A shadow rocket electronic fuze control system and method based on safety authentication

Abstract

The present application relates to a control system and method for an electronic fuze of a human shadow rocket based on security authentication, which belongs to the technical field of ignition control systems for artificial weather modification rockets, and includes a rocket launch controller and multiple rocket electronic fuzes. The rocket launch controller is connected to multiple rocket electronic fuzes and sends security authentication detection instructions. The energy supply unit in the rocket electronic fuze supplies power to the electronic fuze, the carrier communication unit is responsible for communicating with the rocket launch controller, the encryption unit processes communication data and onboard keys, and encrypted transmission ensures safety; the motion acquisition unit detects the rocket posture in real time; the charging unit charges the main control and ignition control units, the detection unit monitors the energy storage status, the rocket launch controller verifies the ignition password and issues an ignition command, the main control unit responds and outputs an ignition pulse, and the ignition control unit sequentially completes the launch, catalyst spreading and parachute opening operations. The present application improves the accuracy, safety and intelligence level of the ignition control of the human shadow rocket.

Description

Technical Field

[0001] The present application relates to the technical field of weather modification rocket ignition control systems, and in particular to a safety-authenticated human shadow rocket electronic fuze control system and method. Background Art

[0002] The shadow rocket is a special rocket used for artificial weather modification rocket operations. It is mainly used to spread cloud catalysts (such as silver iodide) to achieve the purpose of increasing rain (snow), preventing hail, eliminating fog, and preventing frost. It uses scientific and technological means to achieve artificial intervention in the weather, aiming to reduce the impact of meteorological disasters. With the continuous advancement and development of the shadow industry technology, traditional shadow rockets are difficult to meet the requirements of modern shadow rocket operations in terms of safety, accuracy, and scientificity.

[0003] At present, the control technology of traditional shadow rockets mainly relies on pyrotechnics such as fuses and detonators to ignite and detonate rockets. This detonation control method is relatively simple and it is difficult to achieve high-precision ignition control. At the same time, due to the lack of sensors and information processing systems, it is impossible to obtain and process operation information in real time, making traditional shadow rockets less secure, and data is prone to being intercepted or tampered with during transmission. Therefore, how to improve the accuracy, safety and intelligence level of ignition control has become an urgent problem to be solved. Summary of the invention

[0004] In order to improve the accuracy, safety and intelligence level of ignition control, this application provides a human shadow rocket electronic fuze control system and method based on security authentication. By integrating information chips and safety actuators into pyrotechnics, information interaction, state judgment and reliable control between the rocket and the launch controller are realized. At the same time, the system has added a security authentication mechanism, which greatly improves the security of preventing misoperation and unauthorized use through password verification and encrypted data communication. Through the electronic fuze control system, the launch, dispersal and parachute opening time of the rocket are controlled by electrical signals, providing more precise time control capabilities and higher operational flexibility.

[0005] In the first aspect, the present application provides a human shadow rocket electronic fuze control system based on safety authentication, which adopts the following technical solution:

[0006] A human shadow rocket electronic fuze control system based on safety authentication, the control system comprising a rocket launch controller and a plurality of rocket electronic fuzes for ignition control of the human shadow rocket; the rocket launch controller is respectively connected to the plurality of rocket electronic fuzes, and is used to output safety authentication detection instructions corresponding to the human shadow rocket to be launched;

[0007] The rocket electronic fuze includes a main control unit, an energy supply unit, a carrier communication unit, an encryption unit, a motion acquisition unit, an energy charging unit, a detection unit and an ignition control unit;

[0008] The energy supply unit is connected to the rocket launch controller, and is used to receive the electric energy provided by the rocket launch controller and supply power to the rocket electronic fuse;

[0009] The carrier communication unit is connected to the main control unit and is used to communicate with the rocket launch controller via a carrier bus;

[0010] The encryption unit is connected to the main control unit and is used to encrypt the communication data and the pre-stored onboard key data of the human shadow rocket to be launched;

[0011] The motion acquisition unit is connected to the main control unit and is used to detect the posture information of the human shadow rocket to be launched in real time and output a posture detection signal;

[0012] The charging unit is connected to the main control unit, the ignition control unit and the energy supply unit, respectively, and is used to charge the main control unit and the ignition control unit.

[0013] The detection unit is connected to the energy charging unit and the main control unit respectively, and is used to detect the energy storage state of the energy charging unit in real time and output an energy storage state detection signal;

[0014] The main control unit is connected to the rocket launch controller, and is used to respond to the security authentication detection instruction corresponding to the human shadow rocket to be launched, and return the identity query information of the human shadow rocket to be launched to the rocket launch controller; wherein the identity query information includes the rocket shell code and the chip UID;

[0015] The rocket launch controller is also used to send the identity query information to the server, receive and decrypt the query result sent by the server, and obtain the ignition password and preset state rules of the human shadow rocket to be launched;

[0016] The rocket launch controller is further used to verify the ignition password based on the encrypted onboard key data of the human shadow rocket to be launched;

[0017] The main control unit is further used to perform status verification on the posture detection signal and the energy storage status detection signal based on the preset status rule;

[0018] The rocket launch controller is further used to output an ignition instruction in response to the ignition password verification pass result and the status verification pass result;

[0019] The main control unit is used to output an ignition pulse signal in response to the ignition instruction;

[0020] The ignition control unit is connected to the main control unit, and is used to respond to the ignition pulse signal to control the human shadow rocket to be launched to perform launching, catalyst spreading and parachute landing operations in sequence.

[0021] By adopting the above technical solutions, precise control, safety verification and real-time monitoring of the rocket launch process are achieved. Unlike the traditional simple ignition control method that relies on pyrotechnics, the system introduces password verification, encrypted data communication, and attitude and energy storage status detection technologies, which significantly improve the accuracy and reliability of ignition control. At the same time, the system collects rocket attitude information in real time through sensors and encrypts communications to ensure data transmission security, thereby effectively preventing data from being intercepted or tampered with, solving the shortcomings of traditional shadow rockets in terms of safety and intelligent control. This technical solution not only improves the ignition accuracy of rockets, but also greatly improves the safety and intelligence level of the overall system.

[0022] Optionally, the rocket launch controller includes a power module, an MCU module and an M-BUS host;

[0023] The MCU module is connected to the power module and the M-BUS host respectively, and is used to control the rocket launch controller;

[0024] The power supply module is connected to the M-BUS host and the energy supply unit respectively, and is used to supply power to the rocket launch controller and the rocket electronic fuse;

[0025] The carrier communication unit includes an M-BUS slave, and the M-BUS slave is connected to the M-BUS host via an M-BUS bus.

[0026] Optionally, the energy supply unit includes a protection circuit and a power supply circuit, and two ends of the protection circuit are respectively connected to the rocket launch controller and the power supply circuit, and the power supply circuit is used to power the rocket electronic fuse.

[0027] Optionally, the ignition control unit includes a launching unit, a spreading unit and a parachute opening unit;

[0028] The transmitting unit comprises a first control circuit and a first discharge circuit; the first control circuit is connected to the main control unit and the first discharge circuit respectively, and the first discharge circuit is used to connect to the transmitting ignition head;

[0029] The spreading unit includes a second control circuit and a second discharge circuit; the second control circuit is connected to the main control unit and the second discharge circuit respectively, and the second discharge circuit is used to connect to the spreading ignition head;

[0030] The parachute opening unit comprises a third control circuit and a third discharge circuit; the third control circuit is connected to the main control unit and the third discharge circuit respectively, and the third discharge circuit is used to be connected to the parachute opening ignition head.

[0031] Optionally, the charging unit includes a charging control circuit, a main control charging circuit, a first charging circuit, a second charging circuit and a third charging circuit;

[0032] The charging control circuit has one end connected to the main control charging circuit, the first charging circuit, the second charging circuit and the third charging circuit respectively, and the other end connected to the energy supply unit;

[0033] The main control charging circuit is connected to the main control unit and is used to charge the main control unit;

[0034] The first charging circuit is connected to the first discharging circuit and is used to charge the transmitting unit;

[0035] The second charging circuit is connected to the second discharging circuit and is used to charge the spreading unit;

[0036] The third charging circuit is connected to the third discharging circuit and is used for charging the umbrella opening unit.

[0037] Optionally, the detection unit includes a power detection circuit, a first detection circuit, a second detection circuit and a third detection circuit;

[0038] The two ends of the power detection circuit are respectively connected to the main control charging circuit and the main control unit, and are used to detect the energy storage state of the main control charging circuit in real time and send it to the main control unit;

[0039] The two ends of the first detection circuit are respectively connected to the main control unit and the first charging circuit, and are used to detect the energy storage state of the first charging circuit in real time and send it to the main control unit;

[0040] The two ends of the second detection circuit are respectively connected to the main control unit and the second charging circuit, and are used to detect the energy storage state of the second charging circuit in real time and send it to the main control unit;

[0041] Two ends of the third detection circuit are connected to the main control unit and the third charging circuit respectively, and are used to detect the energy storage state of the third charging circuit in real time and send it to the main control unit.

[0042] Optionally, the rocket launch controller is further used to send an ignition parameter configuration instruction to the rocket electronic fuse according to preset ignition parameters; wherein the ignition parameters include launch time, spreading time and parachute opening time;

[0043] The main control unit is further used to detect whether the preset ignition parameters are legal, store the preset ignition parameters when the preset ignition parameters are legal, and update the current ignition parameters according to the preset ignition parameters.

[0044] Optionally, the rocket electronic fuze also includes an auxiliary unit, which includes the human-computer interaction unit, the debugging interface unit, the expansion interface unit and the storage unit, and the main control unit is respectively connected to the human-computer interaction unit, the debugging interface unit, the expansion interface unit and the storage unit.

[0045] In the second aspect, the present application provides a method for controlling an electronic fuse of a shadow rocket based on safety authentication, which adopts the following technical solution:

[0046] A human shadow rocket electronic fuze control method based on safety authentication is applied to a human shadow rocket electronic fuze control system based on safety authentication as described in the first aspect, and the control method comprises:

[0047] The rocket launch controller sends a safety authentication detection instruction corresponding to the human shadow rocket to be launched to the rocket electronic fuse;

[0048] The rocket electronic fuze responds to the safety authentication detection instruction and returns the identity query information of the human shadow rocket to be launched to the rocket launch controller; wherein the identity query information includes the rocket shell code and the chip UID;

[0049] The rocket launch controller sends the identity query information to the server, receives and decrypts the query result sent by the server, and obtains the ignition password and preset state rules of the human shadow rocket to be launched;

[0050] The rocket electronic fuze receives the energy storage state detection signal of the energy charging unit and the posture detection signal of the shadow rocket to be launched, and performs state verification on the posture detection signal and the energy storage state detection signal based on the preset state rule;

[0051] The rocket launch controller verifies the ignition password based on the onboard key data of the shadow rocket to be launched that is encrypted in the rocket electronic fuse;

[0052] The rocket launch controller outputs an ignition command in response to the ignition password verification pass result and the status verification pass result;

[0053] The rocket electronic fuze outputs an ignition pulse signal in response to the ignition command;

[0054] The ignition control unit of the rocket electronic fuze responds to the ignition pulse signal to control the human shadow rocket to be launched to perform the launching, catalyst spreading and parachute landing operations in sequence.

[0055] Optionally, before the step of outputting the ignition instruction in response to the ignition password check result and the status verification result, the step further includes:

[0056] The rocket launch controller sends an ignition parameter configuration instruction to the rocket electronic fuse according to the preset ignition parameters; wherein the ignition parameters include the launch time, the spreading time and the parachute opening time;

[0057] The rocket electronic fuze detects whether the preset ignition parameters are legal;

[0058] If yes, the rocket electronic fuze stores the preset ignition parameters and updates the current ignition parameters according to the preset ignition parameters;

[0059] If not, the rocket electronic fuze will not update the ignition parameters.

[0060] In summary, the present application includes at least one of the following beneficial technical effects: Through multiple security authentication and status monitoring steps, the whole process control from rocket launch preparation, attitude detection, password verification to ignition and launch is realized. The whole process ensures the safety, reliability and accuracy of the launch operation, and prevents unauthorized launches and operational errors. Through real-time monitoring of attitude and energy storage status and encrypted verification of the ignition password, the scheme ensures strict verification before the rocket launch, and accurately controls the entire process of launch, seeding and safe landing, greatly improving the efficiency and safety of artificial weather modification operations. BRIEF DESCRIPTION OF THE DRAWINGS

[0061] Figure 1 It is a structural schematic diagram of a shadow rocket electronic fuze control system according to one of the embodiments of the present application.

[0062] Figure 2 It is a structural schematic diagram of a shadow rocket electronic fuze control system according to another embodiment of the present application.

[0063] Figure 3 It is a structural schematic diagram of a shadow rocket electronic fuze control system according to another embodiment of the present application.

[0064] Figure 4 It is a flow chart of a method for controlling an electronic fuse of a shadow rocket according to one of the embodiments of the present application.

[0065] Figure 5It is a flow chart of a method for controlling an electronic fuse of a shadow rocket according to another embodiment of the present application. DETAILED DESCRIPTION

[0066] In order to make the purpose, technical solutions and advantages of this application more clear, the following Figure 1-5 It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0067] The embodiment of the present application discloses a human shadow rocket electronic fuze control system based on safety authentication.

[0068] Reference Figure 1 , a human shadow rocket electronic fuze control system based on safety authentication, the control system includes a rocket launch controller and a plurality of rocket electronic fuzes for ignition control of the human shadow rocket; the rocket launch controller is respectively connected with the plurality of rocket electronic fuzes, and is used to output safety authentication detection instructions corresponding to the human shadow rocket to be launched;

[0069] The rocket electronic fuze includes a main control unit, an energy supply unit, a carrier communication unit, an encryption unit, a motion acquisition unit, an energy charging unit, a detection unit and an ignition control unit;

[0070] The energy supply unit is connected to the rocket launch controller, and is used to receive the electric energy provided by the rocket launch controller and supply power to the rocket electronic fuse;

[0071] A carrier communication unit, connected to the main control unit, is used to communicate with the rocket launch controller via a carrier bus;

[0072] Among them, the carrier communication unit is connected to the main control unit through UART to realize the issuance and response of the rocket electronic fuze slave command and complete data communication with the rocket launch controller;

[0073] The encryption unit is connected to the main control unit and is used to encrypt the communication data and the pre-stored onboard key data of the human shadow rocket to be launched;

[0074] Among them, the onboard key data of the human shadow rocket includes the chip UID, rocket shell code and ignition password. The onboard key data enables each human shadow rocket to have a unique identity information, ensuring uniqueness and security;

[0075] In the embodiment of the present application, the encryption unit is connected to the main control unit through the IIC bus, and data security encryption is achieved through hardware encryption, ensuring the safe transmission of important data and improving system security;

[0076] The motion acquisition unit is connected to the main control unit and is used to detect the posture information of the shadow rocket to be launched in real time and output a posture detection signal;

[0077] Among them, the motion acquisition unit is connected to the main control unit through the IIC bus to realize the acquisition of the motion state, posture and other information of the shadow rocket;

[0078] The charging unit is connected to the main control unit, the ignition control unit and the energy supply unit respectively, and is used to charge the main control unit and the ignition control unit.

[0079] The detection unit is connected to the energy charging unit and the main control unit respectively, and is used to detect the energy storage state of the energy charging unit in real time and output an energy storage state detection signal;

[0080] The main control unit is connected to the rocket launch controller, and is used to respond to the security authentication detection instruction corresponding to the human shadow rocket to be launched, and return the identity query information of the human shadow rocket to be launched to the rocket launch controller; wherein the identity query information includes the rocket shell code and the chip UID;

[0081] The rocket launch controller is also used to send the identity query information to the server, receive and decrypt the query results sent by the server, and obtain the ignition password and preset state rules of the human shadow rocket to be launched;

[0082] Specifically, when the rocket launch controller receives the chip UID and rocket shell code, it uploads them to the server and queries the server database for the ignition code corresponding to the chip UID. In the embodiment of the present application, during the production process of the human shadow rocket, the rocket shell code, chip UID and ignition code have been bound and encrypted. Therefore, when the human shadow is operating, it must be decrypted according to the preset decryption rules before the rocket can be used.

[0083] The rocket launch controller is also used to verify the ignition code based on the encrypted onboard key data of the human shadow rocket to be launched;

[0084] It should be noted that during the verification, the validity period of the ignition password must also be verified. If the validity period has expired, it can be determined that the ignition password is invalid and ignition operation is prohibited.

[0085] The main control unit is also used to verify the state of the posture detection signal and the energy storage state detection signal based on the preset state rules;

[0086] It should be noted that before ignition, the motion acquisition unit's sensor is used to determine whether the current pitch angle is within the authentic launch range; if it exceeds the authentic launch range, the subsequent attitude verification will fail; after ignition and launch, the current rocket's flight attitude is determined in real time. If the attitude is abnormal, subsequent ignition control is prohibited to prevent accidents caused by secondary ignition.

[0087] The rocket launch controller is further used to output an ignition command in response to the ignition password verification pass result and the status verification pass result;

[0088] Among them, after passing the security authentication and status verification, the ignition command can be sent in sequence, and the charging button of the corresponding channel can be turned on to carry out the ignition control process.

[0089] A main control unit, used to output an ignition pulse signal in response to an ignition instruction;

[0090] Among them, when it is determined that the shadow rocket meets the requirements for launch, the main control unit controls the IO port to output the ignition pulse in sequence according to the delay parameters set in advance;

[0091] Specifically, the system confirms the status before launch based on the data collected by ADC, including whether the ignition password is correct, the charging status is normal, and the posture of the shadow rocket is normal. After meeting the ignition and launch requirements, the main control unit receives the ignition command and sends ignition control pulses (launch, scatter, and parachute opening) in sequence according to the set delay parameters. The main control unit detects online through ADC sampling whether the rocket has successfully left the rack and returns the result to the rocket launch controller through the M-BUS bus.

[0092] The ignition control unit is connected to the main control unit and is used to respond to the ignition pulse signal to control the shadow rocket to be launched to perform the launching, catalyst spreading and parachute landing operations in sequence.

[0093] Specifically, after the shadow rocket is successfully ignited and launched, the main control unit controls the shadow rocket to spread the catalyst at an appropriate height and distance according to the pre-configured spreading delay and pulse parameters, thereby improving the utilization rate of the catalyst; after the shadow rocket spreading operation is completed, the main control unit realizes precise control of the parachute opening time according to the pre-configured parachute opening delay and pulse parameters, effectively controls the flight distance of the shadow rocket, ensures that the shadow rocket lands in an area with fewer people and buildings, and improves the safety of the operation.

[0094] Through the above implementation methods, precise control, safety verification and real-time monitoring of the rocket launch process are achieved. Unlike the traditional simple ignition control method that relies on pyrotechnics, the system introduces technologies such as password verification, encrypted data communication, and attitude and energy storage status detection, which significantly improves the accuracy and reliability of ignition control. At the same time, the system collects rocket attitude information in real time through sensors and encrypts communications to ensure data transmission security, thereby effectively preventing data from being intercepted or tampered with, solving the shortcomings of traditional shadow rockets in terms of safety and intelligent control. This technical solution not only improves the ignition accuracy of rockets, but also greatly improves the safety and intelligence level of the overall system.

[0095] In one embodiment of the present application, the ignition password is a set of specific codes that need to be entered before the launch of the human shadow rocket, which is used to ensure the safety and correctness of the human shadow launch. The use of the ignition password can effectively prevent unauthorized launches, ensure that only authorized personnel can start the rocket, and prevent misoperation or misfire. In addition, as a safety measure, the ignition password must have the following characteristics: the ignition password should be randomly generated without rules; the ignition password will not be lost in the event of a power failure; after the human shadow rocket is produced, no software, rocket launch controller or device can read, display or export the ignition password.

[0096] As an implementation method of the main control unit, the main control unit is responsible for data collection, information processing, and logic control of the rocket electronic fuze, including the coordination of each unit, data processing, and decision-making. Before the launch of the shadow rocket, the main control unit usually performs a self-check on the hardware of each unit to ensure that the hardware of each unit works properly. The system clock of the main control unit uses an external crystal oscillator and is configured with a clock safety function. When the main clock fails, it supports switching to a backup internal RC clock source, thereby improving system reliability.

[0097] As an implementation method of the encryption unit, the encryption unit realizes the encryption and decryption of the onboard key data of the human shadow rocket through built-in hardware and software mechanisms to ensure the security and confidentiality of the data. The hardware can adopt the national secret algorithm encryption product based on the domestic 32-bit security processor, which has high performance and high security, adopts the ultra-high security level encryption algorithm, and has the characteristics of high performance and low power consumption.

[0098] In the embodiment of the present application, in order to meet the requirements that the onboard data of the human shadow rocket will not be lost during power failure and the key data cannot be read out during storage, the SM4 encryption algorithm can be used to encrypt the key data and store it in the EEPROM; after the onboard key data such as UID, shell code and ignition password are injected, the EEPROM is write-protected by hardware to ensure that the data cannot be tampered with by software. In addition, the system performs signature verification on the stored data, and the validity and legality of the data can be detected when the system is running. In extreme cases, even if the data in the EEPROM is tampered with, it cannot be used normally, thereby effectively ensuring the security and reliability of the data. In addition, the onboard key data of the human shadow rocket has been injected before leaving the factory, and cannot be read or changed after injection, ensuring the security of data communication.

[0099] As an implementation of the motion acquisition unit, the motion acquisition unit has the function of collecting the motion state and attitude information of the rocket. It integrates an accelerometer and a gyroscope, and can measure the acceleration and angular velocity of the rocket in three axes. These data are the basis for judging the motion state and attitude changes of the rocket. The sensor is independently mounted through the IIC bus to collect the acceleration and attitude information of the rocket in real time. The main control unit can perform real-time logical judgment based on the current flight attitude of the rocket to determine whether the subsequent ignition conditions are met, thereby providing precise control for subsequent ignition operations.

[0100] Reference Figure 1 , Figure 2 As an implementation of the carrier communication unit, the carrier communication unit is based on the M-BUS bus carrier mode, which is used to realize the power supply and data communication functions between the electronic fuze of the shadow rocket and the rocket launch controller. The two-wire connection based on M-BUS adopts a bus topology structure, and the M-BUS slaves of all channel electronic fuzes are connected to the launch controller master station through a pair of shared communication lines.

[0101] Among them, the carrier communication unit receives data by detecting the bus voltage, and uses the voltage carrier method to realize data transmission between the host and the slave, and at the same time realizes data transmission from the slave to the host by modulating the bus current, that is, the current carrier communication method is adopted. Since the rocket electronic fuze needs to charge the ignition unit and has high power supply requirements, in order to reduce interference, the system realizes the charging and data communication between the rocket launch controller and the electronic fuze through time-sharing multiplexing.

[0102] Reference Figure 1 , Figure 2 , as an implementation of a rocket launch controller, the rocket launch controller includes a power module, an MCU module and an M-BUS host;

[0103] The MCU module is connected to the power module and the M-BUS host respectively, and is used to control the rocket launch controller;

[0104] The power module is connected to the M-BUS host and the energy supply unit respectively, and is used to supply power to the rocket launch controller and the rocket electronic fuse;

[0105] The carrier communication unit comprises an M-BUS slave, and the M-BUS slave is connected with the M-BUS host via an M-BUS bus.

[0106] Among them, the M-BUS host module in the rocket launch controller sends instructions to M-BUS slaves with different addresses through the M-BUS bus to achieve communication with each M-BUS slave module. Each M-BUS slave module receives the instructions from the M-BUS host module, responds and returns corresponding data.

[0107] Specifically, the rocket launch controller has a built-in M-BUS carrier communication host module, which uses a DC carrier communication method and is connected to the carrier communication unit of the rocket electronic fuze through the M-BUS carrier bus. Through address allocation, the host and each slave can communicate and control; the M-BUS bus uses a two-wire non-polarity connection to ensure that the rocket electronic fuze is powered while realizing the data transmission function with the rocket electronic fuze. The carrier communication unit of the rocket electronic fuze has a built-in M-BUS carrier communication slave module, which uses a bus topology structure, is easy to expand, supports communication between multiple rocket electronic fuze boards and a rocket launch controller, and the failure of any slave does not affect the function of the entire bus. The efficiency and reliability of data transmission are guaranteed by optimizing the network protocol.

[0108] Reference Figure 1 As an implementation method of the energy supply unit, the energy supply unit includes a protection circuit and a power supply circuit. The rocket electronic fuze also includes a rectifier circuit. One end of the rectifier circuit is connected to the rocket launch controller, and the other end is respectively connected to the detection unit, the carrier communication unit and one end of the protection circuit. The other end of the protection circuit is connected to the power supply circuit, and the power supply circuit is connected to the charging unit, thereby realizing the power supply to the rocket electronic fuze.

[0109] Among them, the protection circuit is connected to the rectifier circuit to ensure the stability and safety of the rocket electronic fuze power supply system, while improving the reliability and service life of the system. In addition, the power supply through the carrier bus also solves the working power supply and ignition charging problems of the rocket electronic fuze control system.

[0110] In some embodiments, the rectifier circuit uses a bridge circuit to convert the current input from the carrier bus, and the protection circuit uses a voltage regulator diode to ensure the stability of the power supply voltage.

[0111] Reference Figure 1 , Figure 3 , as an implementation of the ignition control unit, the ignition control unit includes a launching unit, a spreading unit and a parachute opening unit;

[0112] The transmitting unit includes a first control circuit and a first discharge circuit; the first control circuit is connected to the main control unit and the first discharge circuit respectively, and the first discharge circuit is used to connect to the transmitting ignition head;

[0113] Specifically, the launch unit supports configuring the parameters of the ignition delay and ignition pulse width through the protocol, and the ignition charging status can be collected through the ADC sampling circuit to complete the closed-loop control. The first detection unit collects the charging voltage of the first charging circuit, and the main control unit determines whether it meets the launch ignition requirements. If it meets the requirements, it continues to wait to determine the status of the sowing unit and the parachute opening unit. If they all meet the requirements, the ignition pulse is output according to the ignition delay parameters. The first control circuit and the first charging circuit work together to the first discharge circuit, and then the ignition charge is directly released to the launch ignition head. The launch ignition head is responsible for igniting the propellant of the human shadow rocket engine to realize the launch of the human shadow rocket.

[0114] The spreading unit includes a second control circuit and a second discharge circuit; the second control circuit is connected to the main control unit and the second discharge circuit respectively, and the second discharge circuit is used to connect to the spreading ignition head;

[0115] Specifically, the spreading unit accurately controls the delayed spreading of the catalyst according to the issued ballistic parameters, and can configure the delay and pulse width through the protocol. The second detection circuit collects the charging voltage of the second charging circuit in real time and transmits it to the main control unit. The main control unit determines whether the spreading conditions are met, and controls the output of the spreading ignition pulse when the conditions are met, starts the spreading device, and evenly spreads the catalyst (such as silver iodide) in the cloud to form a catalytic belt, thereby achieving efficient spreading operations.

[0116] The parachute opening unit comprises a third control circuit and a third discharge circuit; the third control circuit is connected to the main control unit and the third discharge circuit respectively, and the third discharge circuit is used to be connected to the parachute opening ignition head.

[0117] Specifically, the parachute opening unit accurately delays the parachute opening operation of the rocket according to the issued ballistic parameters to ensure the safe landing of the wreckage. The third detection unit monitors the charging status of the third charging circuit in real time through ADC sampling. The main control unit determines whether the parachute opening conditions are met. If the conditions are met, it outputs the parachute opening ignition pulse, activates the parachute opening device or the self-destruction mechanism, and finally realizes the safe parachute landing of the rocket in the air or decomposes the missile body into smaller fragments, ensuring the safe landing of the human shadow rocket wreckage.

[0118] It should be noted that the delay and pulse width of the launching unit, spreading unit and parachute opening unit can all be configured through the protocol to realize the functions of ignition, launching, spreading catalyst and parachute opening of the shadow rocket for safe landing.

[0119] Reference Figure 1 , Figure 3 , as an implementation of the charging unit, the charging unit includes a charging control circuit, a main control charging circuit, a first charging circuit, a second charging circuit and a third charging circuit;

[0120] A charging control circuit, one end of which is respectively connected to the main control charging circuit, the first charging circuit, the second charging circuit and the third charging circuit, and the other end of which is connected to the energy supply unit;

[0121] In some embodiments, the first charging circuit, the second charging circuit and the third charging circuit all use independent energy storage capacitors. Before the rocket is launched, the charging control circuit outputs a 24V voltage, and controls the charging of the corresponding energy storage capacitors through each charging circuit, thereby realizing the function of powering and charging the launching unit, the spreading unit and the parachute opening unit in the ignition control unit.

[0122] The main control charging circuit is connected to the main control unit and is used to charge the main control unit;

[0123] Among them, the power detection circuit can realize fast sampling of the charge capacity stored in the main control charging circuit; in some embodiments, the main control charging circuit adopts a 1.5 F farad capacitor to provide a stable charge source, and the charging control circuit and the main control charging circuit are connected through a 24V cable to achieve stable power supply.

[0124] The first charging circuit is connected to the first discharging circuit and is used to charge the transmitting unit;

[0125] In some embodiments, the transmitting unit is powered by an independent capacitor in the first charging circuit, supports configuration of transmission parameters, and the energy supply unit outputs a 24V voltage connected to the charging control circuit to charge and store energy for the capacitor of the transmitting unit;

[0126] The second charging circuit is connected to the second discharging circuit and is used to charge the spreading unit;

[0127] In some embodiments, the spreading unit is powered by an independent capacitor in the second charging circuit, supports configuration of spreading parameters, and the energy supply unit outputs a 24V voltage connected to the charging control circuit to realize charging and energy storage for the capacitor of the spreading unit;

[0128] The third charging circuit is connected to the third discharging circuit and is used to charge the umbrella opening unit;

[0129] In some embodiments, the parachute opening unit is powered by an independent capacitor in the third charging circuit, supports configuration of parachute opening parameters, and the energy supply unit outputs a 24V voltage connected to the charging control circuit to realize charging and energy storage for the capacitor of the parachute opening unit.

[0130] In the embodiment of the present application, when the rocket electronic fuze system receives the charging instruction, the charging switch is turned on to charge the energy storage capacitors of each charging circuit using the M-BUS bus. After a delay, the charging switch is turned off to detect whether the charging is successful. If successful, a successful result is returned. If failed, "charging failure" is sent back to the rocket launch controller. It should be noted that the time required for charging is determined by the capacitance of the energy storage capacitor and the voltage output by the energy supply unit.

[0131] Reference Figure 1 , Figure 3 , as an implementation of the detection circuit, the detection circuit includes a power detection circuit, a first detection circuit, a second detection circuit and a third detection circuit;

[0132] The two ends of the power detection circuit are respectively connected to the main control charging circuit and the main control unit, and are used to detect the energy storage state of the main control charging circuit in real time and send it to the main control unit;

[0133] Among them, the power detection circuit is connected to the supercapacitor in the main control charging circuit. The power detection circuit first performs pre-stage adaptation processing on the sampling signal, and then switches the acquisition channel through time-sharing control to realize dual-channel multiplexing ADC signal acquisition. The power detection circuit obtains real-time voltage from the previous rectifier circuit and the supercapacitor that provides system power supply through ADC sampling. By providing accurate and real-time voltage sampling data, it is convenient for the main control unit to monitor and analyze the system power supply in real time.

[0134] In the embodiment of the present application, before the human shadow rocket is launched from the frame, the power supply circuit outputs a 3.3V voltage, and charges the main control charging circuit through the LM317 linear voltage regulator. The main control charging circuit uses a 1.5F farad capacitor to ensure that a stable charge source is provided for the entire rocket electronic fuze system. After the rocket is launched from the frame, the main control charging circuit supplies power to the main control unit and each functional module unit; wherein, the main control unit realizes rapid sampling of the charge capacity stored in the main control charging circuit through the power detection circuit.

[0135] Two ends of the first detection circuit are respectively connected to the main control unit and the first charging circuit, and are used to detect the energy storage state of the first charging circuit in real time and send it to the main control unit;

[0136] Among them, the main control unit obtains the real-time data of the launch unit through ADC sampling, which is convenient for monitoring, analyzing and judging whether the energy storage state meets the launch conditions, so as to control the port to output the ignition pulse signal to the ignition unit. After the ignition pulse signal is output, the capacitor energy of the launch unit is directly released to the launch ignition head, which is responsible for igniting the propellant of the shadow rocket engine and realizing the launch of the shadow rocket.

[0137] The two ends of the second detection circuit are respectively connected to the main control unit and the second charging circuit, and are used to detect the energy storage state of the second charging circuit in real time and send it to the main control unit;

[0138] Among them, the main control unit obtains the real-time data of the spreading unit through ADC sampling, which is convenient for monitoring, analyzing and judging whether the energy storage meets the spreading conditions, so as to control the port to output the spreading ignition pulse signal to the spreading unit. After the spreading ignition pulse is output, the capacitor energy of the spreading unit is directly released to the spreading ignition head, which will ignite and start the spreading device of the shadow rocket. The spreading device starts to spread the silver iodide catalyst, so that it forms a catalytic belt in the cloud layer in a line spreading manner, thereby realizing the spreading operation of the shadow rocket.

[0139] Two ends of the third detection circuit are respectively connected to the main control unit and the third charging circuit, and are used to detect the energy storage state of the third charging circuit in real time and send it to the main control unit.

[0140] Among them, the main control unit obtains the real-time data of the parachute opening unit through ADC sampling, which is convenient for monitoring, analyzing and judging whether the energy storage meets the parachute opening conditions, so as to control the port to output the parachute opening ignition pulse to the parachute opening unit. After the parachute opening ignition pulse is output, the capacitor energy of the parachute opening unit is directly released to the parachute opening ignition head, which will ignite and start the safe landing device of the human shadow rocket (start after the sowing is completed), so that the rocket can be safely landed on the ground in the air by parachute opening or self-destruction (blowing the rocket body into smaller fragments and landing on the ground), thereby achieving the safe landing of the human shadow rocket wreckage.

[0141] In the above implementation, the data fed back by the detection unit facilitates the determination of whether the charging energy value and circuit state of each unit in the ignition control unit meet the ignition conditions. By configuring the delay and pulse parameters of the spreading unit, the rocket is controlled to spread the catalyst at a suitable height and distance to improve the catalyst utilization rate; by configuring the delay parameters of the parachute opening unit, the parachute opening time is precisely controlled, the flight distance of the rocket is effectively controlled, and the rocket is ensured to land in an area with fewer people and buildings, thereby improving the safety of the operation.

[0142] As a further implementation of the control system, the rocket launch controller is also used to send an ignition parameter configuration instruction to the rocket electronic fuse according to the preset ignition parameters; wherein the ignition parameters include the launch time, the spreading time and the parachute opening time;

[0143] Specifically, the rocket launch controller can be configured through the communication bus. During configuration, the ignition parameters can be set before the rocket is launched based on the target cloud height, cloud thickness and cloud distribution, thereby achieving precise shadow rocket operations targeting the target cloud.

[0144] The main control unit is also used to detect whether the preset ignition parameters are legal, store the preset ignition parameters when the preset ignition parameters are legal, and update the current ignition parameters according to the preset ignition parameters.

[0145] Specifically, when the main control unit in the rocket electronic fuze receives the ignition parameter setting instruction, it first checks whether the ignition parameters are legal. When it is detected that the ignition parameters are legal values, the ignition parameters are updated and stored in the internal memory (RAM) through the IIC bus. After the storage is completed, the main control unit reads back the stored results. If the result is normal, the ignition parameters are set successfully; otherwise, the ignition parameters are not updated.

[0146] It should be noted that the ignition parameter setting of the shadow rocket is a key link in the shadow rocket launch system. The rocket electronic fuze system supports the precise configuration of rocket ignition launch time, sowing time, parachute opening time and other parameters to achieve precise control of the shadow rocket operation. In addition, during the flight of the shadow rocket, it is also necessary to record the actual parameters such as acceleration, launch ignition time, sowing ignition time, parachute opening ignition time, etc. in real time to provide data support for subsequent analysis.

[0147] In the above implementation, by updating the configuration of preset ignition parameters, the rocket ignition time, spreading time, parachute opening time, etc. can be accurately controlled. This precise control strategy helps to improve the utilization rate and operation effect of the catalyst, thereby realizing precise shadow rocket operation against the target cloud.

[0148] As a further implementation method of the rocket electronic fuze, the rocket electronic fuze also includes an auxiliary unit, the auxiliary unit includes a human-computer interaction unit, a debugging interface unit, an extension interface unit and a storage unit, and the main control unit is respectively connected to the human-computer interaction unit, the debugging interface unit, the extension interface unit and the storage unit.

[0149] Among them, the human-computer interaction unit is connected to the main control unit through the GPIO bus to realize real-time response and feedback of the rocket launch controller instructions; the debugging interface is connected to the main control unit through the SWD bus to realize system debugging; the expansion interface unit is connected to the main control unit through the UART bus to realize module expansion; the storage unit is connected to the main control unit through the IIC bus to realize the writing and reading of rocket-related data.

[0150] In actual application, the electronic fuze control system of the shadow rocket of this application has excellent safety, convenience and accuracy. Through encryption technology and security authentication (such as ignition password verification), the security against misoperation and unauthorized use is greatly improved. The two-wire DC carrier bus technology is adopted to combine the power line and the signal line into one, which simplifies the line structure and improves the convenience of use. The system can accurately control the time of launch, sowing and parachute opening to ensure that the operation is carried out at the right time, and realize precise control of catalyst release and flight trajectory. The configurability of the system allows flexible adjustment of various delay and pulse parameters through the communication bus to match the ignition energy of different ammunition. The system also supports data tracing, records key data during the operation, and provides support for subsequent ballistic analysis and operation effect evaluation.

[0151] The embodiment of the present application also discloses a method for controlling an electronic fuse of a shadow rocket based on safety authentication.

[0152] Reference Figure 4 A human shadow rocket electronic fuze control method based on safety authentication is applied to the above-mentioned human shadow rocket electronic fuze control system based on safety authentication. The control method includes:

[0153] Step S101, the rocket launch controller sends a safety authentication detection instruction corresponding to the human shadow rocket to be launched to the rocket electronic fuse;

[0154] Among them, before launching, the system starts the security authentication process, and the rocket launch controller sends a detection instruction to the rocket's electronic fuse, requesting confirmation of the rocket's identity information.

[0155] Step S102, the rocket electronic fuze responds to the security authentication detection instruction and returns the identity query information of the human shadow rocket to be launched to the rocket launch controller; wherein the identity query information includes the rocket shell code and the chip UID;

[0156] Specifically, after receiving the detection instruction, the rocket electronic fuze extracts the rocket shell code and chip UID stored inside it, and returns it to the rocket launch controller as identity query information; through the unique UID and shell code, the identity of the rocket can be uniquely confirmed, effectively avoiding identity forgery or misuse.

[0157] Step S103, the rocket launch controller sends the identity query information to the server, receives and decrypts the query result sent by the server, and obtains the ignition password and preset state rules of the human shadow rocket to be launched;

[0158] Among them, the rocket launch controller sends the identity information of the shadow rocket to be launched to the background server. The server verifies it based on the database records, and sends the decrypted ignition password and the preset status rules corresponding to the rocket (including the allowable launch rules and the prohibited launch rules).

[0159] Step S104, the rocket electronic fuze receives the energy storage state detection signal of the energy charging unit and the posture detection signal of the shadow rocket to be launched, and performs state verification on the posture detection signal and the energy storage state detection signal based on a preset state rule;

[0160] Among them, the main control unit of the rocket's electronic fuze monitors the charging status (capacitor energy) of the charging unit and the rocket's attitude information (such as pitch angle, etc.) in real time through the detection unit, and verifies the current attitude (such as whether the angle meets the regulations) and energy storage status (whether it meets the launch requirements) of the shadow rocket according to the preset status rules to ensure the safety of the rocket launch, prevent launch failures or dangerous situations caused by improper attitude or insufficient energy storage, and improve the safety and success rate of operations.

[0161] Step S105, the rocket launch controller verifies the ignition code based on the encrypted onboard key data of the human shadow rocket to be launched in the rocket electronic fuze;

[0162] Among them, through the encryption verification mechanism, the ignition password sent by the server is compared with the encrypted data in the rocket's electronic fuse to ensure the uniqueness and correctness of the ignition password and prevent unauthorized operations or illegal password modifications.

[0163] Step S106, the rocket launch controller outputs an ignition command in response to the ignition password verification pass result and the status verification pass result;

[0164] Among them, through double verification, when the password verification and status verification are passed, the rocket launch controller sends an ignition command, allowing it to ignite and launch.

[0165] Step S107, the rocket electronic fuze outputs an ignition pulse signal in response to the ignition command;

[0166] Among them, after the rocket's electronic fuse receives the ignition command, it triggers the ignition pulse signal and transfers energy to the ignition control module to achieve precise control of the rocket launch and ensure the smooth execution of the ignition process.

[0167] Step S108, the ignition control unit of the rocket electronic fuse responds to the ignition pulse signal to control the shadow rocket to be launched to perform the launching, catalyst spreading and parachute landing operations in sequence.

[0168] Among them, the ignition control module executes rocket launch, catalyst spreading and parachute opening actions in sequence through ignition pulse signals to ensure the integrity of the mission, ensure the automatic execution of the entire process from rocket launch to mission completion, achieve precise catalyst spreading and safe landing, and maximize operational effectiveness and safety.

[0169] In the above implementation, through multiple security authentication and status monitoring steps, the whole process control from rocket launch preparation, attitude detection, password verification to ignition and launch is realized. The whole process ensures the safety, reliability and accuracy of the launch operation, and prevents unauthorized launch and operational errors. Through real-time monitoring of attitude and energy storage status and encrypted verification of ignition passwords, the scheme ensures strict verification before rocket launch, and accurately controls the whole process of launch, seeding and safe landing, greatly improving the efficiency and safety of artificial weather modification operations.

[0170] Reference Figure 5 As a further implementation of the control method, before the step of outputting the ignition instruction in response to the ignition password check result and the state verification result, the method further includes:

[0171] Step S201, the rocket launch controller sends an ignition parameter configuration instruction to the rocket electronic fuse according to the preset ignition parameters; wherein the ignition parameters include the launch time, the spreading time and the parachute opening time;

[0172] Step S202, the rocket electronic fuze detects whether the preset ignition parameters are legal;

[0173] If yes, jump to step S203; if no, jump to step S204;

[0174] Step S203, the rocket electronic fuze stores the preset ignition parameters, and updates the current ignition parameters according to the preset ignition parameters;

[0175] Step S204: the rocket electronic fuse does not update the ignition parameters.

[0176] In the above implementation, after the rocket is successfully ignited and launched, the main control unit controls the rocket to spread the catalyst at a suitable height and distance according to the pre-configured spreading delay and pulse parameters to improve the utilization rate of the catalyst. After the rocket spreading operation is completed, the main control unit realizes precise control of the parachute opening time according to the pre-configured parachute opening delay and pulse parameters, effectively controls the flight distance of the rocket, ensures that the rocket lands in an area with fewer people and buildings, and improves the safety of the operation.

[0177] The human shadow rocket electronic fuze control system based on safety authentication in the embodiment of the present application can implement any of the above-mentioned human shadow rocket electronic fuze control methods based on safety authentication, and the specific working process of each step in the human shadow rocket electronic fuze control method based on safety authentication can refer to the corresponding process in the above-mentioned system embodiment.

[0178] In the several embodiments provided in this application, it should be understood that the provided methods and systems can be implemented in other ways. For example, the system embodiments described above are only illustrative; for example, the division of a certain module is only a logical function division, and there may be other division methods in actual implementation, such as multiple modules can be combined or integrated into another system, or some features can be ignored or not executed.

[0179] It should be noted that in the above embodiments, the description of each embodiment has different emphases, and for parts that are not described in detail in a certain embodiment, reference can be made to the relevant descriptions of other embodiments.

[0180] The above are all preferred embodiments of the present application, and are not intended to limit the protection scope of the present application. Any feature disclosed in this specification (including the abstract and drawings), unless otherwise stated, can be replaced by other equivalent or alternative features with similar purposes. That is, unless otherwise stated, each feature is only an example of a series of equivalent or similar features.

Claims

1. A human shadow rocket electronic fuze control system based on safety authentication, characterized in that: The control system includes a rocket launch controller and a plurality of rocket electronic fuses for controlling the ignition of the shadow rocket; the rocket launch controller is respectively connected to the plurality of rocket electronic fuses, and is used to output safety authentication detection instructions corresponding to the shadow rocket to be launched; The rocket electronic fuze includes a main control unit, an energy supply unit, a carrier communication unit, an encryption unit, a motion acquisition unit, a charging unit, a detection unit and an ignition control unit; The energy supply unit is connected to the rocket launch controller, and is used to receive the electric energy provided by the rocket launch controller and supply power to the rocket electronic fuse; The carrier communication unit is connected to the main control unit and is used to communicate with the rocket launch controller via a carrier bus; The encryption unit is connected to the main control unit and is used to encrypt the communication data and the pre-stored onboard key data of the human shadow rocket to be launched; wherein the onboard key data of the human shadow rocket includes the chip UID, the rocket shell code and the ignition password, and the ignition password is randomly generated, cannot be read out and will not be lost when the power is off; The motion acquisition unit is connected to the main control unit and is used to detect the posture information of the human shadow rocket to be launched in real time and output a posture detection signal; The charging unit is connected to the main control unit, the ignition control unit and the energy supply unit respectively, and is used to charge the main control unit and the ignition control unit. The detection unit is connected to the energy charging unit and the main control unit respectively, and is used to detect the energy storage state of the energy charging unit in real time and output an energy storage state detection signal; The main control unit is connected to the rocket launch controller, and is used to respond to the security authentication detection instruction corresponding to the human shadow rocket to be launched, and return the identity query information of the human shadow rocket to be launched to the rocket launch controller; wherein the identity query information includes the rocket shell code and the chip UID; The rocket launch controller is also used to send the identity query information to the server, receive and decrypt the query result sent by the server, and obtain the ignition password and preset state rules of the human shadow rocket to be launched; The rocket launch controller is further used to verify the ignition password based on the encrypted onboard key data of the human shadow rocket to be launched; The main control unit is further used to perform status verification on the posture detection signal and the energy storage status detection signal based on the preset status rule; The rocket launch controller is further used to output an ignition instruction in response to the ignition password verification pass result and the status verification pass result; The main control unit is used to output an ignition pulse signal in response to the ignition instruction; The ignition control unit is connected to the main control unit, and is used to respond to the ignition pulse signal to control the human shadow rocket to be launched to perform launching, catalyst spreading and parachute landing operations in sequence.

2. According to claim 1, a safety-authenticated human shadow rocket electronic fuze control system is characterized in that: The rocket launch controller includes a power module, an MCU module and an M-BUS host; The MCU module is connected to the power module and the M-BUS host respectively, and is used to control the rocket launch controller; The power supply module is connected to the M-BUS host and the energy supply unit respectively, and is used to supply power to the rocket launch controller and the rocket electronic fuse; The carrier communication unit includes an M-BUS slave, and the M-BUS slave is connected to the M-BUS host via an M-BUS bus.

3. According to claim 2, a human shadow rocket electronic fuze control system based on safety authentication is characterized in that: The energy supply unit includes a protection circuit and a power supply circuit. The two ends of the protection circuit are respectively connected to the rocket launch controller and the power supply circuit. The power supply circuit is used to supply power to the rocket electronic fuse.

4. According to claim 3, a human shadow rocket electronic fuze control system based on safety authentication is characterized in that: The ignition control unit includes a launching unit, a spreading unit and a parachute opening unit; The transmitting unit comprises a first control circuit and a first discharge circuit; the first control circuit is connected to the main control unit and the first discharge circuit respectively, and the first discharge circuit is used to connect to the transmitting ignition head; The spreading unit includes a second control circuit and a second discharge circuit; the second control circuit is connected to the main control unit and the second discharge circuit respectively, and the second discharge circuit is used to connect to the spreading ignition head; The parachute opening unit comprises a third control circuit and a third discharge circuit; the third control circuit is connected to the main control unit and the third discharge circuit respectively, and the third discharge circuit is used to be connected to the parachute opening ignition head.

5. The electronic fuze control system of a shadow rocket based on safety authentication according to claim 4 is characterized in that: The charging unit includes a charging control circuit, a main control charging circuit, a first charging circuit, a second charging circuit and a third charging circuit; The charging control circuit has one end connected to the main control charging circuit, the first charging circuit, the second charging circuit and the third charging circuit respectively, and the other end connected to the energy supply unit; The main control charging circuit is connected to the main control unit and is used to charge the main control unit; The first charging circuit is connected to the first discharging circuit and is used to charge the transmitting unit; The second charging circuit is connected to the second discharging circuit and is used to charge the spreading unit; The third charging circuit is connected to the third discharging circuit and is used for charging the umbrella opening unit.

6. The electronic fuze control system of a human shadow rocket based on safety authentication according to claim 5 is characterized in that: The detection unit includes a power detection circuit, a first detection circuit, a second detection circuit and a third detection circuit; The two ends of the power detection circuit are respectively connected to the main control charging circuit and the main control unit, and are used to detect the energy storage state of the main control charging circuit in real time and send it to the main control unit; The two ends of the first detection circuit are respectively connected to the main control unit and the first charging circuit, and are used to detect the energy storage state of the first charging circuit in real time and send it to the main control unit; The two ends of the second detection circuit are respectively connected to the main control unit and the second charging circuit, and are used to detect the energy storage state of the second charging circuit in real time and send it to the main control unit; Two ends of the third detection circuit are connected to the main control unit and the third charging circuit respectively, and are used to detect the energy storage state of the third charging circuit in real time and send it to the main control unit.

7. A human shadow rocket electronic fuze control system based on safety authentication according to any one of claims 1 to 6, characterized in that: The rocket launch controller is also used to send an ignition parameter configuration instruction to the rocket electronic fuse according to the preset ignition parameters; wherein the ignition parameters include the launch time, the spreading time and the parachute opening time; The main control unit is further used to detect whether the preset ignition parameters are legal, store the preset ignition parameters when the preset ignition parameters are legal, and update the current ignition parameters according to the preset ignition parameters.

8. The electronic fuze control system of a human shadow rocket based on safety authentication according to claim 1 is characterized in that: The rocket electronic fuze also includes an auxiliary unit, which includes a human-computer interaction unit, a debugging interface unit, an expansion interface unit and a storage unit. The main control unit is connected to the human-computer interaction unit, the debugging interface unit, the expansion interface unit and the storage unit respectively.

9. A method for controlling electronic fuse of shadow rocket based on safety authentication, characterized in that: A human shadow rocket electronic fuze control system based on safety authentication as described in any one of claims 1 to 8, the control method comprising: The rocket launch controller sends a safety authentication detection instruction corresponding to the human shadow rocket to be launched to the rocket electronic fuse; The rocket electronic fuze responds to the safety authentication detection instruction and returns the identity query information of the human shadow rocket to be launched to the rocket launch controller; wherein the identity query information includes the rocket shell code and the chip UID; The rocket launch controller sends the identity query information to the server, receives and decrypts the query result sent by the server, and obtains the ignition password and preset state rules of the human shadow rocket to be launched; The rocket electronic fuze receives the energy storage state detection signal of the energy charging unit and the posture detection signal of the shadow rocket to be launched, and performs state verification on the posture detection signal and the energy storage state detection signal based on the preset state rule; The rocket launch controller verifies the ignition password based on the onboard key data of the human shadow rocket to be launched that is encrypted in the rocket electronic fuze; wherein the onboard key data of the human shadow rocket includes the chip UID, the rocket shell code and the ignition password, and the ignition password is randomly generated, cannot be read out and is not lost when the power is off; The rocket launch controller outputs an ignition command in response to the ignition password check pass result and the status verification pass result; The rocket electronic fuze outputs an ignition pulse signal in response to the ignition instruction; The ignition control unit of the rocket electronic fuze responds to the ignition pulse signal to control the human shadow rocket to be launched to perform the launching, catalyst spreading and parachute landing operations in sequence.

10. The method for controlling electronic fuse of shadow rocket based on safety authentication according to claim 9 is characterized in that: Before the step of outputting the ignition command in response to the ignition password verification pass result and the status verification pass result, the method further includes: The rocket launch controller sends an ignition parameter configuration instruction to the rocket electronic fuse according to the preset ignition parameters; wherein the ignition parameters include the launch time, the spreading time and the parachute opening time; The rocket electronic fuze detects whether the preset ignition parameters are legal; If yes, the rocket electronic fuze stores the preset ignition parameters and updates the current ignition parameters according to the preset ignition parameters; If not, the rocket electronic fuze will not update the ignition parameters.

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