Device and method for simulating missile ignition wire inspection and activation

Abstract

The invention discloses a device and method for simulating the inspection and activation of missile ignition wires, including a current sensor, an A / D acquisition module and a DSP, wherein current sensors 1 and 2 are connected to an isolation module, an A / D acquisition module and a DSP in sequence, and the DSP is then connected to a data recorder and a drive module respectively, and the drive module is connected to two relays through two loops, and two relays K1 and K2 respectively control a power switch K1-1 and a power signal switch K2-1, and a DO port of the drive module is connected back to a DI port of the DSP through three simulated fault switches and an isolation module; two current sensors are respectively connected to an ignition wire inspection / activation circuit and a simulated ignition wire fault switch is installed. The device has a real simulated ignition wire resistance value and a real simulated ignition wire activation or ignition timing, and verifies the correctness of the logic timing of the ignition control software of the launch control system, the correctness of the activation current or ignition current of the launch control system, and the correctness of the launch control cable.

Description

Technical Field

[0001] The invention belongs to the field of ground test, launch and control of ground-to-air missile weapon systems, and in particular relates to a simulated missile ignition wire inspection and activation device and a working sequence control method. Background Art

[0002] The missile test and launch control system tests the performance of missile equipment and systems and the coordination of signals between them, checks and prepares the missile launch conditions, and implements launch ignition control according to commands for missiles that have passed the inspection and are ready. How to efficiently improve the reliability of the test system or launch control system, so that it has the function of pyrotechnics safety inspection, avoid battery misactivation and missile mislaunch, and how to truly simulate the missile activation sequence and launch ignition sequence to ensure reliable missile ignition and launch have become urgent problems to be solved, but traditional simulators can only simply simulate the on and off of the ignition wire and simulate the power supply function. Summary of the invention

[0003] Aiming at the problem that the traditional simulator can only simply simulate the on-off of the ignition wire and the power supply function, a device and corresponding method for missile testing or self-checking, docking debugging and joint debugging of the launch control system are provided.

[0004] The technical solution of the present invention:

[0005] A device for simulating the inspection and activation of missile ignition wires comprises a current sensor, an A / D acquisition module and a DSP, and is characterized in that: a current sensor 1 and a current sensor 2 are connected to an isolation module, an A / D acquisition module and a DSP in sequence, the DSP is respectively connected to a data recorder and a drive module, the drive module is connected to two relays through two loops, the two relays K1 and K2 respectively control a power switch K1-1 and a power signal switch K2-1, the DO port of the drive module is connected back to the DI port of the DSP through three simulated fault switches and the isolation module; the two current sensors are respectively connected to an ignition wire inspection / activation circuit and are equipped with simulated ignition wire fault switches.

[0006] The ignition wire check / activation circuit includes a battery ignition wire check / activation circuit and an engine ignition wire check / activation circuit. The two circuits are respectively equipped with a simulated battery ignition wire fault switch S1, a resistor R2 and a simulated engine ignition wire fault switch S2, a resistor R3.

[0007] The DSP is connected to the rechargeable battery and the ground power supply port. A battery power switch S6 is provided to control whether the rechargeable battery supplies power. A power resistor R1 is connected to the common end of the ground power supply and the rechargeable battery to simulate the power load on the missile.

[0008] The closing and opening of the simulated ignition wire fault switch simulates the quality of the ignition wire. The missile installation completion failure, battery activation failure and engine ignition failure are simulated by setting three button switches between the DO and DI circuits of the DSP, including the simulated installation completion failure switch S3, the simulated battery activation failure switch S4 and the simulated engine ignition failure switch S5.

[0009] The device is installed in a housing, and a drop-out socket, a DSP interface and a battery charging port are provided on the housing panel, and S1-S6 are also installed on the housing panel.

[0010] A method for simulating the inspection and activation of a missile ignition wire comprises the above-mentioned device for simulating the inspection and activation of a missile ignition wire. The normal function and fault function of the missile installation completion are realized by an electromagnetic relay K2, a key switch S3, a DSP, a drive module and an isolation module. The installation completion circuit is short-circuited with the "ground power supply -", and the normally closed contact of K2-1 is connected in series in the installation completion loop to simulate the normal installation completion of the missile. When simulating the installation completion fault, firstly press the switch S3 for simulating the installation completion fault. At this time, the switch is closed, the circuit is in a pass state, and the signal output by DO1 of the DSP passes through the drive circuit and the isolation circuit processing circuit and then returns to the DI1 port of the DSP. The DSP recognizes the "installation completion fault" signal. At this time, the DSP sends a voltage to power the relay K2 after passing through the drive circuit, and K2-1 is disconnected. The installation completion circuit is in an open circuit state, that is, the simulation of the installation completion fault is realized.

[0011] Resistor R2 simulates the resistance of the battery ignition wire, and the closed and open states of switch S1 respectively simulate the quality of the battery ignition wire. When S1 is closed, the battery ignition wire circuit is in a connection state, simulating that the battery ignition wire is normal; when S1 is opened, the battery ignition wire circuit is in an open circuit state, simulating that the battery ignition wire is abnormal.

[0012] Resistor R3 simulates the resistance of the engine ignition wire. The closed and open states of switch S2 respectively simulate the quality of the engine ignition wire. When S2 is closed, the engine ignition wire circuit is in a connection state, simulating that the engine ignition wire is normal; when S2 is opened, the engine ignition wire circuit is in an open circuit state, simulating that the engine ignition wire is abnormal.

[0013] Simulate the normal function and fault function of missile battery activation: after receiving the battery activation signal, the current sensor 1 sends the sensitive current signal to the isolation module. The isolated signal is collected by the AD module and sent to the DSP. The DSP writes the collected data into the data recorder. The DSP does not recognize the signal at the DI2 port of the simulated battery activation fault, and after the DSP times 400ms (tentative), the DSP sends a signal to power the relay K1 coil to control K1-1 to close, thereby simulating the battery activation on the missile; when simulating the battery activation fault on the missile, first press the simulated battery activation fault switch S4. At this time, the switch is closed and the circuit is in the on state. The signal output by DO2 of the DSP passes through the drive circuit and the isolation circuit processing circuit and then returns to the DI2 port of the DSP. The DSP recognizes the "battery activation fault" signal. At this time, regardless of whether the DSP collects the battery activation signal, the DSP cannot send voltage to the simulated battery-powered relay K1 to power the simulated battery. The simulated battery-powered line is in an open circuit state, and the simulated battery power supply voltage is not sent, completing the missile battery activation fault simulation.

[0014] Simulate the normal function and fault function of missile engine ignition: after receiving the engine ignition signal, the current sensor 2 sends the current signal to the isolation module, and the isolated signal is sent to the DSP after being collected by the AD module. The DSP writes the collected data into the data recorder. The DSP does not recognize the signal at the DI3 port of the simulated engine ignition fault, and after the DSP timing is 100ms (tentative), the DSP sends the signal to power the relay K2 coil, and the corresponding normally closed contact K2-1 is opened, and the installation is completed. The circuit is disconnected, and the simulated missile flies off the launcher, and the simulation of the missile engine ignition circuit is completed; when simulating the missile engine ignition fault, first press the simulated engine ignition fault switch S5, at this time, the switch is closed, and the circuit is in a path state, and the signal output by DO3 of the DSP returns to the DI3 port of the DSP after passing through the drive circuit and the isolation circuit processing circuit, and the DSP recognizes the "engine ignition fault" signal. At this time, no matter whether the DSP collects the engine ignition signal, the DSP cannot send a voltage to power the relay K2 of the simulated engine ignition, and the installation of the missile is completed. The circuit is not disconnected, and the simulation of the missile engine ignition fault is completed.

[0015] The beneficial effects of the present invention are:

[0016] Different from traditional simulators that can only simply simulate the on-off of the ignition wire and the power supply function, this device has the ability to truly simulate the resistance of the ignition wire, truly simulate the battery activation and engine ignition timing, and can record the activation or ignition current. This device can verify the correctness of the logical timing of the launch and control system ignition control software, and ensure reliable ignition of the launch and control system. This device can be used for missile testing or launch and control system self-inspection, docking debugging and joint debugging, etc. It has the characteristics of simple operation, easy to carry, high versatility, strong practicality and good environmental adaptability.

[0017] It can detect whether the test system or the launch control system can safely and reliably check the ignition wire of the pyrotechnics, whether the launch control system can reliably activate the battery, whether it can reliably ignite the engine, and verify the correctness of the launch and ignition timing of the launch control system, avoiding ignition failures due to problems such as assembly, design, components, and the correctness of the logical timing of the ignition control software, thereby improving the reliability of the launch of the launch control system. The equipment combination is simple, low-cost, easy to implement, and has good versatility, and can be promoted and used in multiple types of weapon platforms. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a circuit schematic diagram of the present invention;

[0019] Figure 2 is a schematic diagram of the operation panel of the present invention;

[0020] Figure 3 It is a timing flow chart of the working of the present invention. DETAILED DESCRIPTION

[0021] Embodiment 1:

[0022] The invention discloses a device for simulating the inspection and activation of the ignition wire of a missile, comprising a shell, and mainly comprising a current sensor, an isolation module, an A / D acquisition module, a DSP, a drive module, a data recorder, a rechargeable battery, an electromagnetic relay, a self-locking key switch and a resistor etc. in the shell. The current sensor is located in the ignition wire inspection / activation circuit and is used for sensitive current signals. The isolation module is respectively connected with the current sensor, the A / D acquisition module, the DSP and the key switch. The DSP is respectively connected with the A / D acquisition module, the data recorder, the drive module and the isolation module. The drive module is respectively connected with the relay, the key switch and the DSP. After the rechargeable battery is connected in series with the key switch, it is respectively connected with the DSP and a ground power supply port and is used for supplying power to the device and simulating the power supply of a battery on a missile.

[0023] The DSP model is TMS320F28335, which is a high-performance, low-power 32-bit floating-point digital signal processor with a main clock operating frequency of 150MHz and a single-cycle instruction execution time of 6.67ns. The TMS320F28335 digital signal processor integrates 256Kx16 Flash memory, 8Kx16 boot ROM, digital operation table and 1Kx16 OTPROM, with large data and program storage capacity.

[0024] Driver module model: SN74LVC4245A. The driver circuit is an intermediate circuit used to amplify the signal of the DSP control circuit, that is, to amplify the signal of the control circuit so that it can drive the battery relay.

[0025] Furthermore, the device has the functions of simulating missile installation completion, simulating normal function and fault function of missile battery ignition wire, simulating normal function and fault function of missile engine ignition wire, simulating normal function and fault function of missile battery activation, simulating normal function and fault function of missile engine ignition and data recording function.

[0026] Furthermore, the self-locking key switch is used for fault simulation setting and powering the equipment. The self-locking key switch is connected in series in the pyrotechnic inspection circuit, and the closing and opening of the self-locking key switch are used to simulate the quality of the ignition wire. The installation completion failure, battery activation failure and engine ignition failure are handled by setting a self-locking key switch between the DO and DI circuits of the DSP. If a high level is detected at the DI port, the corresponding fault simulation is performed.

[0027] Furthermore, the data recorder is used to store activation current and ignition current, and the data in the data recorder is read and erased through the DSP.

[0028] Furthermore, the rechargeable battery is connected in series with the key switch S6, and is connected to the DSP and the ground power supply port. The rechargeable battery is used to power the device and simulate the battery power supply on the missile. The switch S6 is used to control when the battery supplies power to the outside. The power resistor R1 is connected to the common end of the ground power supply and the rechargeable battery to simulate the power load on the missile.

[0029] Furthermore, the normal function and fault function of the simulated missile installation are mainly realized by the electromagnetic relay K2, the key switch S3, the DSP, the drive module and the isolation module. The installation completion circuit is short-circuited with the "ground power supply-", and the normally closed contact of K2-1 is connected in series in the installation completion loop, and the simulated missile installation is normal; the drive module is respectively connected to the DO1 port of the DSP, the relay K2, and the key switch S3, and the isolation module is respectively connected to the DI1 port of the DSP and the key switch S3. When simulating the installation completion fault, the self-locking switch S3 of the simulated installation completion fault needs to be manually pressed in advance. At this time, the switch is closed and the circuit is in a pass state. The signal output by DO1 of the DSP passes through the drive circuit and the isolation circuit processing circuit and then returns to the DI1 port of the DSP. The DSP recognizes the "installation completion fault" signal. At this time, the DSP sends a voltage to power the relay K2 after passing through the drive circuit, K2-1 is disconnected, and the installation completion circuit is in an open circuit state, that is, the simulation of the installation completion fault is realized.

[0030] Furthermore, the simulation of the normal function and fault function of the missile battery ignition wire is to connect the push button switch S1 and the resistor R2 in series to the battery ignition wire inspection circuit. The resistor R2 truly simulates the resistance value of the battery ignition wire. The closed and open states of the switch S1 respectively simulate the quality of the battery ignition wire. When S1 is closed, the battery ignition wire circuit is in a connection state, simulating that the battery ignition wire is normal; when S1 is opened, the battery ignition wire circuit is in an open circuit state, simulating that the battery ignition wire is abnormal.

[0031] Furthermore, the simulation of the normal function and fault function of the engine ignition wire connects the push button switch S2 and the resistor R3 in series to the engine ignition wire inspection circuit. The resistor R3 truly simulates the resistance value of the engine ignition wire. The closed and open states of the switch S2 respectively simulate the quality of the engine ignition wire. When S2 is closed, the engine ignition wire circuit is in a connection state, simulating that the engine ignition wire is normal; when S2 is opened, the engine ignition wire circuit is in an open circuit state, simulating that the engine ignition wire is abnormal.

[0032] Furthermore, the simulation of the normal function and fault function of battery activation on the bomb is mainly realized by a current sensor, an isolation module, an A / D acquisition module, a DSP, an isolation module, a relay and a push button switch. The battery activation circuit passes through the current sensor 1 for sensing the battery activation current. The output end of the current sensor 1 is connected to the isolation module, the input end of the A / D acquisition module is connected to the output end of the isolation module, the DSP is respectively connected to the output end of the A / D acquisition, the data recorder, the drive module and the isolation module, the drive module is connected to the relay K1, and the simulated battery activation fault switch S4 is respectively connected to the drive module and the isolation module; the control system sends a battery activation signal, the current sensor sends the sensed current signal to the isolation module, the isolated signal is collected by the AD module and sent to the DSP, the DSP writes the collected data into the data recorder, and the DSP simulates the battery activation fault in the DI Port 2 does not recognize the signal, and after the DSP times 400ms (tentative), the DSP sends a signal to power the coil of relay K1. The signal is amplified by the drive module and then powers the coil of relay K1. The corresponding normally open contact is actuated, that is, K1-1 is closed, to simulate the activation of the battery on the missile; when simulating the battery activation failure on the missile, the self-locking switch S4 of the simulated battery activation failure needs to be manually pressed in advance. At this time, the switch is closed and the circuit is in the on state. The signal output by DO2 of the DSP passes through the drive circuit and the isolation circuit processing circuit and then returns to the DI2 port of the DSP. The DSP recognizes the "battery activation failure" signal. At this time, regardless of whether the DSP collects the battery activation signal, the DSP cannot send voltage to power the relay K1 that simulates battery power supply. The simulated battery power supply line is in an open circuit state, and the simulated battery power supply voltage is not sent, completing the battery activation failure simulation of the missile.

[0033] Furthermore, the simulated missile engine ignition normal function and fault function are mainly realized by current sensor, isolation module, A / D acquisition module, DSP, isolation module, relay and key switch. The battery activation circuit passes through current sensor 2 for sensing engine ignition current. The output end of current sensor 2 is connected to the isolation module, the input end of A / D acquisition module is connected to the output end of isolation module, DSP is respectively connected to the output end of A / D acquisition, data recorder, drive module and isolation module, drive module is connected to relay K2, simulated engine ignition fault switch S5 is respectively connected to drive module and isolation module; the launch control system sends out engine ignition signal, current sensor sends sensed current signal to isolation module, isolated signal is sent to DSP after being collected by AD module, DSP writes collected data into data recorder, DSP is at DI3 port of simulated engine ignition fault No signal is recognized, and after the DSP times for 100ms (tentative), the DSP sends a signal to power the relay K2 coil. The signal is amplified by the drive module and then powers the relay K2 coil. The corresponding normally closed contact K2-1 is opened, and the circuit is disconnected after installation is completed, so as to simulate the missile flying away from the launch pad and complete the simulation of the missile engine ignition circuit. When simulating the missile engine ignition failure, the self-locking switch S5 simulating the engine ignition failure needs to be manually pressed in advance. At this time, the switch is closed and the circuit is in the on state. The signal output by DO3 of the DSP passes through the drive circuit and the isolation circuit processing circuit and then returns to the DI3 port of the DSP. The DSP recognizes the "engine ignition failure" signal. At this time, regardless of whether the DSP collects the engine ignition signal, the DSP cannot send a voltage to power the relay K2 simulating the engine ignition. The missile installation is completed and the circuit is not disconnected, completing the simulation of the missile engine ignition failure.

[0034] Embodiment 2:

[0035] Figure 1This is a circuit diagram of a device for simulating the inspection and activation of missile ignition wires. The device mainly includes a current sensor, an isolation module, an A / D acquisition module, a DSP, a drive module, a data recorder, a rechargeable battery, a relay, a key switch, and a resistor. By inserting a resistor and a self-locking key switch in series in the pyrotechnic inspection circuit, the resistor truly simulates the resistance value of the ignition wire, and the closing and opening of the self-locking key switch simulate the quality of the ignition wire; the activation / ignition circuit passes through the current sensor, and the current sensor sends the sensitive activation / ignition current signal to the isolation module. The isolated signal is sent to the DSP after AD acquisition, and the DSP writes the collected data into the data recorder. ; Set a self-locking key switch between the DO and DI circuits of the DSP. If a high level is detected at the DI port, the corresponding fault simulation is performed; When the DSP receives the activation / ignition signal and the DSP does not recognize the fault simulation signal at the DI port, after the DSP timing requirements are met, the DSP sends a signal, which is amplified by the drive circuit and sent to both ends of the relay coil to control the contact action of the corresponding relay to achieve battery activation or engine ignition simulation; Connect the normally closed contact K2-1 in series in the installation completion circuit. If the DSP detects the installation completion fault signal at the DI port, the DSP supplies power to the K2 relay and disconnects the normally closed contact K2-1 to achieve the installation completion fault simulation. Battery power supply.

[0036] The DSP model is TMS320F28335, which is a high-performance, low-power 32-bit floating-point digital signal processor with a main clock operating frequency of 150MHz and a single-cycle instruction execution time of 6.67ns. The TMS320F28335 digital signal processor integrates 256Kx16 Flash memory, 8Kx16 boot ROM, digital operation table and 1Kx16 OTPROM, with large data and program storage capacity.

[0037] Driver module model: SN74LVC4245A. The driver circuit is an intermediate circuit used to amplify the signal of the DSP control circuit, that is, to amplify the signal of the control circuit so that it can drive the battery relay.

[0038] like Figure 2As shown, a schematic diagram of the operation panel of a simulated missile ignition wire inspection and activation device of the present invention. The drop-out socket in the panel is used to connect with the launch control system or the test system; the DSP interface is used for software update inside the DSP and erasing and reading the data recorder; the battery charging interface is used to charge the rechargeable battery; six self-locking switches, five of which are used for fault setting, and one switch is used to control battery power supply. The initial state of the self-locking switches in the device is: the battery ignition wire fault switch S1 and the engine ignition wire fault switch S2 are in the closed state; the missile installation completion switch S3, the battery activation fault switch S4 and the engine ignition fault switch S5 are in the open state; the battery power supply switch S6 is in the open state when the device is not working, and the switch S6 needs to be closed when working.

[0039] Figure 3 The working sequence flow chart of the simulated missile ignition wire inspection and activation device of the present invention mainly includes four processes: fault setting, pyrotechnic inspection, power connection preparation and launch. Figure 2 and Figure 3 The specific steps of the device are as follows:

[0040] Step 1: The device is connected to the control system or the test system by cable;

[0041] Step 2: close the power switch S6 of the rechargeable battery, the rechargeable battery supplies power to the device, and the device is initialized and self-checked;

[0042] Step three, perform corresponding fault settings on the device as required, wherein the fault settings include simulating a missile battery ignition wire fault, simulating a missile engine ignition wire fault, simulating a missile installation completion fault, simulating a missile battery activation fault, and simulating a missile engine ignition fault; if a missile installation completion fault is set, switch S3 is closed, DSP recognizes a signal at port DI1, DSP supplies power to relay K2, normally closed contact K2-1 is disconnected, and the missile installation completion circuit is in an open circuit state; if a missile battery ignition wire fault is set, switch S1 is opened; if a missile engine ignition wire fault is set, switch S2 is opened; if a missile battery activation fault is set, switch S4 is closed, DSP recognizes a signal at port DI2; if a missile engine ignition fault is set, switch S5 is closed, DSP recognizes a signal at port DI3;

[0043] Step 4: The equipment cooperates with the control system or the test system to complete the installation inspection;

[0044] Step 5: The device cooperates with the launch control system or the test system to complete the inspection of the battery ignition wire and the engine ignition wire;

[0045] Step 5: The control system or the test system supplies ground power to the device;

[0046] Step 6: The device receives the battery activation current sent by the control system, and the current sensor sends the detected signal to the isolation module. The isolated signal is collected by the AD module and sent to the DSP. The DSP writes the collected data into the data recorder. The DSP does not recognize the signal at the DI2 port of the simulated battery activation failure, and after the DSP times for 400ms (tentative), the DSP supplies power to the coil of the electromagnetic relay K1, and the corresponding normally open contact is actuated, that is, K1-1 is closed, to simulate the battery power supply and complete the simulation of successful battery activation; if the DSP does not receive the battery activation signal or recognizes the signal at the DI2 port, the DSP does not supply power to the coil of the relay K1, and the battery activation fails;

[0047] Step 7: The control system disconnects the ground power supply to the device;

[0048] Step 8: The device receives the engine ignition current sent by the launch control system, and the current sensor sends the detected signal to the isolation module. The isolated signal is collected by the AD module and sent to the DSP. The DSP writes the collected data into the data recorder. The DSP does not recognize the signal at the DI3 port of the simulated engine ignition failure, and after the DSP times 100ms (tentative), the DSP supplies power to the coil of the electromagnetic relay K2, and the corresponding normally closed contact K2-1 is closed. After the installation is completed, the circuit is disconnected to simulate the missile flying away from the launch pad and complete the simulation of successful engine ignition. If the DSP does not receive the engine ignition signal or recognizes the signal at the DI3 port, the DSP does not supply power to the coil of the relay K2, and the engine ignition fails.

[0049] Step nine, reading and erasing the data of the data recorder according to the DSP interface;

[0050] Step 10, turn on the power switch S6 of the rechargeable battery, disconnect the power supply of the device, and reset all buttons.

Claims

1. A device for simulating the inspection and activation of missile ignition wires, comprising a current sensor, an A / D acquisition module and a DSP, characterized in that: The current sensor 1 and the current sensor 2 are respectively connected to the first isolation module, the first isolation module is connected to the A / D acquisition module, the A / D acquisition module is connected to the DSP, and the DSP is respectively connected to the data recorder and the drive module. The drive module is connected to two electromagnetic relays through two circuits. The two electromagnetic relays K1 and K2 control the power supply switch K1-1 and the power supply signal switch K2-1 respectively. The DO port of the driver module is connected back to the DI port of the DSP through three analog fault switches and the second isolation module; The current sensor 1 is connected to the battery ignition wire check / activation circuit and a simulated battery ignition wire fault switch S1 and resistor R2 are installed on the circuit; The current sensor 2 is connected to the engine ignition wire check / activation circuit and a simulated engine ignition wire fault switch S2 and a resistor R3 are installed on the circuit.

2. The device for simulating missile ignition wire inspection and activation according to claim 1, characterized in that: The DSP is connected to the rechargeable battery and the ground power supply port. A battery power switch S6 is provided to control whether the rechargeable battery supplies power. A power resistor R1 is connected to the common end of the ground power supply and the rechargeable battery to simulate the power load on the missile.

3. The device for simulating missile ignition wire inspection and activation according to claim 2, characterized in that: The closing and opening of the simulated ignition wire fault switch simulates the quality of the ignition wire. The missile installation completion failure, battery activation failure and engine ignition failure are simulated by setting three button switches between the DO and DI circuits of the DSP, including the simulated installation completion failure switch S3, the simulated battery activation failure switch S4 and the simulated engine ignition failure switch S5.

4. The device for simulating missile ignition wire inspection and activation according to claim 3, characterized in that: The device is installed in a housing, and a drop-out socket, a DSP interface and a battery charging port are provided on the housing panel, and S1-S6 are also installed on the housing panel.

5. A method for simulating the inspection and activation of a missile ignition wire, comprising the device for simulating the inspection and activation of a missile ignition wire according to claim 3 or 4, characterized in that: The electromagnetic relay K2, simulated installation completion fault switch S3, DSP, drive module and second isolation module realize the normal function and fault function of missile installation completion. The installation completion circuit is short-circuited with "ground power supply-", and the normally closed contact of the power supply signal switch K2-1 is connected in series in the installation completion loop to simulate the normal installation of the missile. When simulating the installation completion fault, first press the simulated installation completion fault switch S3. At this time, the switch is closed and the circuit is in the on state. The signal output by DO1 of DSP passes through the drive circuit and the isolation circuit processing circuit and then returns to the DI1 port of DSP. DSP recognizes the "installation completion fault" signal. At this time, DSP sends voltage through the drive circuit to power the electromagnetic relay K2, and the power supply signal switch K2-1 is disconnected. The installation completion circuit is in the open circuit state, which realizes the simulation of the installation completion fault.

6. The method for simulating missile ignition wire inspection and activation according to claim 5, characterized in that: Resistor R2 simulates the resistance of the battery ignition wire, and the closed and open states of switch S1 respectively simulate the quality of the battery ignition wire. When S1 is closed, the battery ignition wire circuit is in a connection state, simulating that the battery ignition wire is normal; when S1 is opened, the battery ignition wire circuit is in an open circuit state, simulating that the battery ignition wire is abnormal.

7. The method for simulating missile ignition wire inspection and activation according to claim 5, characterized in that: Resistor R3 simulates the resistance of the engine ignition wire. The closed and open states of switch S2 respectively simulate the quality of the engine ignition wire. When S2 is closed, the engine ignition wire circuit is in a connection state, simulating that the engine ignition wire is normal; when S2 is opened, the engine ignition wire circuit is in an open circuit state, simulating that the engine ignition wire is abnormal.

8. The method for simulating missile ignition wire inspection and activation according to claim 6, characterized in that Simulate the normal function and fault function of missile battery activation: after receiving the battery activation signal, the current sensor 1 sends the sensitive current signal to the first isolation module. The isolated signal is collected by the AD module and sent to the DSP. The DSP writes the collected data into the data recorder. The DSP does not recognize the signal at the DI2 port of the simulated battery activation fault. After the DSP counts for a certain period of time, the DSP sends a signal to the electromagnetic relay K1 coil to control the power supply switch K1-1 to close, thereby simulating the activation of the battery on the missile. When simulating the battery activation fault on the missile, first press the simulated battery activation fault switch S4. At this time, the switch is closed and the circuit is in the on state. The signal output by DO2 of the DSP passes through the drive circuit and the isolation circuit processing circuit and then returns to the DI2 port of the DSP. The DSP recognizes the "battery activation fault" signal. At this time, regardless of whether the DSP collects the battery activation signal, the DSP cannot send voltage to the electromagnetic relay K1 simulating battery power supply. The simulated battery power supply line is in an open circuit state, and the simulated battery power supply voltage is not sent, completing the missile battery activation fault simulation.

9. The method for simulating missile ignition wire inspection and activation according to claim 5, characterized in that Simulate the normal function and fault function of missile engine ignition: after receiving the engine ignition signal, the current sensor 2 sends the current signal to the first isolation module. The isolated signal is collected by the AD module and sent to the DSP. The DSP writes the collected data into the data recorder. The DSP does not recognize the signal at the DI3 port of the simulated engine ignition fault, and after the DSP counts for a certain period of time, the DSP sends a signal to power the electromagnetic relay K2 coil, and the normally closed contact corresponding to the power supply signal switch K2-1 is opened, and the installation is completed. The circuit is disconnected to simulate the missile flying away from the launcher and complete the simulation of the missile engine ignition circuit; when simulating the missile engine ignition fault, first press the simulated engine ignition fault switch S5. At this time, the switch is closed and the circuit is in the on state. The signal output by DO3 of the DSP passes through the drive circuit and the isolation circuit processing circuit and then returns to the DI3 port of the DSP. The DSP recognizes the "engine ignition fault" signal. At this time, regardless of whether the DSP collects the engine ignition signal, the DSP cannot send voltage to power the electromagnetic relay K2 simulating engine ignition. The installation of the missile is completed and the circuit is not disconnected, completing the simulation of the missile engine ignition fault.

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