Target projectile detection system and target projectile
By introducing data exchange equipment and collaborative control equipment into the target ammunition detection system, the problem that traditional detection methods cannot determine the actual status of the target ammunition equipment is solved, and accurate detection of the target ammunition ignition and launch box control performance is achieved to ensure that the target ammunition is in Reliability of pre-flight status.
Patent Information
- Application Number
- CN202411703017.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-26
- Publication Date
- 2025-01-10
AI Technical Summary
Traditional target bomb detection methods cannot determine the actual status of the target bomb equipment, and cannot accurately judge the effectiveness of the equipment detection results, especially after the equipment has been loaded into the bullet structure, it is impossible to conduct further detection.
A target bullet detection system is designed, including data exchange equipment and collaborative control equipment. The collaborative control equipment includes a target bullet main control module, an ignition control module and a launch box control module. Through these modules, control signals can be received and sent to determine the test. The ignition performance of the target projectile and the launch box control performance.
The accuracy of the ignition detection results of the target projectile to be tested and the detection results of the launch box control are improved, ensuring that the target projectile equipment reaches a normal state before flight, and enhancing the functional integrity and accuracy of the detection system.
Smart Images
Figure CN119289771A_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the field of aircraft technology, and in particular to a target missile detection system and a target missile. Background Art
[0002] Target missiles are targets frequently used in the development, design, finalization, flight tests and training of air defense weapon systems. They are mainly composed of flight control systems, electrical systems, power systems, missile body structures and launch systems. Target missiles play an irreplaceable and important role in simulating the size, motion characteristics, and reflection characteristics of incoming missiles. They provide an important means of testing the research and development of air defense weapon systems, their mission use, and the rapid formation of combat effectiveness after equipment.
[0003] A complete target missile system consists of target missile equipment, launching device and ground station, among which the target missile equipment is the core. It is crucial for the target missile to complete its mission and realize its function in flight and produce output that meets the requirements. Traditional detection methods are to detect individual equipment in the target missile, or to conduct joint detection between two or three equipment in the target missile. After the equipment is detected and found to be correct, it is installed in the missile body structure. For subsequent target missile transportation and pre-launch preparation, the actual status of the equipment corresponding to the target missile cannot be determined, and the detection result corresponding to the equipment cannot be determined because all the equipment of the target missile to be tested has been installed in the missile body structure. Summary of the invention
[0004] In view of this, the purpose of the present application is to provide a target missile detection system and a target missile to overcome at least one of the above-mentioned defects.
[0005] In the first aspect, an embodiment of the present application provides a target missile detection system, the detection system comprising a data exchange device and a collaborative control device, the data exchange device being connected to the collaborative control device via a data bus, the collaborative control device comprising a target missile main control module, an ignition control module and a launch box control module, wherein the ignition control module is used to receive an ignition control signal sent by the target missile main control module, and send it to the target missile booster pyrotechnics to be tested of the target missile to be tested, the ignition control signal is used to instruct the target missile booster pyrotechnics to perform an ignition operation, and the launch box control module is used to receive the launch box control signal sent by the target missile main control module, and send it to The target missile to be tested has a plug-in / plug-out connector, and the launch box control signal is used to instruct the target missile to be tested to perform a separation operation with the target missile to be tested and the target missile plug-in / plug-out connector, and to convert the current state of the target missile to be tested into a ready-to-launch state. The target missile main control module is used to respond to an ignition instruction, generate an ignition control signal, and send it to the ignition control module, receive the target missile ignition signal returned by the target missile to be tested, and determine the detection result of the ignition performance of the target missile to be tested, and respond to the ready-to-launch instruction, generate the launch box control signal, and send it to the launch box control module, receive the launch box detection signal returned by the target missile to be tested, and determine the detection result of the launch box control performance of the target missile to be tested.
[0006] In an optional embodiment of the present application, the target missile main control module is also used to perform the following processing: the target missile main control module controls the detection system to be powered off, and when the detection system is in the powered-off state, the ignition control circuit under the ignition control module is disconnected from the target missile booster pyrotechnics, and a simulated load of a simulated pyrotechnic product is used to replace the ignition control circuit and connect it to the target missile booster pyrotechnics, the target missile main control module controls the detection system to be powered on, the target missile main control module generates an ignition control signal in response to an ignition instruction, and sends it to the ignition control module, and the target missile main control module receives the power-on state of the simulated load to determine the power-on detection result of the ignition control circuit connected to the target missile to be tested.
[0007] In an optional embodiment of the present application, the ignition control circuit includes a hard lock control circuit, a pyrotechnic bus control circuit and a pyrotechnic ignition port control circuit, wherein the ignition control module is used to perform the following processing: the hard lock control circuit in the ignition control module receives a hard lock signal sent by the target missile main control module, and returns a first circuit conduction signal to the target missile main control module after the hard lock control circuit is turned on, the hard lock signal is used to indicate that the first relay in the hard lock control circuit is closed, so that the hard lock control circuit is turned on, the pyrotechnic bus control circuit in the ignition control module receives a first control signal sent by the target missile main control module, and returns a second circuit conduction signal to the target missile main control module after the pyrotechnic bus control circuit is turned on, the first control signal is used to indicate that the MOS tube and the second relay in the pyrotechnic bus control circuit are closed, so that the pyrotechnic bus control circuit is turned on, and the pyrotechnic ignition port control circuit in the ignition control module receives a second control signal sent by the target missile main control module signal, and returns a third circuit conduction signal to the target missile main control module after the pyrotechnic ignition port control circuit is turned on, the second control signal is used to instruct the third relay in the pyrotechnic ignition port control circuit to close, so that the pyrotechnic ignition port control circuit is turned on, and the ignition control signal is sent to the target missile to be tested. The target missile main control module is also used to perform the following processing: the target missile main control module responds to the hard lock instruction, sends the hard lock signal to the hard lock control circuit in the ignition control module, and receives the first circuit conduction signal of the hard lock control circuit; the target missile main control module responds to the first circuit conduction signal, sends the first control signal to the pyrotechnic bus control circuit in the ignition control module, and receives the second circuit conduction signal of the pyrotechnic bus control circuit; the target missile main control module responds to the second circuit conduction signal, sends the second control signal to the pyrotechnic ignition port control circuit in the ignition control module, and receives the third circuit conduction signal of the pyrotechnic ignition port control circuit.
[0008] In an optional embodiment of the present application, the collaborative control device also includes a control panel, which includes a button and a detection interface, wherein the control panel is connected to the target missile test interface of the target missile to be tested through the detection interface, and the control panel generates a test signal corresponding to the button in response to the button being triggered, and transmits the test signal to the target missile to be tested through the detection interface, and the test signal is used to instruct the target missile to be tested to detect the test item corresponding to the triggered button. The target missile main control module is also used to perform the following processing: the target missile main control module receives the detection result of the test item corresponding to the triggered button, and displays the detection result on the test tooling through the data exchange device to determine the detection result of the target missile to be tested for the test item corresponding to the triggered button.
[0009] In an optional embodiment of the present application, the collaborative control device also includes a positioning module, and the detection system also includes a radio frequency device, wherein the positioning module is connected to the radio frequency device via a data bus, wherein the positioning module is connected to an external antenna, receives a GPS signal transmitted by the external antenna, and sends the GPS signal to the target missile main control module, the positioning module receives a positioning detection signal of the target missile to be tested obtained after the target missile main control module parses and compiles the GPS signal, the positioning module sends the positioning detection signal of the target missile to be tested to the radio frequency device, the radio frequency device receives the positioning detection signal of the target missile to be tested from the positioning module, amplifies the positioning detection signal of the target missile to be tested through a radio frequency amplifier, and the radio frequency device sends both the positioning detection signal of the target missile to be tested and the amplified positioning detection signal of the target missile to be tested to the target missile to be tested, so as to determine the detection result of the GPS device of the target missile to be tested.
[0010] In an optional embodiment of the present application, the detection system also includes an engine power control module, which receives an engine power control signal from the target missile main control module, and the engine power control signal is used to instruct the fourth relay of the engine power control module to close, and the engine power control circuit is turned on to power the engine of the target missile to be tested, so that the engine performs the detection of the corresponding equipment of the target missile to be tested, wherein the target missile main control module is also used to perform the following processing: the target missile main control module responds to the transmitter control instruction, sends the engine power control signal, and receives the detection result of the target missile to be tested, and transmits it to the test tooling via the data exchange device to determine the detection result of the target missile to be tested.
[0011] In an optional embodiment of the present application, the control panel also includes a buzzer, and the detection system also includes a target missile emergency stop module, wherein the target missile emergency stop module is used to receive an emergency stop signal from the target missile main control module and send it to the target missile to be tested, and the emergency stop signal instruction is used to instruct the control of the target missile to be tested to be in a stopped state, and the emergency stop performance of the target missile to be tested is determined according to the working logic of the buzzer on the control panel, wherein the target missile main control module is further used to perform the following processing: the target missile main control module responds to the target missile emergency stop instruction, sends the emergency stop signal, and receives the detection result of the target missile to be tested, and transmits it to the test tooling via the data exchange device to determine the detection result of the target missile to be tested.
[0012] In an optional embodiment of the present application, the detection system also includes a power supply device, wherein the power supply device is respectively connected to the data exchange device, the collaborative control device and the radio frequency device to provide power to the data exchange device, the collaborative control device and the radio frequency device.
[0013] In an optional embodiment of the present application, the detection system also includes a built-in battery, wherein the built-in battery is connected to the power supply device, and when an external power input is detected, the external power supply supplies power to the power supply device, and the built-in battery draws power from the external power supply for storage, and when no external power input is detected, the built-in battery supplies power to the power supply device.
[0014] In a second aspect, an embodiment of the present application further provides a target missile, comprising: a target missile body to be tested and a target missile detection system in any of the above-mentioned optional embodiments.
[0015] The target missile detection system and target missile provided in the embodiment of the present application, the detection system includes a data exchange device and a cooperative control device, the cooperative control device includes a target missile main control module, an ignition control module and a launch box control module, the ignition control module receives an ignition control signal and sends it to the target missile booster pyrotechnics of the target missile to be tested, the launch box control module receives the launch box control signal and sends it to the target missile plug-in connector of the target missile to be tested, the target missile main control module generates an ignition control signal and sends it to the ignition control module, receives the target missile ignition signal returned by the target missile to be tested, determines the detection result of the ignition performance of the target missile to be tested, and generates a launch box control signal and sends it to the launch box control module, receives the launch box detection signal returned by the target missile to be tested, and determines the detection result of the launch box control performance of the target missile to be tested. Through this application, the accuracy of the ignition detection result of the target missile to be tested and the launch box control detection result is improved.
[0016] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, preferred embodiments are specifically cited below and described in detail with reference to the attached drawings. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without paying creative work.
[0018] Figure 1 A schematic diagram of the structure of a detection system for a target projectile to be detected provided in an embodiment of the present application;
[0019] Figure 2 A schematic diagram of the structure of another detection system for a target projectile to be detected provided in an embodiment of the present application;
[0020] Figure 3 A schematic diagram of the transmission of the detection result of the target missile to be tested provided in the embodiment of the present application;
[0021] Figure 4 A schematic diagram of the interface of the control panel provided in an embodiment of the present application. DETAILED DESCRIPTION
[0022] To make the purpose, technical scheme and advantages of the embodiments of the present application clearer, the technical scheme in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all of the embodiments. The components of the embodiments of the present application usually described and shown in the drawings here can be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present application provided in the drawings is not intended to limit the scope of the application claimed for protection, but merely represents the selected embodiments of the present application. Based on the embodiments of the present application, each other embodiment obtained by those skilled in the art without making creative work belongs to the scope of protection of the present application.
[0023] First, the application scenarios to which the present application is applicable are introduced. The present application can be applied in the field of aircraft technology.
[0024] Research has found that traditional detection methods are to detect individual devices in the target missile, or to conduct joint detection between two or three devices in the target missile. After the equipment has been detected and found to be correct, it is installed in the missile body structure. During the subsequent target missile transportation and pre-launch preparations, since all the equipment of the target missile to be tested has been installed in the missile body structure, it is impossible to determine the actual status of the equipment corresponding to the target missile, and therefore the detection result corresponding to the equipment cannot be determined.
[0025] Based on this, the embodiment of the present application provides a detection system and a target missile, the detection system includes a data exchange device and a cooperative control device, the cooperative control device includes a target missile main control module, an ignition control module and a launch box control module, the ignition control module receives an ignition control signal and sends it to the target missile booster pyrotechnics of the target missile to be tested, the launch box control module receives the launch box control signal and sends it to the target missile plug-in connector of the target missile to be tested, the target missile main control module generates an ignition control signal and sends it to the ignition control module, receives the target missile ignition signal returned by the target missile to be tested, and determines the detection result of the ignition performance of the target missile to be tested, the target missile main control module generates a launch box control signal and sends it to the launch box control module, receives the launch box detection signal returned by the target missile to be tested, and determines the detection result of the launch box control performance of the target missile to be tested. Through this application, the accuracy of the ignition detection result of the target missile to be tested and the launch box control detection result is improved.
[0026] See also Figure 1 , Figure 1 This is a schematic diagram of the structure of the detection system for the target projectile to be detected provided in the embodiment of the present application. Figure 1As shown in , the detection system provided by the embodiment of the present application includes: a collaborative control device 101 and a data exchange device 102, wherein the collaborative control device 101 includes a target missile main control module 1011, an ignition control module 1012 and a launch box control module 1013.
[0027] The detection system is mainly used to complete the status detection of all electrical equipment on the target missile to be tested. The specific working principle is: after the target missile main control module 1011 of the detection system receives the test instruction issued by the test tooling 104, it sends out the corresponding control signal, obtains the required information and feeds it back to the test tooling 104 for display.
[0028] The self-test information of the on-board equipment can be displayed in real time on the test tooling 104 through the 422 channel between the flight control and the detection system through the data exchange device 102, so that the detection personnel can judge whether the current state is normal. Here, the flight control is the flight control integrated machine in the target missile to be tested, which receives and executes the instructions sent by the detection system, and returns the detection results after execution to the target missile main control module 1011.
[0029] Here, the collaborative control device 101 is the main control chip, which is designed according to the test requirements of the target missile 103 to be tested. It can perform pre-flight tests on the built-in devices of the target missile to ensure that all devices are in normal condition.
[0030] For example, the main control chip can be a domestically produced HC32F4A0 chip.
[0031] The detection system includes a collaborative control device 101 and a data exchange device 102 , and the data exchange device 102 is connected to the collaborative control device 101 via a data bus.
[0032] The ignition control module 1012 is used to receive the ignition control signal sent by the target missile main control module 1011 and send it to the ignition control device of the target missile booster 103 to be tested.
[0033] Here, the ignition control signal is used to instruct the pyrotechnics of the target missile booster to perform the ignition operation.
[0034] The target missile main control module 1011 generates an ignition control signal in response to the ignition instruction and sends it to the ignition control module 1012, receives the target missile ignition signal returned by the target missile 103 to be tested, and determines the detection result of the ignition performance of the target missile 103 to be tested.
[0035] The target missile main control module 1011 is the core of the entire detection system. It exchanges information with the test tooling 104 through the data exchange device 102 and has the data receiving and sending function of the management communication interface. The target missile main control module 1011 sends an I / O signal to the relevant switch control circuit to turn on the corresponding circuit to achieve power on and off control of the equipment. After the switch circuit is turned on, the electrical signal is collected by the acquisition circuit to the target missile main control module 1011, so as to determine whether the circuit is normal.
[0036] The target missile main control module 1011 is also used to perform the following processing:
[0037] The target missile main control module 1011 controls the detection system to power off. When the detection system is in the power-off state, the ignition control circuit under the ignition control module 1012 is disconnected from the target missile booster pyrotechnics, and the ignition control circuit is replaced with a simulated load of a simulated pyrotechnic product to connect to the target missile booster pyrotechnics.
[0038] The target missile main control module 1011 controls the detection system to power on, generates an ignition control signal in response to an ignition command, and sends it to the ignition control module 1012, receives the power-on status of the simulated load to determine the power-on detection result of the ignition control circuit connected to the target missile to be tested.
[0039] The target missile main control module 1011 sends the power-on detection result to the test tooling 104 via the data exchange device 102. For example, the data exchange device 102 can be a switch board. The data exchange device has a built-in switch board. The test tooling only needs to connect to the communication, issue instructions, and collect data through the network port, without the need for multiple peripheral communication interfaces.
[0040] Here, in addition to the detection function, the detection system is also compatible with the ignition control circuit, which can perform the ignition operation of the target missile during the ground stage.
[0041] When testing the target missile 103 item by item, there are certain requirements for the detection of the ignition control circuit. Specifically, when detecting the ignition control circuit, the detection system needs to be powered off, the detection system ignition control circuit and the target missile booster pyrotechnics need to be disconnected, and a resistive load simulating pyrotechnics needs to be connected. The detection system needs to be powered on again, and the test fixture 104 needs to send an ignition command. If the simulated load is powered on normally, it proves that the ignition control circuit is normal and the ignition function can be realized later.
[0042] The ignition control circuit includes a hard lock control circuit, a pyrotechnic bus control circuit and a pyrotechnic ignition port control circuit. The ignition control circuit adopts a three-level control design and can ignite safely and reliably.
[0043] The ignition control module 1012 is used to perform the following processing:
[0044] The hard lock control circuit in the ignition control module 1012 receives the hard lock signal sent by the target missile main control module 1011, and returns the first circuit conduction signal to the target missile main control module 1011 after the hard lock control circuit is turned on.
[0045] Here, the hard lock signal is used to instruct the first relay in the hard lock control circuit to close, so that the hard lock control circuit is turned on.
[0046] The target missile main control module 1011 is also used to perform the following processing:
[0047] The target missile main control module 1011 responds to the hard lock instruction, sends a hard lock signal to the hard lock control circuit in the ignition control module 1012, and receives a first circuit conduction signal from the hard lock control circuit.
[0048] The pyrotechnic bus control circuit in the ignition control module 1012 receives the first control signal sent by the target missile main control module 1011, and returns a second circuit conduction signal to the target missile main control module 1011 after the pyrotechnic bus control circuit is turned on.
[0049] Here, the first control signal is used to instruct the MOS tube and the second relay in the pyrotechnic bus control circuit to close, so that the pyrotechnic bus control circuit is turned on.
[0050] The target missile main control module 1011 responds to the first circuit conduction signal, sends a first control signal to the pyrotechnic bus control circuit in the ignition control module 1012, and receives a second circuit conduction signal from the pyrotechnic bus control circuit.
[0051] The pyrotechnic ignition port control circuit in the ignition control module 1012 receives the second control signal sent by the target missile main control module 1011 .
[0052] Here, the second control signal is used to instruct the third relay in the pyrotechnic ignition port control circuit to close, so that the pyrotechnic ignition port control circuit is turned on and the ignition control signal is sent to the target missile to be tested.
[0053] The target missile main control module 1011 responds to the second circuit conduction signal, sends a second control signal to the pyrotechnic ignition port control circuit in the ignition control module 1012, and receives a third circuit conduction signal from the pyrotechnic ignition port control circuit.
[0054] Specifically, the launch box control module 1013 receives the launch box control signal sent by the target missile main control module 1011, and sends it to the target missile plug-in / disconnect connector of the target missile 103 to be tested.
[0055] The launch box control signal is used to instruct the target missile 103 to be tested to perform a separation operation with the target missile plug-in / plug-out connector, and to convert the current state of the target missile 103 to be tested to a state ready for launch.
[0056] The target missile main control module 1011 generates a launch box control signal in response to the launch instruction, and sends it to the launch box control module 1013, receives the launch box detection signal returned by the target missile 103 to determine the detection result of the control performance of the launch box of the target missile to be tested.
[0057] The launch box control module 1013 is mainly used to supply power to and communicate with the launch box controller in the target missile 103 to be tested. The target missile main control module 1011 controls the launch box controller to separate the target missile to be tested from the target missile plug-in connector by issuing I / O instructions, and the target missile to be tested enters the ready-to-launch state. This detection item is executed after the ground detection is completed and before the target missile enters the ready-to-fly state.
[0058] Specifically, in addition to controlling the ignition control module 1012 and the launch box control module 1013, the target missile main control module 1011 also sends various detection signals to the target missile 103 to be tested so as to realize the detection function for the corresponding equipment of the target missile 103 to be tested.
[0059] See also Figure 2 , Figure 2 This is a schematic diagram of the structure of another detection system for a target projectile to be detected provided in an embodiment of the present application. Figure 2 As shown in, the detection system provided in the embodiment of the present application includes: a collaborative control device 101, a data exchange device 102, a radio frequency device 105, a power supply device 106 and a built-in battery 107, wherein the collaborative control device 101 includes a target missile main control module 1011, an ignition control module 1012, a launch box control module 1013, a positioning module 1014, an engine power supply control module 1015, a target missile power supply control module 1016, a target missile emergency stop module 1017, a target missile data acquisition module 1018, a first communication module 1019, and a first power supply module 1010.
[0060] The data exchange device 102 includes a second communication module 1021 and a second power module 1022 , the radio frequency device 105 includes a third power module 1051 and a power amplifier module 1052 , and the power supply device 106 includes a power supply module 1061 and a power display module 1062 .
[0061] The positioning module 1014 is connected to the radio frequency device 105 via a radio frequency line, wherein the positioning module 1014 is connected to an external antenna, receives a GPS signal transmitted by the antenna, and sends the GPS signal to the target missile main control module 1011 .
[0062] For example, the GPS signal may include whether the target missile is successfully positioned, whether the detection system is successfully positioned, the total number of positioning satellites, and the positioning longitude, latitude and altitude coordinates.
[0063] The target missile main control module 1011 receives the GPS signal, parses and compiles it, obtains the target missile positioning detection signal to be tested, and then outputs the target missile positioning detection signal to be tested to the radio frequency device 105 via the output end of the positioning module 1014. The radio frequency device 105 directly outputs the target missile positioning detection signal to be tested, and amplifies and outputs it through the radio frequency amplifier in the power division amplifier module 1052, and both are output to the target missile 103 to be tested, so as to detect whether the function of the GPS device inside the target missile to be tested is normal. The detection result is sent to the target missile main control module 1011 of the detection equipment via the 211 interface on the control panel. The target missile main control module 1011 parses it according to the corresponding protocol and sends it to the test tooling 104 via the data exchange device 102 to display the detection result.
[0064] The engine power control module 1015 receives the engine power control signal from the target missile main control module 1011 .
[0065] Here, the engine power control signal is used to instruct the fourth relay of the engine power control module 1015 to close.
[0066] After the engine power control module 1015 receives the engine power control signal from the target missile main control module 1011, the engine power control circuit is turned on to supply power to the engine of the target missile 103 to be tested, so that the engine performs detection of the corresponding equipment of the target missile 103 to be tested.
[0067] The engine power supply control module 1015 is a switch circuit controlled by the target missile main control module 1011, which supplies power to the engine of the target missile 103 to be tested. The engine can be tested on the ground to test its "stop", "emergency stop", "main fuel pump test", "ignition fuel pump test", "electric explosion drive box start test", "ignition solenoid valve test", "main oil valve test" functions. The test results are sent by the engine ECU to the flight control device, which is uploaded to the target missile main control module 1011 through the communication module 1019, and then the test results of the target missile to be tested are transmitted to the test fixture 103 for display via the data exchange device 102.
[0068] The target missile main control module 1011 is also used to perform the following processing:
[0069] The target missile main control module 1011 responds to the transmitter control instruction, sends the engine power control signal, and receives the detection result of the target missile 103 to be tested, and transmits it to the test tooling 104 via the data exchange device 102 to determine the detection result of the target missile 103 to be tested.
[0070] The power supply device 106 is connected to the data exchange device, the cooperative control device and the radio frequency device respectively to provide power for the data exchange device, the cooperative control device and the radio frequency device.
[0071] The first power supply module 1010 is mainly used to convert the 28VDC power input by the power supply device 106 into the voltage required by each module of the collaborative control device 101 to support the normal operation of the collaborative control device 101.
[0072] The target missile power supply control module 1016 mainly provides ground power supply for the target missile 103 to be tested, so as to provide the energy required for the self-test of the equipment in the target missile 103 to be tested.
[0073] The power supply module 1061 mainly controls the power supply of other units through the power switch button. When the detection system has external power input, the detection system uses the external power supply to power other units and charges the built-in battery 107. When there is no external power input, the detection system automatically switches to the built-in battery 107 for power supply.
[0074] When the detection system is connected normally, the detection personnel can power on the entire device by pressing the power switch button on the device control panel. After the power switch button is pressed, the status indicator light is on, and the power setting is selected at 0°C, 10%, 35%, 60%, 80%, a total of four gears. The operator can charge and maintain the built-in battery according to the status of the power indicator light.
[0075] The power display module 1062 is implemented through a voltage comparator circuit. The corresponding resistor voltage divider circuit is designed according to the preset voltage display value to meet the power level setting. The voltage at the same phase end of the comparator is compared with the set voltage value at the opposite phase end. If the voltage value at the same phase end is greater than the set voltage value at the opposite phase end, the LED light corresponding to the circuit will light up, otherwise, the corresponding LED light will not light up.
[0076] The built-in battery 107 is connected to the power supply device. When external power input is detected, the external power supply supplies power to the power supply device 106, and the built-in battery 107 draws power from the external power supply for storage. When no external power input is detected, the built-in battery 107 supplies power to the power supply device 106. The detection system includes a built-in battery, which can directly power each device in the detection system. The use is not restricted by the environment, the device is small in size, and easy to carry.
[0077] The built-in battery 107 uses 7 series and 2 parallel ternary lithium batteries with a battery capacity of 6400mAh and a rated discharge voltage of 28V. When fully charged, the detection system can work for 30 minutes. When the detection system is used for functional detection maintenance, from the connection of cables and target missiles to the withdrawal of cables and target missiles, without performing special subsystem tests, the test time of a single target missile shall not exceed 20 minutes.
[0078] The target missile emergency stop module 1017 is used to receive an emergency stop signal from the target missile main control module 1011 and send it to the target missile 103 to be tested.
[0079] Here, the emergency stop signal is used to indicate that the target projectile 103 to be tested is in a stopped state, and the emergency stop performance of the target projectile to be tested is determined according to the working logic of the buzzer on the control panel.
[0080] The target missile main control module 1011 is also used to perform the following processing:
[0081] The target missile main control module 1011 responds to the target missile emergency stop command, sends an emergency stop signal, receives the detection result of the target missile 103 to be tested, and transmits it to the test tooling 104 via the data exchange device 102 to determine the detection result of the target missile 103 to be tested.
[0082] The target missile data acquisition module 1018 includes hard lock circuit voltage acquisition, pyrotechnic bus circuit voltage acquisition, pyrotechnic resistance acquisition, ignition control circuit voltage acquisition, input and output circuit voltage acquisition, and output circuit current acquisition. All acquisition circuits are designed through operational amplifier sampling differential circuits to proportionally amplify or reduce the input and output values to the range that the ADC can sample, and then sample. The target missile main control module 1011 calculates and outputs the sampled values in proportion to the test fixture 104 for display.
[0083] like Figure 3 As shown, Figure 3 This is a schematic diagram of the transmission of the detection results of the target missile to be tested provided in the embodiment of the present application. Figure 3 As shown in the figure, the target missile 301 to be tested, the RS422 path circuit 302, the PHY chip 303, the network transformer 304 and the data exchange device 305.
[0084] The target missile 301 to be tested transmits RS422 differential data to the RS422 path circuit 302 , the RS422 path circuit 302 transmits RS422 data to the PHY chip 303 , the PHY chip 303 transmits network differential data to the network transformer 304 , and the network transformer 304 transmits network differential data to the data exchange device 305 .
[0085] The first communication module 1019 includes three communication modes: network port communication, serial port to network port communication, and serial port communication. The core of the network port communication is an Ethernet chip, which mainly provides a network port communication link for the target missile main control module 1011 and the data exchange device 102; the serial port communication mainly provides software upgrade function for the flight control equipment in the target missile to be tested; the core of the serial port to network port communication is a PHY chip, which is a network serial port dialysis chip with an internal integrated TCP / IP protocol stack, which can realize two-way transparent transmission of network data packets and serial port data. The RS422 data uploaded by the target missile to be tested is converted into data under the network port protocol through the PHY chip and sent to the data exchange device 102.
[0086] The communication mode of the first communication module 1019 of the target missile main control module 1011 is serial communication, the communication mode between the target missile 103 to be tested and the first communication module 1019 of the target missile main control module 1011 is serial communication, the communication mode between the target missile main control module 1011 and the first communication module 1019 is serial communication, and the communication mode between the first communication module 1021 of the target missile main control module 1011 and the second communication module 1021 of the data exchange device 102 is serial port to network port communication.
[0087] The communication mode between the second communication module 1021 of the data exchange device 102 and the test fixture 104 is network port communication, and the detection result received from the target missile main control module 1011 is transmitted to the test fixture 104 for display.
[0088] The second power supply module 1022 is mainly used to convert the 28VDC power input by the power supply device 106 into the voltage required by each module of the data switching device 102 to support the normal operation of the switch unit.
[0089] The second communication module 1021 uses an Ethernet chip, which is a professional high-end system-level chip for Ethernet switch or NVR application, including 9 low-power fast Ethernet transceiver ports. This design uses 4 Ethernet ports to connect to other units internally, and 4 Ethernet ports to communicate with the test fixture 104 or other devices externally, which can quickly and reliably realize data communication between various devices.
[0090] The third power supply module 1051 is mainly used to convert the 28VDC power input by the power supply unit into the voltage required by each module of the radio frequency device 105 to support the normal operation of the radio frequency device 105 .
[0091] The power divider and amplifier module 1052 is used to receive the radio frequency signal transmitted by the positioning module 1014 in the collaborative control device 101, forward the signal to the receiving end through the power divider, and then forward it to the receiving end after being amplified by 20dB through the radio frequency amplifier. Here, the receiving end is the target missile 103 to be tested.
[0092] The collaborative control device 101 also includes a control panel (not shown in FIG. Figure 2 ), the control panel includes buttons and a detection interface.
[0093] See also Figure 4 , Figure 4 This is a schematic diagram of the interface of the control panel provided in the embodiment of the present application. Figure 4As shown in the figure, the detection system provided in the embodiment of the present application includes: a battery charging port 201, a power switch 202, a power bar 203, a status indicator light 204, a DB9 interface 205, a buzzer 206, an emergency stop button 207, a radio power switch 208, a hard lock button 209, a radio power supply communication interface 210, a detection interface 211 and a data exchange interface 212.
[0094] The control panel is the main panel of the detection system. Figure 4 It can be seen that the external interfaces of the detection system include a battery charging port 201 of the target missile 103 to be tested, a power switch 202, a power bar 203, a status indicator light 204, a DB9 interface 205, a buzzer 206, an emergency stop button 207, a radio power switch 208, a hard lock button 209, a radio power supply communication interface 210, a detection interface 211 and a data exchange interface 212. In addition, there are a battery power display bar and a detection system status indicator light on the control panel.
[0095] The battery charging port 201 is connected to the built-in battery 107, the power switch 202 is connected to the built-in battery 107, the DB9 interface 205 is connected to the target missile main control module 1011, the DB9 interface 205 is a reading interface for the self-test of the detection system, and an interface for determining whether the detection system is normal, the buzzer 206 is an emergency stop device, the data exchange interface 212 is four network ports connecting the data exchange device 102 and the test fixture 104, the radio power switch 208 controls the power supply of the ground radio 108, the radio power supply communication interface 210 is an interface for powering the ground radio 108, GNSS IN is the input end of the GPS module, and the output is used as the input end of the radio frequency device 105. GNSS IN is connected to an external antenna, GNSS OUT1 and GNSS OUT2 are connection interfaces between the radio frequency device 105 and the target missile 103 to be tested, GNSS OUT1 is a transmission interface for transmitting the signal to the target missile 103 to be tested after amplification, and GNSS OUT2 is a transmission interface for transmitting the signal to the target missile 103 to be tested without amplification. Before testing, the target missile 103 to be tested is connected to the detection interface 211 in the detection system, and the radio power supply communication interface 210 supplies power to the detection system.
[0096] Here, the triggering of the emergency stop button 207 and the hard lock button 209 can send corresponding test signals to the target missile main control module 1011 to control the target missile 103 to be tested to perform corresponding tests.
[0097] For example, there are two sending ends of the hard lock signal and the emergency stop signal, one of which can be the test tool 104, and the other can be the triggering of the emergency stop button 207 and the hard lock button 209 on the control panel.
[0098] Here, the test tool 104 displays the detection data returned by the target missile to be tested, and the ground station 108 displays the detection data returned by the target missile to be tested and the real-time data of the detection system.
[0099] The control panel is connected to the target missile test interface of the target missile to be tested through the detection interface 211.
[0100] In response to a button being triggered, the control panel generates a test signal corresponding to the button, and transmits the test signal to the target projectile 103 to be tested through the detection interface 211.
[0101] The test signal is used to instruct the target projectile 103 to perform a test on the test item corresponding to the triggered button.
[0102] The target missile main control module 1011 is also used to perform the following processing:
[0103] The target missile main control module 1011 receives the test results of the test items corresponding to the triggered buttons, and transmits the test results to the test fixture 104 through the data exchange device 102 for display on the test fixture 104 to determine the test results of the target missile 103 to be tested for the test items corresponding to the triggered buttons.
[0104] Here, the emergency stop buzzer in the control panel.
[0105] There are two types of emergency stop module in ground testing, one is the emergency stop command issued by the test tool, and the other is manual emergency stop. After the test tool issues the emergency stop command, the target missile main control module 1011 receives and responds to the corresponding operation to realize the emergency stop function. When this method is used for emergency stop, the buzzer 206 does not work.
[0106] Manual emergency stop means that the detection personnel presses the emergency stop button 207 on the control panel, which generates an emergency stop signal and sends it to the target missile main control module 1011 for emergency stop operation. After the emergency stop button 207 is pressed, the buzzer 206 on the detection system starts working. The operator can judge whether the manual emergency stop signal is valid based on this logic.
[0107] The status indicator light on the control panel can display the power level of the built-in battery, so the operator can charge and maintain the battery in time.
[0108] The built-in battery of the detection system can work without an external power supply. Users can charge and maintain the battery in time according to the power bar on the control panel of the detection system.
[0109] The detection system also includes packaging boxes, which are made of finished portable equipment plastic boxes. Plastic products are light in weight, easy to carry and store, moisture-proof and shock-proof, and strong and durable.
[0110] The detection system is mainly used for ground testing of target missiles. The specific test items include: target missile total power supply voltage, target missile total current, booster pyrotechnic resistance, booster voltage, launch box voltage, target missile engine power supply voltage, and the status of each device loaded on the target missile. The flight control sends the data to the detection system through the serial port, and then the detection system uploads it to the test tooling.
[0111] During the test, the testers need to cooperate and observe the corresponding actions of the target missile's rudder and other components. The test system can supply power to the equipment on the target missile to be tested, and the power supply path is controllable. The test process of the test system is as follows:
[0112] 1) Confirm that the cables and connectors are connected properly. When checking the connectors, pay attention to whether the locking assembly of the connectors is tightened to prevent poor interface contact from affecting the detection function.
[0113] 2) Confirm that the detection system is powered on and the test tooling can display the test interface normally; after the detection system is powered on, pay attention to the power of the built-in battery and charge and maintain it in time;
[0114] 3) Click the test items one by one according to the test tooling to determine whether the test results are normal. If there is any abnormality, immediately press the "Emergency Stop" button and then cut off the power supply;
[0115] 4) When testing each item one by one, there are certain requirements for the detection of the ignition circuit. When testing the ignition circuit, the equipment needs to be powered off, the ignition circuit of the detection system needs to be disconnected from the target missile booster pyrotechnics, and connected with a resistance load simulating pyrotechnics. The equipment needs to be powered on again, and the test tooling needs to send an ignition command. If the simulated load is powered on normally, it proves that the ignition circuit is normal and the ignition function can be realized.
[0116] 5) The detection system analyzes and uploads the self-test data of each device sent by the flight control system in the missile according to the communication protocol. The test personnel can judge whether there is any abnormality in the equipment on the missile through the information displayed by the test tooling;
[0117] 6) If all test items are normal, power off the device and disconnect it from the target missile to be tested. Reconnect it before the target missile takes off and perform the booster ignition operation.
[0118] In a second aspect, an embodiment of the present application provides a target missile, including: a target missile body to be tested and the above-mentioned target missile detection system.
[0119] The target missile detection system and target missile provided in the embodiment of the present application, the detection system includes a data exchange device and a cooperative control device, the cooperative control device includes a target missile main control module, an ignition control module and a launch box control module, the ignition control module receives an ignition control signal and sends it to the target missile booster pyrotechnics of the target missile to be tested, the launch box control module receives the launch box control signal and sends it to the target missile plug-in connector of the target missile to be tested, the target missile main control module generates an ignition control signal and sends it to the ignition control module, receives the target missile ignition signal returned by the target missile to be tested, determines the detection result of the ignition performance of the target missile to be tested, and generates a launch box control signal and sends it to the launch box control module, receives the launch box detection signal returned by the target missile to be tested, and determines the detection result of the launch box control performance of the target missile to be tested. Through this application, the accuracy of the ignition detection result of the target missile to be tested and the launch box control detection result is improved.
[0120] During the ground inspection process of target missile equipment, a detection system that can perform comprehensive functional testing is needed. The detection system should detect whether the target missile meets the required electrical performance indicators, especially after being tested in various ground simulation environments, to detect whether its performance is excellent. Through testing, performance that does not meet technical conditions, imperfect functions, mismatched electrical interfaces and design defects are exposed. Therefore, a detection system with complete functions, excellent performance and easy application is of great significance to the ground testing of target missiles.
[0121] The detection system designed this time can test the functions of various devices in the target missile to be tested, including voltage and current detection of each device, flight control information interaction, ignition function test, rudder system communication control test, etc. It can perform various functional tests on the target missile to be tested when it is fully installed, ensuring that the target missile to be tested is in a normal state before flight, laying the foundation for the successful flight of the target missile.
[0122] Those skilled in the art can clearly understand that, for the convenience and brevity of description, the specific working processes of the systems, devices and units described above can refer to the corresponding processes in the aforementioned method embodiments and will not be repeated here.
[0123] In the several embodiments provided in the present application, it should be understood that the disclosed systems, devices and methods can be implemented in other ways. The device embodiments described above are merely schematic. For example, the division of the units is only a logical function division. There may be other division methods in actual implementation. For example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some communication interfaces, and the indirect coupling or communication connection of devices or units can be electrical, mechanical or other forms.
[0124] The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed on multiple network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of this embodiment.
[0125] In addition, each functional unit in each embodiment of the present application may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit.
[0126] If the functions are implemented in the form of software functional units and sold or used as independent products, they can be stored in a non-volatile computer-readable storage medium that is executable by a processor. Based on this understanding, the technical solution of the present application can essentially be embodied in the form of a software product, or in other words, the part that contributes to the prior art or the part of the technical solution. The computer software product is stored in a storage medium, including several instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the method described in each embodiment of the present application. The aforementioned storage medium includes: various media that can store program codes, such as a USB flash drive, a mobile hard disk, a read-only memory (ROM), a random access memory (RAM), a magnetic disk or an optical disk.
[0127] Finally, it should be noted that the above-described embodiments are only specific implementation methods of the present application, which are used to illustrate the technical solutions of the present application, rather than to limit them. The protection scope of the present application is not limited thereto. Although the present application is described in detail with reference to the above-mentioned embodiments, ordinary technicians in the field should understand that any technician familiar with the technical field can still modify the technical solutions recorded in the above-mentioned embodiments within the technical scope disclosed in the present application, or can easily think of changes, or make equivalent replacements for some of the technical features therein; and these modifications, changes or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application, and should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.
Claims
1. A target missile detection system, characterized in that: The detection system includes a data exchange device and a collaborative control device, wherein the data exchange device is connected to the collaborative control device via a data bus, and the collaborative control device includes a target missile main control module, an ignition control module and a launch box control module. The ignition control module is used to receive the ignition control signal sent by the target missile main control module and send it to the pyrotechnics of the target missile booster to be tested. The ignition control signal is used to instruct the pyrotechnics of the target missile booster to be tested to perform an ignition operation. The launch box control module is used to receive the launch box control signal sent by the target missile main control module and send it to the target missile plug-in connector of the target missile to be tested. The launch box control signal is used to instruct the target missile to be tested to perform a separation operation with the target missile plug-in connector and convert the current state of the target missile to be tested into a ready-to-launch state. The target missile main control module is used to generate an ignition control signal in response to an ignition instruction, and send it to the ignition control module, receive the target missile ignition signal returned by the target missile to be tested, and determine the detection result of the ignition performance of the target missile to be tested; and generate the launch box control signal in response to a launch instruction, and send it to the launch box control module, receive the launch box detection signal returned by the target missile to be tested, and determine the detection result of the launch box control performance of the target missile to be tested.
2. The detection system according to claim 1, characterized in that: The target missile main control module is also used to perform the following processing: The target missile main control module controls the detection system to be powered off. When the detection system is powered off, the ignition control circuit under the ignition control module is disconnected from the target missile booster pyrotechnics, and a simulated load of a simulated pyrotechnic is used to replace the ignition control circuit and connect it to the target missile booster pyrotechnics. The target missile main control module controls the detection system to power on. The target missile main control module generates an ignition control signal in response to the ignition command and sends it to the ignition control module. The target missile main control module receives the power-on status of the simulated load to determine the power-on detection result of the ignition control circuit connected to the target missile to be tested.
3. The detection system according to claim 2, characterized in that: The ignition control circuit includes a hard lock control circuit, a pyrotechnic bus control circuit and a pyrotechnic ignition port control circuit. Wherein, the ignition control module is used to perform the following processing: The hard lock control circuit in the ignition control module receives the hard lock signal sent by the target missile main control module, and returns a first circuit conduction signal to the target missile main control module after the hard lock control circuit is turned on. The hard lock signal is used to instruct the first relay in the hard lock control circuit to close, so that the hard lock control circuit is turned on. The pyrotechnic bus control circuit in the ignition control module receives the first control signal sent by the target missile main control module, and returns a second circuit conduction signal to the target missile main control module after the pyrotechnic bus control circuit is turned on. The first control signal is used to instruct the MOS tube and the second relay in the pyrotechnic bus control circuit to close, so that the pyrotechnic bus control circuit is turned on. The pyrotechnic ignition port control circuit in the ignition control module receives the second control signal sent by the target missile main control module, and returns a third circuit conduction signal to the target missile main control module after the pyrotechnic ignition port control circuit is turned on. The second control signal is used to instruct the third relay in the pyrotechnic ignition port control circuit to close, so that the pyrotechnic ignition port control circuit is turned on and the ignition control signal is sent to the target missile to be tested. The target missile main control module is also used to perform the following processing: The target missile main control module responds to the hard lock instruction, sends the hard lock signal to the hard lock control circuit in the ignition control module, and receives the first circuit conduction signal of the hard lock control circuit. The target missile main control module responds to the first circuit conduction signal, sends the first control signal to the pyrotechnic bus control circuit in the ignition control module, and receives the second circuit conduction signal of the pyrotechnic bus control circuit. The target missile main control module responds to the second circuit conduction signal, sends the second control signal to the pyrotechnic ignition port control circuit in the ignition control module, and receives the third circuit conduction signal of the pyrotechnic ignition port control circuit.
4. The detection system according to claim 1, characterized in that: The collaborative control device also includes a control panel, which includes buttons and a detection interface. Wherein, the control panel is connected to the target missile test interface of the target missile to be tested through the detection interface, In response to the button being triggered, the control panel generates a test signal corresponding to the button, and transmits the test signal to the target projectile to be tested through the detection interface, wherein the test signal is used to instruct the target projectile to be tested to detect the test item corresponding to the triggered button. The target missile main control module is also used to perform the following processing: The target missile main control module receives the detection result of the test item corresponding to the triggered button, and displays the detection result on the test tool through the data exchange device to determine the detection result of the target missile to be tested for the test item corresponding to the triggered button.
5. The detection system according to claim 1, characterized in that: The collaborative control device further includes a positioning module, and the detection system further includes a radio frequency device, wherein the positioning module is connected to the radio frequency device via a radio frequency cable. The positioning module is connected to an external antenna, receives a GPS signal transmitted by the external antenna, and sends the GPS signal to the target missile main control module. The positioning module receives the target missile positioning detection signal obtained by the target missile main control module after parsing and compiling the GPS signal, The positioning module sends the positioning detection signal of the target missile to be detected to the radio frequency device, The radio frequency device receives the detection signal of the target missile to be detected from the positioning module, amplifies the detection signal of the target missile to be detected through a radio frequency amplifier, The radio frequency device sends both the target missile positioning detection signal and the amplified target missile positioning detection signal to the target missile to be tested, so as to determine the detection result of the GPS device of the target missile to be tested.
6. The detection system according to claim 5, characterized in that: The detection system also includes an engine power control module, The engine power control module receives the engine power control signal of the target missile main control module, and the engine power control signal is used to instruct the fourth relay of the engine power control module to close, and the engine power control circuit is turned on to supply power to the engine of the target missile to be tested, so that the engine performs the detection of the corresponding equipment of the target missile to be tested. The target missile main control module is also used to perform the following processing: The target missile main control module responds to the transmitter control instruction, sends the engine power control signal, receives the detection result of the target missile to be tested, and transmits it to the test tooling via the data exchange device to determine the detection result of the target missile to be tested.
7. The detection system according to claim 4, characterized in that: The control panel also includes a buzzer, and the detection system also includes a target missile emergency stop module. The target missile emergency stop module is used to receive an emergency stop signal from the target missile main control module and send it to the target missile to be tested. The emergency stop signal is used to indicate that the target missile to be tested is in a stopped state. The emergency stop performance of the target missile to be tested is determined according to the working logic of the buzzer on the control panel. The target missile main control module is also used to perform the following processing: The target missile main control module responds to the target missile emergency stop command, sends the emergency stop signal, receives the detection result of the target missile to be tested, and transmits it to the test fixture via the data exchange device to determine the detection result of the target missile to be tested.
8. The detection system according to claim 5, characterized in that: The detection system also includes a power supply device, Among them, the power supply device is connected to the data exchange device, the collaborative control device and the radio frequency device respectively to provide power to the data exchange device, the collaborative control device and the radio frequency device.
9. The detection system according to claim 8, characterized in that: The detection system also includes a built-in battery, The built-in battery is connected to the power supply device, and when an external power input is detected, the external power supply supplies power to the power supply device. The built-in battery draws power from the external power source for storage, and when it is detected that there is no external power input, the built-in battery supplies power to the power supply device.
10. A target missile, characterized in that: include: A target missile body to be tested and a target missile detection system as described in any one of claims 1 to 9.