A ground test system and test method for on-board equipment

Abstract

The present invention relates to a ground test system for on-board equipment and a test method thereof, belonging to the technical field of missile testing. A ground test system for on-board equipment includes: a control board, a panel, a power supply system, a housing, and an external connector; wherein, the panel and the external connector are located on the surface of the housing, the control board and the power supply system are embedded in the housing, the power supply system is connected to the control board, the control board is connected to the panel, the power supply system is used to supply power to the control board, and the control board realizes the measurement of the on-board equipment through the external connector; then, the ground test system for on-board equipment is used to collect and provide corresponding missile current and voltage, and conduct missile communication to complete a complete set of missile test processes.

Description

Technical Field

[0001] The present invention relates to a ground test system for on-board equipment and a test method thereof, belonging to the technical field of missile testing. Background Art

[0002] Traditional testing and acceptance methods for missiles require a lot of time, equipment and manpower. Generally, a laptop computer, an oscilloscope, a DC regulated power supply, an RS422 to USB conversion module, a multimeter, etc. are needed. At the same time, operators need to have high professional knowledge and a lot of operation experience. In order to complete the functional testing of a certain type of missile at the technical position and technical workshop and meet the requirements of one-key testing and non-opening testing of the missile, a ground test system for on-board equipment needs to be developed. Summary of the Invention

[0003] The present invention provides a ground test system for on-board equipment and a test method, which can meet the needs of one-key testing and non-opening testing of missiles.

[0004] A ground test system for on-board equipment includes: a control board, a panel, a power supply system, a housing, and an external connector;

[0005] Among them, the panel and the external connector are located on the surface of the housing, the control board and the power supply system are embedded in the housing, the power supply system is connected to the control board, the control board is connected to the panel, the power supply system is used to supply power to the control board, the control board measures the on-board equipment through the external connector, and six indicator lights are attached to the panel;

[0006] The power supply system includes: a battery, a 220V adapter, a 28V DC power input module, an anti-reverse connection circuit, an overvoltage protection circuit, a power-on button, a filtering module, a first relay module, and a second relay module;

[0007] Among them, the battery is connected to the first input terminal of the first relay, the 220V adapter is respectively connected to the second input terminal and the coil control terminal of the first relay, and the output of the first relay is connected to the first input terminal of the second relay; the 28V DC power input module is sequentially connected in series with an anti-reverse connection module, an overvoltage protection module and a diode and then respectively connected to the second input terminal and the coil control terminal of the second relay, the output of the second relay is connected to the power-on button, and the output of the power-on button is connected to the control board after passing through the filtering module.

[0008] Further, the control board includes a 28V DC / DC module, a 5V DC / DC module, a first energy storage module, a second energy storage module, FK-I path MOS, FK-II path MOS, a first current detection module, a second current detection module, an STM32 minimum system, an isolation op-amp module, an isolation RS422 chip, an isolation optocoupler module, and an isolation opto-MOS module;

[0009] The input of the 28V DC / DC module is connected to the power supply system, and the outputs are respectively connected to the first energy storage module, the second energy storage module, and the 5V DC / DC module. The output of the first energy storage module is connected to the input of the FK-I path MOS, and the first current detection module is connected to the output of the FK-I path MOS, and its output is used to supply power to the FK-I path of the missile; the output of the second energy storage module is connected to the input of the FK-II path MOS, and the second current detection module is connected to the output of the FK-II path MOS, and its output is used to supply power to the FK-II path of the missile; the output of the 5V DC / DC module supplies power to the STM32 minimum system. The first interface of the STM32 minimum system is connected to an isolation operational amplifier for detecting the current and voltage of the missile, the second interface of the STM32 minimum system is connected to an isolation RS422 chip for missile communication and upper computer communication, the third interface of the STM32 minimum system is connected to an isolation optocoupler for cable self-check and button detection, and the fourth interface of the STM32 minimum system is connected to an isolation optical MOS for supplying power to the panel and controlling the power supply of the FK-I path and the FK-II path.

[0010] Furthermore, for the isolation optical MOS, its output is divided into three paths. One output path supplies power to the panel, one output path controls the on / off of the FK-I path MOS, and one output path controls the on / off of the FK-II path MOS.

[0011] Furthermore, for the isolation RS422 chip, the output end of the isolation RS442 chip is divided into two interfaces, one end for communicating with the missile and one end for communicating with the upper computer.

[0012] A test method based on the on-board equipment ground test equipment includes the following steps:

[0013] Step 1: The STM32 minimum system receives cable self-check and button detection information through the path where the isolation optocoupler is located. After the information is detected to be normal, it communicates with the missile through the isolation RS422 chip to check the on-orbit status. If it is detected that the missile is not on orbit, the STM32 minimum system stops the test, transmits data to the upper computer, and the STM32 minimum system controls all indicator lights to turn red through the isolation optical MOS module. If it shows that the missile is on orbit, the output end interface of the isolation optical MOS controls the FK-II path MOS to conduct to complete the power supply of the missile's FK-II path;

[0014] Step 2: After passing through the isolation operational amplifier, the STM32 minimum system receives the power supply information of the missile's FK-II MOS terminal. If it detects abnormal power supply at the missile's FK-II MOS terminal, the STM32 minimum system stops the test, transmits data to the host computer, and controls the first indicator light to turn red through the isolation optical MOS module. If it detects normal power supply at the missile's FK-II MOS terminal, the STM32 minimum system checks the missile communication status through the isolation RS422 chip after communication with the missile;

[0015] Step 3: After passing through the isolation RS422 chip, the STM32 minimum system checks the communication status through communication with the missile. If it detects abnormal missile communication, the STM32 minimum system stops the test, transmits data to the host computer, and controls the second indicator light to turn red through the isolation optical MOS module. If it detects normal missile communication, the output terminal interface of the isolation optical MOS controls the FK-I MOS to conduct to complete the power supply of the missile's FK-I path;

[0016] Step 4: After passing through the isolation operational amplifier, the STM32 minimum system receives the power supply information of the missile's FK-I MOS terminal. If it detects abnormal power supply at the missile's FK-I MOS terminal, the STM32 minimum system stops the test, transmits data to the host computer, and controls the third indicator light to turn red through the isolation optical MOS module. If it detects normal power supply at the missile's FK-I MOS terminal, the STM32 minimum system checks the working status of each component of the missile through the isolation RS422 chip after communication with the missile;

[0017] Step 5: If it detects abnormal operation of each component of the missile, the STM32 minimum system stops the test, transmits data to the host computer, and controls the fourth, fifth, and sixth indicator lights to turn red through the isolation optical MOS module. If it detects normal operation of each component of the missile, the test is completed.

[0018] Beneficial effects:

[0019] First, the power supply system of the system. The corresponding power priority distribution circuit is completed through two relay coils therein, and the corresponding priority is external DC power supply > battery charging > battery power supply. The DC power input has priority in power supply. When the DC power supply is not powered, the 220V adapter starts to charge the battery, and then the battery supplies power. That is, as long as the DC power supply is started, due to the function of the second relay, only the DC power input circuit exists, which is the highest priority. When the DC power is not input, as long as the 220V adapter is started, due to the function of the first relay, the battery and the 220V adapter are conducted to charge, which is the second priority. Only when both of the above two power supplies are not started can the battery start to enter the battery input state. During operation, in the corresponding battery charging state, the 220V adapter charges the battery. When the 220V adapter is connected, the corresponding coil J1 conducts the coil, and the battery and the 220V adapter form a loop to charge, avoiding the danger of the missile being detonated due to the 220V voltage input into the system during the system charging process.

[0020] Second, two working modes can be carried in this system because of the isolated RS422 chip. The output end of the isolated RS442 chip is divided into two-way interfaces, one end communicates with the missile, and the other end communicates with the upper computer. It can meet the two working modes of the system. The system working process is divided into two types: offline mode and online mode, both of which are "one-key testing", and the system automatically determines the working mode. In the offline mode working process, it is not necessary to connect a laptop computer and a test system. In the online mode, it is necessary to connect a laptop computer powered only by the battery and a test system before the missile test process. The laptop computer serves as the upper computer. Open the laptop computer software, select the appropriate port number and open it, and then start the missile working process test. It improves the portability of the system.

[0021] Third, the power supply part and the control board in the system are both wrapped in a housing, which has certain rainproof, sand and dust proof, and anti-drop capabilities, and has good portability, suitable for use in the field sand and dust environment. Description of the Drawings

[0022] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required to be used in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0023] Figure 1 It is a schematic diagram of the appearance of the test system.

[0024] Figure 2 It is a schematic diagram of the structure of the test system.

[0025] Figure 3It is a schematic diagram of the composition of the test system.

[0026] Figure 4 It is an under-voltage, over-voltage and reverse protection circuit.

[0027] Figure 5 It is a schematic diagram of power supply priority allocation.

[0028] Figure 6 It is a RS422 communication circuit diagram.

[0029] Figure 7 It is the digital quantity of the control panel indicator light.

[0030] Figure 8 It is the digital quantity of the control power supply output.

[0031] Figure 9 It is a schematic diagram of the input digital quantity.

[0032] Figure 10 It is a schematic diagram of AD acquisition.

[0033] Figure 11 It is a flowchart of the embedded software.

[0034] Figure 12 It is a schematic diagram of the host computer software interface. Specific implementation mode

[0035] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0036] This embodiment provides a ground test system and test method for on-board equipment. The system is as shown in the attached Figure 1 and attached Figure 2 figures, and includes: handle 1, panel 2, housing 3, external connectors 4, 5, 6, 7, control board 8, power supply system 9;

[0037] Among them, the panel and the external connectors are located on the surface of the housing, the control board and the power supply system are embedded in the housing, the power supply system is connected to the control board, and the control board is connected to the panel; the circuit board and each integrated module are screwed to the chassis through mounting ears or pressure plates, which improves the overall stiffness of the housing, effectively reduces the bending and deformation of the printed circuit board and each module under vibration and impact, and at the same time installs shock pads to improve the overall anti-vibration and anti-impact capabilities. Components with high power consumption such as batteries are directly connected to the housing, shortening the conduction path and increasing the contact area, so that the battery heat can be quickly dissipated to the outer wall of the chassis; by copper plating on the printed board, the heat dissipation area is increased to ensure reliability. For heat-generating devices on the printed circuit board such as power modules, heat-dissipating copper foils are placed at the bottom of the module, and at the same time, the heat-dissipating copper foils are connected to the chassis studs through the chassis, and the heat is exported through the studs to improve the power supply reliability. When the height permits, heat sinks are placed on the power modules for heat dissipation. Waterproof connectors are selected. In the structural design, a boss connection method is adopted, and sealing rings and sealing grooves are added at the housing joints. Protective paint is coated on the surface of the chassis and the module surface. Materials resistant to salt spray and damp heat are selected for the chassis and connectors. At the same time, the printed circuit board adopts three-proof (anti-salt spray, anti-mildew, anti-sand and dust) measures.

[0038] As shown in the appendix Figure 3 As shown, the control board includes a 28V DC / DC module, a 5V DC / DC module, a first energy storage module, a second energy storage module, an FK I-way MOS, an FK II-way MOS, a first current detection module, a second current detection module, an STM32 minimum system, an isolation op-amp module, an isolation RS422 chip, an isolation optocoupler module, and an isolation opto-MOS module;

[0039] The input of the 28V DC / DC module is connected to the power supply system, and the outputs are respectively connected to the first energy storage module, the second energy storage module, and the 5V DC / DC module. The output of the first energy storage module is connected to the input of the FK I-way MOS, the first current detection module is connected to the output of the FK-I way MOS, the output of the second energy storage module is connected to the input of the FK-II way MOS, the second current detection module is connected to the output of the FK-II way MOS, and the output of the 5V DC / DC module supplies power to the STM32 minimum system. The four outputs of the STM32 minimum system are respectively connected to the isolation op-amp, the isolation RS422 chip, the isolation optocoupler, and the isolation opto-MOS. The functions of the components of the system are as follows:

[0040] (1) Power supply system design;

[0041] The power supply system includes: a battery, a 220V adapter, a 28V DC power input module, an anti-feedback circuit, an overvoltage protection circuit, a power-on button, a filtering module, a first relay module, and a second relay module;

[0042] Among them, the under-voltage, over-voltage and reverse protection circuits are as Figure 4 shown;

[0043] As shown in the appendix Figure 5 shown, where the battery is connected to the input of the first relay, the 220V adapter is respectively connected to the input interface and the coil control terminal of the first relay, the output of the first relay is connected to the input of the second relay, and after the coil is powered on, the magnetic flux device pulls down the switch, and the battery and the 220V adapter form a charging circuit; the 28V DC power input module is connected to the reverse connection prevention and over-voltage protection circuit, and its output is respectively connected to the input terminal and the coil control terminal of the second relay, the output of the second relay is connected to the power-on button, and the output of the power-on button is connected to the 28V DC / DC module after passing through the filtering module.

[0044] In terms of the working mode, it has a power priority allocation function. The power system has three working conditions: battery power supply, AC power charging, and DC power supply. In the case where the input and output are the same connector, according to the actual usage characteristics, that is, as long as the DC power is started, due to the role of the second relay, only the DC power input circuit is caused, which is the highest priority. When the DC power is not input, as long as the 220V adapter is started, due to the role of the first relay, the battery and the 220V adapter are conducted for charging, which is the second priority. Only when both of the above two power supplies are not started, the battery can be started to enter the battery input state. It can be seen that the priority order of the three working conditions is: external DC (i.e., 28V DC power) power supply > battery charging > battery power supply. The priority allocation of different working conditions is realized through two relays.

[0045] Battery power supply state: The battery supplies power to the system, and the corresponding 220V adapter and 28V DC output are not conducted, and the battery directly supplies power to the system.

[0046] Battery charging state: The 220V adapter charges the battery, the 220V adapter is connected, the corresponding coil J1 conducts the coil, and the battery and the 220V adapter form a loop for charging, avoiding the system being powered on and used during the system charging process, and improving the safety of missile testing.

[0047] Battery power supply state: The 28V DC voltage conducts, and the corresponding J2 coil is powered on, so that the system is directly connected to the external 28VDC and enters the DC power supply state. It ensures that the system can still work normally and safely when the battery is damaged and in the charging state.

[0048] (2) RS422 communication circuit design

[0049] The test system shall include two-way RS422 communication functions, which communicate with the missile and the laptop computer respectively. The interface circuit for communication selects an isolated transceiver. This device includes an integrated isolated DC / DC power supply, and isolation is achieved through different isolated grounds, eliminating the need for an external DC / DC isolation module. The circuit schematic diagram is as attached Figure 6 as shown.

[0050] Furthermore, for the isolated RS422 chip, the output terminals of the isolated RS442 chip are divided into two-way interfaces, one end communicates with the missile and the other end communicates with the host computer. It can meet the two working modes of the system. The system working process is divided into two types: offline mode and online mode, both of which are "one-key testing", and the system automatically determines the working mode. In the offline mode working process, there is no need to connect the laptop computer and the test system. In the online mode, a laptop computer powered only by battery and the test system need to be connected before the missile test process. The laptop computer serves as the host computer. Open the laptop computer software, select the appropriate port number and open it, and then start the missile working process test.

[0051] (3) Design of digital output circuit

[0052] That is the KO circuit on the control board. In this embodiment, in order to more intuitively display the operating state of the system, an indicator light module is added. The digital output is mainly used to control the panel indicator lights and the power supply output. In this design, an isolated opto-MOS transistor and a Darlington transistor are used to implement the circuit design. Among them, the panel indicator lights are controlled by the Darlington transistor, and the power supply output is controlled by the opto-MOS transistor. The schematic diagram is shown in Attachment Figure 7 and Attachment Figure 8 as shown.

[0053] (4) Design of digital input circuit

[0054] That is the KI circuit in the control board circuit diagram. The digital input function is mainly used for cable self-check, panel button detection, and missile on-orbit / off-orbit detection. This signal is input to the controller after being isolated by an optocoupler, and its input status is queried. The KI interface circuit is shown in Attachment Figure 9 as shown.

[0055] (5) Design of voltage acquisition circuit

[0056] The test system needs to monitor the power supply voltage and current of the missile in real time. It is connected to the AD part of the control board, and the sampled voltage is designed with isolation. The schematic diagram of the circuit principle is shown in Attachment Figure 10 as shown.

[0057] (6) Cable self-check design

[0058] After the self-check of the power supply signal lines of Launch Control I and Launch Control II passes through cable reconnection, they are connected to the isolation optocoupler, enter the STM32 minimum system through the KI circuit, and access the input digital quantity detection circuit of GPIO. The input digital quantity of the power signal detected by GPIO indicates that the cable self-check is qualified. The electrical separation is the same. For the RS422 communication of the launch control box, the input-output short-circuit method at the reconnection plug is selected to implement the serial port loopback, and the correct loopback data indicates that the cable detection is qualified.

[0059] A test method based on the ground test equipment of the on-missile equipment includes the following steps, as shown in the appendix Figure 11 as follows:

[0060] Step 1: The STM32 minimum system receives the cable self-check and key detection information through the path where the isolation optocoupler is located. After the information is detected normally, it passes through the isolated RS422 chip to check the on-orbit status with the missile. If it is detected that the missile is not on orbit, the STM32 minimum system stops the test, the STM32 minimum system controls all indicator lights to turn red through the isolated optical MOS module, and transmits data to the host computer. If it shows that the missile is on orbit, the output interface of the isolated optical MOS controls the FK-II path MOS to conduct to complete the power supply of the missile's FK-II path.

[0061] Step 2: After passing through the isolation operational amplifier, the STM32 minimum system receives the power supply information of the missile's FK-II path MOS terminal. If it is detected that the power supply of the missile's FK-II path MOS terminal is abnormal, the STM32 minimum system stops the test and transmits data to the host computer. The STM32 minimum system controls the first indicator light to turn red through the isolated optical MOS module. If it is detected that the power supply of the missile's FK-II path MOS terminal is normal, the STM32 minimum system checks the missile communication status through the isolated RS422 chip.

[0062] Step 3: After passing through the isolated RS422 chip, the STM32 minimum system checks the communication status with the missile. If it is detected that the missile communication is abnormal, the STM32 minimum system stops the test and transmits data to the host computer. The STM32 minimum system controls the second indicator light to turn red through the isolated optical MOS module. If it is detected that the missile communication is normal, the output interface of the isolated optical MOS controls the FK-I path MOS to conduct to complete the power supply of the missile's FK-I path.

[0063] Step 4: After the STM32 minimum system passes through the isolation operational amplifier, it receives the power supply information of the MOS terminal of the missile's FK-I path. If it detects that the power supply of the MOS terminal of the missile's FK-I path is abnormal, the STM32 minimum system stops the test, transmits data to the host computer, and the STM32 minimum system controls the third indicator light to turn on a red light through the isolation optical MOS module. If it detects that the power supply of the MOS terminal of the missile's FK-I path is normal, the STM32 minimum system communicates with the missile through the isolation RS422 chip to check the working status of each component of the missile;

[0064] Step 5: If it detects that each component of the missile is working abnormally, the STM32 minimum system stops the test, transmits data to the host computer, and the STM32 minimum system controls the fourth, fifth, and sixth indicator lights to turn on red lights through the isolation optical MOS module. If it detects that each component of the missile is working normally, the test is completed.

[0065] As described above, it is only the specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims

1. A ground test system for on-board equipment, characterized in that, Including: Control board, panel, power supply system, housing, and external connectors; Among them, the panel and the external connectors are located on the surface of the housing, the control board and the power supply system are embedded in the housing, the power supply system is connected to the control board, the control board is connected to the panel, the power supply system is used to supply power to the control board, the control board measures the on-board equipment through the external connectors, and six indicator lights are attached to the panel; The power supply system includes: a battery, a 220V adapter, a 28V DC power input module, an anti-reverse connection circuit, an overvoltage protection circuit, a power-on button, a filtering module, a first relay module, and a second relay module; Among them, the battery is connected to the first input terminal of the first relay, the 220V adapter is respectively connected to the second input terminal and the coil control terminal of the first relay, and the output of the first relay is connected to the first input terminal of the second relay; the 28V DC power input module is sequentially connected in series with an anti-reverse connection module, an overvoltage protection module, and a diode and then respectively connected to the second input terminal and the coil control terminal of the second relay, the output of the second relay is connected to the power-on button, and the output of the power-on button is connected to the control board after passing through the filtering module.

2. The system according to claim 1, wherein The control board includes a 28VDC / DC module, a 5VDC / DC module, a first energy storage module, a second energy storage module, FK-I path MOS, FK-II path MOS, a first current detection module, a second current detection module, an STM32 minimum system, an isolation operational amplifier module, an isolation RS422 chip, an isolation optocoupler module, and an isolation optical MOS module; The input of the 28VDC / DC module is connected to the power supply system, and the outputs are respectively connected to the first energy storage module, the second energy storage module, and the 5VDC / DC module. The output of the first energy storage module is connected to the input of the FK-I path MOS, and the first current detection module is connected to the output of the FK-I path MOS, and its output is used to supply power to the FK-I path of the missile; The output of the second energy storage module is connected to the input of the FK-II path MOS, and the second current detection module is connected to the output of the FK-II path MOS, and its output is used to supply power to the FK-II path of the missile; The output of the 5VDC / DC module supplies power to the STM32 minimum system. The first interface of the STM32 minimum system is connected to the isolation operational amplifier to detect the current and voltage of the missile. The second interface of the STM32 minimum system is connected to the isolation RS422 chip for missile communication and communication with the upper computer. The third interface of the STM32 minimum system is connected to the isolation optocoupler for cable self-check and button detection. The fourth interface of the STM32 minimum system is connected to the isolation optical MOS for supplying power to the panel and controlling the power supply of the FK-I path and the FK-II path.

3. The system according to claim 2, wherein The isolation optical MOS module has three output paths. The first output path supplies power to the panel, the second output path controls the on-off of the FK-I path MOS, and the second output path controls the on-off of the FK-II path MOS.

4. The system according to claim 2, wherein For the isolation RS422 chip, the output terminal of the isolation RS422 chip is divided into two interfaces, one end for missile communication and the other end for communication with the upper computer.

5. A method for ground testing of on-board equipment based on any one of the testing systems in claims 1-4, including the following steps: Step 1: The STM32 minimum system receives the cable self-check and button detection information through the path where the isolation optocoupler is located. After the information detection is normal, it communicates with the missile through the isolation RS422 chip to check the on-orbit status. If it is detected that the missile is not on orbit, the STM32 minimum system stops the test and transmits data to the host computer. The STM32 minimum system controls all the indicator lights to turn red through the isolation optical MOS module. If it shows that the missile is on orbit, the output interface of the isolation optical MOS controls the FK-II path MOS to conduct to complete the power supply of the missile's FK-II path. Step 2: After passing through the isolation operational amplifier, the STM32 minimum system receives the power supply information of the missile's FK-II path MOS terminal. If it is detected that the power supply of the missile's FK-II path MOS terminal is abnormal, the STM32 minimum system stops the test and transmits data to the host computer. The STM32 minimum system controls the first indicator light to turn red through the isolation optical MOS module. If it is detected that the power supply of the missile's FK-II path MOS terminal is normal, the STM32 minimum system communicates with the missile through the isolation RS422 chip to check the missile communication status. Step 3: After passing through the isolation RS422 chip, the STM32 minimum system communicates with the missile to check the communication status. If it is detected that the missile communication is abnormal, the STM32 minimum system stops the test and transmits data to the host computer. The STM32 minimum system controls the second indicator light to turn red through the isolation optical MOS module. If it is detected that the missile communication is normal, the output interface of the isolation optical MOS controls the FK-I path MOS to conduct to complete the power supply of the missile's FK-I path. Step 4: After passing through the isolation operational amplifier, the STM32 minimum system receives the power supply information of the missile's FK-I path MOS terminal. If it is detected that the power supply of the missile's FK-I path MOS terminal is abnormal, the STM32 minimum system stops the test and transmits data to the host computer. The STM32 minimum system controls the third indicator light to turn red through the isolation optical MOS module. If it is detected that the power supply of the missile's FK-I path MOS terminal is normal, the STM32 minimum system communicates with the missile through the isolation RS422 chip to check the working status of each component of the missile. Step 5: If it is detected that the working of each component of the missile is abnormal, the STM32 minimum system stops the test and transmits data to the host computer. The STM32 minimum system controls the fourth, fifth, and sixth indicator lights to turn red through the isolation optical MOS module. If it is detected that the working of each component of the missile is normal, the test is completed.

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