CN211207168U - Airborne fire control system ground detection device - Google Patents
Airborne fire control system ground detection device Download PDFInfo
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- CN211207168U CN211207168U CN202020188028.3U CN202020188028U CN211207168U CN 211207168 U CN211207168 U CN 211207168U CN 202020188028 U CN202020188028 U CN 202020188028U CN 211207168 U CN211207168 U CN 211207168U
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Abstract
The utility model relates to an airborne fire control system ground detection device for to coming from airborne fire control system and guided missile emitter be used for control before aircraft carry guided missile the crosslinked signal of guided missile detects its characterized in that, detection device includes: a missile simulation device; a signal conditioning unit; a signal acquisition unit; a signal transmitting unit; a central processing unit; provided is a handheld terminal. The utility model provides a machine carries fire control system function fault lacks the difficult problem of detection means, and the device portability is good, easy operation, test result are directly perceived, do benefit to reduction trouble and erroneous judgement machine and carry fire control system trouble, improve the security of maintenance.
Description
Technical Field
The utility model relates to a guided missile and machine carry fire control system crosslinked signal's detection technology field, especially, relate to a detection device.
Background
At present, live ammunition or training ammunition needs to be mounted in the detection and maintenance of an airplane airborne fire control system in an airport, and whether the performance of the airplane airborne fire control system is normal or not is judged by manually observing the deflection, rotation and other conditions of a live ammunition or training ammunition guide head mounted on the airplane. However, the judgment method has high misjudgment rate, and some airborne signals cannot be judged manually at all. If the missile is in an on-hook state and works abnormally, the guarantee personnel cannot judge that the missile works abnormally due to the fault of an onboard fire control system or the fault of the missile. At present, a special device for detecting the function of an airborne fire control system is not available.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a detection device for cross-linked signal to between guided missile and the airborne fire control system simulates and detects, and detection device is connected with airborne weapon stores pylon device, is used for simulating the signal cross-linked condition under the actual carry guided missile.
The utility model discloses a through following technical scheme realize.
An airborne fire control system ground detection device for detecting a cross-linking signal from an airborne fire control system and a missile launching device for controlling a missile before the missile is mounted on an aircraft, the detection device comprising:
the missile simulation device is electrically connected with a missile launching device of the airborne fire control system and used for simulating the circuit working condition under the actual mounted missile;
the signal conditioning unit is used for receiving the cross-linking signal sent by the airborne fire control system, converting the cross-linking signal and outputting the signal to the signal acquisition unit, and receiving the signal sent by the signal sending unit, converting the signal and outputting the signal to the airborne fire control system, so that the output signal meets the requirement of the airborne fire control system on the signal;
the signal acquisition unit is used for receiving the sampling data of the signal conditioning unit and sending the sampling data to the central processing unit;
the signal sending unit is used for receiving the sending data of the central processing unit and sending the sending data to the signal conditioning unit;
the central processing unit is in wireless connection with the handheld terminal and is used for realizing data conversion and transmission among the signal acquisition unit, the signal sending unit and the handheld terminal;
and the handheld terminal is in wireless connection with the central processing unit and is used for monitoring and displaying monitoring information and monitoring results in real time.
Preferably, the system also comprises a wireless unit for realizing the information communication between the central processing unit and the handheld terminal.
Preferably, the signal acquisition unit is also provided with an A/D conversion module for realizing the conversion from the analog signal to the digital signal; the signal sending unit is also provided with a D/A conversion module to realize the conversion from the digital signal to the analog signal.
Preferably, the missile simulation device is powered by the aerial carrier when working; the hand-held terminal is internally provided with a battery as a power supply and is charged through a common 220V50Hz socket or a USB port.
Preferably, the cross-linked signals received and transmitted by the missile simulation device comprise discrete signals, analog signals and frequency signals.
Preferably, the discrete signal corresponding to the cross-linking signal comprises: "target indication", "selector channel", "on hook guidance", "distance instruction", "height instruction" signals, analog signals including: a "heading steering voltage" signal, a "pitch steering voltage" signal, a frequency signal comprising: "spatial gating signal" and "adjustment signal" signals.
Preferably, the central processing unit is further provided with a data processing module for preprocessing the monitoring data.
Preferably, the central processing unit is further provided with a conversion module for converting the monitoring data into a digital signal.
Preferably, the handheld terminal is used for loading detection software of the detection device, and ground in-situ detection of the airborne fire control system function is achieved.
Preferably, the real-time detection of the airborne fire control system by the detection device comprises the following mode combinations of the airborne fire control system:
"live-shot" or "training shot" mode;
a "drop" or "no drop" mode;
"seeker 1" or "seeker 2" or "seeker 3" modes.
The ground detection method of the airborne fire control system adopts any one of the ground detection devices of the airborne fire control system, and comprises the following steps:
the central processing unit receives detection data generated under the drive of an input instruction, and the detection data is generated after a signal conditioning unit receives a cross-linking signal of the onboard fire control system, is converted and is sampled by a signal acquisition unit;
the central processing unit carries out data preprocessing and conversion on the detection data and wirelessly transmits the data to the mobile phone terminal;
and the handheld terminal monitors the detection data in real time and displays the test result in real time.
Preferably, the detection method further includes outputting a fault reason when a fault is encountered through the handheld terminal real-time output detection stage.
Compared with the prior art, the utility model has the advantages that: the utility model discloses machine carries fire control system ground detection device and detection method, through detecting the crosslinked signal that is used for controlling the guided missile, show, differentiate, and show for ground crew through handheld terminal, be convenient for in time monitor and discover machine carries fire control system trouble, the difficult problem that the airport lacks the detection means to machine carries fire control system trouble in the past has been solved, and simultaneously, the device portability is good, operating procedure is simple, the test result is directly perceived, the greatly reduced causes the error of guided missile trouble or misjudgement guided missile trouble because of machine carries fire control system problem, the security of maintenance is improved.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification. In the drawings:
FIG. 1 is a schematic block diagram of a preferred embodiment of the detection device of the present invention;
FIG. 2 is a schematic view of the preferred embodiment of the present invention in a configuration for mounting the detector assembly to an aircraft;
FIG. 3 is a schematic flow chart of a detection method according to a preferred embodiment of the present invention;
FIG. 4 is a schematic diagram of a software login interface in a preferred embodiment of the present invention;
fig. 5 is a software operation interface in the preferred embodiment of the present invention.
FIG. 6 is an interface for operating a missile simulator in accordance with a preferred embodiment of the present invention;
description of reference numerals:
1. a cockpit;
2. an onboard fire control system;
3. a missile launching device;
4. a detection device;
5. simulating to throw in the cable;
6. the plug is dropped;
001. a missile simulation device;
002. a signal conditioning unit;
003. an information acquisition unit;
004. a central processing unit;
005. a wireless unit;
006. a handheld terminal;
007. a signal transmitting unit.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and specific embodiments, but the present invention is not limited thereto.
The utility model discloses a preferred embodiment provides an airborne fire control system ground detection device for cross-linked signal who is used for controlling the guided missile that comes from airborne fire control system detects before aircraft carries the guided missile, refer to figure 1, this detection device includes:
the missile simulation device 001 is electrically connected with a missile launching device of the airborne fire control system and is used for simulating the circuit working condition under the actual mounted missile;
the signal conditioning unit 002 is used for receiving the cross-linked signal sent by the onboard fire control system, converting the cross-linked signal and outputting the signal to the signal acquisition unit 003, and receiving the signal sent by the signal sending unit 007, converting the signal and outputting the signal to the onboard fire control system, so that the output signal meets the requirement of the onboard fire control system on the signal;
the signal acquisition unit 003 is used for receiving the sampling data of the signal conditioning unit 002 and sending the sampling data to the central processing unit 004;
the signal sending unit 007 is configured to receive the sending data of the central processing unit 004 and send the sending data to the signal conditioning unit 002;
the central processing unit 004 is wirelessly connected with the handheld terminal 006 and is used for realizing data conversion and transmission among the signal acquisition unit 003, the signal sending unit 007 and the handheld terminal 006;
and the handheld terminal 006 is in wireless connection with the central processing unit 004 and is used for monitoring and displaying monitoring information and monitoring results in real time.
The detection device of the embodiment detects, displays and judges the cross-linked signal for controlling the missile, and displays the cross-linked signal to ground crew through the handheld terminal 006, so that airborne fire control system faults can be monitored and found in time, the problem that the airborne fire control system faults lack detection means in the past airport is solved, and meanwhile, the device is good in portability, simple in operation steps and intuitive in test result, the errors of missile faults or misjudgment of the missile faults caused by the airborne fire control system problems are greatly reduced, and the maintenance safety is improved.
Preferably, referring to fig. 2, the detection device is connected with the missile launching device and the onboard fire control system through the simulated drop cable 5 and the drop plug 6. And a wireless unit 005 for realizing wireless communication between the central processing unit 004 and the handheld terminal 006. The detection device can output appropriate missile feedback signals to the cross-linked signal channel according to time sequence and working conditions, the signal conditioning unit 002 can also feed the missile intercepted signals of the target back to the airborne fire control system, and the signals are displayed on the handheld terminal 006 after the central processing unit 004 is wirelessly connected with the handheld terminal 006 to be read by ground crew so as to judge the state of the device and judge whether the aircraft missile launching device and the airborne fire control system are normal or not.
Preferably, the missile simulation device 001 does not need to be charged and is powered by the aerial carrier during operation; the hand-held terminal 006 is provided with a built-in battery as a power source and can be charged through a common 220V50Hz socket or a USB port.
Preferably, the cross-linked signals received and transmitted by missile simulation device 001 in this example include discrete signals, analog signals, and frequency signals. The discrete signals corresponding to the cross-linking signals in this example include: signals such as "target indication", "selector channel", "on-hook guidance", "distance instruction", "height instruction", etc., analog signals include: signals such as "heading guide voltage", "pitching guide voltage", and the like, and the frequency signals include: "spatial gating signal", "adjustment signal", etc.
Preferably, the central processing unit 004 in this example is further provided with a data processing module for preprocessing the monitoring data, and processing and transmitting the data sent by the signal acquisition unit 003 and the handheld terminal 006, and the central processing unit 004 in this example is further provided with a conversion module for converting the monitoring data into a digital signal, and converting the data sent by the signal acquisition unit 003 into a digital signal, and then transmitting the digital signal to the handheld terminal 006.
Preferably, in this embodiment, the signal acquisition unit 003 further has an a/D conversion module for converting an analog signal into a digital signal, the signal transmission unit 007 further has a D/a conversion module for converting a digital signal into an analog signal, the signal acquisition module 003 integrates acquisition functions of analog signal acquisition, discrete signal acquisition and frequency signal, and can completely meet the acquisition requirements of the airborne signal detector due to the integration of the acquisition of various types of signals, the signal acquisition unit 003 internally includes a 32-bit RISCARM single chip microcomputer and integrates a control kernel of a real-time operating system, and when data is acquired, the data is converted into a digital signal through the data conversion module, and the digitized sampling data is transmitted to the handheld terminal 006 through L ORA wireless communication.
Preferably, in this embodiment, the handheld terminal 006 adopts a wince6.0 system based on an embedded computer platform. The wince6.0 system is a core of the detection apparatus, the embedded device is used as a hardware core platform, the wince6.0 system is a software platform which is actually operated, and the handheld terminal 006 receives a signal transmitted by the central processing unit 004 through the wireless unit 005. Software in the handheld terminal 006 will further process, determine and identify these signals. Handheld terminal 006 is from taking the display screen, can show detection device's real-time demonstration to operating personnel observes, judges, can respond the button on the handheld terminal 006 simultaneously, accomplishes the switching of software function and operating mode.
In this embodiment, the Windows ce operating system is a member of the Windows family, and is a system environment specifically designed for use in personal digital assistants (HPCs) and embedded devices. Such an operating system may enable a full mobile technology to work integrated with existing Windows desktop technology. Windows ce is designed as a general-purpose operating system for small devices, which are typically diskless systems with limited memory. And 6.0 represents the version of the system.
According to the working principle of the detection device, the test software of the ground detection device of the airborne fire control system adopts a modular design, and the system software can complete the functions of system self-checking, test flow and the like and realize the functions of real-time processing, display and the like of information. The test software design mainly completes the following work:
1. carrying out data acquisition on the discrete signal, the analog signal and the frequency signal;
2. carrying out algorithm analysis according to the acquired data, and judging and displaying in real time;
3. and generating and outputting a specified signal according to the acquired data.
Preferably, refer to fig. 3 and illustrate the detection flow of the ground detection method of the airborne fire control system in the preferred embodiment of the present invention. After starting, entering a target parameter loading stage; and secondly, entering a power supply stage, starting a software interface, sending a power supply instruction to the central processing unit 004 by the aerial carrier through the missile launcher, and starting to establish connection between the handheld terminal 006 and the central processing unit 004. After the central processing unit 004 and the handheld terminal 006 receive the power supply instruction, the handheld terminal 006 performs self-inspection on the detection device and feeds back the initial state of the detection device to the carrier; after the detection is finished, checking the power supply control flow of the airborne fire control system, and judging whether the initial state of the airborne fire control system has a fault; then, entering a good power supply stage, after the initial detection is normal, the onboard fire control system sends a target search instruction to the central processing unit 004 through the missile launcher and guides the detection device 001 to search for a target; then, entering a search stage, after receiving a search instruction issued by the carrier, the central processing unit 004 guides search flow inspection and cross-linked signal characteristic inspection until a target is searched; then, in an interception stage, after the airborne fire control system searches a target signal according to the detection device, the cooperative relationship is checked, and an emission instruction is output to the central processing unit 004; and finally, entering a transmission flow checking stage, after receiving the transmission instruction, the central processing unit 004 performs transmission action or non-transmission operation according to the initial setting of the central processing unit, and ends the detection process. In the above process, as long as any one link fails, the central processing unit 004 displays the failure information through the handheld terminal 001, and stops the detection process until the failure is removed and detection is performed again. The judgment of the correctness of the detection items by the central processing unit 004 is based on the correctness of various types of signals transmitted to the missile simulation device 001 by the acquisition airborne fire control system, if the types and the ranges of the acquired signals are correct, the detection items are correct, the next detection item is carried out, and the steps are repeated until all the detection items are checked. The software interface mainly comprises a login interface (see fig. 4), a real-time display interface (see fig. 5) and the like.
Preferably, in this example, the real-time detection of the onboard fire control system by the detection device includes the following mode combinations of the onboard fire control system:
"live-shot" or "training shot" mode;
a "drop" or "no drop" mode;
"seeker 1" or "seeker 2" or "seeker 3" modes. Referring to fig. 6, the use of the detection device missile simulator 001 in this example:
1. the load switch is used for simulating whether the missile is hung on the missile launcher or not. When the switch is turned to be a load, the missile is hung on the missile launcher, and the missile simulator 001 can be electrified; when the switch is turned to be off, the missile is not hung on the missile launcher, and the power cannot be supplied at the moment. Therefore, when the onboard fire control system is checked on the ground, the load switch must be turned on to be powered up.
2. The training bomb flag switch is used to simulate a "live bomb" or "training bomb" mode. When the switch is turned to live ammunition, the detection device simulates a live ammunition mode, the airborne fire control system identifies the type of the missile as live ammunition, and the working process of the fire control system is executed according to the working process of the live ammunition; when the switch is turned to the training missile, the detection device simulates a training missile mode, the airborne fire control system identifies the type of the missile as the training missile, and the working process of the fire control system is executed according to the working process of the training missile. When ground inspection is carried out on the airborne fire control system, a ground inspection mode needs to be adopted, and at the moment, a switch needs to be switched to a training bomb mode.
3. And the release selection switch is used for controlling whether a pilot ready signal is sent out or not under an automatic process. Under the automatic process, when the switch is turned to a 'putting-in' mode, if the launch condition is met on the aircraft and the 'launch' button is pressed, the detection device returns a 'pilot ready' signal according to the process, the process can be carried out to the 'normal launch' moment, and the detection device lights a 'launch' signal lamp; when the switch is turned to the 'no-throw-in' mode, if the launch condition is met on the aircraft and the 'launch' button is pressed, the detection device does not return a 'pilot ready' signal, the process cannot be carried out to the 'normal launch' time, and the detection device does not light the 'launch' signal lamp.
4. The seeker type selection switch is used for setting the seeker type. When the wave band switch rotates to a 'leading 1' mode, the detection device executes a No. 1 seeker fire control process; when the wave band switch rotates to a 'leading 2' mode, the detection device executes a No. 2 seeker fire control process; when the wave band switch rotates to a 'leading 3' mode, the detection device executes a No. 3 seeker fire control process. The seeker type setting must be done before the detection device is powered up and after power up the setting is disabled.
All signal lamps on the missile simulation device 001 are used for displaying the working state of corresponding equipment. The "communication" signal lamp is used for indicating the communication state between the detection device central processing unit 004 and the handheld terminal 006, when the handheld terminal 006 communicates with the central processing unit 004 once, the "communication" signal lamp flashes once, and if the "communication" signal lamp does not flash, it indicates that there is no communication between the handheld terminal 006 and the central processing unit 004. The 'power supply' signal lamp, the 'power supply good' signal lamp, the 'search' signal lamp, the 'interception' signal lamp and the 'emission' signal lamp are respectively used for indicating the stage of the onboard fire control function inspection.
According to the utility model discloses an on the other hand still provides an airborne fire control system ground detection method, adopts above-mentioned airborne detection device, and detection method includes:
the central processing unit 004 receives detection data generated under the drive of an input instruction, and the detection data is generated after a signal conditioning unit 002 receives a cross-linking signal of the onboard fire control system, is converted and is sampled by a signal acquisition unit 003;
the central processing unit 004 preprocesses and converts the detection data and transmits the data to the mobile phone terminal (006) in a wireless way;
the handheld terminal 006 monitors the detection data in real time and displays the test result in real time.
Preferably, the automatic test method of the detection device to the onboard fire control system comprises the following steps:
1. cable connection:
(1) connecting one end of a simulated drop cable 5, which is connected with a detection device, to a socket 2 of a detection device missile simulation device 001, and connecting one end of a launching cradle to an inspection socket of a missile launching cradle;
(2) connecting a missile shedding plug 6 of the detection device with a missile shedding socket of a missile launcher;
2. preparation before testing
(1) When the ground inspection is carried out on the carrier, a training bullet mark switch of the detection device is set to be in a training bullet state, a throwing selection switch is set to be in a throwing state, a seeker type switch is set to be any one of a No. 1 seeker, a No. 2 seeker and a No. 3 seeker, and each seeker needs to be electrified again to carry out a complete inspection process;
(2) checking whether the simulated drop cable of the detection device is normal or not to ensure that the connection is correct;
(3) confirming target radio parameters loaded by the onboard electronic warfare;
(4) a load switch on the missile simulation device 001 of the detection device is arranged at a load position;
(5) the aerial carrier executes missile power-up according to a normal working process and executes a launching control process according to a ground inspection mode.
3. Test procedure
Referring to fig. 5, in an automatic test interface of the test software, the onboard fire control function is automatically checked by the detection device when the onboard fire control function is powered on by the onboard fire control device without being operated by a person. After the detection device is powered on, an operator on the aircraft starts searching, and the detection device automatically executes a corresponding fire control process according to the type of a preset seeker to check the aircraft-mounted fire control system.
When a certain step in the process is executed normally, the corresponding process indicator lamp is lightened, if a fault occurs in the step executing process, the process is stopped, and the corresponding process indicator lamp is not lightened.
If the launching control flow is normally executed until the missile is allowed to launch, the missile launching button can be pressed on the carrier at the moment. If the detection device detects that the missile launching process of the aircraft is normal and receives a normal launching signal, the launching indicating lamp is lightened, at the moment, a ground operator needs to manually place a load switch at an off position, and the aircraft is normally powered off. Before the launching process is checked, the connection of the safe wrapping belt of the detection device is confirmed to be reliable, and no personnel or other equipment is arranged below or nearby the missile launching device, so that accidents are prevented.
The utility model discloses choose general embedded computer as main control platform for use, as input control and real-time display test result through handheld terminal, cross-linked signal to airborne fire control system and detection device has designed signal conditioning unit 002, design on WinCe6.0 system, software detection flow and algorithm have been worked out, finally produce an airborne fire control system ground detection device, through experimental verification feasible, also tried on the customer site, the feedback is good, the difficult problem that airport lacks the detection means to airborne fire control system cross-linked signal transmission trouble in the past has been solved, and simultaneously, equipment portability is good, operating procedure is simple, the test result is directly perceived, from the report on probation, the needs in airport have been satisfied, customer's recognition has been obtained, can significantly reduce because of airborne fire control system problem causes the error of guided missile trouble or misjudgement guided missile trouble.
The above description is only an example of the preferred embodiment of the present invention, and not intended to limit the scope of the present invention, and those skilled in the art should be able to realize the equivalent alternatives and obvious variations of the present invention.
Claims (8)
1. An airborne fire control system ground detection device for detecting a cross-linking signal from an airborne fire control system and a missile launching device for controlling a missile before the missile is mounted on an aircraft, the detection device comprising:
the missile simulation device (001) is electrically connected with a missile launching device of the airborne fire control system and is used for simulating the circuit working condition under the actual mounted missile;
the signal conditioning unit (002) is used for receiving the cross-linking signal sent by the airborne fire control system, converting the cross-linking signal and outputting the signal to the signal acquisition unit (003), and receiving the signal sent by the signal sending unit (007), converting the signal and outputting the signal to the airborne fire control system, so that the output signal meets the requirement of the airborne fire control system on the signal;
the signal acquisition unit (003) is used for receiving the sampling data of the signal conditioning unit (002) and sending the sampling data to the central processing unit (004);
a signal transmitting unit (007) for receiving the transmission data of the central processing unit (004) and transmitting the transmission data to the signal conditioning unit (002);
the central processing unit (004) is in wireless connection with the handheld terminal (006) and is used for realizing data conversion and transmission among the signal acquisition unit (003), the signal sending unit (007) and the handheld terminal (006);
and the handheld terminal (006) is in wireless connection with the central processing unit (004) and is used for monitoring and displaying monitoring information and monitoring results in real time.
2. The ground detection device of the airborne fire control system of claim 1, further comprising a wireless unit (005) for realizing information communication between the central processing unit (004) and the handheld terminal (006).
3. The ground detection device of the airborne fire control system according to claim 1, wherein the signal acquisition unit (003) is further provided with an A/D conversion module for realizing conversion from an analog signal to a digital signal; the signal sending unit (007) is further provided with a D/A conversion module to realize conversion from digital signals to analog signals.
4. The on-board fire control system ground detection device of claim 1, wherein the missile simulator (001) is powered by the on-board vehicle during operation; the hand-held terminal (006) is provided with a built-in battery as a power supply and is charged through a common 220V50Hz socket or a USB port.
5. The on-board fire control system ground detection device of claim 1, wherein the cross-linked signals received and transmitted by the missile simulation device (001) comprise discrete signals, analog signals, and frequency signals.
6. The ground detection device of claim 5, wherein the discrete signal corresponding to the cross-linked signal comprises: "target indication", "selector channel", "on hook guidance", "distance instruction", "height instruction" signals, analog signals including: a "heading steering voltage" signal, a "pitch steering voltage" signal, a frequency signal comprising: "spatial gating signal" and "adjustment signal" signals.
7. The ground detection device of the airborne fire control system according to claim 1, wherein the handheld terminal (006) is used for loading detection software of the detection device to realize ground in-situ detection of the functions of the airborne fire control system.
8. The ground detection device of the airborne fire control system according to claim 1, wherein the detection device for real-time detection of the airborne fire control system comprises the following mode combinations:
"live-shot" or "training shot" mode;
a "drop" or "no drop" mode;
"seeker 1" or "seeker 2" or "seeker 3" modes.
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| CN202020188028.3U CN211207168U (en) | 2020-02-20 | 2020-02-20 | Airborne fire control system ground detection device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115035764A (en) * | 2022-05-27 | 2022-09-09 | 中国航空工业集团公司沈阳飞机设计研究所 | Airborne launcher simulation transmission method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115035764A (en) * | 2022-05-27 | 2022-09-09 | 中国航空工业集团公司沈阳飞机设计研究所 | Airborne launcher simulation transmission method |
| CN115035764B (en) * | 2022-05-27 | 2024-01-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Airborne emission simulation emission method |
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Granted publication date: 20200807 |