Split type plasma ignition device and ignition system for passivating agent

Abstract

The invention relates to the technical field of plasma ignition, in particular to a split type plasma ignition device and ignition system for passivating gunpowder, which comprises an ignition tube assembly and an oscillation control assembly, the ignition tube assembly comprises an ignition tube, gunpowder and a hollow resonance coil; the oscillation control assembly comprises a coil support, an excitation coil and an oscillator circuit module. The excitation coil on the coil support is used for being matched with an insulation tube in an ignition tube in an inserted mode. An ignition pulse excites an oscillator circuit module to generate a high-frequency excitation signal, the high-frequency excitation signal is released by an excitation coil and coupled to a hollow resonance coil in an electromagnetic induction mode to form LC resonance, the LC resonance enables a discharge part to generate a high-intensity electric field, the high-intensity electric field excites plasmas on the surface of gunpowder to ignite the gunpowder, and ignition is completed. The device breaks through multiple limitations of a traditional ignition mode, and intrinsic safety and high reliability of passivation agent ignition are achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of plasma ignition, and in particular to a split plasma ignition device and an ignition system for passivating medicine. Background Art

[0002] Solid rocket motors are crucial propulsion components for various weaponry, small and medium-sized rockets, and multi-domain combined-power aircraft. With the rapid growth of commercial aerospace in recent years, solid rocket motors have become increasingly popular for low-cost, rapid-response launch missions. Solid rocket motor fuel (powder) typically utilizes passivated energetic materials, such as trihydroxyaminobenzene and trinitroanisole. These solid motor fuels exhibit stringent ignition requirements, ensuring they remain inflammable even under brief exposure to open flames or impact, enhancing safety during transportation and storage.

[0003] In actual applications, in order to reliably ignite solid motor charges, traditional ignition devices (ignition tubes) generally use a multi-stage structure to achieve energy transfer and ignition. The first stage of the ignition device contains a highly sensitive thermal explosive, which then increases the energy step by step through the stages of fire transfer powder, combustion powder, etc., and finally ignites the main charge of the engine. Although this type of solution is technically mature, the ignition device contains sensitive drugs inside, and according to the explosives management regulations, it needs to be included in the first-level hazardous materials management (the same level as detonators). Although the overall charge of the solid motor can be managed as low-sensitivity (4-5 levels) hazardous materials, the ignition tube alone requires special warehousing, transportation, management, and approval links. Not only is the management cost high, but the approval procedures are time-consuming and the pre-launch test safety control process is complicated. It has become a bottleneck link in commercial aerospace, rapid-response launch and other missions. Specifically: 1) Safety hazards: The first stage of pyrotechnics generally contains highly sensitive agents, which require extremely strict explosion-proof management during transportation, storage and assembly. There is also a risk of accidental detonation, and the management cost is high. The ignition tube and engine usually need to be transported separately and assembled before launch. Temporary ignition body resistance testing, functional equivalence testing, and re-inspection procedures are required at the launch site. The process is time-consuming and affects the rapid response of the mission.

[0004] 2) Reliability bottleneck: Multi-stage ignition transmission structures (e.g., thermal explosives → output charge → main charge) carry risks such as energy decay and misfire. To improve safety, existing technologies attempt to physically separate the primary / secondary ignition modules from the ignition transmission structure through a split design. This further exacerbates the risk of failure, making it difficult to strike a balance between reliability and safety. In practice, two or three redundant ignition device groups are typically required to ensure reliability.

[0005] 3) Thermal trigger power consumption: Currently, the first stage of the ignition tube generally uses a thermally sensitive explosive, which uses heat from a resistance wire to trigger a chemical reaction. This requires a trigger current of at least 10A, but typically a margin of 2-3 times is allowed, along with dual ignition redundancy. This places a demand on the power supply and distribution system of 50-60A. This places a significant strain on the power supply system of the aircraft or launch vehicle. To achieve ignition times of just a few hundred milliseconds, the onboard battery and power supply and distribution system require significant additional capacity.

[0006] Plasma ignition technology has a concentrated high temperature area (>5000K) and high energy density (10 6 -10 8 W / cm 3 ) and high energy efficiency, making it a research hotspot for novel ignition schemes. This technology, which generates non-equilibrium plasma through high-voltage discharge / electromagnetic field excitation, can efficiently ignite difficult-to-ignite media such as oxygen-depleted mixtures in aircraft engine preburners and insensitive propellants in scramjets. Its advantages have been demonstrated in new aerospace and combined-power engines.

[0007] However, applying plasma ignition technology to solid rocket propellant ignition still faces key challenges, such as the efficient integration of electronic components and energetic materials, efficient electrical / combustion excitation, and safety measures to prevent accidental activation. Currently, there is no established electronically controlled plasma ignition system that is independent of sensitive explosives, inherently safe, highly efficient, and consumes minimal power. This system can directly ignite various propellants (including three-base solid rocket propellants and passivated flare propellants).

[0008] Therefore, it is necessary to provide a split plasma ignition device and an ignition system for passivating agents to solve the above problems. Summary of the Invention

[0009] To address the problems of low system integration, insufficient coupling efficiency, and safety issues that still exist when plasma ignition technology is applied to the ignition of explosive passivation charges, the present invention provides a split plasma ignition device and ignition system for passivation charges. By physically decoupling the oscillation control component and the ignition tube component, combined with a miniaturized high-voltage oscillation circuit and resonant matching energy transfer technology, this device overcomes many limitations of traditional ignition methods, achieving intrinsic safety (completely eliminating pyrotechnics and highly sensitive agents) and high reliability (millisecond-level response, single-stage direct-ignition energy transfer) for passivation charge ignition, thereby resolving existing problems.

[0010] A first aspect of the present invention provides a split plasma ignition device for a passivating agent, comprising: An ignition tube assembly includes an ignition tube having two interconnected cavities, one of which is filled with gunpowder and has a fire transmission hole provided on the wall of the corresponding cavity; an insulating tube is provided on the inner wall of the other cavity, a hollow resonant coil is provided around the outer circumference of the insulating tube, a discharge component is connected to the hollow resonant coil, and an end of the discharge component contacts the gunpowder; and an oscillation control assembly, comprising: a coil support on which an excitation coil is wound, an oscillator circuit module connected to the excitation coil being provided on a side of the coil support facing away from the excitation coil; Among them, the excitation coil on the coil bracket is used to plug and cooperate with the insulating tube in the ignition tube; the ignition pulse excites the oscillator circuit module to generate a high-frequency excitation signal, which is released through the excitation coil and coupled to the hollow resonant coil in an electromagnetic induction manner to form LC resonance. The LC resonance causes the discharge component to generate a high-intensity electric field, and the high-intensity electric field excites the plasma on the surface of the gunpowder to ignite the gunpowder and complete the ignition.

[0011] Preferably, the gunpowder adopts a three-base passivation powder added with metal powder, wherein the metal powder is aluminum powder or boron powder.

[0012] Preferably, the discharge component is an elastic discharge needle, wherein the tip of the discharge needle faces the central area of ​​the gunpowder.

[0013] Preferably, the oscillator circuit module comprises: LC oscillator, used to generate a high-frequency excitation signal of a specific frequency, wherein the frequency range is: 50kHz~20MHz; Input protection unit, which is used to protect the ignition pulse from overcurrent and overvoltage; The rectifier and filter unit is used to convert the DC power of uncertain polarity in the ignition pulse into DC power of certain polarity, realize bipolar triggering and filter out high-frequency noise; Energy storage unit, used to store electrical energy and supply energy; A DC / DC circuit unit, used for converting the DC voltage provided by the energy storage unit into a voltage suitable for the operation of the LC oscillator; The window voltage comparison unit is used to monitor the voltage pulse amplitude of the energy storage unit in real time and trigger the LC oscillator to work when the voltage pulse amplitude meets the starting pulse amplitude threshold; The input port of the oscillator circuit module is used to input an ignition pulse, and the output port of the oscillator circuit module is electrically connected to the excitation coil.

[0014] Preferably, the input protection unit comprises: a fuse and a current-limiting resistor connected in series between the input port of the oscillator circuit module and the rectification and filtering unit.

[0015] Preferably, it further comprises: a delay unit, which is arranged between the window voltage comparison unit and the LC oscillator and is used for delaying the triggering of the LC oscillator after the voltage monitored by the window voltage comparison unit meets the start threshold.

[0016] Preferably, the ignition tube is mechanically locked to the coil support of the oscillation control assembly by means of a bolt connection, a snap connection or an elastic snap-in connection.

[0017] Preferably, the discharge needle is made of one or a composite material of tungsten, stainless steel, and graphene.

[0018] Preferably, a metal shielding layer is provided inside the shell of the ignition tube, and the metal shielding layer is used to prevent the gunpowder, the hollow resonant coil and the discharge component inside the ignition tube from being interfered by the external high-frequency signal.

[0019] A second aspect of the present invention provides a multi-channel radio frequency plasma ignition system supporting parallel control of multiple ignition tubes, comprising: an oscillation control component in the split plasma ignition device for passivating agents of the present invention and a plurality of ignition tube assemblies with independently configured frequencies, wherein the resonant frequency of the hollow resonant coil of each ignition tube assembly is different, and the oscillation control component integrates a frequency switching module, an address encoding module, and a multi-channel output port.

[0020] The beneficial effects of the present invention are: The present invention separates the ignition tube assembly from the oscillation control assembly. This means that before use, the "ignition tube assembly" and the "oscillation control assembly" are two independent, non-interconnected modules. The ignition tube assembly is a passive element, lacking a built-in power supply, control circuit, or chemical energy storage medium. It cannot be excited or ignited on its own, and discharges only through the energy of the high-frequency excitation signal received by the hollow resonant coil. The oscillation control assembly, on the other hand, is an active element. The plasma ignition device only has ignition capability after it is placed in proximity to the hollow resonant coil of the ignition tube assembly and emits a high-frequency excitation signal of a set frequency. The oscillation frequency is unique, similar to an "authorization key," and does not rely on complex communication protocols. It utilizes the inherent anti-interference properties of physical resonance, resulting in superior security.

[0021] Specific advantages include the following: (1) Significantly improve system safety: The ignition tube assembly does not contain any pyrotechnics such as detonators and primers, and cannot detonate on its own under normal circumstances. This avoids the explosion risk of traditional pyrotechnic devices during transportation, storage and operation, and greatly reduces the difficulty of safety management.

[0022] (2) Structural separation and control isolation: By separating the ignition tube assembly and the oscillation control assembly, the plasma can be activated only when the frequency matches and they are close to the plug-in state, achieving dual physical and electromagnetic isolation, effectively preventing false triggering and electromagnetic interference.

[0023] (3) Fast response speed and reliable ignition: The present invention adopts the principle of radio frequency coupling to excite high-temperature plasma in nanoseconds, quickly ignite the three-base passivation charge with added metal powder, and achieve high-precision and low-latency ignition requirements. It is suitable for high-speed blasting and high-dynamic response scenarios.

[0024] (4) The technology is highly versatile and easy to expand: By adjusting the parameters of the high-frequency excitation signal and the coil structure, it can adapt to various ignition requirements and support multi-channel independent control, with good scalability and system integration. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0026] Figure 1 This is a schematic diagram of the overall structure of a split plasma ignition device for passivating medicine according to Example 1 of the present invention; Figure 2 This is a circuit diagram of an oscillator circuit module in a split-type plasma ignition device for passivating agents according to Example 1 of the present invention; Figure 3 This is a schematic diagram of the working process of a split plasma ignition device for passivating medicine according to Example 1 of the present invention.

[0027] In the figure: 1. Ignition tube; 2. Mounting flange; 3. Fire hole; 4. Gunpowder; 5. Hollow resonant coil; 6. Discharge needle tip; 7. Excitation coil; 8. Coil bracket; 9. Oscillator circuit module; 10. Input port; 11. Ignition pulse; 12. High-frequency excitation signal; 13. Fuse; 14. Current-limiting resistor; 15. Rectifier and filter unit; 16. Energy storage unit; 17. DC / DC circuit unit; 18. Window voltage comparison unit; 19. Delay unit; 20. LC oscillator; 21. Output port. DETAILED DESCRIPTION

[0028] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0029] Example 1 Example 1 provides a split plasma ignition device for passivation medicine, such as Figure 1 As shown, the ignition device of this embodiment includes: an ignition tube assembly and an oscillation control assembly, wherein the ignition tube assembly is used to be plugged into the oscillation control assembly. The ignition tube assembly and the oscillation control assembly are stored independently of each other when not in use to ensure safety during storage or transportation. When in use, they work together through mechanical plug-in and radio frequency coupling to achieve efficient and controllable plasma ignition function.

[0030] like Figure 1 As shown, the ignition tube assembly includes: an ignition tube 1, which has two connected cavities, one of which is filled with gunpowder 4, and a fire transmission hole 3 is set on the tube wall corresponding to the cavity, and an insulating tube is set in the inner wall of the other cavity. A hollow resonant coil 5 is wound around the outer circumference of the insulating tube, and a discharge component is connected to the hollow resonant coil 5, and the end of the discharge component is in contact with the gunpowder 4. Figure 2 As shown, the oscillation control assembly includes a coil support 8, on which an excitation coil 7 is wound. An oscillator circuit module 9 connected to the excitation coil 7 is disposed on the side of the coil support 8 facing away from the excitation coil 7. The excitation coil 7 on the coil support 8 is configured to plug into and mate with the insulating tube within. In this plugged-in state, an ignition pulse 11 excites the oscillator circuit module 9 to generate a high-frequency excitation signal 12, which is released through the excitation coil 7 and coupled to the hollow resonant coil 5 by electromagnetic induction, forming LC resonance. The LC resonance causes the discharge component to generate a high-intensity electric field, which excites plasma on the surface of the gunpowder 4, igniting the gunpowder 4 and completing ignition.

[0031] For example, in one specific embodiment, the gunpowder 4 utilizes a three-base passivation agent with added metal powder. The metal powder is aluminum powder or boron powder to enhance total energy release. The three-base passivation agent comprises guanidine nitrate, ammonium peroxide, and nitroamidine. The filling can be in the form of a pressed solid charge or microgranular pellets, with a single dose of 5mg to 20mg. This area is connected to the chamber filled with gunpowder 4 via a flash hole 3. The flash hole 3 has an inner diameter of 3mm and a length of 8mm. The inner wall of the flash hole 3 is coated with a high-temperature ceramic material to resist the thermal erosion effects of the plasma.

[0032] For example, in a specific embodiment, the outer shell of the ignition tube 1 is made of stainless steel or titanium alloy material with a thickness of 1.5 mm to 3 mm, and 2 mm is taken in this embodiment. The ignition tube 1 is hollow cylindrical with an outer diameter of Φ30 mm and a length of 80 mm. A metal shielding layer is provided inside the ignition tube 1. The metal shielding layer is used to isolate the gunpowder 4, the hollow resonant coil 5 and the discharge component inside the ignition tube 1 from interference from external high-frequency signals.

[0033] For example, in one specific embodiment, the hollow resonant coil 5 includes: a coil formed by winding a copper tube or metal wire. In this embodiment, the hollow resonant coil 5 is wound with silver-plated copper wire with a diameter of 1 mm. The hollow resonant coil 5 is spirally wound on an insulating tube with 5 turns. The inductance of the hollow resonant coil 5 and the distributed capacitance between the coil turns are used to form a high-Q resonator. The resonance point can be fine-tuned to be consistent with the LC resonant frequency by the number of winding turns. The overall diameter of the coil is Φ18 mm and the height is 15 mm. The hollow resonant coil 5 is arranged between the inner wall of the cavity of the ignition tube 1 and the outer periphery of the insulating tube. When in use, it is coaxially arranged with the excitation coil 7 in the external oscillation control component to form an inductive coupling loop for achieving LC resonance.

[0034] For example, in a specific embodiment, the discharge component is a discharge needle 6 that is elastic along the axial direction of the insulating tube, wherein the tip of the discharge needle 6 is directed toward the central area of ​​the gunpowder 4 to ensure uniform ignition. In this embodiment, the discharge needle 6 is made of one of tungsten, titanium or graphene, or a composite conductive material of the two materials, and the tip diameter of the discharge needle 6 is 0.3 mm.

[0035] For example, in one embodiment, excitation coil 7 is also wound with five turns of 1mm silver-plated copper wire and secured to a coil support 8 made of high-frequency insulating ceramic or polytetrafluoroethylene. Coil support 8 has an outer diameter of 25mm and a length of 30mm. It features a snap-fit ​​or threaded structure, ensuring a secure connection with the mounting flange of ignition tube 1.

[0036] For example, in a specific embodiment, the oscillator circuit module 9 includes: an LC oscillator 20, an input protection unit, a rectifier and filter unit 15, an energy storage unit 16, a DC / DC circuit unit 17, a window voltage comparison unit 18, and a delay unit 19, wherein the LC oscillator 20 is used to generate a high-frequency excitation signal 12 of a specific frequency (50kHz~20MHz); the input protection unit is used to perform overcurrent and overvoltage protection on the input ignition pulse 11; the rectifier and filter unit 15 is used to convert the DC power of uncertain polarity in the ignition pulse 11 into DC power of certain polarity, thereby achieving bipolar triggering and filtering out high-frequency noise therein; the energy storage unit 16 is used to store electrical energy and supply energy; the DC / DC circuit unit 17 is used to convert the DC voltage provided by the energy storage unit into a voltage suitable for the operation of the LC oscillator 20. It should be noted that The ignition energy can be preset through the DC / DC circuit unit to adapt to the ignition energy of different gunpowders; the window voltage comparison unit 18 is used to monitor the voltage pulse amplitude of the energy storage unit in real time, and trigger the LC oscillator 20 to work when the voltage pulse amplitude meets the starting pulse amplitude threshold (when the voltage pulse amplitude is greater than the starting pulse amplitude threshold, the voltage pulse amplitude meets the starting pulse amplitude threshold), that is, only pulses within a specific voltage range can trigger the LC oscillator 20 to work, ensuring that there will be no false triggering; the delay unit 19 is arranged between the window voltage comparison unit 18 and the LC oscillator 20, and is used to delay the triggering of the LC oscillator 20 after the voltage monitored by the window voltage comparison unit 18 meets the starting threshold; wherein, the input port 10 of the oscillator circuit module 9 is used to input the ignition pulse 11, and the output port 21 of the oscillator circuit module 9 is electrically connected to the excitation coil 7. It should be noted that a delay unit 19 is provided after the window voltage comparison unit 18 to delay the triggering of the LC oscillator 20, preventing premature excitation and improving the stability and safety of the device. In one specific embodiment, the oscillator circuit module 9 is configured to provide a high-frequency RF signal at a set frequency (e.g., 13.56 MHz or 27.12 MHz), with an adjustable output power between 5 W and 30 W. It features a programmable pulse triggering mechanism with a trigger duration controlled between 10 and 100 nanoseconds. The oscillator circuit module 9 also incorporates a frequency authorization mechanism, enabling the system to initiate discharge only when the RF output frequency precisely matches the resonant frequency of the hollow resonant coil 5 of the ignition tube 1. The input protection unit includes a fuse 13 and a current-limiting resistor 14 connected in series between the input port 10 of the oscillator circuit module 9 and the rectifier and filter unit. This design achieves impedance matching with conventional excitation systems. The blowing of the fuse 13 provides instantaneous physical isolation after the ignition pulse 11, enhancing system safety. The current limiting resistor R14 is generally 1.5Ω, and the impedance is close to 0Ω before the fuse 13 blows. Before ignition, R14 and fuse 13 short-circuit the subsequent stage, making the input impedance of the entire system 1.5Ω, the same as the input impedance of a traditional igniter.At the moment of ignition, the current is the ratio of the input voltage to R14. The design ensures that the instantaneous current is greater than the fuse melting current to ensure that the system can work normally.

[0037] It should be noted that when the external detonator generates an ignition pulse signal, the ignition pulse signal first enters the circuit through the fuse 13 of the input port 11 and the matching current limiting resistor 13. This input design not only provides overcurrent protection, but its impedance characteristics also match the traditional excitation device, thereby improving compatibility with existing systems. After the ignition pulse 11 is triggered, the fuse 13 melts instantly, playing a one-time physical isolation and protection role, thereby improving the safety of the circuit itself. Subsequently, the pulse electrical energy of the ignition pulse 11 is converted into stable direct current by the rectification and filtering unit 15, and stored in the large-capacity capacitor of the energy storage unit 16 for use by the LC oscillator 20 and the discharge module. This energy is further boosted or adjusted to a voltage level that is adapted to the working conditions of the LC oscillator 20 by the DC / DC converter of the DC / DC circuit unit 17. In order to improve the overall safety and reliability of the ignition system, a window voltage comparison unit 18 and a programmable delay unit 19 are introduced in this embodiment. When the system detects that the voltage pulse amplitude of the energy storage unit 16 exceeds the startup pulse amplitude threshold (26V in this embodiment, as the standard spacecraft power interface voltage is typically 28V, so the system design must match this voltage), the controller does not immediately activate the LC oscillator 20. Instead, it uses the delay unit 19 to execute a preset wait time (typically 1 to 5 milliseconds, adjustable depending on the type of energetic material and the charging characteristics of the energy storage capacitor). This delay design effectively mitigates the risk of false detonation caused by sudden voltage changes or false triggering. Only after the delay expires and the voltage continuously meets the window conditions of the window voltage comparison unit 18 does the system allow the LC oscillator 20 to activate, thereby outputting a high-frequency excitation signal 12. This high-frequency excitation signal 12 is released through the excitation coil 7 and electromagnetically coupled to the air-core resonant coil 5, forming an LC resonance. This LC resonance causes the discharge component to generate a high-intensity electric field, which excites the plasma on the surface of the gunpowder 4, igniting the gunpowder 4 and effectively igniting the passivation charge. This circuit architecture offers excellent electromagnetic compatibility, fast startup response, and high control precision.

[0038] For example, in a specific embodiment, the ignition tube 1 is mechanically locked with the coil bracket 8 of the oscillation control component by means of bolt connection, snap connection or elastic snap-in; in this embodiment, a mounting flange 2 is provided at the end of the ignition tube 1 and the end of the coil bracket 8 close to the oscillator circuit module 9. After the coil bracket 8 of the oscillation control component is inserted into the hollow resonant coil 5 in the cavity of the ignition tube 1, the mounting flange 2 on the ignition tube 1 and the coil bracket 8 is connected by screws to achieve mechanical locking of the ignition tube 1 and the coil bracket 8 of the oscillation control component to ensure the precise positioning of the oscillation control component and the ignition tube 1.

[0039] Example 2 This embodiment 2 provides a multi-channel radio frequency plasma ignition system that supports parallel control of multiple ignition tubes, which is suitable for application scenarios requiring multi-point precise control in shipborne blasting devices, rocket multi-stage detonation sequences, and urban demolition projects.

[0040] The plasma ignition system includes a set of universal oscillation control components and several ignition tube components with independently configured frequencies, forming a one-to-many control topology. The structure of each ignition tube component is the same as that of Example 1, but the resonant frequency of its hollow resonant coil 5 is independently designed. Typical configurations include different frequencies such as 13.56MHz, 14.12MHz, 15.30MHz, and 17.85MHz to avoid interference between different channels. The oscillation control component integrates a frequency switching module, an address encoding module, and a multi-channel output port. The control unit can activate excitation signals of different frequencies one by one through programmable settings. Each time it is activated, the excitation coil 7 only transmits a signal to the ignition tube 1 with the corresponding frequency matching, ensuring that a single detonation event does not affect other unactivated points. In addition, the oscillator circuit module integrates an ignition feedback module, which can monitor the excitation state of each channel in real time and return a confirmation signal. The excitation power is adjustable according to the channel type, ranging from 5W to 30W. The ignition delay time is precisely controllable, and the ignition sequence can be preset, remotely or automatically scheduled according to mission requirements. This plasma ignition system not only improves system controllability, but also significantly reduces the risk of cable connection and triggering errors, and has high industrial application promotion value.

[0041] How it works During the work process, the specific work process is as follows Figure 3As shown, it is divided into five core stages: insertion → matching → excitation → discharge → ignition. First, the oscillation control component is inserted into the ignition tube component, and the ignition tube 1 is fixed to the coil bracket 8 through the mounting flange 2. That is, at this time, the excitation coil 7 on the coil bracket 8 and the insulating tube of the inner circle of the hollow resonant coil 5 of the ignition tube 1 are plugged in and matched. The control system is started, and the ignition pulse 11 is input to the input port 10 of the oscillator circuit module. After the input protection unit performs overcurrent and overvoltage protection, the rectifier and filter unit 15 converts the uncertain polarity DC power of the ignition pulse 11 into a certain polarity DC power, realizing bipolar triggering and filtering out high-frequency noise. At the same time, the energy storage unit 16 provides a DC voltage to the DC / DC circuit unit. The DC / DC circuit unit converts the DC voltage provided by the energy storage unit into a voltage suitable for the operation of the LC oscillator 20. The window voltage comparison unit 18 monitors the voltage pulse amplitude of the energy storage unit and detects the voltage pulse amplitude. When the starting pulse amplitude threshold is met, the delay unit 19 triggers the LC oscillator 20 with a delay. The LC oscillator 20 then outputs a high-frequency excitation signal 12 at a set frequency. This high-frequency excitation signal 12 enters the excitation coil 7 from the output port 21 of the oscillator circuit module. The excitation coil 7 then emits electromagnetic energy, which forms an inductive coupling with the hollow resonant coil 5 and generates LC resonance. This LC resonance causes the discharge component to generate a high-intensity electric field, which excites plasma on the surface of the gunpowder 4. The plasma directly acts on the metal-powdered three-base passivation charge, causing it to ignite rapidly and then ignite the main charge through the flame transfer hole 3. The entire ignition response time is less than 100 nanoseconds, the ignition energy is controllable, and the process is highly precise and reliable.

[0042] Example 3 Example 3 provides a split-type plasma ignition device for igniting a solid rocket motor. The device's overall structure is essentially the same as that of Example 1, differing in that the ignition tube assembly contains a high-density, three-base passivated propellant specifically designed for high-thrust engines. Nanoaluminum powder and an oxidizer are added to the propellant to improve ignition success rates. The ignition tube 1 is bolted to the ignition interface of the engine nozzle, with the flame transfer port 3 aligned directly with the engine's main combustion chamber.

[0043] During ignition, the oscillation control component generates a high-frequency excitation signal 12 at a frequency of 13.56MHz and a power output of 20W. This generates a high-temperature plasma exceeding 6000K within nanoseconds, ensuring successful ignition of the engine's main charge within milliseconds. This application scenario is suitable for solid propulsion systems on medium- to large-scale rockets requiring high-reliability ignition, and supports stable ignition in extreme environments such as cold regions and low oxygen levels.

[0044] Example 4 Example 4 provides a split plasma ignition device for igniting passivated flares, which is applied to plasma ignition of passivated flares. That is, the overall structure of the device is basically the same as that of Example 1, except that the ignition tube assembly is adapted to passivated flares with a body diameter of Φ60 mm, and the gunpowder 4 is a highly stable three-base passivating agent, mainly composed of guanidine nitrate, ammonium peroxide and nitroamidine, and doped with trace metal aluminum powder to improve the ignition responsiveness.

[0045] During use, the oscillation control assembly can be deployed in a portable manner and is triggered by the onboard ignition power supply. The ignition pulse signal enters the oscillator circuit module 9 through the input port 10. The excitation frequency is set to 13.56MHz, the output power is 8W, and the radio frequency signal forms a strong LC resonance through the excitation coil 7 and the hollow resonant coil 5. The discharge needle 6 generates a high-intensity electric field, which excites the plasma on the surface of the gunpowder 4 to form a high-temperature plasma above 5000K. The high-temperature plasma acts on the charge column, effectively igniting the charge column inside the flare, achieving fast and reliable ignition. This embodiment solves the problems of insufficient ignition safety and poor environmental adaptability of traditional flares and is suitable for a variety of application scenarios such as shipboard, airdrop, and emergency signaling.

[0046] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A split plasma ignition device for passivation agent, characterized in that: include: An ignition tube assembly includes an ignition tube having two interconnected cavities, one of which is filled with gunpowder and has a fire transmission hole provided on the wall of the corresponding cavity; an insulating tube is provided on the inner wall of the other cavity, a hollow resonant coil is provided around the outer circumference of the insulating tube, a discharge component is connected to the hollow resonant coil, and an end of the discharge component contacts the gunpowder; and an oscillation control assembly, comprising: a coil support on which an excitation coil is wound, an oscillator circuit module connected to the excitation coil being provided on a side of the coil support facing away from the excitation coil; Among them, the excitation coil on the coil bracket is used to plug and cooperate with the insulating tube in the ignition tube; the ignition pulse excites the oscillator circuit module to generate a high-frequency excitation signal, which is released through the excitation coil and coupled to the hollow resonant coil in an electromagnetic induction manner to form LC resonance. The LC resonance causes the discharge component to generate a high-intensity electric field, and the high-intensity electric field excites the plasma on the surface of the gunpowder to ignite the gunpowder and complete the ignition.

2. A split plasma ignition device for passivation medicine according to claim 1, characterized in that: The gunpowder uses a three-base passivation powder with added metal powder.

3. A split type plasma ignition device for passivation medicine according to claim 1, characterized in that: The discharge component is an elastic discharge needle, wherein the needle tip of the discharge needle faces the central area of ​​the gunpowder.

4. A split type plasma ignition device for passivation medicine according to claim 1, characterized in that: The oscillator circuit module includes: LC oscillator, used to generate a high-frequency excitation signal of a specific frequency; Input protection unit, which is used to protect the ignition pulse from overcurrent and overvoltage; The rectifier and filter unit is used to convert the DC power of uncertain polarity in the ignition pulse into DC power of certain polarity, realize bipolar triggering and filter out high-frequency noise; Energy storage unit, used to store electrical energy and supply energy; A DC / DC circuit unit, used for converting the DC voltage provided by the energy storage unit into a voltage suitable for the operation of the LC oscillator; The window voltage comparison unit is used to monitor the voltage pulse amplitude of the energy storage unit in real time and trigger the LC oscillator to work when the voltage pulse amplitude meets the starting pulse amplitude threshold; The input port of the oscillator circuit module is used to input an ignition pulse, and the output port of the oscillator circuit module is electrically connected to the excitation coil.

5. A split type plasma ignition device for passivation medicine according to claim 4, characterized in that: The input protection unit includes: a fuse and a current limiting resistor connected in series between the input port of the oscillator circuit module and the rectification and filtering unit.

6. A split type plasma ignition device for passivation medicine according to claim 4, characterized in that: Also includes: The delay unit is arranged between the window voltage comparison unit and the LC oscillator, and is used for delaying triggering the LC oscillator after the voltage monitored by the window voltage comparison unit meets the start threshold.

7. A split type plasma ignition device for passivation medicine according to claim 1, characterized in that: The ignition tube is mechanically locked with the coil support of the oscillation control component by means of bolt connection, snap connection or elastic snap-in.

8. A split type plasma ignition device for passivation medicine according to claim 3, characterized in that: The discharge needle is made of one of tungsten, stainless steel, and graphene, or a composite material of the two.

9. A split type plasma ignition device for passivation medicine according to claim 1, characterized in that: A metal shielding layer is provided inside the shell of the ignition tube, and the metal shielding layer is used to prevent the gunpowder, hollow resonant coil and discharge components inside the ignition tube from being interfered by external high-frequency signals.

10. A multi-channel radio frequency plasma ignition system supporting parallel control of multiple ignition tubes, characterized in that: include: An oscillation control component and a plurality of independently frequency-configured ignition tube assemblies in the plasma ignition device according to any one of claims 1 to 9, wherein the resonant frequency of the hollow resonant coil of each ignition tube assembly is different, and the oscillation control component integrates a frequency switching module, an address encoding module, and a multi-channel output port.

Images