments of this application, according to the fourth selection strategy, an iterative selection method combining finite element inductance data and the current wire procedure can rapidly iterate the four indicators of each stage of the pulse power device, thereby enabling rapid engineering cost estimation and pulse power device selection, greatly improving design efficiency. For Type II PFN excitation, For current pulse width selection under operating conditions, it is recommended to use actual engineering simulation verification data for device selection.

[0131] For a designed multi-wound coil electromagnetic launch system, electromagnetic-thermal coupling simulation is performed using the selection parameters of the thyristors, diodes, and freewheeling resistors in the excitation source, the capacitance parameters at the highest thrust peak, the geometric configuration parameters, and the coil turns parameters. Under natural convection cooling and a room temperature of 25°C, because the launcher armature is composed of multiple wound coils connected together, compared to traditional multi-stage wound electromagnetic launch systems, the multiple wound coils distribute the 127 thrust pulses, thus distributing the 127 thermal pulses, which can significantly reduce the temperature rise of the wound coils. Accelerating from 72 m / s to 680 m / s with a 10 kg load, the maximum temperature rise of a single wound metal coil is 15°C. Figure 17 As shown in (a) above, under the same acceleration conditions, the temperature rise is approximately 1 / 4 that of a traditional multi-stage wound electromagnetic launch system at 58°C. This significantly reduces the temperature rise of the launcher's armature coil, easily meets the heat resistance requirements of insulating materials, and is more suitable for ultra-high-speed operation. Figure 17 As shown in (b) above, this is a schematic diagram of the temperature distribution of a single wound metal coil. The drive coil only experiences five thermal pulses, and the temperature rise is negligible.

[0132] In the multi-wound coil electromagnetic launch system of this application embodiment, the temperature rise of a single wound coil is significantly reduced, and the thermal stress of a single wound coil is significantly reduced to 122.98 MPa, meeting the structural strength requirements of the insulating material. Compared with traditional multi-stage wound electromagnetic launch systems, it is more suitable for ultra-high-speed operation. Here, the maximum thermal stress distribution of a single wound coil is as follows: Figure 18 As shown.

[0133] Figure 19 (a) is a stress distribution diagram of the drive coil structure provided in the embodiment of this application, (b) is a stress distribution diagram of the armature coil structure of the self-closing transmitter, and (c) is a gas pressure distribution diagram of the transmitter at an ultra-high speed of 680 m / s. Among them, the maximum electromagnetic stress of the drive coil is 15.417 MPa, the maximum electromagnetic stress of the transmitter armature coil is 9.1755 MPa, and the maximum absolute total gas pressure of the transmitter at 680 m / s is 1.54 MPa, which meets the structural strength requirements of the insulating material. This verifies the feasibility and superiority of the multi-wound coil electromagnetic transmission system provided in the embodiment of this application.

[0134] The method of this application embodiment clarifies the design principles of a multi-wound coil electromagnetic launch system. It adopts an iterative design of a multi-stage wound electromagnetic launch system that combines finite element inductance data with current wire programming. Compared with traditional parameter scanning design methods such as finite element engineering simulation, it greatly saves computing resources and design time, and significantly improves design efficiency and design accuracy.

[0135] It is understood that the various numerical designations used in the embodiments of this application are merely for the convenience of description and are not intended to limit the scope of the embodiments of this application.

[0136] It should be understood that expressions such as “comprising” and “may include” used in this application indicate the existence of the disclosed functions, operations, or constituent elements, and do not limit one or more additional functions, operations, and constituent elements. In this application, terms such as “comprising” and / or “having” are to be interpreted as indicating a particular characteristic, number, operation, constituent element, component, or combination thereof, but not to exclude the existence or possibility of adding one or more other characteristics, numbers, operations, constituent elements, components, or combinations thereof.

[0137] In the description of the embodiments of this application, it should be noted that, unless otherwise explicitly specified and limited, the term "connection" should be interpreted broadly. For example, "connection" can be a detachable connection or a non-detachable connection; it can be a direct connection or an indirect connection through an intermediate medium. "Fixed connection" refers to a connection where the relative positional relationship remains unchanged after connection. "Rotary connection" refers to a connection where the components can rotate relative to each other after connection. "Sliding connection" refers to a connection where the components can slide relative to each other after connection. The directional terms mentioned in the embodiments of this application, such as "top," "bottom," "inner," "outer," "left," and "right," are only for reference to the directions in the accompanying drawings. Therefore, the directional terms used are for better and clearer explanation and understanding of the embodiments of this application, and are not intended to indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the embodiments of this application.

[0138] Furthermore, the mathematical concepts mentioned in the embodiments of this application, such as symmetry, equality, parallelism, and perpendicularity, are limitations specific to the current technological level, rather than absolute and strict mathematical definitions. Slight deviations are permissible; approximations of symmetry, equality, parallelism, and perpendicularity are all acceptable. For example, "A and B are parallel" means that A and B are parallel or approximately parallel, and the angle between A and B can be between 0 and 10 degrees. "A and B are perpendicular" means that A and B are perpendicular or approximately perpendicular, and the angle between A and B can be between 80 and 100 degrees.

[0139] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A multi-wound coil reconnection gun structure, characterized by, include: Excitation source, multiple sets of drive coils, and transmitter armature for transmitting load; The transmitter armature is disposed within the transmission track composed of the multiple sets of drive coils; Each set of driving coils is connected to the excitation source to generate electromagnetic force under the excitation of the excitation source, so as to drive the transmitter armature to drive the load to emit; the transmitter armature includes a connecting mold and multiple self-closing multilayer metal coil disks, wherein each of the self-closing multilayer metal coil disks is arranged collinearly at equal distances and is fixed together by the connecting mold.

2. The multiwound coil reconnection gun structure of claim 1, wherein, The multiple sets of drive coils are arranged collinearly at equal distances along the horizontal direction, and each set of drive coils includes two hollow coil disks connected in series or in parallel and arranged coaxially to form a launch track; each of the self-closing multilayer metal coil disks is arranged in parallel within the launch track.

3. The multiwound coil reconnection gun structure of claim 1, wherein, The arrangement distance between the axes of two adjacent self-closing multilayer metal coil disks is determined based on the number of the self-closing multilayer metal coil disks and the arrangement distance between the axes of the two adjacent drive coils.

4. A method of designing an electromagnetic launch system for use with a multi- wrap coil re-coil gun structure as claimed in any one of claims 1 to 3, wherein, include: The system launch efficiency was analyzed using the thrust model of the wound electromagnetic launch system, and the first selection strategy for the geometric configuration of the drive coil and the launcher armature coil was determined. The system thrust, capacitor discharge in the excitation source, and changes in pulse power device current are analyzed to determine a second selection strategy for the number of turns of the drive coil and the number of turns of the transmitter armature coil. Based on the thrust model, the electromagnetic performance of the electromagnetic thrust generated between adjacent self-closing multilayer metal coil disks is analyzed to determine the third selection strategy for the capacitor in the excitation source of the electromagnetic launch system. A parameter selection analysis is performed on the repetitive peak voltage, pulse peak current, critical rate of rise of on-state current, and current pulse width of the excitation source to determine the fourth selection strategy for pulse power devices in the excitation source. The electromagnetic launch system is designed according to the first selection strategy, the second selection strategy, the third selection strategy, and the fourth selection strategy.

5. The electromagnetic launch system design method of claim 4, wherein, The electromagnetic performance analysis of the electromagnetic thrust generated between adjacent self-closing multilayer metal coil disks based on the thrust model, and the determination of the third selection strategy for the capacitor in the excitation source of the electromagnetic launch system, include: Based on the thrust model, determine the target thrust model for the electromagnetic thrust generated between adjacent self-closing multilayer metal coil disks. The target thrust model is integrated according to the impulse theorem to obtain the launcher armature velocity model. With the goal of achieving optimal electromagnetic coupling conditions for the armature coil of the transmitter, the capacitor selection model under the maximum thrust peak is determined by extrapolation and analysis based on the aforementioned armature velocity model of the transmitter. The third selection strategy is determined based on the capacitor selection model.

6. The electromagnetic launch system design method of claim 5, wherein, The process aims to achieve optimal electromagnetic coupling conditions for the launcher armature coil. Based on the launcher armature velocity model, a derivation and analysis are performed to determine the capacitor selection model under the highest thrust peak, including: The time model of the capacitor discharge stage in the excitation source when the armature coil of the transmitter reaches the optimal electromagnetic coupling condition is determined. The transmitter armature velocity model is integrated based on the capacitor discharge stage time model to obtain the transmitter armature displacement model. Based on the capacitor discharge stage time model and the transmitter armature displacement model, the capacitor selection model under the highest thrust peak is determined.

7. The electromagnetic launch system design method of claim 4, wherein, The first selection strategy for determining the geometric configuration of the drive coil and the armature coil of the launcher by analyzing the system launch efficiency using the thrust model of the wound electromagnetic launch system includes: Based on the thrust model, the electromagnetic coupling curve model of the system is determined; Determine the system inductance model, and based on the system electromagnetic coupling curve model and the system inductance model, determine the system emission efficiency-size ratio model; The system's emission efficiency-size ratio model is used to perform model output maximization analysis to determine the first selection strategy for the geometric configuration of the drive coil and the transmitter armature coil.

8. The electromagnetic launch system design method of claim 4, wherein, The analysis of system thrust, capacitor discharge in the excitation source, and changes in pulsed power device current to determine the second selection strategy for the number of turns in the drive coil and the number of turns in the transmitter armature coil includes: Determine the system inductance model; Determine the peak thrust model of the transmitter armature under optimal electromagnetic coupling conditions, the time model of the capacitor discharge stage in the excitation source, and the peak pulse current model of the thyristor; Using the system inductance model, the peak thrust model of the transmitter armature, the time model of the capacitor discharge stage, and the peak current model of the thyristor pulse, the changes in system thrust, capacitor discharge in the system excitation source, and pulse power device current are analyzed. Based on the analysis results, a second selection strategy was determined for the number of turns in the drive coil and the number of turns in the emitter armature coil.

9. The electromagnetic launch system design method of claim 4, wherein, The pulsed power device includes a thyristor; the parameter selection analysis of the repetitive peak voltage, pulse peak current, critical rate of rise of on-state current, and current pulse width of the excitation source to determine the fourth selection strategy for the pulsed power device in the excitation source includes: Based on the capacitance value and initial voltage of the excitation source, the self-inductance of the emitter armature coil, the self-inductance of the drive coil, and the mutual inductance between the drive coil and the emitter armature coil, a selection model for the forward repetitive peak voltage, pulse peak current, and critical rate of rise of the on-state current of the thyristor is determined. Based on the self-inductance of the drive coil, the capacitance and freewheeling resistor in the system excitation source, the current pulse width selection model of the thyristor is determined. Based on the selection model of the thyristor's forward repetitive peak voltage, pulse peak current, and critical rise rate of on-state current, as well as the selection model of the thyristor's current pulse width, the selection strategy of the thyristor is determined; the fourth selection strategy includes the selection strategy of the thyristor.

10. The electromagnetic launch system design method of claim 4, wherein, The pulsed power device includes a diode; the fourth selection strategy for determining the pulsed power device in the excitation source by performing parameter selection analysis on the repetitive peak voltage, pulse peak current, critical rate of rise of on-state current, and current pulse width of the excitation source includes: Based on the self-inductance of the emitter armature coil, the self-inductance of the drive coil, the mutual inductance between the drive coil and the emitter armature coil, and the freewheeling resistor, capacitance value and initial voltage of the capacitor in the excitation source of the system, a selection model is determined for the reverse repetitive peak voltage, pulse peak current and critical rate of rise of the on-state current of the diode. Based on the self-inductance of the driving coil, the capacitance and freewheeling resistor in the system excitation source, the current pulse width selection model of the diode is determined; Based on the selection model of the diode's reverse repetitive peak voltage, pulse peak current, and critical rise rate of on-state current, as well as the diode's current pulse width selection model, the selection strategy for the diode is determined; the fourth selection strategy includes the selection strategy for the diode.

11. The electromagnetic launch system design method according to any one of claims 4-10, characterized in that, The design of the multi-wound coil electromagnetic launch system based on the first selection strategy, the second selection strategy, the third selection strategy, and the fourth selection strategy includes: Based on the first selection strategy, determine the geometric configuration parameters of the drive coil and the transmitter armature coil; Based on the second selection strategy, determine the coil turns parameters of the drive coil and the transmitter armature; According to the third selection strategy, the capacitor parameters under the highest thrust peak are determined by using the preset launcher armature incident velocity and the capacitor energy of the system excitation source for parameter iterative calculation. Based on the fourth selection strategy, the selection parameters of the thyristors and diodes for the system excitation source are determined; The electromagnetic launch system is designed based on the selection parameters of the thyristor and the diode, the capacitance parameters at the highest thrust peak, the geometric configuration parameters, and the coil turns parameters.

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