A method of designing a solenoidal electromagnetic launch system

Abstract

This application belongs to the field of ultra-high-speed electromagnetic launch design analysis, specifically disclosing a design method for a wound-type electromagnetic launch system. The method includes: analyzing the electromagnetic performance of the wound-type electromagnetic launch system based on its thrust model to determine a first selection strategy for the capacitor in the system's excitation source; analyzing the system thrust, capacitor discharge in the system's excitation source, and changes in the 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 launcher's armature coil; performing parameter selection analysis on the repetitive peak voltage, pulse peak current, critical rate of rise of the on-state current, and current pulse width of the system's excitation source to determine a third selection strategy for the pulse power device in the system's excitation source; and designing the wound-type electromagnetic launch system based on the first, second, and third selection strategies. This application enables the efficient and high-precision rapid design of wound-type electromagnetic launch systems.

Description

Technical Field

[0001] This application belongs to the field of ultra-high-speed electromagnetic launch design analysis, specifically involving the field of mechanism model technology, and more specifically, involving a design method for a wound electromagnetic launch system. 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. Electromagnetic launch technology directly converts electromagnetic energy into the kinetic energy of the launch vehicle, offering high efficiency, low noise, high controllability, and is not limited by the speed of sound, making it a promising field for ultra-high-speed launches.

[0003] Traditional electromagnetic launch systems use a solid metal plate for the launcher armature. Due to the significant skin effect of eddy currents within the armature and their uneven distribution, current analytical methods for electromagnetic fields are extremely difficult to apply, making it impossible to determine the mathematical essence of traditional electromagnetic launch systems and thus lacking clear design principles. Existing wound electromagnetic launch systems, however, use a wound, self-closing metal coil for the launcher armature. This allows for a more uniform distribution of eddy currents within the armature coil, significantly reducing analytical difficulty and making theoretical design of the electromagnetic launch system possible. Although existing wound electromagnetic launch systems have a mathematical foundation, research on design methods for wound electromagnetic launch systems is currently scarce, hindering the effective design of such systems.

[0004] Therefore, how to effectively design a wound electromagnetic launch system has become a pressing technical problem to be solved in the field of ultra-high-speed electromagnetic launch. Summary of the Invention

[0005] In view of the shortcomings of the prior art, the purpose of this application is to effectively realize the design of a wound electromagnetic launch system.

[0006] To achieve the above objectives, in a first aspect, this application provides a design method for a wound electromagnetic launching system, comprising: Electromagnetic performance analysis is performed based on the thrust model of the wound electromagnetic launch system to determine the first selection strategy for the capacitor in the system's excitation source. The system thrust, capacitor discharge in the system 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. 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 of the system to determine the third selection strategy for pulse power devices in the excitation source of the system. The winding electromagnetic launch system is designed based on the first selection strategy, the second selection strategy, and the third selection strategy.

[0007] Optionally, the step of performing electromagnetic performance analysis based on the thrust model of the wound electromagnetic launch system to determine the first selection strategy for the capacitor in the system's excitation source includes: The 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 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 first selection strategy is determined based on the capacitor selection model.

[0008] Optionally, the step of determining the capacitor selection model under the highest thrust peak by performing a deduction and analysis based on the transmitter armature velocity model, with the goal of achieving optimal electromagnetic coupling conditions for the transmitter armature coil, includes: Determine the time model of the capacitor discharge stage in the system 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 transmitter armature displacement model, the capacitor selection model under the highest thrust peak is determined.

[0009] Optionally, the second selection strategy for analyzing the system thrust, the capacitor discharge in the system excitation source, and the changes in the pulsed power device current to determine the number of turns in the drive coil and the armature coil of the emitter includes: Determine the system inductance model; Determine the peak thrust model of the transmitter armature coil under optimal electromagnetic coupling conditions, the time model of the capacitor discharge stage in the excitation source of the system, and the peak pulse current model of the thyristor; Using the system inductance model, the peak thrust model of the transmitter armature coil, 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.

[0010] Optionally, 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 system excitation source to determine the third selection strategy for the pulsed power device in the system excitation source includes: Based on the capacitance value and initial voltage of the excitation source in the system, the self-inductance of the emitter armature coil, the self-inductance of the drive coil, and the mutual inductance between the emitter armature coil and the drive 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 third selection strategy includes the selection strategy of the thyristor.

[0011] Optionally, the step of determining the current pulse width selection model for the thyristor based on the self-inductance of the drive coil, the capacitance in the system excitation source, and the freewheeling resistor includes: When the system excitation source is a type I PFN excitation source or a type II PFN excitation source, 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 and freewheeling resistor in the system excitation source; the first parameter is determined based on the capacitance and freewheeling resistor in the system excitation source.

[0012] Optionally, the pulsed power device includes a diode; 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 system excitation source to determine the third selection strategy for the pulsed power device in the system 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 third selection strategy includes the diode's selection strategy.

[0013] Optionally, the design of the wound electromagnetic launch system based on the first selection strategy, the second selection strategy, and the third selection strategy includes: Based on the second selection strategy, determine the coil turns parameters of the drive coil and the transmitter armature; Based on the first 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 third selection strategy, the selection parameters of the thyristors and diodes for the system excitation source are determined; The design of the wound electromagnetic launch system is based on the selection parameters of the thyristor and the diode, the capacitance parameters at the highest thrust peak, and the coil turns parameters.

[0014] Optionally, the wound electromagnetic launch system includes an excitation source, a launcher armature for launching the load, and multiple sets of drive coils; each set of drive coils is connected to the excitation source and is used to generate electromagnetic force under the excitation of the excitation source to drive the launcher armature to launch the load; the launcher armature is a self-closing multilayer metal coil disk.

[0015] Optionally, each group of drive coils includes two hollow metal coil disks connected in series or in parallel, arranged coaxially; the multilayer metal coil disks are arranged in parallel between the two hollow metal coil disks.

[0016] Overall, the technical solutions conceived in this application have the following beneficial effects compared with the prior art: This application provides a design method for a wound-type electromagnetic launch system. Based on the mathematical analysis of the wound-type electromagnetic launch system, it further explores the influence of the capacitor in the system excitation source on the system thrust, the influence of the number of turns of the system drive coil and the number of turns of the launcher armature coil on the system thrust, the capacitor discharge in the system excitation source and the current of the pulse power device, 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, 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 the wound-type electromagnetic launch system with high efficiency and high precision, and is suitable for the design application scenarios of induction electromagnetic guns such as wound-type launcher armature coil guns and wound-type launcher armature reconnection guns. Attached Figure Description

[0017] Figure 1 This is a flowchart illustrating the design method of the wound electromagnetic launch system provided in the embodiments of this application; Figure 2 This is a schematic diagram of the structure of the coiled reconnector provided in the embodiment of this application; Figure 3This is a schematic diagram of the structure of the wound electromagnetic launching system provided in the embodiments of this application; Figure 4 This is a schematic diagram showing the accuracy verification results of the capacitor selection model under the highest thrust peak provided in the embodiments of this application; Figure 5 (a) is a schematic diagram of the effect of the number of turns of the drive coil on the system thrust provided in the embodiment of this application; (b) is a schematic diagram of the effect of the number of turns of the drive coil on the speed of the transmitter armature provided in the embodiment of this application; and (c) is a schematic diagram of the effect of the number of turns of the drive coil on the drive coil current provided in the embodiment of this application. Figure 6 (a) is a schematic diagram comparing the simulation and analytical results of the thyristor pulse peak current when the emitter armature incident velocities are 72 m / s, 300 m / s, and 680 m / s, respectively, according to the embodiments of this application; (b) is a schematic diagram comparing the simulation and analytical results of the critical rate of rise of the thyristor on-state current when the emitter armature incident velocities are 72 m / s, 300 m / s, and 680 m / s, respectively, according to the embodiments of this application. Figure 7 (a) is a schematic diagram showing the simulation and analytical comparison of the thyristor current pulse width under a certain operating condition provided by the embodiment of this application for type I PFN excitation; Figure 7 (b) is a schematic diagram showing the simulation and analytical comparison of the thyristor current pulse width under another operating condition of the type I PFN excitation provided in the embodiments of this application; Figure 8 This is a schematic diagram showing the simulation and analytical comparison results of the thyristor current pulse width under a certain operating condition provided by the implementation of the Type II PFN provided in this application; Figure 9 This is a schematic diagram of the simulation results of the thyristor current waveform under one operating condition provided by the implementation of the Type II PFN provided in this application; Figure 10 (a) is a schematic diagram comparing the simulation and analysis results of the diode pulse peak current under operating conditions provided by an embodiment of this application, and (b) is a schematic diagram comparing the simulation and analysis results of the critical rise rate of the on-state current under operating conditions provided by an embodiment of this application. Figure 11 (a) is a schematic diagram comparing the simulation and analysis results of the diode pulse peak current under another operating condition provided by the embodiment of this application, and (b) is a schematic diagram comparing the simulation and analysis results of the critical rise rate of the on-state current under another operating condition provided by the embodiment of this application. Figure 12(a) is a schematic diagram comparing the simulation and analysis results of the diode current pulse width under one operating condition of the Type I PFN excitation provided in the embodiment of this application, and (b) is a schematic diagram comparing the simulation and analysis results of the diode current pulse width under another operating condition of the Type I PFN excitation provided in the embodiment of this application. Figure 13 This is a schematic diagram of the circuit structure of the system excitation source capacitor in the reverse voltage discharge stage provided in the embodiment of this application; Figure 14 This is a schematic diagram showing the simulation and analytical comparison results of diode current pulse width under a certain operating condition provided by the embodiments of this application for type II PFN excitation; Figure 15 This is a schematic diagram of the simulation results of the diode current waveform under one operating condition provided by the embodiment of this application for type II PFN excitation; Figure 16 (a) is a schematic diagram of the effect of the freewheeling resistor value provided in the embodiment of this application on the current of the system excitation source pulse power device; (b) is a schematic diagram of the effect of the freewheeling resistor value provided in the embodiment of this application on the electromagnetic thrust of the system transmitter armature. Figure 17 This is a schematic diagram illustrating the accuracy verification results of the system transmission efficiency provided in this application embodiment; Figure 18 This is a schematic diagram showing the comparison results of the acceleration effect of the transmitter armature of the system under different outer diameters of the drive coil provided in the embodiments of this application; Figure 19 (a) is a schematic diagram showing the distribution of the peak thrust capacitor selection parameters of the multi-stage electromagnetic launch system provided in the embodiments of this application, and (b) is a comparative schematic diagram showing the simulation of the multi-stage electromagnetic launch system provided in the embodiments of this application by the program method and the finite element method respectively. Figure 20 (a) is a schematic diagram of the data change of the thrust of the system at each stage when the transmitter armature accelerates from a speed of 72 m / s to 210 m / s according to the embodiment of this application; (b) is a schematic diagram of the data change of the thrust of the system at each stage when the transmitter armature accelerates from a speed of 644 m / s to 680 m / s according to the embodiment of this application. Figure 21 (a) is a schematic diagram of the loss distribution of the wound-type transmitter armature under single-stage launch conditions provided in the embodiments of this application; (b) is a schematic diagram of the loss distribution of the solid metal plate transmitter armature under single-stage launch conditions provided in the embodiments of this application; (c) is a schematic diagram of the temperature distribution of the wound-type transmitter armature under single-stage launch conditions provided in the embodiments of this application; and (d) is a schematic diagram of the temperature distribution of the solid metal plate transmitter armature under single-stage launch conditions provided in the embodiments of this application. Figure 22This is a schematic diagram showing the highest temperature result of the transmitter armature in the wound multi-stage electromagnetic launch system provided in this application embodiment when it is accelerated from 72m / s to 680m / s; Figure 23 (a) is a schematic diagram of the highest structural stress distribution of the drive coil in the wound multi-stage electromagnetic launch system provided in the embodiment of this application; (b) is a schematic diagram of the highest structural stress distribution of the transmitter armature coil in the wound multi-stage electromagnetic launch system provided in the embodiment of this application; (c) is a schematic diagram of the absolute total gas pressure distribution of the transmitter armature in the wound multi-stage electromagnetic launch system provided in the embodiment of this application at ultra-high speed. Figure 24 This is a schematic diagram illustrating the accuracy verification results of the displacement estimation method considering acceleration effects provided in the embodiments of this application. Detailed Implementation

[0018] 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.

[0019] 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.

[0020] 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.

[0021] 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.

[0022] The embodiments of this application are described below with reference to the accompanying drawings.

[0023] Figure 1 This is a flowchart illustrating the design method of the wound electromagnetic launch system provided in the embodiments of this application, as shown below. Figure 1 As shown, it includes: Step S1: Perform electromagnetic performance analysis based on the thrust model of the wound electromagnetic launch system to determine the first selection strategy for the capacitor in the system excitation source. Step S2: Analyze the changes in system thrust, capacitor discharge in the system 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: 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 system excitation source to determine the third selection strategy for pulse power devices in the system excitation source. Step S4: Design the wound electromagnetic launch system according to the first selection strategy, the second selection strategy and the third selection strategy.

[0024] Specifically, the first selection strategy described in the embodiments of this application refers to a strategy for determining the selection parameters of the capacitor in the system excitation source.

[0025] The second selection strategy described in the embodiments of this application refers to a strategy for determining the selection parameters for the number of turns of the system drive coil and the transmitter armature coil.

[0026] The third selection strategy described in the embodiments of this application refers to a strategy for determining the selection parameters of pulse power devices in the system excitation source.

[0027] Here, the coiled electromagnetic launch system can specifically include induction-type electromagnetic gun systems such as coiled launcher armature coil guns and coiled launcher armature reconnection guns.

[0028] Through the inventor's research, the wound electromagnetic launch system has a clear mathematical analysis basis. Based on the mathematical analysis basis, the parameter selection model of the external circuit excitation source device and the body structure of the electromagnetic system can be derived, which greatly improves the design efficiency of the electromagnetic system.

[0029] The structural diagram of the coiled reconnector is shown below. Figure 2 As shown, Figure 2 (a) in the diagram represents a traditional electromagnetic launch system, and (b) represents a wound electromagnetic launch system. Both electromagnetic launch systems include a drive coil and a launcher armature for the launch load. In the wound electromagnetic launch system, the launcher armature is replaced by a wound self-closing metal coil structure instead of a traditional solid metal plate.

[0030] like Figure 3 As shown, the wound electromagnetic launch system specifically includes an excitation source 1, a launcher armature 2, and multiple sets of drive coils 3. Each set of drive coils 3 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 launcher armature 2 to launch the load. The launcher armature 2 is a self-closing multi-layer metal coil disk. In this way, the launcher armature and the launcher armature plus an external load, or a single launcher armature used as an electromagnetic projectile, form the entire launch system. Specifically, in the embodiments of this application, a wound electromagnetic launch system is constructed by employing an excitation source, a drive coil structure, and a transmitter armature, wherein the transmitter armature is a self-closing multilayer metal coil disk. Here, each set of drive coil structures is connected to the excitation source, which provides high-power pulse energy to excite the drive coil structure and the transmitter armature to undergo electromagnetic coupling, thereby generating electromagnetic force to drive the transmitter armature to launch.

[0031] Among them, the self-closing multilayer metal coil disc refers to a disc-shaped structure formed by multiple closely spaced coils made by spirally winding a single metal wire, with the ends of the metal wire connected to form a closed loop.

[0032] Each set of drive coils can be made of hollow metal coil disks arranged on the top and bottom, and each hollow metal coil disk is formed by multiple layers of tightly attached hollow metal multi-turn coils.

[0033] 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.

[0034] The method of this application embodiment, by deeply considering the relationship between the transmitter armature structure and the eddy current skin effect it generates, cleverly designs the transmitter armature as a self-closing multilayer metal coil disk structure, which can greatly enhance the current carrying capacity of the transmitter armature, increase the peak electromagnetic thrust generated by the system and the emission velocity of the transmitter armature, and improve the overall performance of the electromagnetic launch system.

[0035] Optionally, in the embodiments of this application, each group of drive coils includes two hollow metal coil disks connected in series or in parallel and arranged coaxially; the multilayer metal coil disks are arranged in parallel between the two hollow metal coil disks.

[0036] Specifically, in the embodiments of this application, each set of drive coil structures may include two hollow metal coil disks connected in series or parallel, arranged coaxially. A self-closing multilayer metal coil disk is arranged parallel to the two hollow metal coil disks. In this way, the coaxial arrangement of the drive coil structures ensures that the axial repulsive forces on the launcher armature coil cancel each other out, resulting in a balanced force on the launcher armature coil along its axis. This allows the launcher armature to move more stably on the central launch track of the drive coil structure, improving the firing performance of the re-launching gun.

[0037] The two hollow metal coil disks can have rectangular, square, or circular shapes, and this application does not impose any specific limitations on their external structure. Similarly, the armature coil of the transmitter can also have rectangular, square, or circular shapes, and this application does not impose any specific limitations on its external structure.

[0038] 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.

[0039] Furthermore, the two hollow metal coil disks arranged coaxially can be connected in series or in parallel according to actual design requirements, which can meet more reconnection gun application requirements. In the embodiments of this application, the design principles are derived based on the mathematical analysis of the series winding electromagnetic launch system. The derivation method of the design principle of the parallel winding electromagnetic launch system can also refer to the derivation method of this invention.

[0040] In the embodiments of this application, in step S1, electromagnetic performance analysis is performed 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 thrust model can be expressed as: (1); in, For the mutual inductance between the drive coil and the emitter armature coil, This is the mutual inductance gradient between the drive coil and the emitter armature coil.

[0041] When the armature coil of the launcher reaches the optimal electromagnetic coupling condition, the thrust reaches its peak value. It can be represented as: (2); In order to more accurately derive the peak capacitance of the maximum thrust, the optimal electromagnetic coupling point can be defined as the electromagnetic system. At the maximum position, where, 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. This refers to the system uptime.

[0042] 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 launcher armature coil achieves the highest thrust peak, and at this point, the launcher armature coil reaches the optimal electromagnetic coupling condition. Based on the above embodiment, as an optional embodiment, step S1 involves performing electromagnetic performance analysis based on the thrust model of the wound electromagnetic launch system to determine the first selection strategy for the capacitor in the system's excitation source, including: The 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 first selection strategy is determined based on the capacitor selection model.

[0043] Specifically, considering the acceleration effect, it is necessary to perform time integration on the thrust model formula. According to the above model formula (1), it can be seen that the thrust model has three variables. and The integration is difficult, and the thrust function is mainly composed of a sine function to simulate the thrust function. Instead of integrating the actual thrust, it has higher accuracy, namely: (3); In the embodiments of this application, the simulated thrust function corresponding to the above thrust model can be integrated according to the impulse theorem. This process can be expressed as: (4); in, This represents the rate of change during the capacitor discharge phase. Let the initial incident velocity be... For the armature velocity of the transmitter, This represents the total mass of the launcher.

[0044] Further derivation of equation (4) above yields the following model for the armature velocity of the transmitter: (5); Furthermore, in the embodiments of this application, 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, and a capacitor selection model under the highest thrust peak can be derived.

[0045] 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 system 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.

[0046] Specifically, in the embodiments of this application, based on the mathematical analysis of the wound electromagnetic launch system, and based on the mutual inductance corresponding to the optimal electromagnetic coupling point of the system, the self-inductance of the armature coil of the launcher, and the self-inductance of the drive coil, the time model of the capacitor discharge stage of the pulse capacitor in the system excitation source can be determined, which can be expressed as: (6); In the formula, This refers to the capacitor discharge phase time of the pulse capacitor.

[0047] Furthermore, by integrating the above-mentioned carrier armature velocity model formula once to obtain the corresponding displacement expression, the carrier armature displacement model can be obtained, so that at the end of the capacitor discharge stage, the carrier armature coil is at the position of the electromagnetic optimal coupling point, and the highest thrust peak is obtained.

[0048] Considering the engineering constraints of pulse capacitor materials, processes, usage conditions, size, space, and cost, and given that the energy of the pulse capacitor is constant, the pulse capacitor in the excitation source can be made as either a large capacitor with a small voltage or a small capacitor with a large voltage. Taking into account the capacitor energy constraint, a capacitor selection model can be derived, which can be expressed as: (7); in, Let be the distance between the optimal electromagnetic coupling point and the axis of the driving coil. By further deriving the above equation (7), the capacitor selection model under the highest thrust peak can be determined, which can be expressed as: (8); In the formula, = , = , = , = , = , = , = .

[0049] Here, this model does not recommend simplifying for significant digits or decimal places. If simplification is performed, it is easy to fail to converge at high speeds due to the limited number of significant digits to retain, thus leading to incorrect solutions.

[0050] Optionally, a uniform acceleration motion calculation method can be used to estimate the displacement of the armature capacitor during the discharge stage of the launcher, determine the capacitor selection model and the corresponding initial capacitor voltage model under the highest thrust peak, and thus select the capacitor with the highest thrust peak and the corresponding initial capacitor voltage. This process can be expressed as:

[0051] (9); 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 relevant preset operating parameters can be substituted into the above capacitor selection model to calculate the corresponding optimal capacitor.

[0052] In one specific embodiment of this application, such as Figure 4 As shown, the launch system is set with the structural parameters in Table 1. Under the condition that the incident velocity of the launcher armature is 300 m / s, the optimal capacitor can be selected as 0.55031 mF according to the capacitor selection model (8) and 0.54826 mF according to the capacitor selection model (9). After simulation by engineering software, the launcher armature obtained the highest thrust peak of 468.38 kN under the excitation of a capacitor value of 0.55 mF, which verifies that the above capacitor selection model has high accuracy.

[0053] Table 1

[0054] Furthermore, in the embodiments of this application, in step S2, with the goal of optimal electromagnetic coupling of the system, the changes in system thrust, capacitor discharge in the system excitation source and pulse power device current are analyzed to determine the second selection strategy for the number of turns of the drive coil and the number of turns of the armature coil of the electromagnetic launch system.

[0055] Based on the above embodiments, as an optional embodiment, step S2 involves analyzing the changes in system thrust, capacitor discharge in the system 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 coil under optimal electromagnetic coupling conditions, the time model of the capacitor discharge stage in the excitation source of the system, and the peak pulse current model of the thyristor; Using the system inductance model, the peak thrust model of the transmitter armature coil, the time model of the capacitor discharge stage, and the peak current model of the thyristor pulse, the system thrust, the capacitor discharge in the system excitation source, and the current of the pulse power device are analyzed. Based on the analysis results, a second selection strategy for the number of turns of the drive coil and the number of turns of the transmitter armature coil is determined.

[0056] Specifically, in the embodiments of this application, it is first necessary to determine the inductance model of the electromagnetic launch system, including the self-inductance model of the drive coil, based on the circuit structure of the wound electromagnetic launch system. Self-inductance model of the transmitter armature coil And the mutual inductance model between the drive coil and the transmitter armature coil. M Under the condition of optimal electromagnetic coupling, the peak thrust model of the transmitter armature coil, the time model of the capacitor discharge stage, and the peak current model of the thyristor pulse were determined. Then, using the inductance model of the electromagnetic launch system, the peak thrust model of the transmitter armature coil, 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 were analyzed.

[0057] More specifically, taking a wound-reconnected gun system with two stator coils connected in series as an example, the peak thrust model of the launcher armature coil is as follows: This process can be represented as: (10); in, 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.

[0058] 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. The second selection strategy includes: the number of turns, size, and shape of drive coil 1 and drive coil 2 are exactly the same.

[0059] Substituting the definition of the electromagnetic system inductance model in equation (10) into equation (10) 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. Under the parameters in Table 1 above, such as Figure 5 The simulation results shown in (a) show that, with the increase in the number of turns of the drive coil... With the increase of [unclear], the peak thrust of the system will remain basically unchanged.

[0060] Under optimal electromagnetic coupling conditions, a time model of the capacitor discharge stage in the system's excitation source is provided. Refer to equation (6) above. Substituting the electromagnetic system inductance model in equation (10) 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 for maximum thrust, the armature of 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.

[0061] At an incident velocity of 72 m / s, under the parameters in Table 1, such as Figure 5 As shown in simulation results (a) and (b), the second selection strategy also includes increasing the number of turns of the drive coil, which helps to prolong the duration of the current in the circuit, slow down the energy consumption rate in the circuit, and increase the duration of the thrust.

[0062] 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: (11); 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.

[0063] like Figure 5 The simulation results shown in (c) indicate that the second selection strategy also includes: under optimal electromagnetic coupling conditions, increasing the number of turns in the drive coil helps reduce the peak pulse current and the rate of rise of the on-state critical current of the pulse power device. Although this slows down the current decay rate and increases the current pulse width, the peak pulse current is the main factor affecting the cost of pulse power devices, and the rate of rise of the critical current is the most stringent and difficult indicator to overcome in device manufacturing processes. The current pulse width can meet thermal management requirements through heat dissipation systems (cold plates, water cooling, etc.). Increasing the number of turns in the drive coil allows for the selection of low-power pulse power devices, reducing the cost of the wound electromagnetic launch system.

[0064] Based on the aforementioned capacitor discharge phase time model, when the transmitter armature is launched to ultra-high speed, since the velocity change is relatively small compared to the incident velocity at high speeds, the duration of the capacitor discharge phase is not considered here. The voltage rating remains unchanged. If the withstand voltage 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... It remains unchanged, while also satisfying 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 .

[0065] 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 aforementioned equation (9). 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.

[0066] Therefore, a second selection strategy for determining the number of turns in the drive coil also includes: when designing the drive coil, through the design of the wire insulation layer thickness and a specific wire winding method, ensuring that the inter-turn withstand voltage of the drive coil is 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. Subsequently, by using the iterative selection method of the highest thrust peak capacitor, the system's withstand voltage requirements can be met relatively easily, with almost no need for redesign.

[0067] 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 armature coil also includes: the number of turns in the launcher armature 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 reduce the influence of the eddy current skin effect and meet the prerequisites for the wound electromagnetic launch system.

[0068] More specifically, based on the design of the maximum speed of the transmitter armature. Taking the estimation of eddy current skin depth as an example, the emitter armature current is equivalent to a sinusoidal alternating current, based on the equivalence relation When electromagnetic coupling is optimal, the armature of 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: (13); in, , 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.

[0069] 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.

[0070] Furthermore, in the embodiments of this application, in step S3, 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 system excitation source according to different types of system excitation sources, thereby determining the third selection strategy for pulse power devices in different system excitation sources.

[0071] Furthermore, in the embodiments of this application, in step S4, based on the aforementioned first selection strategy, second selection strategy and third selection strategy, the capacitance parameters of the system excitation source pulse capacitor, the coil turn parameters of the transmitter armature coil and drive coil, 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.

[0072] The design method for the wound electromagnetic launch system in 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 number of turns of the system drive coil and the number of turns of the launcher armature coil on the system thrust, the capacitor discharge in the system excitation source and the current of the pulse power device, 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, and the capacitor and pulse power device in the system excitation source, achieving the performance conditions of optimal electromagnetic coupling of the system. It can effectively realize the design of the wound electromagnetic launch system and is applicable to the design application scenarios of induction electromagnetic guns such as wound launcher armature coil guns and wound launcher armature reconnection guns.

[0073] Based on the above embodiments, as an optional embodiment, step S3, 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 system excitation source to determine a third selection strategy for the pulse power device in the system excitation source, including: Based on the capacitance value and initial voltage of the excitation source in the system, 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 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 thyristor selection strategy is determined; the third selection strategy includes the thyristor selection strategy.

[0074] Specifically, in the embodiments of this application, based on the mathematical analysis of the wound electromagnetic launch system, the selection of the thyristor in the system 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: (14); in, This represents the system mutual inductance at the end of the capacitor discharge phase.

[0075] It should be noted that regardless of the position of the emitter armature 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: (15); like Figure 6 As shown in the embodiments of this application, the accuracy of the selected model is verified according to the parameters in Table 1. Figure 6 (a) shows the peak pulse current of the thyristor when the armature incident velocities of the emitter are 72 m / s, 300 m / s, and 680 m / s, respectively. The simulation and analytical comparison results Figure 6 (b) represents the critical rate of rise of the on-state current when the armature incident velocities of the emitter are 72 m / s, 300 m / s, and 680 m / s, respectively. The simulation and analytical results are compared.

[0076] 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.

[0077] 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, the current pulse width selection model of the thyristor is determined based on the relationship between the first parameter and the self-inductance of the drive coil, using the self-inductance of the drive coil, the capacitance and freewheeling resistor in the system excitation source; the first parameter is determined based on the capacitance and freewheeling resistor in the system excitation source.

[0078] 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.

[0079] 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.

[0080] 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.

[0081] 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: (16); Furthermore, considering that regardless of the position of the transmitter armature at the end of capacitor discharge, the corresponding system mutual inductance should guarantee the safety of the thyristor, the thyristor current pulse width under this operating condition can be derived. The selection model is as follows: (17); 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: (18); like Figure 7 As shown in the embodiments of this application, the accuracy of the selected model is verified according to the parameters in Table 1. Figure 7 (a) represents the conditions when a Type I PFN excitation source is used, and the armature incident velocities of the emitter are 72 m / s, 300 m / s, and 680 m / s, respectively. Current pulse width under operating conditions The simulation and analytical comparison results; Figure 7 (b) represents the conditions when a Type I PFN excitation source is used, and the armature incident velocities of the emitter are 72 m / s, 300 m / s, and 680 m / s, respectively. Current pulse width under operating conditions The simulation and analytical results are compared.

[0082] 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 commutation phase ends, the transmitter armature has already traveled a certain distance. As an approximation, this process can be represented as: (19); 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: (20); like Figure 8 As shown in the embodiments of this application, the accuracy of the selection model is verified according to the parameters in Table 1. The figure shows the results when a Type II PFN excitation source is used, and the armature incident velocities of the emitter are 72 m / s, 300 m / s, and 680 m / s, respectively. Current pulse width under operating conditions The simulation and analytical results are compared.

[0083] Furthermore, when the operating condition is The diode commutation stage ends at [time]. , can be represented as: (twenty one); in, There is no solution. Theoretically, the turn-off time of a thyristor is infinite, meaning it will never turn off. Figure 9 As shown, under different incident velocities of 72 m / s, 300 m / s, and 680 m / s, the thyristor current approaches zero infinitely within 6 ms, theoretically making it impossible to turn off. Since the transcendental function has no sign analytical solution, and the Taylor expansion results in an equation of too high a degree, solving it is difficult. Therefore, under a type II PFN excitation source, and with the operating condition... In such cases, it is recommended to use actual data verified by engineering simulation to select the thyristor current pulse width.

[0084] 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.

[0085] 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.

[0086] Based on the above embodiments, as an optional embodiment, the pulsed power device includes a diode; 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 system excitation source to determine a third selection strategy for the pulsed power device in the system 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 third selection strategy includes the diode selection strategy.

[0087] Specifically, in the embodiments of this application, based on the mathematical analysis of the wound electromagnetic launch 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 .

[0088] 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 process only needs to be divided into... and We will discuss both scenarios, without needing to differentiate between the types of incentive sources.

[0089] 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 two); 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.

[0090] Similarly, considering that regardless of the position of the emitter armature at the end of capacitor discharge, the corresponding system mutual inductance should ensure the safety of the diode. 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 three); like Figure 10 As shown in the embodiments of this application, the accuracy of the selected model is verified according to the parameters in Table 1. Figure 10 In the figure (a), the armature incident velocities of the transmitter are 72 m / s, 300 m / s, and 680 m / s, respectively. Diode pulse peak current under operating conditions The simulation and analytical comparison results; Figure 10 (b) represents the armature incident velocities of the emitter at 72 m / s, 300 m / s, and 680 m / s, respectively. Critical rate of rise of diode on-state current under operating conditions The simulation and analytical results are compared.

[0091] 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: (twenty four); in, These are algebraic variables with no physical meaning. Similarly, considering that regardless of the position of the emitter armature at the end of capacitor discharge, its corresponding system mutual inductance should guarantee the safety of the diode. 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: (25); 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. Model accuracy is as follows Figure 11 As shown.

[0092] like Figure 11 As shown in the embodiments of this application, the accuracy of the selected model is verified according to the parameters in Table 1. Figure 11 In the figure (a), the armature incident velocities of the transmitter are 72 m / s, 300 m / s, and 680 m / s, respectively. Diode pulse peak current under operating conditions The simulation and analytical comparison results; Figure 11 (b) represents the armature incident velocities of the emitter at 72 m / s, 300 m / s, and 680 m / s, respectively. Critical rate of rise of diode on-state current under operating conditions The simulation and analytical results are compared.

[0093] 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.

[0094] 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 for a certain safety margin: the time required for the diode current pulse width to rise from 0 to fall back to 10% of the pulse peak value.

[0095] Furthermore, in embodiments of this application, based on the self-inductance of the driving coil Capacitors in the system excitation source C and 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 armature has already 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:

[0096] (26); Furthermore, the diode current pulse width under this operating condition can be derived. The selection model is as follows: (27); 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: (28); like Figure 12 As shown in the embodiments of this application, the accuracy of the selected model is verified according to the parameters in Table 1. Figure 12(a) represents the conditions when a Type I PFN excitation source is used, and the armature incident velocities of the emitter are 72 m / s, 300 m / s, and 680 m / s, respectively. Diode current pulse width under operating conditions The simulation and analytical comparison results; Figure 12 (b) represents the conditions when a Type I PFN excitation source is used, and the armature incident velocities of the emitter are 72 m / s, 300 m / s, and 680 m / s, respectively. Diode current pulse width under operating conditions The simulation and analytical results are compared.

[0097] 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 armature has already traveled a considerable distance. The solution is performed, and its circuit structure diagram is as follows: Figure 13 As shown.

[0098] The loop equation for this stage can be expressed as: (29); Solving for the given information yields: (30); in, This indicates the current flowing through the freewheeling resistor. This represents the voltage across the capacitor.

[0099] During this stage, the thyristor is turned off, does not output energy, and does not generate electromagnetic thrust. Therefore, it can be deduced that: (31); The diode current pulse width under this operating condition can be solved. The selection model is as follows: (32); like Figure 14 As shown in the embodiments of this application, the accuracy of the selected model is verified according to the parameters in Table 1. Figure 14 The figure shows the armature incident velocities of the emitter when using a type II PFN excitation source, which are 72 m / s, 300 m / s, and 680 m / s, respectively. Diode current pulse width under operating conditions The simulation and analytical results are compared.

[0100] Furthermore, in the embodiments of this application, when the operating condition is... The diode commutation stage ends at [time]. It can be represented as: (33); in, There is no solution. Theoretically, the turn-off time of a thyristor is infinite, meaning it will never turn off. Figure 15 As shown, under different incident velocities of 72 m / s, 300 m / s, and 680 m / s, the diode current approaches zero infinitely within 6 ms, theoretically making it impossible to turn off. Since the transcendental function has no sign analytical solution, and the Taylor expansion results in an equation of too high a degree, solving it is difficult. Therefore, under a type II PFN excitation source, and with the operating condition... In such cases, it is recommended to use actual data verified by engineering simulation to select the diode current pulse width.

[0101] Similarly, when selecting diodes for actual engineering projects, a certain safety margin factor still needs to be multiplied by the diode selection model formula.

[0102] 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.

[0103] It should also be noted that, in practical applications, as shown by the above analytical formula, when the pulse power device is difficult to manufacture, the freewheeling resistor can be adjusted. This ensures that the selection of pulse power devices meets current manufacturing specifications. For example... Figure 16 As shown, Figure 16 (a) shows the effect of the freewheeling resistor value on the current of the system's excitation source pulse diode; (b) shows the effect of the freewheeling resistor value on the electromagnetic thrust of the system's transmitter armature. Here, "mohm" represents the unit of resistance, "milliohm" (mΩ). From the mathematical analysis of wound electromagnetic launch systems, it can be seen that a higher freewheeling resistor helps reduce the pulse peak current and critical rise rate of the on-state current of the pulse power device, accelerates energy consumption in the circuit, reduces the device's requirement for current pulse width, and reduces the cost of the pulse power device. However, it reduces the thrust width and degrades the launch performance. Therefore, the selection of the freewheeling resistor must balance cost and launch performance according to actual requirements.

[0104] Therefore, 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 can be determined, thus realizing the selection and design of diodes in the excitation source.

[0105] Based on the above embodiments, as an optional embodiment, step S4, designing the wound electromagnetic launch system according to the first selection strategy, the second selection strategy, and the third selection strategy, includes: Based on the second selection strategy, determine the coil turns parameters of the drive coil and the transmitter armature; Based on the first selection strategy, the capacitor parameters under the maximum 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 third selection strategy, determine the selection parameters of the thyristors and diodes for the system excitation source; The design of the wound electromagnetic launch system is based on the selection parameters of thyristors and diodes, the capacitance parameters at the highest thrust peak, and the coil turns parameters.

[0106] Specifically, in the embodiments of this application, the number of turns of the driving coil and the transmitter armature, as well as the initial energy of the pulse capacitor in the excitation source, are first selected based on the second selection strategy, existing space size constraints, and conductor current density. E .

[0107] Specifically, targeting Figure 3 The multi-stage reconnection electromagnetic launcher system shown in the diagram accelerates the launcher armature to hypersonic speeds through progressive acceleration. The required launcher armature mass is determined based on... Acceleration distance Final velocity and initial velocity Derive the equivalent thrust It can be represented as: (34); The series of thrust pulses of a multi-stage reconnection gun is equivalent to a constant thrust. Both are equivalent in terms of the energy input to the armature of the launcher. Observing the shape of the thrust pulse, it is equivalent to an axisymmetric trigonometric function graph, which has high accuracy and a simpler computational model. Under the condition of optimal electromagnetic coupling, that is, simulating the thrust in spatial dimensions... Replacing thrust pulses for calculations offers higher accuracy. When the drive coils are closely arranged, the distance between the centers of adjacent shafts in a multi-stage reconnected gun is equal to the outer diameter of the drive coil. Furthermore, the formula for single-stage emission efficiency can be derived. This process can be represented as: (35); Furthermore, when the armature velocity of the launcher ranges from 72 m / s to 680 m / s, and the parameters of the winding reconnection gun are as shown in Table 1, under optimal electromagnetic coupling conditions, the resolving efficiency is 14.8%, and the launch efficiency of each stage closely matches the resolving efficiency. The accuracy results are as follows: Figure 17 As shown. Here, it can be understood that one stage is a set of drive coils.

[0108] Furthermore, substituting the definition of inductance in equation (10) into the above formula for single-stage emission efficiency, it can be seen that the emission efficiency of the wound electromagnetic emission system is independent of the number of turns, and only related to the magnetic permeability, i.e., the coil configuration. Figure 18 As shown in Table 1, with the thickness of the drive coil and the armature coil of the launcher remaining unchanged, and the spacing between the coils remaining unchanged, the other structural parameters of the main body are proportionally doubled. The outer diameter of the drive coil is increased from 160mm to 320mm. This is considered for electromagnetic catapult fighter jets, electromagnetic projectiles carrying large-mass armor-piercing missile warheads, ultra-high-speed maglev transportation, and aerospace electromagnetic launches, etc., where the mass of the wound metal coil has almost no effect on the total mass of the launcher, and the total mass of the launcher remains unchanged. Under the initial energy of the capacitor as shown in Table 1, and under the same optimal electromagnetic coupling conditions, the velocity change increases from 72m / s to 108m / s, and the efficiency increases from 11.3% to 26%, almost doubling, indicating that there is great potential for efficiency improvement.

[0109] As can be seen from the efficiency formula above, the single-stage efficiency of a wound electromagnetic launcher system is mainly related to the coil configuration and the distance between the optimal electromagnetic coupling point and the trigger position, and is independent of the number of turns. A larger coil configuration and a greater distance from the optimal electromagnetic coupling point help improve the efficiency of the single-stage launcher armature.

[0110] Furthermore, given a preliminary coil configuration, the design process for a multi-stage wound electromagnetic launch system is as follows: First, the initial energy of the pulse capacitor should be selected. Number of turns of the drive coil and the spatial dimensions of the drive coil cross-section .

[0111] (36); Based on the mathematical analysis of wound electromagnetic systems, the peak value of the driving coil current... for: (37); Regardless of the position of the emitter armature at the end of the capacitor discharge phase, system safety must be ensured. The system mutual inductance is estimated based on the position where the emitter armature coil axis coincides with the drive coil axis. At this point, the peak current is at its maximum, i.e.: (38); Therefore, under the premise of meeting the current pulse width specification of pulse power devices, the number of turns of the drive coil... The number of turns should be as high as possible, as this helps improve the system's emission performance and reduce the cost of the excitation source circuit. It is also necessary to ensure a certain withstand voltage capability. When selecting the number of turns of the drive coil, engineering parameters such as the thickness of the insulating varnish must still be considered.

[0112] Optionally, the current density limit of the electromagnetic launch system It can be designed to With sufficient margin, usually ,Right now It depends only on the actual engineering size limitations, so the coil configuration can be determined in the early stages of design.

[0113] In the embodiments of this application, once the number of turns and the coil configuration of the drive coil are determined, the corresponding inductance data can be determined. Here, the finite element method can be used to determine the inductance data for the parameter iteration process in the subsequent design of the multi-stage wound electromagnetic launch system.

[0114] It should be noted that traditional finite element engineering simulation and other parametric scanning design methods are computationally time-consuming and have high performance requirements. Furthermore, when multiple parameters are scanned simultaneously, expensive workstations are required to prevent memory crashes, making simulation almost impossible. Scanning only a few parameters cannot yield the globally optimal design solution; moreover, finite element parametric scanning simulation design methods lack theoretical support, only providing qualitative conclusions and analyzing trends, resulting in low design efficiency and ambiguous design accuracy.

[0115] Furthermore, in the embodiments of this application, according to the first selection strategy, parameter iterative calculations are performed using the preset launcher armature incident velocity and the capacitor energy of the system excitation source to determine the capacitor parameters at the highest thrust peak. Specifically, based on the incident velocity and capacitor energy, the inductance data determined by the finite element method can be combined with the current wire method to perform iterative design of a multi-stage wound electromagnetic launch system, selecting the capacitor with the highest thrust peak to achieve optimal electromagnetic coupling and optimal thrust peak. The entire iterative process takes several minutes and has almost no requirements on computer performance.

[0116] More specifically, in the embodiments of this application, the current wire program method for multi-stage coil launching is used. Based on the inductance data determined by the finite element method, as well as the initial energy of the capacitor and the incident velocity, the inductance data is imported into the current wire program. Formula (9) is used as the multi-stage launching iteration formula, and the highest thrust peak capacitance and initial voltage of each stage of the multi-stage wound electromagnetic launching system can be iterated. Taking the parameters in Table 1 as an example, the highest thrust peak capacitance and its initial voltage of 134 stages can be iterated in just 3 minutes.

[0117] like Figure 19(a) is a schematic diagram showing the distribution of the peak thrust capacitor selection parameters for the multi-stage launch system provided in this application embodiment. It illustrates the distribution relationship between the peak thrust capacitor of each stage of the system and the corresponding initial voltage when the launcher armature is accelerated from a speed of 72 m / s to 680 m / s. Figure 19 As shown in (b), this procedural method has higher engineering accuracy compared with the finite element method, which greatly improves the design efficiency of the wound electromagnetic launch system.

[0118] Figure 20 Figures (a) and (b) show the thrust variations of the system at different stages as the launcher armature accelerates from 72 m / s to 210 m / s and from 644 m / s to 680 m / s, respectively. Figure 20 It can be seen that after selecting the highest thrust peak capacitor at level 134, the finite element simulation shows that the thrust peak is almost aligned with the thrust peak line, and there is no attenuation of the thrust peak as the speed increases. According to After selecting the capacitor with the highest thrust peak, the thrust peak depends only on the coil shape and the initial energy of the pulse capacitor. The alignment of the thrust peak with the thrust line indirectly confirms the high accuracy of the analytical model formula of this application.

[0119] Furthermore, in the embodiments of this application, based on the aforementioned third selection strategy, the selection parameters of the thyristors and diodes in the system excitation source are determined using the selection model of the repetitive peak voltage, pulse peak current, critical rate of rise of on-state current, and current pulse width of each pulse power device in the strategy. Specifically, an iterative selection method combining inductance data determined by the finite element method with the current wire procedure method can be used to rapidly iterate the four indicators of each stage of pulse power devices (thyristors and diodes), thereby enabling rapid engineering cost estimation and selection of pulse power devices, greatly improving design efficiency.

[0120] For type II PFN excitation sources, For current pulse width selection under operating conditions, it is recommended to use actual engineering simulation verification data for device selection.

[0121] Furthermore, in the embodiments of this application, a wound electromagnetic launch system is designed based on the aforementioned selection parameters of thyristors and diodes, capacitance parameters at the highest thrust peak, and coil turns parameters. Multiphysics coupling simulation is then performed on the designed wound electromagnetic launch system to verify its feasibility and safety. Here, electromagnetic-thermal coupling is applied to the designed wound electromagnetic launch system. Under natural convection cooling and single-stage launch conditions, the wound launcher armature coil exhibits uniform eddy current distribution, uniform loss distribution, and a large equivalent heat dissipation area, resulting in excellent heat dissipation conditions. Figure 21As shown in (a) in the image. Traditional solid metal plate emitter armatures, however, have uneven eddy current distribution, large losses concentrated at the tail of the emitter armature, small effective heat dissipation area, and poor heat dissipation conditions, such as... Figure 21 As shown in (b) of the table. Under initial conditions of room temperature 25°C and the parameters shown in Table 1, the maximum temperature rise of the armature coil of the single-stage emitter is 1.8°C, as... Figure 21 As shown in (c), the maximum temperature rise of the solid metal plate emitter armature is 135°C, as... Figure 21 As shown in (d) in the figure. It can be seen that the solid metal plate emitter armature has a high risk of melting in the case of multi-stage emission, while the temperature rise of the wound emitter armature coil is very small, making it more suitable for multi-stage ultra-high-speed electromagnetic emission.

[0122] Under the excitation of the highest thrust peak capacitance of level 134, with parameters as shown in Table 1, the emitter armature accelerates from 72 m / s to 680 m / s, and the highest temperature of the coil wound around the emitter armature rises to 58.22℃, which meets the temperature limit of the insulating material. This result is as follows... Figure 22 As shown, the drive coil experiences only one thermal pulse per discharge, therefore its temperature rise is negligible.

[0123] Furthermore, an electromagnetic-structural field coupling analysis was performed on the design scheme. The highest structural stress of the driving coil was 15.42 MPa. Figure 23 As shown in (a) of the diagram. The highest structural stress of the transmitter armature coil is 9.18 MPa, as... Figure 23 As shown in (b) above. Through fluid-structure interaction analysis, the maximum absolute total gas pressure of the emitter armature at the ultra-high speed of 680 m / s is 1.54 MPa, as shown in (b). Figure 23 As shown in (c), the structural strength of the insulating material is satisfied, verifying the feasibility of the design system.

[0124] Optionally, in the embodiments of this application, during the mathematical analysis of the wound electromagnetic launch system, the mutual inductance of the system at the end of the capacitor discharge stage is crucial. This mutual inductance is used to estimate the duration of the capacitor discharge stage. Therefore, a displacement estimation method considering the acceleration effect of the capacitor discharge stage is also proposed, which can then estimate the mutual inductance. Specifically, using uniformly accelerated motion as an approximate estimate, the following can be derived with reference to the aforementioned formula (9): (39); in, The function representing the fit of the mutual inductance gradient with respect to the position of the transmitter armature coil is denoted as . This represents the fitting function of mutual inductance with respect to the position of the transmitter armature coil.

[0125] In the embodiments of this application, the displacement during the capacitor discharge stage can be obtained by solving the above three equations. The accuracy verification results of this method are as follows: Figure 24 As shown, the red dots represent the displacement results of the finite element simulation, and the intersections of the meshes represent the analytical displacements. It can be seen that the red dots are distributed on the intersections of the meshes, demonstrating the high precision of the analytical model formula provided in this application embodiment and verifying that the method has high precision.

[0126] The method of this application embodiment clarifies the design principles of the wound electromagnetic launch system. It adopts a multi-stage iterative design of the wound electromagnetic launch system by combining finite element inductance data and current wire programming method. Compared with the traditional parameter scanning design method such as finite element engineering simulation, it greatly saves computing resources and design time, and greatly improves design efficiency and design accuracy.

[0127] 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.

[0128] 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.

[0129] 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.

[0130] 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.

[0131] 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 technical scope 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 method of designing a solenoidal electromagnetic launch system, characterized by, include: Electromagnetic performance analysis is performed based on the thrust model of the wound electromagnetic launch system to determine the first selection strategy for the capacitor in the system's excitation source. The system thrust, capacitor discharge in the system 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. 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 of the system to determine the third selection strategy for pulse power devices in the excitation source of the system. The winding electromagnetic launch system is designed based on the first selection strategy, the second selection strategy, and the third selection strategy.

2. The design method for a wound electromagnetic launching system according to claim 1, characterized in that, The electromagnetic performance analysis based on the thrust model of the wound electromagnetic launch system, and the determination of the first selection strategy for the capacitor in the system's excitation source, include: The 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 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 first selection strategy is determined based on the capacitor selection model.

3. The design method for a wound electromagnetic launching system according to claim 2, characterized in that, 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: Determine the time model of the capacitor discharge stage in the system 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 transmitter armature displacement model, the capacitor selection model under the highest thrust peak is determined.

4. The design method for a wound electromagnetic launching system according to claim 1, characterized in that, The analysis of system thrust, capacitor discharge in the system 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 coil under optimal electromagnetic coupling conditions, the time model of the capacitor discharge stage in the excitation source of the system, and the peak pulse current model of the thyristor; Using the system inductance model, the peak thrust model of the transmitter armature coil, 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.

5. The design method for a wound electromagnetic launching system according to claim 1, characterized in that, 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 system excitation source, to determine the third selection strategy for the pulsed power device in the system excitation source, includes: Based on the capacitance value and initial voltage of the excitation source in the system, 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 third selection strategy includes the selection strategy of the thyristor.

6. The design method for a wound electromagnetic launching system according to claim 5, characterized in that, The current pulse width selection model for the thyristor, based on the self-inductance of the driving coil, the capacitance in the system excitation source, and the freewheeling resistor, includes: When the system excitation source is a type I PFN excitation source or a type II PFN excitation source, 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 and freewheeling resistor in the system excitation source; the first parameter is determined based on the capacitance and freewheeling resistor in the system excitation source.

7. The design method for a wound electromagnetic launching system according to claim 1, characterized in that, The pulsed power device includes a diode; 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 system excitation source, to determine the third selection strategy for the pulsed power device in the system 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 third selection strategy includes the diode's selection strategy.

8. The design method for a wound electromagnetic launching system according to any one of claims 1-7, characterized in that, The design of the wound electromagnetic launch system based on the first selection strategy, the second selection strategy, and the third selection strategy includes: Based on the second selection strategy, determine the coil turns parameters of the drive coil and the transmitter armature; Based on the first 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 third selection strategy, the selection parameters of the thyristors and diodes for the system excitation source are determined; The design of the wound electromagnetic launch system is based on the selection parameters of the thyristor and the diode, the capacitance parameters at the highest thrust peak, and the coil turns parameters.

9. The design method for a wound electromagnetic launching system according to any one of claims 1-7, characterized in that, The wound electromagnetic launch system includes an excitation source, a launcher armature for launching the load, and multiple sets of drive coils; each set of drive coils is connected to the excitation source and is used to generate electromagnetic force under the excitation of the excitation source to drive the launcher armature to launch the load; the launcher armature is a self-closing multilayer metal coil disk.

10. The design method for a wound electromagnetic launching system according to claim 9, characterized in that, Each group of driving coils includes two hollow metal coil disks connected in series or in parallel, arranged coaxially at the top and bottom; the multi-layer metal coil disks are arranged in parallel between the two hollow metal coil disks.

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