CN113470476B - Dynamic simulation training operation table of airplane control system and application method - Google Patents
Dynamic simulation training operation table of airplane control system and application method Download PDFInfo
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- CN113470476B CN113470476B CN202110964750.0A CN202110964750A CN113470476B CN 113470476 B CN113470476 B CN 113470476B CN 202110964750 A CN202110964750 A CN 202110964750A CN 113470476 B CN113470476 B CN 113470476B
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- 238000012549 training Methods 0.000 title claims abstract description 49
- 238000005094 computer simulation Methods 0.000 title claims abstract description 12
- 238000000034 method Methods 0.000 title claims abstract description 12
- 238000004088 simulation Methods 0.000 claims abstract description 28
- 239000002184 metal Substances 0.000 claims description 12
- 230000006870 function Effects 0.000 claims description 7
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- 230000002159 abnormal effect Effects 0.000 claims description 3
- 230000005540 biological transmission Effects 0.000 claims description 3
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- 238000012360 testing method Methods 0.000 claims description 3
- 238000013024 troubleshooting Methods 0.000 claims description 3
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- 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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Abstract
The invention belongs to the technical field of aircraft assembly and manufacturing, and particularly relates to a dynamic simulation training operation platform of an aircraft control system and a use method thereof. The operation platform comprises an electrical system, a fault simulation system, a pneumatic execution system, a conduit laying system and a cable laying system. The operation platform integrates the professions of machinery, electricity, automatic control, airplane assembly debugging and the like into a whole, and the dynamic simulation training operation platform of the airplane operation system has the advantages of high automation degree, full coverage of professional skills, wide application range, strong pertinence to the improvement of new staff skills, short period and high quality. The new staff can quickly understand and master the operation process and the working principle of the airplane operation system through operating the equipment and the airplane action picture in the touch screen, so that the theory and practice are quickly promoted.
Description
Technical Field
The invention belongs to the technical field of aircraft assembly and manufacture, and relates to a platform which can be used for displaying the detailed working principle of an aircraft control system for staff and realizing the improvement and exercise of necessary basic skills of an operator in the aircraft manufacturing process by using a dynamic simulation training operation platform of the aircraft control system in the process of installing and debugging the aircraft control system.
Background
In the process of aircraft assembly and debugging, not only can installation of thousands of finished products, cables, pipes and parts of components be involved, but also accurate debugging of all movable components and related technical parameters of an operating system is involved, but because of the precision and complexity of the finished products and the parts of the components of the aircraft, operators need to have certain operation skills to finish the related assembly and debugging work, so that the method is an important work for new staff how to quickly improve the training quality of the new staff and shorten the training period.
The conventional training mode at present is to intensively carry out the explanation of necessary airplane working principles, safety operation specifications and relevant post skill knowledge on staff entering a factory, and then distribute the staff to each working post according to skill worker distribution standards. However, the skill foundation of the new staff is very weak, and the new staff is temporarily not provided with independent operation capability, so that each new staff is required to be provided with a master for teaching, and the master is firstly taught and operated, however, the new staff can only watch at one side and can carry out basic practical operation exercise under the guidance of the master after basically understanding the new staff, and the production period of each procedure is certain, so that the learning time and the exercise opportunity of the new staff are not long, and once the work completed by the new staff is unqualified, the new staff needs to be reworked, so that the production period is prolonged, the training difficulty is increased and other problems exist for carrying out skill training on the handles of the new staff by using an actual airplane.
In view of the above reasons, the invention provides the dynamic simulation training operation platform of the aircraft control system, which integrates the basic requirements of dynamic demonstration of the aircraft control system, laying of aircraft ducts, basic requirements of laying of aircraft cables, fault simulation of the aircraft electrical system and other basic training skills, and can reduce training cost, improve training quality and shorten training period.
Disclosure of Invention
Aiming at the problems, the invention provides a dynamic simulation training operation platform of an airplane control system.
The technical scheme of the invention is as follows:
The utility model provides an aircraft control system developments simulation and reality standard operation panel which characterized in that, this aircraft control system developments simulation and reality standard operation panel includes: an electrical system, a fault simulation system, a pneumatic execution system, a conduit laying system and a cable laying system;
Further, the electrical system consists of a state indication module 1, a logic control module 2, a touch screen operation module 3, a relay logic control module 4, a key operation module 5, a fault simulation module 6, a power supply control device 7, a direct current power supply module 8 and a cable 25;
the state indicating module 1 is composed of a DC24V indicating lamp and is used for indicating the working state of each movable part of each operating system, the state indicating module 1 is fixed to the designated position of the operating platform 14 through a screw, and then the state indicating module 1 is electrically connected with the relay logic control module 4 and the direct current power supply module 8 through a cable 25;
the logic control module 2 is composed of a small single chip microcomputer and comprises an input part and an output part, the logic control module 2 is fixed on the operation desk 14 through a screw, the logic control module 2 is connected with the key operation module 5 through a cable 25, and the logic control module 2 transmits switching value signals acquired from the key operation module 5 to the relay logic control module 4 through the cable 25 after calculation;
the touch screen control module 3 is fixed at a designated position of the operation desk 14 through a screw, and the on-off state of the input and output of the logic control module 2 is displayed in real time;
The relay logic control module 4 is fixed at a designated position of the operating platform 14 through a screw and is connected with the logic control module 2 and the pneumatic electromagnetic valve 17 through a cable 25, and the relay logic control module 4 transmits an output signal of the logic control module 2 to the pneumatic electromagnetic valve 17 to drive the pneumatic electromagnetic valve 17 to work;
The key control module 5 simulates each control system in the aircraft cabin by installing a support arm by itself and fixing the support arm at a designated position of the operation table 14 by a screw, and transmits signals of the control system to an input part of the logic control module 2 in a form of switching value;
The fault simulation module 6 is a switch with an on-off function, is fixed at a designated position of the operation table 14 through a screw, and is used for connecting and disconnecting a cable 25 of a certain manipulation function system through the fault simulation module 6 so as to artificially simulate a fault;
the power supply control device 7 is fixed at a designated position of the operating table 14 through a screw, and the power supply control device 7 supplies power to all electrical systems of the whole training equipment through a cable 25;
The direct current power supply module 8 is fixed at a designated position of the operation desk 14 through a screw, converts AC220V into DC24, and then supplies power to the logic state indicating module 1, the logic control module 2, the touch screen operating module 3, the relay logic control module 4 and the pneumatic electromagnetic valve 17 through a cable 25;
Further, the fault simulation system consists of a state indication module 1 and a fault simulation module 6, and the fault simulation system cuts off the conductivity of the cable of the control system through the on-off of the switch so as to simulate the line fault on the aircraft;
Further, the pneumatic execution system consists of an adapter 15, an air source device 16, a pneumatic electromagnetic valve 17, a plastic conduit 18, a pneumatic busbar 19, a plug 20, a regulating valve 21, a direct pushing cylinder 22, a lever cylinder 23 and a rotary cylinder 24, and the pneumatic execution system simulates the working state of control surfaces of all control systems on an aircraft;
the adapter 15 is fixed at the designated position of the operating platform 14 by a screw through a self-carrying support arm, and the adapter 15 connects the metal conduit 9 with the plastic conduit 18 to realize air source transmission;
The air source device 16 is a power source of the whole equipment;
The pneumatic electromagnetic valve 17 is fixed at a designated position of the pneumatic busbar 19 through a screw, and after receiving a signal of a corresponding branch of the relay logic control module 4, the pneumatic electromagnetic valve 17 is connected with or disconnected from an air source of the branch;
The plastic conduit 18 and the metal conduit 9 are used for transmitting an air source for the pneumatic electromagnetic valve 17;
the pneumatic busbar 19 respectively conveys the air source of the air source device 16 to the pneumatic solenoid valves 17 of the systems;
the plug 20 plugs redundant air holes of the pneumatic busbar 19;
The regulating valve 21 is arranged on the air inlet and exhaust holes of the direct pushing cylinder 22, the lever cylinder 23 and the rotating cylinder 24, regulates the flow of an air source and controls the action speed of the cylinders;
the straight pushing cylinder 22, the lever cylinder 23 and the rotating cylinder 24 simulate the working state of each movable part on the aircraft;
Further, the catheter laying system consists of a metal catheter 9, a catheter positioning clamp 10, a straight-through connector 11, a three-way connector 12, a four-way connector 13, an operation table 14 and a fixing screw 26; the conduit laying system simulates the technical requirement of the installation of a hydraulic system conduit on an aircraft and provides a practical training platform for basic skills which are necessary for the installation of the conduit;
the metal conduit 9 transmits the air source of the pneumatic electromagnetic valve 17 to the corresponding direct pushing air cylinder 22, lever air cylinder 23 and rotary air cylinder 24 through the direct connection 11, the three-way connection 12 and the four-way connection 13 to simulate the working state of each operation movable part on the aircraft;
The catheter positioning clamp 10 secures all the metallic catheters 9 on the device to the designated positions of the console 14;
the straight joint 11, the three-way joint 12 and the four-way joint 13 divide an air source in the metal conduit into a plurality of branches;
the console 14 provides a body mounting structure for all components;
The catheter positioning clamp 10 and the clamp 27 are fixed by the fixing screw 26;
Further, the cable laying system consists of a cable 25, a clamp 27 and a quick-release plug 28;
Cables 25 connect the individual electrical modules;
a clamp 27 secures the cable 25 in a prescribed position of the device;
A quick release plug 28 connects the cables 25.
The application method of the dynamic simulation training operation platform of the aircraft control system comprises the following steps:
(1) Preparing necessary tools and instruments for practical training, and then picking up parts and standard parts to be sent to an operation table surface of a practical training table.
(2) According to the technical drawing laid by the duct, the duct is correctly installed according to the requirement, the gap between the duct and the surrounding structure, the gap between the finished product and the movable piece are adjusted, and the duct joint is subjected to necessary insurance.
(3) According to the technical drawing of cable laying, correctly installing the cable according to the requirement, adjusting the clearance between the cable and surrounding structures, moving parts, finished products and the guide pipes, and carrying out necessary insurance on the cable plug.
(4) The training platform is powered ON by AC220V power, then a total power switch ON an operation panel is turned ON, at the moment, an AC220V power indicator HL1 of an equipment indication area is lightened to indicate normal power supply, at the moment, a power switch of a touch screen and a programmable controller is turned ON, at the moment, indicator HL2 and HL3 in the equipment indication area are lightened to prove that all equipment is powered ON normally.
(5) The power switch of the air pump is placed in the "ON" position, and then the compressed air switch is pulled over the "ON" position.
(6) At this time, whether all the connecting pipelines have air leakage phenomenon is checked, if so, the compressed air switch is required to be turned to the closed position, and then the fastening is performed until no air leakage exists.
(7) The manual automatic switch is placed at a manual position on the operation panel, the long-distance switch is placed at a short-distance position, then the operation buttons on the practical training platform of the airplane operation system are shifted one by one, whether the actions of the dynamic indication, the indication lamp state indication area and the execution cylinder on the touch screen are consistent or not is observed, if the indication is abnormal, the cable connection is proved to have faults, and relevant measurement equipment is required to be used for removing.
(8) The manual automatic switch is firstly placed at an 'automatic' position on the operation panel, the long-distance switch is placed at a 'remote' position, then an automatic control button on a practical training platform of the airplane control system is pressed, at the moment, all the status indicator lamps and dynamic indication on the touch screen are synchronous, if the status indicator lamps and the dynamic indication on the touch screen are not synchronous, the fault of the line connection is indicated, and the fault is eliminated by using related measuring equipment.
(9) If all the functions of the operation training platform are checked, the equipment can be subjected to fault simulation through the buttons of the fault simulation area, so that the troubleshooting capability of staff is further enhanced.
(10) When all the tests are finished, the power supply switch of the equipment is required to be turned off, and then all the cables and the guide pipes are detached and placed in a designated area so as to be convenient for subsequent training.
The invention has the beneficial effects that:
1. the dynamic simulation training operation table for the aircraft control system integrates the professions of machinery, electricity, automatic control, aircraft assembly and debugging and the like, and is high in automation degree, full in coverage of professional skills, wide in application range, high in pertinence to improvement of new staff skills, short in period and high in quality.
2. As the invention sets the guide pipe and cable installation training projects, compared with the prior practical airplane training, the invention shortens the training period of new staff, reduces the training cost by tens of times, and most importantly strictly ensures the lead time and quality of the airplane.
3. The invention discloses a fault simulation module, which can simulate the line fault of an airplane by changing the state of a fault switch in a fault simulation area, thereby improving the graph recognition, fault analysis and fault rejection capability of staff, and comprehensively mastering the use methods of various meters and the measurement methods of fault points by the staff.
4. The invention provides the dynamic simulation module of the airplane control system, so that new staff can quickly understand and master the control process and the working principle of the airplane control system through operating the device and the airplane action picture in the touch screen, thereby achieving the quick promotion of theory and practice.
Drawings
FIG. 1 is a schematic diagram of a dynamic simulation training console for an aircraft control system
In the figure: 1 state indicating module, 2 logic control module, 3 touch screen operating module, 4 relay logic control module, 5 key operation, 6 fault simulation module, 7 power supply control device, 8 direct current power supply module, 9 metal guide pipe, 10 guide pipe locating clamp, 11 direct connection joint, 12 three-way joint, 13 four-way joint, 14 operation platform, 15 conversion joint, 16 air source device, 17 pneumatic electromagnetic valve, 18 plastic guide pipe, 19 pneumatic bus bar, 20 screw plug, 21 regulating valve, 22 direct pushing cylinder, 23 lever cylinder, 24 rotating cylinder, 25 cable, 26 fixing screw, 27 clamp, 28 quick-release plug
Detailed Description
The specific implementation mode and the steps of the invention are as follows:
1. Preparing necessary tools and instruments for practical training, and then picking up parts and standard parts to be sent to an operation table surface of a practical training table.
2. According to the technical drawing laid by the duct, the duct is correctly installed according to the requirement, the gap between the duct and the surrounding structure, the gap between the finished product and the movable piece are adjusted, and the duct joint is subjected to necessary insurance.
3. According to the technical drawing of cable laying, correctly installing the cable according to the requirement, adjusting the clearance between the cable and surrounding structures, moving parts, finished products and the guide pipes, and carrying out necessary insurance on the cable plug.
4. The training platform is powered ON by AC220V power, then a total power switch ON an operation panel is turned ON, at the moment, an AC220V power indicator HL1 of an equipment indication area is lightened to indicate normal power supply, at the moment, a power switch of a touch screen and a programmable controller is turned ON, at the moment, indicator HL2 and HL3 in the equipment indication area are lightened to prove that all equipment is powered ON normally.
5. The power switch of the air pump is placed in the "ON" position, and then the compressed air switch is pulled over the "ON" position.
6. At this time, whether all the connecting pipelines have air leakage phenomenon is checked, if so, the compressed air switch is required to be turned to the closed position, and then the fastening is performed until no air leakage exists.
7. The manual automatic switch is placed at a manual position on the operation panel, the long-distance switch is placed at a short-distance position, then the operation buttons on the practical training platform of the airplane operation system are shifted one by one, whether the actions of the dynamic indication, the indication lamp state indication area and the execution cylinder on the touch screen are consistent or not is observed, if the indication is abnormal, the cable connection is proved to have faults, and relevant measurement equipment is required to be used for removing.
8. The manual automatic switch is firstly placed at an 'automatic' position on the operation panel, the long-distance switch is placed at a 'remote' position, then an automatic control button on a practical training platform of the airplane control system is pressed, at the moment, all the status indicator lamps and dynamic indication on the touch screen are synchronous, if the status indicator lamps and the dynamic indication on the touch screen are not synchronous, the fault of the line connection is indicated, and the fault is eliminated by using related measuring equipment.
9. If all the functions of the operation training platform are checked, the equipment can be subjected to fault simulation through the buttons of the fault simulation area, so that the troubleshooting capability of staff is further enhanced.
10. When all the tests are finished, the power supply switch of the equipment is required to be turned off, and then all the cables and the guide pipes are detached and placed in a designated area so as to be convenient for subsequent training.
Claims (2)
1. The utility model provides an aircraft control system developments simulation and reality standard operation panel which characterized in that, this aircraft control system developments simulation and reality standard operation panel includes: an electrical system, a fault simulation system, a pneumatic execution system, a conduit laying system and a cable laying system;
The electric system consists of a state indicating module (1), a logic control module (2), a touch screen operating module (3), a relay logic control module (4), a key operating module (5), a fault simulation module (6), a power supply control device (7), a direct current power supply module (8) and a cable (25);
The state indicating module (1) is composed of a DC24V indicating lamp and is used for indicating the working state of each movable part of each operating system, the state indicating module (1) is fixed to the appointed position of the operating platform (14) through a screw, and then the state indicating module (1) is electrically connected with the relay logic control module (4) and the direct current power supply module (8) through a cable (25);
The logic control module (2) is composed of a small single chip microcomputer and comprises an input part and an output part, the logic control module (2) is fixed on the operation table (14) through a screw, the logic control module (2) is connected with the key control module (5) through a cable (25), and the logic control module (2) calculates a switching value signal acquired from the key control module (5) and transmits the switching value signal to the relay logic control module (4) through the cable (25);
The touch screen control module (3) is fixed at a designated position of the operating platform (14) through a screw, and the input and output switching value states of the logic control module (2) are displayed in real time;
The relay logic control module (4) is fixed at a designated position of the operating platform (14) through a screw and is connected with the logic control module (2) and the pneumatic electromagnetic valve (17) through a cable (25), and the relay logic control module (4) transmits an output signal of the logic control module (2) to the pneumatic electromagnetic valve (17) to drive the pneumatic electromagnetic valve (17) to work;
The key control module (5) is fixed at the appointed position of the operation desk (14) through a self-contained mounting support arm by a screw, simulates each control system in the aircraft cabin, and transmits signals of the control system to the input part of the logic control module (2) in a switching value mode;
The fault simulation module (6) is a switch with an on-off function, is fixed at a designated position of the operation table (14) through a screw, and is used for connecting and disconnecting a cable (25) of a certain manipulation function system through the fault simulation module (6), so that a fault is simulated artificially;
The power supply control device (7) is fixed at a designated position of the operating platform (14) through a screw, and the power supply control device (7) supplies power to all electrical systems of the whole training equipment through a cable (25);
The direct current power supply module (8) is fixed at a designated position of the operating platform (14) through a screw, converts AC220V into DC24, and then supplies power to the logic state indicating module (1), the logic control module (2), the touch screen operating module (3), the relay logic control module (4) and the pneumatic electromagnetic valve (17) through a cable (25);
the fault simulation system consists of a state indication module (1) and a fault simulation module (6), and cuts off the conductivity of a cable of the control system through the on-off of a switch so as to simulate line faults on an airplane;
The pneumatic execution system consists of an adapter (15), an air source device (16), a pneumatic electromagnetic valve (17), a plastic conduit (18), a pneumatic busbar (19), a plug (20), a regulating valve (21), a direct pushing cylinder (22), a lever cylinder (23) and a rotary cylinder (24), and the pneumatic execution system simulates the working state of control surfaces of all control systems on an aircraft;
The adapter (15) is fixed at the appointed position of the operating platform (14) by a screw through the self-carrying support arm, and the adapter (15) connects the metal conduit (9) with the plastic conduit (18) to realize air source transmission;
the air source device (16) is a power source of the whole equipment;
The pneumatic electromagnetic valve (17) is fixed at a designated position of the pneumatic busbar (19) through a screw, and after receiving a signal of a corresponding branch of the relay logic control module (4), the pneumatic electromagnetic valve (17) is connected with or disconnected from an air source of the branch;
The plastic conduit (18) and the metal conduit (9) are used together as a pneumatic electromagnetic valve (17) transmission air source;
the pneumatic busbar (19) respectively transmits air sources of the air source device (16) to pneumatic electromagnetic valves (17) of all systems;
The plug (20) plugs redundant air holes of the pneumatic busbar (19);
The regulating valve (21) is arranged on the air inlet and exhaust holes of the direct pushing cylinder (22), the lever cylinder (23) and the rotary cylinder (24), regulates the flow of an air source and controls the action speed of the cylinder;
The direct pushing cylinder (22), the lever cylinder (23) and the rotating cylinder (24) simulate the working state of each movable part on the aircraft;
The catheter laying system consists of a metal catheter (9), a catheter positioning clamp (10), a straight-through connector (11), a three-way connector (12), a four-way connector (13), an operating table (14) and a fixing screw (26); the conduit laying system simulates the technical requirement of the installation of a hydraulic system conduit on an aircraft and provides a practical training platform for basic skills which are necessary for the installation of the conduit;
The metal conduit (9) transmits the air source of the pneumatic electromagnetic valve (17) to the corresponding direct pushing cylinder (22), lever cylinder (23) and rotary cylinder (24) through the direct connection (11), the three-way connection (12) and the four-way connection (13), and simulates the working state of each operation movable part on the aircraft;
a catheter positioning clamp (10) fixes all metal catheters (9) on the equipment to a designated position of an operation table (14);
the straight-through connector (11), the three-way connector (12) and the four-way connector (13) divide an air source in the metal conduit into a plurality of branches;
The console (14) provides a body mounting structure for all components;
the catheter positioning clamp (10) and the clamp (27) are fixed through the fixing screw (26);
the cable laying system consists of a cable (25), a clamp (27) and a quick-release plug (28);
a cable (25) connecting the individual electrical modules;
a clamp (27) secures the cable (25) in a prescribed position of the device;
A quick release plug (28) connects the cables (25).
2. The method of using a dynamic simulation training console of an aircraft manipulation system of claim 1, comprising the steps of:
(1) Preparing a tool and an instrument which are necessary for practical training, and then picking up parts and standard parts and sending the parts and standard parts to an operation table top of a practical training table;
(2) According to the technical drawing laid by the guide pipe, the guide pipe is correctly installed according to the requirement, the gap between the guide pipe and the surrounding structure, the gap between the finished product and the movable piece are adjusted, and the guide pipe joint is ensured;
(3) According to the technical drawing of cable laying, correctly installing the cable according to the requirement, adjusting the gaps between the cable and surrounding structures, movable parts, finished products and the guide pipes, and ensuring the cable plug;
(4) Switching ON an AC220V power supply of the training platform, then switching ON a total power switch ON an operation panel to an ON position, turning ON an AC220V power supply indicator lamp HL1 of an equipment indication area, indicating that power supply is normal, switching ON a power switch of a touch screen and a programmable controller to an ON position, turning ON indicator lamps HL2 and HL3 in the equipment indication area, and proving that all equipment is normally powered;
(5) Placing a power switch of the air pump at an ON position, and then pulling the compressed air switch to an ON position;
(6) At the moment, checking whether all the connecting pipelines have air leakage phenomenon, if so, turning the compressed air switch to the closed position, and fastening until no air leakage exists;
(7) Firstly, placing a manual automatic switch at a manual position on an operation panel, placing a long-distance switch at a short-distance position, then stirring operation buttons on an airplane operation system practical training platform one by one, observing whether the actions of a dynamic indication area, an indication lamp state indication area and an execution cylinder on a touch screen are consistent or not, and if the indication is abnormal, indicating that the cable connection has faults and needing to be removed by using related measurement equipment;
(8) Firstly, placing a manual automatic switch at an 'automatic' position on an operation panel, placing a long-distance switch at a 'remote' position, then pressing an automatic control button on a practical training platform of an airplane control system, synchronously performing all state indicator lamps and dynamic indication on a touch screen, and if the state indicator lamps and the dynamic indication on the touch screen are not synchronously performed, indicating that the line connection has a fault, and removing the fault by using related measuring equipment;
(9) If all the functions of the operation training platform are checked, performing fault simulation on the equipment through a button of a fault simulation area, and further enhancing the troubleshooting capability of staff;
(10) When all the tests are finished, the power supply switch of the equipment is required to be turned off, and then all the cables and the guide pipes are detached and placed in a designated area so as to be convenient for subsequent training.
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| CN215730341U (en) * | 2021-08-20 | 2022-02-01 | 沈阳飞机工业（集团）有限公司 | Dynamic simulation training operating platform of airplane control system |
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| US8794969B2 (en) * | 2011-06-09 | 2014-08-05 | Alaska Airlines, Inc. | Aircraft pneumatics training aid and methods |
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| US20150379884A1 (en) * | 2013-02-05 | 2015-12-31 | One-G, Llc | Aircraft simulator |
| CN103473966A (en) * | 2013-08-29 | 2013-12-25 | 南京航空航天大学 | Semi-physical digital simulation control platform of aircraft cockpit |
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| CN211928790U (en) * | 2019-10-25 | 2020-11-13 | 中国飞行试验研究院 | Aviation aircraft outside service special professional training platform |
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| CN215730341U (en) * | 2021-08-20 | 2022-02-01 | 沈阳飞机工业（集团）有限公司 | Dynamic simulation training operating platform of airplane control system |
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| CN113470476A (en) | 2021-10-01 |
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