CN107544458B - Airborne detection device and detection method for air-to-air missile - Google Patents
Airborne detection device and detection method for air-to-air missile Download PDFInfo
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- CN107544458B CN107544458B CN201710785125.3A CN201710785125A CN107544458B CN 107544458 B CN107544458 B CN 107544458B CN 201710785125 A CN201710785125 A CN 201710785125A CN 107544458 B CN107544458 B CN 107544458B
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Abstract
The invention discloses an airborne detection device and a detection method for an air-to-air missile, wherein the airborne detection device comprises: the simulation load device is electrically connected with the missile launching device and used for simulating the circuit working condition under the actual mounted air-to-air missile; the signal conditioning circuit is used for receiving the cross-linking signal, converting the cross-linking signal and outputting the cross-linking signal to the data acquisition unit; the data acquisition unit is used for receiving the sampling data and sending the sampling data to the signal processing unit; the signal processing unit is used for carrying out real-time monitoring according to the output of the data acquisition unit and converting a monitoring result into display data; the first display unit and the second display unit are respectively arranged in the aircraft cockpit and outside the aircraft cockpit, are in communication connection with the signal processing unit and are used for displaying display data. The problem that cross-linked signal transmission faults of an airborne fire control system and a missile launching device lack detection means is solved, the equipment is good in portability, simple to operate and intuitive in test result, and faults or misjudgment missile faults are reduced.
Description
Technical Field
The invention relates to the field of missile guidance control, in particular to an air-to-air missile airborne detection device and a detection method.
Background
During the use process of the air-to-air missile and the flight training missiles of corresponding models, the situation that the faults of the air-to-air missile are caused by the transmission faults of cross-linked signals of an airplane fire control system and a missile launching device occurs in practice, for example, the missile is damaged due to abnormal power supply, the missile fails to intercept a target due to abnormal target indicating signals, the missile cannot work due to blockage of a nitrogen pipeline, and the air-to-air missile is returned to the factory for maintenance but the practical problem is still not solved. However, a special device for detecting the cross-linked signals of the airborne fire control system and the missile launching device related to the air-to-air missile is not available at present, and in reality, the airport mainly depends on crew and pilots to carry out manual judgment according to experience, so that misjudgment or product damage is easy to occur.
Disclosure of Invention
The invention provides an air-to-air missile airborne detection device and a detection method, and aims to solve the technical problems that no special equipment for detecting cross-linking signals of an air-to-air missile associated airborne fire control system and a missile launching device exists in the prior art, so that self-checking and omission of an airplane is caused, and the operation of a missile is influenced.
The technical scheme adopted by the invention is as follows:
according to one aspect of the invention, an airborne detection device for an air-to-air missile is provided, which is used for detecting a cross-linking signal for controlling the air-to-air missile from an airborne fire control system and a missile launching device before an aircraft is loaded with the air-to-air missile, and comprises:
the simulation load device is electrically connected with the missile launching device and used for simulating the circuit working condition under the actual mounted air-to-air missile;
the signal conditioning circuit is used for receiving the cross-linking signal, converting the cross-linking signal and outputting the cross-linking signal to the data acquisition unit;
the data acquisition unit is used for receiving the sampling data and sending the sampling data to the signal processing unit;
the signal processing unit is used for carrying out real-time monitoring according to the output of the data acquisition unit and converting a monitoring result into display data related to control;
the first display unit and the second display unit are respectively arranged in the aircraft cockpit and outside the aircraft cockpit, are in communication connection with the signal processing unit and are used for displaying display data.
Further, the airborne detection device of the invention also comprises:
and the power circuit is used for converting the airborne power supply and supplying power to the airborne detection device.
Furthermore, the cross-linked signal received by the signal conditioning circuit comprises a switching value signal and/or an analog signal, and the data acquisition unit comprises an I/O sampling port for receiving the switching value signal and an ADC sampling port for receiving the analog signal.
Further, the instructions for cross-linking the signal include: at least one of a refrigeration valve opening instruction, a missile position marker electric lock instruction, a two-way target indication instruction, a platform disconnection instruction, a free tracking instruction, an ignition instruction, a transmitting instruction, an uncontrollable transmitting instruction and an interception instruction for simulating normal operation feedback of a missile by a detector.
Furthermore, the signal processing unit is provided with a storage module for storing the monitoring result.
Furthermore, the signal processing unit is also arranged on a conversion module for converting the monitoring result into graphical display data.
Furthermore, the first display screen and/or the second display screen are touch display screens and are used as instruction input ends to switch the working modes of the signal processing unit.
According to another aspect of the invention, the invention also provides an airborne detection method of the air-to-air missile, which adopts the above airborne detection device, and the detection method comprises the following steps:
the signal processing unit receives detection data generated under the drive of an input instruction, and the detection data is generated after the cross-linking signals of the airplane fire control system and the missile launching device are received by the signal conditioning circuit, converted and sampled by the data acquisition unit;
the signal processing unit monitors the detection data in real time and displays the test result in real time through the first display unit and the second display unit.
Further, the real-time monitoring of the detection data by the signal processing unit includes at least one of:
after the refrigeration electric door is started, whether the monitored nitrogen pressure value meets the requirement or not is judged;
under the condition of using the helmet sight, the indicating angles in four directions of the head sight state, the upper direction, the lower direction, the left direction and the right direction are monitored;
in the case of using the "optical ring", indication angles in four directions, up, down, left, and right, of the "optical ring" state are monitored.
Further, the detection method of the present invention further comprises:
and outputting a detection report through the signal processing unit, and locking the fault type and/or fault position through the detection report.
The invention has the following beneficial effects:
the airborne detection device and the detection method of the air-to-air missile of the invention detect, display and judge the cross-linked signal for controlling the missile, display the cross-linked signal to the pilot through the first display unit arranged in the cockpit, and display the cross-linked signal to ground crew through the second display unit arranged outside the cockpit, thereby being convenient for finding and monitoring the cross-linked signal fault in time, solving the problem that the prior airport lacks detection means for the cross-linked signal transmission fault of the airborne fire control system and the missile launching device, simultaneously having good equipment portability, simple operation steps and intuitive test results, and greatly reducing the errors of missile fault or misjudgment of the missile fault caused by airplane problems.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic block diagram of an airborne detection device for an air-to-air missile according to a preferred embodiment of the invention;
FIG. 2 is a schematic structural view of the airborne detection device of an air-to-air missile according to the preferred embodiment of the invention mounted on an airplane;
FIG. 3 is a schematic diagram of the power supply circuit in the preferred embodiment of the present invention;
FIG. 4 is a schematic flow chart of an airborne detection method for air-to-air missiles in a preferred embodiment of the invention;
FIG. 5 is a schematic diagram of a signal processing system software login interface in a preferred embodiment of the present invention;
FIG. 6 is a schematic view of a test interface shown in the preferred embodiment of the present invention;
fig. 7 is a flow chart of an airborne detection method of an air-to-air missile in another preferred embodiment of the invention.
Description of reference numerals:
1. an onboard fire control system;
2. a missile launching device;
3. inspecting the cable; 31. an aviation plug;
4. an airborne signal detection device;
5. a cockpit;
100. a simulated load device;
200. a signal conditioning circuit;
300. a data acquisition unit;
400. a signal processing unit;
500. a first display unit;
600. a second display unit;
700. a power supply circuit.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
The preferred embodiment of the present invention provides an airborne detection device for air-to-air missiles, which is used for detecting cross-linking signals for controlling the air-to-air missiles from an airborne fire control system and a missile launching device before an aircraft mounts the air-to-air missiles, and referring to fig. 1, the airborne detection device of the present embodiment includes:
the simulation load device 100 is electrically connected with the missile launching device and used for simulating the circuit working condition under the condition of actually mounting the air-to-air missile;
the signal conditioning circuit 200 is configured to receive the cross-linked signal, convert the cross-linked signal, and output the converted cross-linked signal to the data acquisition unit 300;
a data acquisition unit 300 for receiving the sampled data and transmitting the sampled data to the signal processing unit 400;
a signal processing unit 400 for performing real-time monitoring according to the output of the data acquisition unit 300 and converting the monitoring result into display data;
the first display unit 500 and the second display unit 600 are respectively disposed in the cockpit and outside the cockpit, and are all in communication connection with the signal processing unit 400 for displaying display data.
The airborne detection device of the embodiment detects, displays and judges the cross-linked signal for controlling the missile, displays the cross-linked signal to a pilot through the first display unit arranged in the cockpit, displays the cross-linked signal to ground crew through the second display unit arranged outside the cockpit, is convenient for finding and monitoring the cross-linked signal fault in time, solves the problem that the prior airport lacks detection means for the cross-linked signal transmission fault of the airborne fire control system and the missile launcher, and meanwhile, has good equipment portability, simple operation steps and visual test results, and greatly reduces the error of missile fault or misjudgment of the missile fault caused by airplane problems.
Referring to fig. 2, the airborne detection device 4 of the present embodiment is connected to the missile launching device 2 and the airborne fire control system 1 via the detection cable 3 and the aviation plug 31, the second display unit 600 is arranged at the detection device as a main display screen, and the first display screen 500 is arranged in the cockpit 5 as a secondary display screen. The detection device can output proper missile feedback signals to the cross-linked signal channel according to time sequence and working conditions, the signal conditioning circuit 200 can also feed back the intercepted signals of the missiles to the targets to the missile launching device, the intercepted signals are displayed on a display screen of an aircraft cockpit after passing through the missile launching device and the airborne fire control system and are read by a pilot to judge the state of a product, and ground crew can judge whether the aircraft missile launching device 2 and the airborne fire control system 1 are normal or not through detection data displayed by the display screen positioned outside the cockpit.
Preferably, in order to satisfy the requirement of external field detection without being limited by the use limitation of ac power supply, the onboard detection device of the present embodiment further includes a power circuit 700 for converting the onboard power supply and supplying the converted onboard power supply to the onboard detection device. In this embodiment, the power supply requirements of the data acquisition unit 300 and the signal processing unit 400 are +24V dc, and the stability of the onboard power supply is not good, which is not beneficial to the work of the data acquisition unit 300 and the signal processing unit 400. In order to realize the switching and operation stability of the power supply, a switching module and a power supply filter circuit of the dc power supply are added to the circuit of the power supply circuit 700 to ensure the normal operation of the detection apparatus, and the circuit structure thereof is as shown in fig. 3. By adopting the power supply circuit 700, the detection device has the advantages of small structure volume, portability, wide input voltage range, isolated input and output and strong anti-interference capability, and preferably, a short circuit/overcurrent protection circuit is arranged in the power supply circuit 700 so as to enhance the reliability of power supply.
In this embodiment, the load simulator 100 is formed by a power resistor to simulate a current working condition of an actual mounted air-to-air missile. In particular to the air-to-air missile of the embodiment, the airplane provides +20V, -20V, +27V, -27V, +27V (bi) five-way direct current power supply and 36V-400Hz three-phase alternating current power supply for the missile through a missile launching device, wherein +27V (bi) is used as power supply for the missile weather mark preheating. Starting current and normal working current can be generated when the air-to-air missile is actually mounted, and a high-power resistor is selected to form a simulation load device according to the magnitude of the current consumed by each power supply, so that the working condition of the actual mounted air-to-air missile can be simulated. It should be noted that, since the +20V power supply is also used to supply power to the signal conditioning circuit, the consumed current of the signal conditioning circuit needs to be subtracted when calculating the resistance value of the analog load.
In this embodiment, the cross-linked signal received by the signal conditioning circuit 200 includes a switching value signal and/or an analog signal, and the data acquisition unit 300 includes an I/O sampling port for receiving the switching value signal and an ADC sampling port for receiving the analog signal.
Preferably, the instructions for cross-linking signals include: at least one of a refrigeration valve opening instruction, a missile position marker electric lock instruction, a two-way target indication instruction, a platform disconnection instruction, a free tracking instruction, an ignition instruction, a transmitting instruction, an uncontrollable transmitting instruction and an interception instruction for simulating normal operation feedback of a missile by a detector.
In this embodiment, the signal conditioning circuit 200 further receives the nitrogen pressure value monitored by the pressure sensor, so that the signal processing unit 400 monitors the nitrogen pressure value of the missile.
In this embodiment, the signal conditioning circuit 200 is responsible for reducing the power supply voltage to the effective input range of the acquisition processing unit and filtering out noise and interference. Meanwhile, for a certain type of air-to-air missile, signals to be detected in cross-linked signals from an airborne fire control system and a missile launching device include a 'refrigerating valve opening' instruction, a missile marker electric lock instruction, two-way target indication instructions, a 'platform disconnection, free tracking' instruction, an ignition instruction, a launching instruction, an uncontrollable launching instruction and an interception instruction of simulating normal operation feedback of the missile by a detector, the instructions can find actual physical meanings only in the corresponding certain type of air-to-air missile, for example, the 'refrigerating valve opening' instruction is used for opening a small nitrogen bottle on the missile, the ignition instruction is used for igniting a missile engine, and if the missile is changed to be of other types, the instruction changes and redesigns a conditioning circuit according to the actual condition of the missile. The instructions have pure switching signals and analog signals, and the signal conditioning circuit can reduce all signals to the effective input range of sampling according to the signal characteristic difference and correspondingly provide the signals to an IO (input/output) end or an ADC (analog-to-digital converter) sampling port of the data acquisition unit.
In this embodiment, the data acquisition unit 300 integrates the functions of differential/single-ended analog acquisition, analog output, digital acquisition and digital output, 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 data acquisition module internally comprises a 32-bit RISC ARM single chip microcomputer and integrates a control kernel of a real-time operating system, when data are acquired, the data are changed into nodes of an RS485 bus network through an optional NDAM-9010 communication module, and digitized sampling data are sent to the signal processing unit 400 of the airborne signal detection device through the RS485 bus.
In this embodiment, the signal processing unit 400 adopts an embedded computer platform based monitoring and Control general system mcgs (monitor and Control Generated system). The MCGS system is a core circuit of the detection device, takes an embedded computer as a hardware core platform, is a software system which is actually operated, receives the acquired data sent by the data acquisition unit 300 through an RS485 bus, and is used for further processing according to analog quantity signals and instruction switch signals in the data. The MCGS system is provided with a touch display screen, can display the detection result of the detector in real time so as to facilitate observation and reading of an operator, and can respond to a touch key which is independently defined on the touch display screen to complete switching of software functions and working modes.
In the embodiment, the missile airborne signal detection device MCGS software adopts a modular design, and the system software completes the functions of system self-checking, signal monitoring and the like and realizes the functions of real-time information storage, recording, display and the like. The MCGS system is based on a Windows platform, is used for quickly constructing and generating a configuration software system of an upper computer monitoring system, and mainly completes the acquisition and monitoring of field data and the processing and control of front-end data.
According to the working principle of the detection device, the software design of the MCGS system mainly completes the following work:
1. carrying out data acquisition on the power supply signal and other instruction signals;
2. carrying out algorithm analysis and imaging display according to the collected target indication signal;
3. simulating the output of the intercepted signal;
4. and performing real-time detection and storage on the maximum value of the data.
Fig. 4 shows a detection process of MCGS software in the airborne detection method for an air-to-air missile in the preferred embodiment of the present invention, and after the software is started, the detection of a recording instruction by recording a power signal specifically includes: the method comprises the steps of recording nitrogen pressure data to monitor the nitrogen pressure value in real time, detecting and recording target indication data, inputting an interception instruction, detecting and recording various instruction signals, and outputting a test report. The software interface mainly comprises a login interface (see figure 5), a real-time display interface (see figure 6), detection report output, data export and historical data query.
Preferably, the signal processing unit 400 is provided with a storage module for saving the monitoring result. In this embodiment, preferably, a file storage manner in a csv format is adopted, which has the advantage of easy display and search, and considering that a small amount of test data can be exported regularly, the limitation of large storage memory requirement will not cause an influence.
Preferably, the signal processing unit 400 is further provided with a conversion module for converting the monitoring result into graphical display data. The missile launcher sends voltage signals representing polar coordinates to the detection device, and the voltage signals need to be converted in order to be solved, digitized and graphed. Because of the corresponding relation between the voltage and the polar coordinate, the polar coordinate and the displayed azimuth angle, the secondary conversion is needed, and the MCGS system does not have the azimuth display function, so that the graphical display is more difficult. In this embodiment, the voltage signal is converted into a digital signal by the data acquisition unit, and the digital signal is transmitted to the signal processing unit through the RS485 communication, and then data processing is performed. And extracting corresponding polar coordinate information according to the voltage signal, and converting the polar coordinate information into a corresponding direction angle of a Cartesian rectangular coordinate system. As for the MCGS system without the function of azimuth display, the whole interface is divided into areas, the azimuth display is made into a single area, the value range of the X coordinate and the Y coordinate of the area is calculated, the azimuth of the target in a three-dimensional state can be accurately described by using an auxiliary Cartesian coordinate system (circular coordinates), and the azimuth moving track of the target is displayed by changing the X, Y coordinates of the points. Preferably, the display area is made as a dual coordinate system display (i.e. both cartesian and polar coordinate systems) taking into account the visualization of its respective orientation.
According to another aspect of the invention, an airborne detection method for the air-to-air missile is further provided, and by adopting the airborne detection device of the above embodiment, the detection method includes:
the signal processing unit 400 receives detection data generated under the drive of an input instruction, the detection data is generated after the signal conditioning circuit 200 receives cross-linking signals of an airplane fire control system and a missile launching device, the cross-linking signals are converted and are sampled by the data acquisition unit 300;
the signal processing unit 400 monitors the detection data in real time and displays the test result in real time through the first display unit 500 and the second display unit 600.
Preferably, the real-time monitoring of the detection data by the signal processing unit 400 includes at least one of:
after the refrigeration electric door is started, whether the monitored nitrogen pressure value meets the requirement or not is judged;
under the condition of using the helmet sight, the indicating angles in four directions of the head sight state, the upper direction, the lower direction, the left direction and the right direction are monitored;
in the case of using the "optical ring", indication angles in four directions, up, down, left, and right, of the "optical ring" state are monitored.
Preferably, the detection method of the present invention further comprises:
the detection report is output via the signal processing unit 400 and the fault type and/or fault location is locked in via the detection report.
The airborne signal detection device of the air-to-air missile of the embodiment adopts a modular design, and after the design and manufacture of the equipment are completed according to the steps, the working flow of the airborne signal detection device is shown in fig. 7 in practical use. The helmet sighting device and the optical ring are two different modes for a pilot on an airplane to operate the missile, and the switching of other instructions and states also truly simulates the working process of an actual missile. Through the completion of the whole detection process, the technical requirements of qualified items are contrasted, the conclusion whether an aircraft fire control system and a missile launching device associated with a certain type of air-to-air missile are normal can be finally obtained, if the aircraft fire control system and the missile launching device are in fault, the fault phenomenon can be locked, the fault part is reduced, and further fault elimination is facilitated. After the conclusion that the detection is qualified is obtained, the crew can mount the empty missile at ease, the missile is not required to be damaged, misjudgment of the missile due to faults of the airborne fire control and missile launching device is not required to be unqualified, the training efficiency is improved, and the smooth flight training task is guaranteed.
The invention selects a general embedded computer on the market as a main control platform, uses a touch screen button and a button switch as input control, uses a display screen to display a test result in real time, designs a signal conditioning unit aiming at a cross-linking signal of an aircraft fire control system and a missile launching device of an associated air-to-air missile, software detection processes and algorithms are designed and programmed on an MCGS system, an airborne signal detector for a certain type of air-to-air missile is finally manufactured, and the airborne signal detector is feasible through test verification, also is tried on site by a client, has good feedback, solves the problem that the prior airport lacks a detection means for the cross-linked signal transmission fault of an airborne fire control system and a missile launcher, meanwhile, the device has good portability, simple operation steps and visual test results, meets the requirements of airports from the aspect of trial reports, obtains the approval of customers, and can greatly reduce the errors of missile faults or misjudgment of the missile faults caused by airplane problems.
The detection device and the detection method are not only specific to a certain type of air-to-air missile airborne signal detector of an actual product, but also applicable to other types of missiles, and can simulate the actual working conditions of the missiles as long as the signal change and the working mode switching of the cross-linking of the associated missiles with the airborne fire control system and the missile launching device are known, so that the detection device and the detection method are wide in applicability.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. An air-to-air missile airborne detection device is used for detecting a cross-linking signal which comes from an airborne fire control system and a missile launching device and is used for controlling an air-to-air missile before an aircraft is mounted with the air-to-air missile, and is characterized in that the airborne detection device comprises:
the simulation load device (100) is electrically connected with the missile launching device and is used for simulating the circuit working condition under the condition of actually mounting the air-to-air missile;
the signal conditioning circuit (200) is used for receiving the cross-linked signal, converting the cross-linked signal and outputting the cross-linked signal to the data acquisition unit (300);
a data acquisition unit (300) for receiving sampled data and sending the sampled data to a signal processing unit (400);
the signal processing unit (400) is used for carrying out real-time monitoring according to the output of the data acquisition unit (300) and converting a monitoring result into control-related display data;
the first display unit (500) and the second display unit (600) are respectively arranged in the aircraft cockpit and outside the aircraft cockpit, are in communication connection with the signal processing unit (400), and are used for displaying the display data;
the power supply circuit (700) is used for supplying power to the airborne detection device after the airborne power supply is converted, the circuit of the power supply circuit (700) comprises a conversion module of a direct-current power supply and a power supply filter circuit, and a short circuit/overcurrent protection circuit is arranged in the power supply circuit (700) so as to enhance the reliability of power supply;
the data acquisition unit (300) integrates the functions of differential/single-ended analog acquisition, analog output, digital acquisition and digital output, the data acquisition unit (300) internally comprises a 32-bit RISC ARM single chip microcomputer and is integrated with a control kernel of a real-time operating system, after data are acquired, the data are changed into nodes of an RS485 bus network through an optional NDAM-9010 communication module, and digitized sampling data are sent to a signal processing unit (400) of the airborne signal detection device through an RS485 bus;
the signal processing unit (400) adopts a monitoring and control general system MCGS based on an embedded computer platform, MCGS software adopts a modular design, the system software completes a system self-checking function and a signal monitoring function and realizes real-time storage, recording and displaying of information, the MCGS system is based on a Windows platform and is used for quickly constructing and generating a configuration software system of an upper computer monitoring system and mainly completes the acquisition and monitoring of field data and the processing and control of front-end data, and the MCGS system software design mainly completes the following work: the power supply signal and other instruction signals are subjected to data acquisition, algorithm analysis and imaging display are carried out according to the acquired target instruction signals, the output of intercepted signals is simulated, and the maximum value of the data is detected and stored in real time;
the signal processing unit (400) is also provided with a conversion module for converting the monitoring result into graphical display data, a voltage signal is converted into a digital signal through the data acquisition unit (300), corresponding polar coordinate information is extracted according to the voltage signal, the digital signal is transmitted to the signal processing unit (400) through RS485 communication, then data processing is carried out through the conversion module, the digital signal is converted into a corresponding azimuth angle of a Cartesian rectangular coordinate system, the whole interface is divided into regions, azimuth display is made into an independent region, the value ranges of an X coordinate and a Y coordinate of the region are calculated, meanwhile, the azimuth of the target in a three-dimensional state is accurately described by using an auxiliary Cartesian coordinate system, and the azimuth moving track of the target is displayed by changing the X, Y coordinate of a point;
the cross-linking signal received by the signal conditioning circuit (200) comprises a switching value signal and/or an analog value signal, and the corresponding instruction of the cross-linking signal comprises: the missile position marker system comprises a data acquisition unit (300), a signal conditioning circuit (200) and a control unit, wherein the data acquisition unit comprises at least one of an instruction of opening a refrigeration valve, an instruction of an electric lock of a missile position marker, an instruction of indicating two paths of targets, an instruction of disconnecting a platform, a free tracking instruction, an ignition instruction, an emission instruction, an uncontrollable emission instruction and an interception instruction for simulating normal work feedback of a missile by a detector, the data acquisition unit comprises an I/O sampling port for receiving a switching value signal and an ADC sampling port for receiving an analog quantity signal, and all signals can be reduced to an effective sampling input range according to signal characteristic difference and correspondingly provided to an IO end or an ADC sampling port of the data acquisition unit (300);
the signal processing unit (400) is provided with a storage module for storing the monitoring result, and the storage module adopts a file storage mode of a csv format;
the first display screen and/or the second display screen are/is a touch display screen and are used as instruction input ends to switch the working mode of the signal processing unit (400);
the signal conditioning circuit (200) also receives a nitrogen pressure value monitored by the pressure sensor so that the signal processing unit (400) can monitor the nitrogen pressure value of the missile during working;
the signal conditioning circuit (200) is responsible for reducing the power supply voltage to the effective input range of the acquisition processing unit and filtering out noise waves and interference.
2. An airborne detection method of an air-to-air missile, which is characterized by adopting the airborne detection device as claimed in claim 1, and comprises the following steps:
the signal processing unit (400) receives detection data generated under the drive of an input instruction, and the detection data is generated after a signal conditioning circuit (200) receives cross-linking signals of an aircraft fire control system and a missile launching device, is converted and is sampled by a data acquisition unit (300);
the signal processing unit (400) monitors the detection data in real time, and displays the test result in real time through the first display unit (500) and the second display unit (600).
3. The airborne detection method of an air-to-air missile of claim 2,
the signal processing unit (400) monitors the detection data in real time and comprises at least one of the following steps:
after the refrigeration electric door is started, whether the monitored nitrogen pressure value meets the requirement or not is judged;
under the condition of using the helmet sight, the indicating angles in four directions of the head sight state, the upper direction, the lower direction, the left direction and the right direction are monitored;
in the case of using the "optical ring", indication angles in four directions, up, down, left, and right, of the "optical ring" state are monitored.
4. The air-to-air missile airborne detection method of claim 3, further comprising:
-outputting a detection report via the signal processing unit (400), and-locking the type of fault and/or the location of the fault via the detection report.
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| CN108646705A (en) * | 2018-04-16 | 2018-10-12 | 西安飞机工业（集团）有限责任公司 | A kind of airplane ground test interconnection of signals TT＆C system |
| CN109388075B (en) * | 2018-12-12 | 2021-06-18 | 中国航发南方工业有限公司 | Signal detector |
| CN109613910B (en) * | 2018-12-12 | 2021-06-04 | 中国航发南方工业有限公司 | Signal detector and signal detection method |
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