Multi-stage safety ignition system based on missile-boat communication

Abstract

The invention discloses a multi-stage safety ignition system based on missile-boat communication, which comprises a boat-mounted device and a missile-mounted device, the ship-mounted device is electrically connected with the missile-mounted device, the ship-mounted device is electrically connected with an upper computer, the ship-mounted device is fixedly connected with the missile-mounted device through a plugging structure, and the upper computer is electrically connected with the ship-mounted device. The plugging structure is connected with a motor; the boat-mounted device comprises a first power supply control module, a first microprocessor, a first signal acquisition module, a first data storage module and a first communication line channel, and the first microprocessor independently communicates with the upper computer, the missile-mounted device and the motor to complete instruction transmission and data interaction work; the missile-borne device comprises a second power supply control module, a second microprocessor, a second signal acquisition module, a second data storage module, a second communication line channel and an ignition circuit. The multi-stage safety ignition system based on missile and boat communication is clear in structure, safe and multi-stage, and unmanned operation in the shell ignition process is met.

Description

Technical Field

[0001] The present invention relates to the technical field of communication and ignition control, and in particular to a multi-level safety ignition system based on missile boat communication. Background Art

[0002] In the modern military and aerospace fields, the safety and reliability of missile-borne weapons such as missiles and torpedoes are of vital importance. Regarding the ignition method of underwater missile-borne weapons, the existing communication and ignition systems still face some problems in practical applications. For example, in a high-interference environment or severe weather conditions, the communication signal may be interfered with or attenuated, affecting the reliability of the system. Secondly, the traditional single-stage ignition system has safety hazards. Once the communication fails, it may cause mis-ignition or ignition failure, and even threaten the safety of personnel during ground testing. In addition, the existing ignition system is relatively simple in design in terms of multi-level safety, which is difficult to meet the high requirements of modern military missions for safety and complexity.

[0003] In the prior art, the multi-level safe ignition method is mainly based on the isolation of the ignition voltage and the on-off of the relay, but these device-based isolation methods obviously cannot fully realize the safety of the test process. There is a common phenomenon that many situations in the ignition test are not handled, such as mis-ignition, ignition failure, ignition stop, ignition lock (no ignition will be caused by sending any command), etc., which cannot truly achieve unmanned ignition process, nor can it truly realize multi-level safety processing of the ignition system.

[0004] The Chinese patent application number CN202410167312.5 discloses a portable ignition control system and method. First, an ignition command is sent to a main control unit through an RS232 serial port via a touch screen; then the main control unit sequentially controls the corresponding relays in the relay matrix according to the signal control amplifier circuit, thereby controlling the sample tank to spray powder into the explosion tank; after waiting for the powder spraying time to end, the main control unit controls the ignition, thereby realizing the dust explosion in the explosion tank; finally, after the ignition delay time ends, the control relay is disconnected. However, this method uses the RS232 serial port as a communication method for sending instructions, and the transmission distance will be limited, generally not exceeding 15 meters, which limits its application in long-distance communication occasions. In addition, for scenes that require high-speed data transmission such as real-time viewing, the maximum transmission rate of RS232 is relatively low. In addition, the anti-interference ability of RS232 is relatively weak, and it is easily affected by electromagnetic interference and noise, which may cause errors or losses in data transmission. Importantly, for ignition scenes, multi-level safety is particularly important. Although this method has an abnormal termination function, the multi-level safety processing of the ignition function is still not in place.

[0005] The Chinese patent application number CN202311128025.5 discloses an ignition system and explosion device for explosives, which are mainly composed of a bus control circuit, a channel control circuit, an ignition circuit and an explosive bridge wire. The bus control circuit is divided into a primary bus control and a secondary bus control, and the channel control circuit is divided into a first channel control and a second channel control. The ignition circuit is divided into a first relay, a second relay and a third relay. In actual testing, the primary bus is first controlled to turn on the MOS tube, and then the secondary bus is controlled to turn on the first relay. Next, the channel control circuit is used to select the second relay and the third relay to turn on to complete the ignition work. However, this method fails to effectively handle situations such as mis-ignition, temporary cancellation of the ignition plan, and secondary ignition after ignition failure, and cannot completely prevent the occurrence of similar situations, and cannot effectively guarantee the safety of the experimenters. Summary of the invention

[0006] The purpose of the present invention is to provide a multi-level safety ignition system based on missile-boat communication to solve the problems raised by the above-mentioned background technology. The physical + program ignition method and the automatic locking ignition function adopted can meet the unmanned operation and high safety of the artillery shell ignition process.

[0007] To achieve the above-mentioned object, the present invention provides a multi-level safety ignition system based on missile-boat communication, comprising a ship-borne device and a missile-borne device, the ship-borne device and the missile-borne device are electrically connected, the ship-borne device is electrically connected to a host computer, the ship-borne device is fixedly connected to the missile-borne device through a plug-in structure, and the plug-in structure is connected to a motor;

[0008] The boat-borne device includes a first power supply control module, a first microprocessor, a first signal acquisition module, a first data storage module and a first communication line. The first microprocessor communicates independently with the host computer, the missile-borne device and the motor to complete command transmission and data interaction. The missile-borne device includes a second power supply control module, a second microprocessor, a second signal acquisition module, a second data storage module, a second communication line and an ignition circuit.

[0009] Preferably, the first power supply control module is used to receive a control signal from the first microprocessor and provide a power supply voltage to the first microprocessor, the first signal acquisition module, the first data storage module and the first communication line;

[0010] The first microprocessor is used to output a control signal of the first power supply control module, receive a signal from the first signal acquisition module, and complete the data storage and reading work of the first signal acquisition module;

[0011] The first signal acquisition module is used to collect key signals during the test, including pressure signals and posture signals;

[0012] The first data storage module is used to store the collected signals without losing data due to power failure. After the test is completed, the data in the memory is read and the underwater data of the onboard device is analyzed.

[0013] The first communication channel is used to undertake the communication task with the host computer and the missile-borne device, and is responsible for transmitting heartbeat packets, instructions and data.

[0014] Preferably, the second power supply control module is used to receive a control signal from the second microprocessor and provide a power supply voltage to the second microprocessor, the second signal acquisition module, the second data storage module, the second communication line and the ignition circuit;

[0015] The second microprocessor is used to output the control signal of the second power supply control module, complete the signal acquisition and data storage of the second signal acquisition module, complete the output of the ignition signal in the ignition circuit, and complete the reception of the control instruction sent by the onboard device through the second communication line;

[0016] The second signal acquisition module is used to collect key signals during the test, including pressure signals and posture signals;

[0017] The second data storage module is used to store the collected signals without losing data when power is off, and after the missile body is recovered, the data in the memory is read to analyze the missile body posture data;

[0018] The second communication channel is used to undertake the communication task with the onboard device and is responsible for transmitting heartbeat packets, instructions and data;

[0019] The ignition circuit is used to receive the ignition control instruction of the second microprocessor, output an ignition voltage signal, and complete the ignition work.

[0020] Preferably, the power supply control of the first power supply control module selects an external battery or an external voltage regulator as the power supply for the onboard device, and inputs the power supply voltage to the first microprocessor, the first signal acquisition module, the first data storage module and the first communication line;

[0021] The external battery or the external voltage stabilizing source generates an external voltage signal, and the isolation between the external voltage signal and the boat-borne device adopts a relay plus triode isolation method.

[0022] Preferably, the pressure signal in the first signal acquisition module is acquired by using a sensor module in combination with a peripheral circuit built around an operational amplifier, and the pressure signal reflects depth information;

[0023] The gesture signal is collected by using a sensor module in combination with a peripheral resistor-capacitor circuit. The gesture signal includes three-axis acceleration, three-axis angular velocity and three-axis angle.

[0024] Preferably, the first data storage module is implemented by using a FLASH memory chip that does not lose data when power is off to build a peripheral resistor and capacitor circuit;

[0025] The first data storage module allows the host computer to send instructions to read data in the memory.

[0026] Preferably, the first communication channel includes RS-485 channel I, RS-485 channel II and RS-485 channel III, and the command communication and data transmission are completed with the host computer through RS-485 channel I, the command transmission and data interaction are completed with the missile-carrying device through RS-485 channel II, and the driving work of the plug-in structure is completed with the motor through RS-485 channel III;

[0027] The second communication channel includes RS-485 channel II, which completes the reception of control instructions sent by the boat-borne device via RS-485 channel II and sends the instructions to the second microprocessor.

[0028] Preferably, the power supply control of the second power supply control module selects an external battery or an external voltage regulator as the power supply for the missile-borne device, and inputs the power supply voltage to the second microprocessor, the second signal acquisition module, the second data storage module, the second communication line and the ignition circuit;

[0029] The external battery or the external voltage stabilizing source generates an external voltage signal, and the isolation between the external voltage signal and the missile-carrying device adopts a relay plus triode isolation method.

[0030] Preferably, the second microprocessor completes the reception of control instructions sent by the boat-borne device through the second communication channel, undertakes the control instruction output of the second power supply control module, receives the signal of the second signal acquisition module and sends it to the host computer for display in real time, completes the data storage and reading of the signal acquisition of the second signal acquisition module, and completes the instruction transmission and data interaction work of communicating with the boat-borne device.

[0031] Preferably, the ignition circuit adopts a physical + program ignition method, specifically:

[0032] First, whether the voltage signal of the ignition circuit is input is used as the first-level safety processing;

[0033] Secondly, the physical ignition method uses a normally closed relay, which is in an isolated state as a secondary safety treatment;

[0034] Then, the program ignition method uses the determination of whether the heartbeat packet is disconnected as the third-level safety processing;

[0035] Finally, the ignition voltage output in the ignition circuit and the second microprocessor detect the designed control instructions as the fourth level of safety processing.

[0036] Therefore, the present invention adopts the above-mentioned multi-level safety ignition system based on missile boat communication, and the beneficial effects are as follows:

[0037] (1) The first microprocessor and the second microprocessor of the present invention both adopt on-board microcontroller chips, which reduces the need for connectors and other external components, occupies less space, reduces manufacturing costs and improves the reliability of the overall system, reduces the length and resistance of electrical connections, improves the reliability and speed of signal transmission, and helps reduce power consumption.

[0038] (2) The present invention adopts a multi-channel communication line method to ensure that there is no redundancy between signals, reduce the probability of signal electromagnetic interference, adopt RS485 communication method, support multi-point communication, have strong anti-interference ability, and be suitable for complex electromagnetic environments. It improves the reliability of the system and increases the signal transmission length while ensuring the signal transmission quality.

[0039] (3) The present invention is provided with an onboard battery charging function, and the battery charging function can still be completed during the dive of the missile body and before the air plug is separated, thereby effectively preventing the situation in which the ignition circuit cannot output the ignition voltage normally due to insufficient battery power after the actual missile body is launched.

[0040] (4) The present invention adopts a four-level safety processing ignition method, which adopts physical + procedural safety processing. Only when both physical and procedural conditions are met will the ignition process be entered, and an ignition lock function is also provided to ensure the all-round safety of the test process for the experimenter, and meet the unmanned and safety requirements of the test process.

[0041] The technical solution of the present invention is further described in detail below through the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Figure 1 It is an overall flow chart of an embodiment of a multi-level safety ignition system based on missile boat communication of the present invention;

[0043] Figure 2 It is a structural block diagram of a first power supply control module of an embodiment of a multi-level safety ignition system based on missile boat communication of the present invention;

[0044] Figure 3 The present invention is a block diagram of the ignition circuit structure of a multi-level safety ignition system embodiment based on missile boat communication.

[0045] Reference numerals

[0046] 1. First relay; 2. Second relay; 3. Third relay; 4. First transistor; 5. Second transistor; 6. Third transistor; 7. Voltage conversion module; 8. Isolated gate driver; 9. N-channel MOSFET field effect transistor; 10. Ignition head connector; 11. Normally closed relay. DETAILED DESCRIPTION

[0047] The technical solution of the present invention is further described below through the accompanying drawings and embodiments.

[0048] Unless otherwise defined, the technical terms or scientific terms used in the present invention should be understood by people with ordinary skills in the field to which the present invention belongs. The words "first", "second" and similar words used in the present invention do not indicate any order, quantity or importance, but are only used to distinguish different components. "Include" or "comprise" and similar words mean that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, without excluding other elements or objects. "Connect" or "connected" and similar words are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. "Up", "down", "left", "right" and the like are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0049] Embodiment 1

[0050] like Figure 1 As shown, a multi-level safety ignition system based on missile-boat communication includes a missile-borne device and a boat-borne device, and the ship-borne device is electrically connected to a host computer. The ship-borne device and the missile-borne device are connected through a plug-in structure, and the plug-in structure is driven by a motor to realize the connection or separation of the ship-borne device and the missile-borne device. When the ship-borne device is connected to the missile-borne device, the ship-borne device and the missile-borne device are electrically connected; when the ship-borne device and the missile-borne device are separated, the ship-borne device and the missile-borne device cannot transmit electrical signals.

[0051] The boat-borne device includes a first power supply control module, a first microprocessor, a first signal acquisition module, a first data storage module and a first communication line. The missile-borne device includes a second power supply control module, a second microprocessor, a second signal acquisition module, a second data storage module, a second communication line and an ignition circuit.

[0052] The first power supply control module is used to provide power supply voltage to the first microprocessor, the first signal acquisition module, the first data storage module and the first communication line. The power supply of the onboard device is mainly provided by an external battery or an external voltage regulator. The selection method is that the first microprocessor outputs a control instruction to the first power supply control module. Figure 2As shown, the first power supply control module includes a first relay 1, a second relay 2, a third relay 3, a first transistor 4, a second transistor 5, a third transistor 6 and an external resistor-capacitor circuit, and the external resistor-capacitor circuit includes an external battery and an external voltage stabilizing source.

[0053] The input pin of the first relay 1 is connected to the positive pin of the external battery, the input pins of the second relay 2 and the third relay 3 are connected to the positive pin of the external voltage regulator, the output pins of the first relay 1, the second relay 2 and the third relay 3 are connected to the power supply input pins of the first microprocessor, the first signal acquisition module, the first data storage module and the first communication line, the positive power supply of the first relay 1 is directly connected to the external battery, the negative power supply of the first relay 1 is directly connected to the collector of the first transistor 4, the emitter of the first transistor 4 is connected to the board ground, the base of the first transistor 4 is connected to the power supply control instruction output pin of the first microprocessor, the positive power supply of the second relay 2 and the third relay 3 is directly connected to the external voltage regulator, the negative power supply of the second relay 2 and the third relay 3 is respectively connected to the collector of the second transistor 5 and the third transistor 6, the emitter of the second transistor 5 and the third transistor 6 is connected to the board ground, and the base of the second transistor 5 and the third transistor 6 is connected to the power supply control instruction output pin of the first microprocessor. When the power supply control command output pin is at a high level, the collector and emitter of the transistor are turned on, and the relay starts working when it is powered on. Turning on the first relay 1 selects an external battery as the power supply for the boat-borne device, turning on the second relay 2 selects an external voltage stabilizer as the power supply for the boat-borne device, and turning on the third relay 3 can charge the external battery.

[0054] The first power supply control module of the missile-borne device is substantially the same as the second power supply control module of the boat-borne device, except that the second power supply control module of the missile-borne device is also used to provide power supply voltage to the ignition circuit.

[0055] The first microprocessor of the boat-borne device is a high-performance, low-cost, low-power 32-bit microcontroller chip based on the ARMCortex-M core produced by ST. It is electrically connected to the first power supply control module, the first signal acquisition module, the first data storage module, and the first communication line. The first microprocessor is used to output power supply control instructions to the first power supply control module to select the main power supply of the system. The ADC acquisition pin built into the microcontroller chip is connected to the first signal acquisition module to collect real-time data in the boat-borne device test. The SPI communication pin built into the microcontroller chip is connected to the first data storage module to complete the key data storage during the system test. The microcontroller chip also interacts with the host computer, the missile-borne device, and the motor transmission control instructions and data through the first communication line.

[0056] The second microprocessor of the missile-borne device is basically the same as the first microprocessor of the boat-borne device. The difference is that the second communication channel of the second microprocessor is only responsible for transmitting instructions and data interaction with the boat-borne device, and the second microprocessor of the missile-borne device is also connected to the ignition circuit to output ignition instructions and complete the ignition function.

[0057] The first signal acquisition module of the onboard device is mainly used to collect pressure signals, attitude signals and external battery power during system testing. There is a mathematical fitting relationship between the pressure signal and the underwater depth. The depth information can be calculated based on the pressure signal data. The pressure signal acquisition is achieved by using a sensor module with a peripheral circuit built around an operational amplifier.

[0058] Specifically, the pressure signal sensor module uses a two-wire pressure sensor, and the output physical quantity is a current value of 4-20mA. A resistor circuit and a resistor-capacitor filter circuit are set before the input pin of the operational amplifier. The current signal is converted into a voltage signal through the resistor circuit, and then input into the operational amplifier after the resistor-capacitor filter circuit. The output pin of the operational amplifier is connected to the ADC acquisition pin of the first microprocessor to complete the pressure signal acquisition. The attitude signal acquisition is realized by using a sensor module with an external resistor-capacitor circuit. The attitude signal sensor module is composed of a nine-axis attitude sensor and a three-axis accelerometer. The three-axis angle, three-axis angular velocity, and three-axis acceleration signals can be collected through the attitude signal sensor module. The output pin of the attitude signal sensor module is connected to the serial port pin of the first microprocessor to complete the data acquisition work, so that it is convenient to check at any time whether the external battery power supports the underwater operation of the system. The voltage of the external battery is reduced to 0-3.3V by a resistor voltage divider circuit and then connected to the ADC acquisition pin of the first microprocessor to complete the external battery power acquisition work. The second signal acquisition module of the missile-borne device is exactly the same as the first signal acquisition module of the boat-borne device.

[0059] The first data storage module of the boat-borne device mainly completes the data storage work of the first signal acquisition module during the system ignition performance test. The memory uses a FLASH chip with a large storage space of 512Mbits, which has the characteristics of no data loss during power failure and flexibility beyond ordinary serial flash memory devices. The FLASH chip is connected to the first microprocessor SPI communication. The boat-borne device uses two FLASH chips, one for normal data storage and the other for acquisition data backup. The second data storage module of the missile-borne device is exactly the same as the first data storage module of the boat-borne device.

[0060] The first communication channel of the boat-borne device mainly includes RS-485 channel I, RS-485 channel II and RS-485 channel III. RS-485 channel I is responsible for the transmission of instructions and data interaction between the boat-borne device and the host computer. RS-485 channel II is responsible for the communication between the boat-borne device and the missile-borne device, completing the missile-boat communication, and the transmission content includes control instructions and collected data. In this embodiment, the plug-in structure is an aviation plug, and RS-485 channel III is responsible for sending drive instructions to the motor to control the plug-in structure to unplug the aviation plug and start the ignition function test. The instructions sent by the host computer include relevant control instructions sent to the boat-borne device, and the transmission and real-time boat-borne device data query are completed by RS-485 channel I. The instructions sent by the host computer also include relevant control instructions sent to the missile-borne device. The boat-borne device acts as a transfer station, and transmits the control instructions of the missile-borne device to the first microprocessor of the boat-borne device via RS-485 channel I, and then sends them to the missile-borne device via RS-485 channel II to complete the relevant operations. The real-time data of the missile-borne device is also sent to the boat-borne device via RS-485 channel II, and then sent to the host computer via RS-485 channel I for display. The instructions sent by the host computer also include the working instructions of the drive motor, which are sent to the boat-borne device via RS-485 channel I. The boat-borne device acts as a transfer station and sends them to the motor via RS-485 channel III, driving the click to complete the plug-in and unplug operation. In addition, the missile-borne device and the boat-borne device are set to send heartbeat packets to each other through RS-485 channel II to detect whether the aviation plug is disconnected. Once the aviation plug is disconnected, the program detects the disconnection of the heartbeat packet, and enters the ignition test process after a period of time.

[0061] The second communication channel of the missile-borne device is partially the same as the first communication channel of the boat-borne device. The similarity is that the missile-borne device also uses RS-485 channel II as the channel for sending heartbeat packets to each other. The difference is that the missile-borne device only uses one RS-485 channel to complete the functions of sending heartbeat packets, receiving control commands, and sending data.

[0062] The ignition circuit of the missile-carrying device mainly receives the ignition signal output by the second microprocessor and outputs the ignition voltage. Figure 3As shown, the ignition circuit includes a voltage conversion module 7, an isolated gate driver 8, an N-channel MOSFET field effect transistor 9, an ignition head plug terminal 10, and a normally closed relay 11. The second microprocessor outputs a power supply control instruction to select a power supply voltage, and inputs the power supply voltage into the voltage conversion module 7. The voltage conversion module 7 converts the input voltage into a voltage value of an ignition signal. The voltage conversion module 7 has an output power of up to 30W, a conversion efficiency of up to 90%, input undervoltage protection, output short circuit, overcurrent protection and other characteristics. The ignition signal voltage value output by the voltage conversion module 7 is connected to the power supply voltage input pin of the isolated gate driver 8 and the input end of the normally closed relay 11. The function of the isolated gate driver 8 is to receive the ignition signal output by the second microprocessor and turn on the N-channel MOSFET field effect transistor 9. The output pin of the isolated gate driver 8 is connected to the gate G of the N-channel MOSFET field effect transistor 9, the source S of the N-channel MOSFET field effect transistor 9 is connected to the board ground, the drain D of the N-channel MOSFET field effect transistor 9 is connected to one pin of the ignition head connector terminal 10, and the other pin of the ignition head connector terminal 10 is connected to the output end of the normally closed relay 11.

[0063] The function of the normally closed relay 11 is to isolate the ignition voltage. When the normally closed relay 11 is in the power supply voltage state, the normally closed relay 11 maintains the isolation state, and always isolates one pin of the ignition head connector terminal 10 from the output pin of the normally closed relay 11. When the voltage signal of the ignition circuit is not input, as a first-level safety process, when the ignition function is tested, the second microprocessor outputs a power supply control instruction to select the main power supply and completes the first-level ignition condition. The normally closed relay 11 is in an isolated state. As a second-level safety process, the second microprocessor outputs an instruction to unplug the aviation plug, drives the plug-in structure to unplug the aviation plug, and the power supply pin of the normally closed relay 11 and the RS-485 line II are unplugged. The normally closed relay 11 is in a power-off state, the isolation state disappears, and one pin of the ignition head connector terminal 10 is connected to the output pin of the normally closed relay 11, meeting the second-level ignition condition of physical ignition. The heartbeat packet mutual transmission state is a third-level safety process. When the second microprocessor detects that the heartbeat packet is disconnected, it enters the third-level ignition program.

[0064] Before the ignition voltage in the ignition circuit is output, the second microprocessor does not detect the designed control instruction. As a fourth-level safety process, the control instruction is specifically: the second microprocessor outputs a high-level ignition signal to the isolated gate driver 8, and the output pin of the isolated gate driver 8 will output voltage and form a voltage difference with the source S of the N-channel MOSFET field effect transistor 9. The MOSFET field effect transistor 9 will be turned on, and the drain D and the source S will form a loop to meet the fourth-level ignition conditions. When the system meets the fourth-level ignition conditions, it will output the ignition voltage and complete the ignition function.

[0065] The system also has an ignition lock function. When the first-level ignition conditions are met, but the aviation plug is not unplugged within the specified time, the system will automatically start the lock ignition function to prevent accidental ignition from causing casualties to test personnel. Specifically, before the ignition test, the system real-time status, battery power and other information can be queried through instructions. Sending any instructions other than the wake-up ignition function instruction will not enter the ignition process. In the formal ignition test, only when the wake-up ignition function instruction is sent and the ignition conditions are physically met within a period of time, will the ignition process be entered. If the wake-up ignition function instruction is sent, but the ignition plan is temporarily canceled and no measures are taken for a period of time, that is, the physical ignition conditions are not met, the ignition circuit is automatically locked to meet the unmanned and safety of the test process.

[0066] Usage process:

[0067] The aviation plug cable includes the signal A line and signal B line of RS-485 line II, and the positive and negative power supply lines of the normally closed relay in the ignition circuit. The shipborne device connection cable also includes the positive and negative poles of the external battery, the positive and negative poles of the external voltage regulator, the positive and negative poles of the motor power supply, the signal A line of RS-485 line I and RS-485 line III, and the signal B line. The missile-borne device connection cable also includes the positive and negative poles of the external battery, and the positive and negative poles of the external voltage regulator. To ensure safety during the test, the battery is in a power-free state when connected to the shipborne device and the missile-borne device.

[0068] The first step is to charge the external battery: turn on the output of the external voltage regulator. At this time, both the shipborne device and the missile-borne device are powered on. The host computer sends a charging instruction for the external battery of the boat-borne device through RS-485 channel I. After receiving the instruction, the first microprocessor returns the same instruction as the charging instruction for the external battery of the boat-borne device as the first response of the external battery. The host computer sends a charging instruction for the external battery of the missile-borne device through RS-485 channel I. After receiving the instruction, the first microprocessor sends the instruction to the second microprocessor through RS-485 channel II. After receiving the instruction, the second microprocessor returns the same instruction as the charging instruction for the external battery of the missile-borne device through RS-485 channel II as the second response of the external battery. After receiving the second response of the external battery, the first microprocessor sends it to the host computer through RS-485 channel I.

[0069] The second step is to query the current device status: the host computer sends the current status query instruction of the boat-borne device through RS-485 channel I. After receiving it, the first microprocessor returns the current status data packet of the boat-borne device. The current status data packet of the boat-borne device includes: external battery power, pressure value, three-axis acceleration, three-axis angular velocity, and three-axis angle; the host computer sends the current status query instruction of the missile-borne device through RS-485 channel I. After receiving it, the first microprocessor sends it to the second microprocessor through RS-485 channel II. After receiving it, the second microprocessor returns the current status data packet of the missile-borne device through RS-485 channel II. After receiving the current status data packet of the missile-borne device, the first microprocessor sends it to the host computer through RS-485 channel I. The current status data packet of the missile-borne device includes: external battery power, pressure value, three-axis acceleration, three-axis angular velocity, and three-axis angle.

[0070] The third step is to select the external battery as the main power supply: the host computer sends the external battery power supply control command of the boat-borne device through RS-485 line I. After receiving it, the first microprocessor outputs a control signal to the first power supply control module, isolates the second transistor 5 and the third transistor 6, then turns on the first transistor 4, turns off the second relay 2 and the third relay 3, and finally turns on the first relay 1. Finally, the first microprocessor returns the same content as the external battery power supply control command of the boat-borne device through RS-485 line I as the first external battery power supply response; the host computer sends the missile-borne device through RS-485 line I. The first microprocessor receives the external battery power supply control instruction, which is sent to the second microprocessor through RS-485 line II. After receiving the external battery power supply control instruction, the second microprocessor outputs a control signal to the second power supply control module to isolate the transistor and relay related to the external voltage regulator, and then turn on the transistor and relay related to the external battery. Finally, the second microprocessor returns the content that is exactly the same as the external battery power supply control instruction of the missile-borne device through RS-485 line II as the second external battery power supply response. After receiving the second external battery power supply response, the first microprocessor sends it to the host computer through RS-485 line I.

[0071] The fourth step is to start the ignition process: the host computer turns on the heartbeat packet mutual transmission function. At this time, the boat-borne device and the missile-borne device are in the process of sending heartbeat packets to each other. The heartbeat packet returned by the missile-borne device to the boat-borne device can be seen on the host computer. The host computer sends a motor drive instruction to the first microprocessor through the RS-485 line I. After receiving the instruction, the first microprocessor sends the motor drive instruction to the motor through the RS-485 line III. After receiving the instruction, the motor rotates, driving the plug-in structure to unplug the aviation plug connecting the boat-borne device and the missile-borne device. At this time, the heartbeat packet transmission is disconnected, and the power supply of the normally closed relay 11 is disconnected. After the second microprocessor detects that the heartbeat packet is disconnected, it delays for a period of time and inputs a high-level ignition signal to the isolated gate driver 8. The output pin of the isolated gate driver 8 will output voltage and form a voltage difference with the source S of the N-channel MOSFET field effect transistor 9. The drain D and the source S will form a loop, and the MOSFET will be turned on, meeting the last level ignition condition (fourth level ignition condition). The ignition terminal is externally connected to an ignition head with gunpowder, and the internal type fuse structure has an internal resistance of about 0.5Ω. When the ignition terminal outputs the ignition voltage, the current value is approximately equal to the current value required for the fuse to reach the critical point of melting. It will melt after a few seconds and ignite the ignition head with gunpowder to complete the ignition operation.

[0072] The fifth step is to read the stored data: the program is set to start collecting data 2s before the start of ignition and end data collection 20s after the end of ignition, that is, the memory stores the pressure and attitude data of the projectile for a total of 22s before and after ignition. The projectile is salvaged after the launch. When the projectile is salvaged, there is a waterproof aviation plug for the boat-borne device to connect. After the connection, the host computer sends a command to read the data of the projectile-borne device. The data is sent to the first microprocessor via RS-485 channel II and then to the host computer via RS-485 channel I.

[0073] Therefore, the present invention adopts the above-mentioned multi-level safety ignition system based on missile boat communication to solve a series of potential safety hazards existing in the traditional single-stage ignition system. The physical + program ignition method adopted by this system can effectively meet the high requirements of modern military missions for safety and complexity. The multi-level safety ignition system of this system can also realize unmanned and high safety during the ignition test. In addition, the automatic locking ignition function set in this system also provides a strong guarantee for the safety of experimental testers.

[0074] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that they can still modify or replace the technical solution of the present invention with equivalents, and these modifications or equivalent replacements cannot cause the modified technical solution to deviate from the spirit and scope of the technical solution of the present invention.

Claims

1. A multi-level safety ignition system based on missile boat communication, characterized in that: It includes a shipborne device and a missile-borne device, the shipborne device is electrically connected to the missile-borne device, the shipborne device is electrically connected to a host computer, the shipborne device is fixedly connected to the missile-borne device through a plug-in structure, and the plug-in structure is connected to a motor; The boat-borne device includes a first power supply control module, a first microprocessor, a first signal acquisition module, a first data storage module and a first communication line. The first microprocessor communicates independently with the host computer, the missile-borne device and the motor to complete command transmission and data interaction. The missile-borne device includes a second power supply control module, a second microprocessor, a second signal acquisition module, a second data storage module, a second communication line and an ignition circuit.

2. The multi-level safety ignition system based on missile boat communication according to claim 1 is characterized in that: The first power supply control module is used to receive the control signal of the first microprocessor and provide power supply voltage to the first microprocessor, the first signal acquisition module, the first data storage module and the first communication line; The first microprocessor is used to output a control signal of the first power supply control module, receive a signal from the first signal acquisition module, and complete the data storage and reading work of the first signal acquisition module; The first signal acquisition module is used to collect key signals during the test, including pressure signals and posture signals; The first data storage module is used to store the collected signals without losing data due to power failure. After the test is completed, the data in the memory is read and the underwater data of the onboard device is analyzed. The first communication channel is used to undertake the communication task with the host computer and the missile-borne device, and is responsible for transmitting heartbeat packets, instructions and data.

3. The multi-level safety ignition system based on missile boat communication according to claim 2 is characterized in that: The second power supply control module is used to receive the control signal of the second microprocessor and provide power supply voltage to the second microprocessor, the second signal acquisition module, the second data storage module, the second communication line and the ignition circuit; The second microprocessor is used to output the control signal of the second power supply control module, complete the signal acquisition and data storage of the second signal acquisition module, complete the output of the ignition signal in the ignition circuit, and complete the reception of the control instruction sent by the onboard device through the second communication line; The second signal acquisition module is used to collect key signals during the test, including pressure signals and posture signals; The second data storage module is used to store the collected signals without losing data when power is off, and after the missile body is recovered, the data in the memory is read to analyze the missile body posture data; The second communication channel is used to undertake the communication task with the onboard device and is responsible for transmitting heartbeat packets, instructions and data; The ignition circuit is used to receive the ignition control instruction of the second microprocessor, output an ignition voltage signal, and complete the ignition work.

4. The multi-level safety ignition system based on missile boat communication according to claim 3 is characterized in that: The power supply control of the first power supply control module selects an external battery or an external voltage regulator as the power supply for the onboard device, and inputs the power supply voltage to the first microprocessor, the first signal acquisition module, the first data storage module and the first communication line; The external battery or the external voltage stabilizing source generates an external voltage signal, and the isolation between the external voltage signal and the boat-borne device adopts a relay plus triode isolation method.

5. The multi-level safety ignition system based on missile boat communication according to claim 4 is characterized in that: The pressure signal in the first signal acquisition module is collected by using a sensor module in combination with a peripheral circuit built around an operational amplifier, and the pressure signal is used to reflect depth information; The gesture signal is collected by using a sensor module in combination with a peripheral resistor-capacitor circuit. The gesture signal includes three-axis acceleration, three-axis angular velocity and three-axis angle.

6. The multi-level safety ignition system based on missile boat communication according to claim 5 is characterized in that: The first data storage module is implemented by using a FLASH memory chip that does not lose data when power is off to build a peripheral resistor and capacitor circuit; The first data storage module allows the host computer to send instructions to read data in the memory.

7. The multi-level safety ignition system based on missile boat communication according to claim 6 is characterized in that: The first communication channel includes RS-485 channel I, RS-485 channel II and RS-485 channel III, through which command communication and data transmission are completed with the host computer, command transmission and data interaction are completed with the missile-borne device through RS-485 channel II, and driving work of the plug-in structure is completed with the motor through RS-485 channel III; The second communication channel includes RS-485 channel II, which completes the reception of control instructions sent by the boat-borne device via RS-485 channel II and sends the instructions to the second microprocessor.

8. The multi-level safety ignition system based on missile boat communication according to claim 7 is characterized in that: The power supply control of the second power supply control module selects an external battery or an external voltage regulator as the power supply of the missile-borne device, and inputs the power supply voltage to the second microprocessor, the second signal acquisition module, the second data storage module, the second communication line and the ignition circuit; The external battery or the external voltage stabilizing source generates an external voltage signal, and the isolation between the external voltage signal and the missile-carrying device adopts a relay plus triode isolation method.

9. The multi-level safety ignition system based on missile boat communication according to claim 8 is characterized in that: The second microprocessor completes the reception of control instructions sent by the boat-borne device through the second communication channel, undertakes the control instruction output of the second power supply control module, receives the signal of the second signal acquisition module and sends it to the host computer for display in real time, completes the data storage and reading of the signal acquisition of the second signal acquisition module, and completes the instruction transmission and data interaction work of communicating with the boat-borne device.

10. The multi-level safety ignition system based on missile boat communication according to claim 9 is characterized in that: The ignition circuit adopts a physical + program ignition method, specifically: First, whether the voltage signal of the ignition circuit is input is used as the first-level safety processing; Secondly, the physical ignition method uses a normally closed relay, which is in an isolated state as a secondary safety treatment; Then, the program ignition method uses the determination of whether the heartbeat packet is disconnected as the third-level safety processing; Finally, the ignition voltage output in the ignition circuit and the second microprocessor detect the designed control instructions as the fourth level of safety processing.

Images