CN110060541B - Simulation training system for airplane navigation posture equipment - Google Patents
Simulation training system for airplane navigation posture equipment Download PDFInfo
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- CN110060541B CN110060541B CN201910420641.5A CN201910420641A CN110060541B CN 110060541 B CN110060541 B CN 110060541B CN 201910420641 A CN201910420641 A CN 201910420641A CN 110060541 B CN110060541 B CN 110060541B
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- 238000012549 training Methods 0.000 title claims abstract description 94
- 238000004088 simulation Methods 0.000 title claims abstract description 77
- 238000009434 installation Methods 0.000 claims abstract description 19
- 238000012937 correction Methods 0.000 claims abstract description 12
- 238000012544 monitoring process Methods 0.000 claims description 14
- 238000006243 chemical reaction Methods 0.000 claims description 7
- 238000000034 method Methods 0.000 claims description 7
- 230000005540 biological transmission Effects 0.000 claims description 6
- 230000008054 signal transmission Effects 0.000 claims description 4
- 230000001360 synchronised effect Effects 0.000 claims description 4
- 230000008859 change Effects 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 4
- 239000000306 component Substances 0.000 description 9
- 238000010586 diagram Methods 0.000 description 5
- 238000012360 testing method Methods 0.000 description 4
- 238000001514 detection method Methods 0.000 description 3
- 239000008358 core component Substances 0.000 description 2
- 238000004132 cross linking Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
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- 239000004973 liquid crystal related substance Substances 0.000 description 1
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- 238000011056 performance test Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000000819 phase cycle Methods 0.000 description 1
- 238000013024 troubleshooting Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
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- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B9/00—Simulators for teaching or training purposes
- G09B9/02—Simulators for teaching or training purposes for teaching control of vehicles or other craft
- G09B9/08—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
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- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B9/00—Simulators for teaching or training purposes
- G09B9/02—Simulators for teaching or training purposes for teaching control of vehicles or other craft
- G09B9/08—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
- G09B9/12—Motion systems for aircraft simulators
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- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B9/00—Simulators for teaching or training purposes
- G09B9/02—Simulators for teaching or training purposes for teaching control of vehicles or other craft
- G09B9/08—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
- G09B9/16—Ambient or aircraft conditions simulated or indicated by instrument or alarm
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- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B9/00—Simulators for teaching or training purposes
- G09B9/02—Simulators for teaching or training purposes for teaching control of vehicles or other craft
- G09B9/08—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
- G09B9/16—Ambient or aircraft conditions simulated or indicated by instrument or alarm
- G09B9/20—Simulation or indication of aircraft attitude
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Abstract
The invention discloses an aircraft attitude equipment simulation training system, which belongs to the technical field of attitude simulation equipment and comprises an operation training table and a training control table, wherein the operation training table comprises a simulation real-world installation and a simulation cabin panel, the simulation real-world installation comprises a full-attitude combined gyroscope, a magnetic heading sensor, a comprehensive amplifier, a magnetic heading correction calculator, a control box, a relay box, a heading position indicator and a horizon indicator, and the simulation cabin panel comprises an attitude power switch and a quick coordination button; the training control console comprises a main control computer, a fault setting unit and a power supply system, wherein the main control computer is connected with the control box, the main control computer is connected with the relay box through the fault setting unit, and the power supply system supplies power for the training control console and the operation training console. The simulation training system for the airplane navigation posture equipment can simulate various frequent faults and has the characteristics of good training effect and low training cost.
Description
Technical Field
The invention relates to the technical field of avionic simulation equipment, in particular to an airplane avionic simulation training system.
Background
The attitude determination system is one of important airborne equipment, and is mainly used for measuring and indicating the heading angle and attitude angle of an airplane and providing heading and attitude references for other equipment on the airplane. At present, as no special device for training the navigation attitude system is provided, the universities and the colleges mainly rely on the navigation attitude system to carry out teaching, and the main defects are as follows: firstly, the cost of the mounting equipment is high, and the training cost is high; secondly, in the teaching and training process, the incorrect operation can also cause damage to the mounting equipment; thirdly, if training is performed by using the real-world model, the fault phenomenon in the using process cannot be reproduced.
The patent document with the publication number of CN109733643A discloses an aircraft attitude and heading reference equipment test system, which belongs to the technical field of aircraft attitude and heading reference, and comprises a control system, a power supply control unit, a signal modulation unit and a display, wherein the control system comprises an industrial personal computer and a functional board card group; the power supply control unit is connected with the tested navigation attitude system and is used for providing electric energy, phase sequence detection and power supply protection for the tested navigation attitude system. The airplane attitude and heading reference equipment test system is simple in structure, compact in design, high in test precision and comprehensive in test content. However, the application is suitable for performance test and fault location of the attitude and heading reference system, and cannot be suitable for low-cost simulation training of the aircraft attitude and heading reference system, which aims at simulation training and can perform fault simulation reproduction.
Patent document with publication number CN 108897239A discloses a spacecraft two-stage attitude control simulation system for verifying three-override technologies such as ultra-high precision pointing, ultra-high stability control and ultra-agility control of a spacecraft. The verification system includes: the system comprises a star, a load simulator, an active pointing platform, a star primary control loop and a load simulator secondary control loop; the star primary control loop and the load simulator secondary control loop both comprise: the device comprises a control unit, an executing mechanism and a measuring unit; the star primary control loop is connected with the load simulator secondary control loop through a platform; the active pointing platform provides active control force for a secondary control loop of the load simulator; the load simulator transmits the reaction force of the active control force to the star primary control loop through the active pointing platform. The spacecraft two-stage attitude control simulation system constructed by the invention can verify the three-super-platform spacecraft multi-stage composite control technology and control performance indexes. However, the application cannot solve the problem of low-cost simulation training of the aircraft attitude and heading reference system, which aims at the simulation training and can perform fault simulation reproduction.
Disclosure of Invention
In view of the defects of the conventional mounting training, the invention designs an aircraft attitude equipment simulation training system which can realize the functions of performance detection training and fixed inspection of an aircraft attitude system, power-on method training, typical fault simulation and troubleshooting training and the like, and meets the requirements of developing attitude system teaching in institutions.
In order to solve the technical problems, the invention adopts the following technical scheme: the simulation training system for the aircraft attitude equipment comprises an operation training platform and a training control console, wherein the operation training platform comprises a simulation real-world installation and a simulation cabin panel, the simulation real-world installation comprises a full-attitude combined gyroscope, a magnetic heading sensor, a comprehensive amplifier, a magnetic heading correction calculator, a control box, a relay box, a heading position indicator and a horizon indicator, and the simulation cabin panel comprises an attitude power switch and a quick coordination button; the training control console comprises a main control computer, a fault setting unit and a power supply system, wherein the main control computer is connected with the control box, the main control computer is connected with the relay box through the fault setting unit, and the power supply system supplies power for the training control console and the operation training console.
Further, the magnetic heading sensor, the magnetic heading correction calculator and the heading position indicator are sequentially connected, the full-attitude combined gyroscope, the comprehensive amplifier and the heading position indicator are sequentially connected, the control box and the relay box are both connected with the full-attitude combined gyroscope, and the relay box and the full-attitude combined gyroscope are both connected with the horizon indicator.
Furthermore, the navigation attitude power switch controls the on-off of the simulated real-package power supply, and the quick coordination button controls the connection of the simulated real-package circuit.
Further, the fault setting unit comprises a relay board card and a component access control interface, and the main control computer, the relay board card, the component access control interface and the relay box are sequentially connected.
Further, the power supply system comprises power supply monitoring and power supply conversion, and 36V/400Hz three-phase alternating current and 27V direct current supply power to the simulation package and the fault setting unit through the power supply monitoring and the power supply conversion.
Further, the 36V/400Hz three-phase alternating current and the 27V direct current directly supply power to the simulation installation through the power supply monitoring, and the 27V direct current is converted into the fault setting unit through the power supply monitoring and the power supply to provide secondary power supplies of +5V and +12V.
Further, the relay board card is controlled by a PCL-722 board card based on a PCI backboard bus and installed in the main control computer.
Further, the main control computer controls the power supply circuit, the signal transmission circuit, the synchronous follow-up system circuit, the input and output circuit of the amplifier and the power supply and control circuit of the relay box which are installed in an analog mode through an RS232 bus.
Compared with the prior art, the invention has the following beneficial effects:
The simulation training system of the aircraft attitude equipment comprises a full-attitude combined gyroscope, a magnetic heading sensor, a comprehensive amplifier, a magnetic heading correction calculator, a control box, a relay box, a heading position indicator and a horizon indicator, wherein the simulation cabin panel comprises an attitude power switch and a quick coordination button, so that the aircraft attitude system can be comprehensively and comprehensively simulated and trained, and the cost can be reduced while the training effect is ensured by operating a training table and a training control table to cooperate with the simulation training;
The operation training platform with transmit information between the training control platform, the training control platform the trouble sets up the unit, its core component is relay integrated circuit, and relay integrated circuit is under the main control computer drive, and control simulation real dress power supply circuit, sensor circuit, transmission line, amplifier circuit, control box circuit, relay box circuit and indicator circuit, relay integrated circuit adopts circuit breaking, short circuit and cluster income resistance, simulation branch road resistance change etc. methods, realizes that power supply failure, combination top trouble, magnetic sensor trouble, transmission line trouble, amplifier trouble, control box trouble, relay box trouble etc. 176 typical frequently send out the scene simulation of trouble such as gesture separation part and gesture system are passed through to the relay integrated circuit, and the simulation content is extensive, and training effect is good moreover, can carry out repeated training many times, satisfies the demand of gesture system teaching of colleges and universities.
Drawings
FIG. 1 is a schematic view of the structure of the operation training table of the present invention;
FIG. 2 is a schematic diagram of the structure of the training console of the present invention;
FIG. 3 is a circuit diagram of the present invention;
FIG. 4 is a drive circuit diagram of the relay board of the present invention;
Fig. 5 is a circuit diagram of an inventive power supply system.
Detailed Description
For a better understanding of the present invention, the following examples are set forth to further illustrate the invention, but are not to be construed as limiting the invention. In the following description, numerous specific details are set forth in order to provide a more thorough understanding of the present invention. It will be apparent, however, to one skilled in the art that the invention may be practiced without one or more of these details.
Example 1
As shown in fig. 1-3, an aircraft attitude equipment simulation training system comprises an operation training platform and a training control console, wherein the operation training platform comprises a simulation real-world installation and a simulation cabin panel, the simulation real-world installation comprises a full-attitude combined gyroscope, a magnetic heading sensor, a comprehensive amplifier, a magnetic heading correction calculator, a control box 3, a relay box, a heading position indicator 2 and a horizon indicator 1, and the simulation cabin panel comprises an attitude power switch 4 and a quick coordination button 5; the training control console comprises a main control computer 6, a fault setting unit and a power supply system, wherein the main control computer is connected with the control box, the main control computer is connected with the relay box through the fault setting unit, and the power supply system supplies power for the training control console and the operation training console.
The magnetic heading sensor, the magnetic heading correction calculator and the heading position indicator 2 are sequentially connected, the full-attitude combined gyroscope, the comprehensive amplifier and the heading position indicator 2 are sequentially connected, the control box and the relay box are connected with the full-attitude combined gyroscope, and the relay box and the full-attitude combined gyroscope are connected with the horizon indicator 1.
The navigation attitude power switch controls the on-off of the simulated real power supply, and the quick coordination button controls the connection of the simulated real circuit.
The course indicator and the horizon indicator are arranged on the operation training table in parallel, the course and horizon are displayed respectively, the observation of an operator is facilitated, the control box is a navigation gesture control box and is used for adjusting navigation gestures, and the control box is arranged below the course indicator and is convenient to operate.
According to the simulation training system for the airplane navigation attitude equipment, provided by the embodiment of the invention, through the cross-linking simulation control of the operation training table and the training control table, the functions of performance detection training, calibration and power-on method training, typical fault simulation, fault removal training and the like of the airplane navigation attitude system are realized, and the requirements of developing navigation attitude system teaching in institutions are met.
Example two
As shown in fig. 1-3, an aircraft attitude equipment simulation training system comprises an operation training platform and a training control console, wherein the operation training platform comprises a simulation real-world installation and a simulation cabin panel, the simulation real-world installation comprises a full-attitude combined gyroscope, a magnetic heading sensor, a comprehensive amplifier, a magnetic heading correction calculator, a control box 3, a relay box, a heading position indicator 2 and a horizon indicator 1, and the simulation cabin panel comprises an attitude power switch 4 and a quick coordination button 5; the training control console comprises a main control computer 6, a fault setting unit and a power supply system, wherein the main control computer is connected with the control box, the main control computer is connected with the relay box through the fault setting unit, and the power supply system supplies power for the training control console and the operation training console.
The magnetic heading sensor, the magnetic heading correction calculator and the heading position indicator 2 are sequentially connected, the full-attitude combined gyroscope, the comprehensive amplifier and the heading position indicator 2 are sequentially connected, the control box and the relay box are connected with the full-attitude combined gyroscope, and the relay box and the full-attitude combined gyroscope are connected with the horizon indicator 1.
The navigation attitude power switch controls the on-off of the simulated real power supply, and the quick coordination button controls the connection of the simulated real circuit.
The simulation training system for the airplane navigation posture equipment provided by the embodiment of the invention is different from the first embodiment in that: the fault setting unit comprises a relay board card and a component access control interface, and the main control computer, the relay board card, the component access control interface and the relay box are sequentially connected.
The relay board card is controlled by a PCL-722 board card based on a PCI backboard bus and installed in the main control computer.
In the embodiment of the invention, the core component of the fault setting unit is a relay board card, the relay board card is driven by a main control computer to control a power supply circuit, a sensor circuit, a transmission line, an amplifier circuit, a control box circuit, a relay box circuit and an indicator circuit which are installed in a simulation mode, the relay board card adopts methods of open circuit, short circuit, series-in resistance, simulated branch resistance change and the like to realize on-site simulation of 176 typical frequent faults such as power supply faults, combined gyro faults, magnetic sensor faults, transmission line faults, amplifier faults, control box faults, relay box faults, indicator faults and the like of a navigation attitude separation component and a navigation attitude system, has wide simulation content and good training effect, and can perform repeated training for a plurality of times.
The fault setting unit realizes the disconnection, short circuit and resistor series connection of the cross-linking circuit of each component of the avionic device through the switching and control of the relay, thereby simulating the fault of the avionic system. The relay board card is controlled by a PCL-722 board card based on a PCI backboard bus arranged in a main control computer, wherein the PCL-722 is a full-length PCI board card and is provided with a programmable digital I/O port with 144 paths divided into six main ports (CN 0-CN 5). Each port emulates the operation of mode O of one 8255 programmable peripheral interface, but is capable of providing higher drive capability than 8255. Each port consists of three 8-bit sub-ports (a, B, C), which are all TTL-compatible parallel interfaces, providing a tri-state buffer function as input and a data latch function as output, which can be set by software as input or output ports, respectively. The drive circuit of the relay board is shown in fig. 4.
The working principle of the driving circuit is as follows: the main control computer sends the control logic to the input end of the photoelectric isolator through the I/O output port of the PCL-722 board card to drive the luminous tube, the output end of the luminous tube outputs the level logic corresponding to the input end, and the luminous tube passes through the Darlington reverse phase driver ULN2803A with an open collector to directly drive the relay. When the output data of the PCL-722 board card is 0, the optocoupler is turned on, the output indicator lamp is on, and the relay is operated; when the output data is 1, the optocoupler is not conducted, the output indicator lamp is turned off, and the relay board card does not work.
Example III
The simulation training system for the airplane navigation posture equipment provided by the embodiment of the invention is different from the first embodiment and the second embodiment in that: the power supply system comprises a power supply monitor 7 and a power supply converter, wherein 36V/400Hz three-phase alternating current and 27V direct current supply power to the simulation real-package and the fault setting unit through the power supply monitor 7 and the power supply converter.
The 36V/400Hz three-phase alternating current and the 27V direct current are directly supplied to the simulation real installation through the power supply monitoring, and the 27V direct current is converted into the fault setting unit through the power supply monitoring and the power supply to provide secondary power supplies of +5V and +12V.
In the embodiment of the invention, the power supply system mainly provides power for the simulated real installation of the operation training platform and the fault setting unit of the training control platform, wherein 36V/400Hz three-phase alternating current and 27V direct current are provided for the simulated real installation, and +5V and +12V secondary power is provided for the fault setting unit. The internal relationship diagram is shown in fig. 5.
Example IV
As shown in fig. 1-3, an aircraft attitude equipment simulation training system comprises an operation training platform and a training control console, wherein the operation training platform comprises a simulation real-world installation and a simulation cabin panel, the simulation real-world installation comprises a full-attitude combined gyroscope, a magnetic heading sensor, a comprehensive amplifier, a magnetic heading correction calculator, a control box 3, a relay box, a heading position indicator 2 and a horizon indicator 1, and the simulation cabin panel comprises an attitude power switch 4 and a quick coordination button 5; the training control console comprises a main control computer 6, a fault setting unit and a power supply system, wherein the main control computer is connected with the control box, the main control computer is connected with the relay box through the fault setting unit, and the power supply system supplies power for the training control console and the operation training console.
The magnetic heading sensor, the magnetic heading correction calculator and the heading position indicator 2 are sequentially connected, the full-attitude combined gyroscope, the comprehensive amplifier and the heading position indicator 2 are sequentially connected, the control box and the relay box are connected with the full-attitude combined gyroscope, and the relay box and the full-attitude combined gyroscope are connected with the horizon indicator 1.
The fault setting unit comprises a relay board card and a component access control interface, and the main control computer, the relay board card, the component access control interface and the relay box are sequentially connected.
The relay board card is controlled by a PCL-722 board card based on a PCI backboard bus and installed in the main control computer.
The navigation attitude power switch controls the on-off of the simulated real power supply, and the quick coordination button controls the connection of the simulated real circuit.
The power supply system comprises power supply monitoring and power supply conversion, wherein 36V/400Hz three-phase alternating current and 27V direct current supply power to the simulation real-package and the fault setting unit through the power supply monitoring 7 and the power supply conversion.
The 36V/400Hz three-phase alternating current and the 27V direct current are directly supplied to the simulation real installation through the power supply monitoring, and the 27V direct current is converted into the fault setting unit through the power supply monitoring and the power supply to provide secondary power supplies of +5V and +12V.
The simulation training system for the airplane navigation posture equipment provided by the embodiment of the invention is different from the first, second and third embodiments in that: the main control computer 6 controls the power supply circuit, the signal transmission circuit, the synchronous follow-up system circuit, the input and output circuit of the amplifier and the power supply and control circuit of the relay box which are installed in an analog manner through an RS232 bus.
The main control computer is a control center for simulation training of the attitude and heading system, performs operations such as system start control, fault setting, training subject selection and the like, selects a Huihua 610H industrial control computer, internally installs a PCL-722 digital I/O card, is matched with a mouse, a keyboard, a large-visual angle liquid crystal display and the like, and controls simulation real installation through software so as to simulate the functions of the attitude and heading system.
In the embodiment of the invention, the main control computer of the training control console controls the power supply circuit, the signal transmission circuit, the synchronous follow-up system circuit, the input and output circuit of the amplifier, the power supply and the control circuit of the relay box of the analog component through the RS232 bus, simulates and creates the same working environment as the airborne attitude system, and ensures that the use and operation of the training object are more lifelike.
Finally, it is noted that the above-mentioned embodiments are merely for illustrating the technical solution of the present invention, and that other modifications and equivalents thereof by those skilled in the art should be included in the scope of the claims of the present invention without departing from the spirit and scope of the technical solution of the present invention.
Claims (5)
1. An aircraft avionics simulation training system, which is characterized in that: the operation training platform comprises a simulation real installation and a simulation cabin panel, wherein the simulation real installation comprises a full-attitude combined gyroscope, a magnetic heading sensor, a comprehensive amplifier, a magnetic heading correction calculator, a control box, a relay box, a heading position indicator and a horizon indicator, and the simulation cabin panel comprises a navigation attitude power switch and a quick coordination button; the training console comprises a main control computer, a fault setting unit and a power supply system, wherein the main control computer is connected with the control box, the main control computer is connected with the relay box through the fault setting unit, and the power supply system supplies power for the training console and the operation training console;
The magnetic heading sensor, the magnetic heading correction calculator and the heading position indicator are sequentially connected, the full-attitude combined gyroscope, the comprehensive amplifier and the heading position indicator are sequentially connected, the control box and the relay box are both connected with the full-attitude combined gyroscope, and the relay box and the full-attitude combined gyroscope are both connected with the horizon indicator; the navigation attitude power switch controls the on-off of the simulated real power supply, and the quick coordination button controls the connection of the simulated real circuit;
the course position indicator and the horizon indicator are arranged on the operation training table in parallel and respectively display the course and horizon, the control box is a navigation gesture control box and is used for adjusting the navigation gesture, and the control box is arranged below the course position indicator;
The fault setting unit comprises a relay board card and a component access control interface, and the main control computer, the relay board card, the component access control interface and the relay box are connected in sequence; the relay board card is driven by a main control computer to control a power supply circuit, a sensor circuit, a transmission line, an amplifier circuit, a control box circuit, a relay box circuit and an indicator circuit which are simulated to be mounted, and the relay board card adopts a method of breaking, short-circuiting and serial-in resistance and simulating branch resistance change to realize the field simulation of power supply faults, combined gyro faults, magnetic sensor faults, transmission line faults, amplifier faults, control box faults, relay box faults and indicator faults of the attitude and heading reference system.
2. An aircraft avionics simulation training system as claimed in claim 1, characterized in that: the power supply system comprises power supply monitoring and power supply conversion, wherein 36V/400Hz three-phase alternating current and 27V direct current supply power to the simulation real-package and the fault setting unit through the power supply monitoring and the power supply conversion.
3. An aircraft avionics simulation training system as claimed in claim 2, characterized in that: the 36V/400Hz three-phase alternating current and the 27V direct current are directly supplied to the simulation real installation through the power supply monitoring, and the 27V direct current is converted into the fault setting unit through the power supply monitoring and the power supply to provide secondary power supplies of +5V and +12V.
4. An aircraft avionics simulation training system as claimed in claim 1, characterized in that: the relay board card is controlled by a PCL-722 board card based on a PCI backboard bus and installed in the main control computer.
5. An aircraft avionics simulation training system as claimed in claim 1, characterized in that: the main control computer controls the power supply circuit, the signal transmission circuit, the synchronous follow-up system circuit, the input and output circuit of the amplifier and the power supply and control circuit of the relay box which are installed in an analog mode through an RS232 bus.
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| CN201910420641.5A CN110060541B (en) | 2019-05-20 | 2019-05-20 | Simulation training system for airplane navigation posture equipment |
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| CN201910420641.5A CN110060541B (en) | 2019-05-20 | 2019-05-20 | Simulation training system for airplane navigation posture equipment |
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| CN110060541B true CN110060541B (en) | 2024-04-26 |
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| CN110444070A (en) * | 2019-08-05 | 2019-11-12 | 中国人民解放军陆军工程大学 | Simulated maintenance training device for antiaircraft gun equipment |
| CN112634696B (en) * | 2020-12-21 | 2023-01-31 | 贝壳技术有限公司 | Fault positioning exercise method and device, electronic equipment and storage medium |
| CN114550561A (en) * | 2022-03-04 | 2022-05-27 | 石思群 | Electronic components analog circuit training synthesizes demonstration platform |
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