A simulated aircraft flight training cockpit

Abstract

This application discloses a simulated aircraft flight training cockpit, comprising: a cockpit body; an instrument panel equipped with instruments, electrical switches, and lights; a control console equipped with landing gear control components, an engine switch, an air conditioning switch, an oil injector, a throttle component, an elevator adjustment component, and a flap control component; a seat disposed on the inner floor of the cockpit body; a control stick; foot pedals; and an operation instruction unit for generating instructions for operating or viewing various devices within the cockpit body. By incorporating instruments, electrical switches, lights, landing gear control components, an engine switch, an air conditioning switch, an oil injector, a throttle component, an elevator adjustment component, a flap control component, a seat, a control stick, and foot pedals within the cockpit body, this application highly replicates the actual layout of an aircraft cockpit, enabling pilots to train in a highly realistic cockpit and significantly improving training quality.

Description

Technical Field

[0001] This application relates to the field of aircraft simulation training equipment technology, and in particular to a simulated aircraft flight simulation training cockpit. Background Technology

[0002] Simulation training is an essential process for pilots before their official flights. Through simulation training, pilots can gradually become familiar with and understand how to fly an aircraft, eventually reaching a level where they can fly a real aircraft independently.

[0003] Currently, flight simulation mainly falls into two categories: training through virtual scenarios and virtual operating platforms, and training through virtual scenarios and real operating platforms. While the former has the advantage of low cost, it cannot provide pilots with a realistic operating environment, whereas the latter effectively overcomes this shortcoming. Pilots can deepen their operational memory through highly simulated operating platforms, thus laying a solid foundation for improving their piloting skills.

[0004] However, most current simulation operating platforms are simply simulations of real cockpits, only simulating the main instruments and equipment such as joysticks and instruments. The degree of restoration of the real cockpit is not high, which greatly reduces the training effect. Summary of the Invention

[0005] This application provides a simulated aircraft flight training cockpit to solve the problem of low fidelity in the reproduction of cockpits in the prior art.

[0006] On one hand, embodiments of this application provide a simulated aircraft flight simulation training cockpit, including:

[0007] cockpit main body;

[0008] The instrument panel is located on the inner bottom surface of the main body of the cockpit, and it is equipped with instruments, electrical switches and lights;

[0009] The control panel is located on the inner bottom surface of the main cockpit. The control panel is equipped with landing gear control components, engine switch, air conditioning switch, oil injector, throttle components, elevator adjustment components and flap control components.

[0010] The seats are located on the inner floor of the main cabin body;

[0011] The control stick is located on the inner bottom surface of the cockpit main body;

[0012] Foot pedals are located on the inner bottom surface of the main body of the cockpit;

[0013] The operation instruction unit is located inside the cockpit body. The operation instruction unit is used to generate indication information for operating or viewing instruments, electrical switches, lights, landing gear control components, engine switches, air conditioning switches, lubricators, throttle components, elevator adjustment components, flap control components, control sticks, and pedals.

[0014] The simulated aircraft flight training cockpit described in this application has the following advantages:

[0015] By installing instruments, electrical switches, lights, landing gear control components, engine switches, air conditioning switches, oil injectors, throttle components, elevator adjustment components, flap control components, seats, control sticks, and foot pedals inside the main cockpit, the layout of the aircraft cockpit is greatly replicated, allowing pilots to train in a highly realistic cockpit and significantly improving training quality. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 A schematic diagram of the external structure of a simulated aircraft flight simulation training cockpit provided for an embodiment of this application;

[0018] Figure 2 A schematic diagram of the structure of the dashboard provided in the embodiments of this application;

[0019] Figure 3 This is a schematic diagram of the structure of the left control panel provided in an embodiment of this application;

[0020] Figure 4 This is a schematic diagram of the structure of the right control panel provided in an embodiment of this application;

[0021] Figure 5 This is a structural schematic diagram of the cockpit door provided in an embodiment of this application;

[0022] Figure 6 This is a schematic diagram of the landing gear control assembly provided in an embodiment of this application;

[0023] Figure 7 This is a schematic diagram of the structure of the engine switch provided in an embodiment of this application;

[0024] Figure 8 This is a schematic diagram of the structure of the oil injector provided in the embodiments of this application;

[0025] Figure 9 This is a schematic diagram of the elevator adjustment assembly provided in an embodiment of this application;

[0026] Figure 10 This is a schematic diagram of the flap control assembly provided in an embodiment of this application.

[0027] Explanation of reference numerals: 100 - Cockpit main body, 200 - Instrument panel, 300 - Left control panel, 310 - Right control panel, 400 - Door panel, 410 - Rotation mechanism, 420 - Locking mechanism, 430 - Seat, 440 - Cushion, 500 - Landing gear control housing, 510 - Landing gear control handle, 520 - Landing gear control synchronizer pulley, 530 - Landing gear control sensor, 600 - Engine control panel, 610 - Engine control damper, 620 - Engine control sensor, 630 - Engine control pointer 700-Lubricator control lever, 710-Lubricator control frame, 720-Lubricator control limit lever, 730-Lubricator control sensor, 740-Lubricator rebound unit, 800-Elevator adjustment disc, 810-Elevator adjustment damper, 820-Intermediate transmission assembly, 821-Elevator adjustment limit lever, 830-Elevator adjustment sensor, 840-Elevator adjustment limit block, 900-Flap control housing, 910-Flap control lever, 920-Flap control timing pulley, 930-Flap control sensor. Detailed Implementation

[0028] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0029] Figure 1-10 This is a structural schematic diagram of a simulated aircraft flight simulator training cockpit provided in an embodiment of this application. This embodiment of the application provides a simulated aircraft flight simulator training cockpit, including:

[0030] The main body of the cockpit is 100.

[0031] The instrument panel 200 is located on the inner bottom surface of the cockpit body 100, and the instrument panel 200 is equipped with instruments, electrical switches and lights;

[0032] The control panel is located on the inner bottom surface of the cockpit body 100. The control panel is equipped with landing gear control components, engine switch, air conditioning switch, oil injector, throttle components, elevator adjustment components and flap control components.

[0033] Seat 430 is installed on the inner bottom surface of the main body of the cabin 100;

[0034] The control stick is located on the inner bottom surface of the cockpit body 100;

[0035] Foot pedals are located on the inner bottom surface of the main body of the cockpit 100;

[0036] The operation instruction unit is located inside the cockpit body 100. The operation instruction unit is used to generate instruction information for operating or viewing instruments, electrical switches, lights, landing gear control components, engine switches, air conditioning switches, lubricators, throttle components, elevator adjustment components, flap control components, control sticks and pedals.

[0037] For example, the cockpit body 100 can be installed in a venue capable of simulating flight scenarios, such as in conjunction with display devices like projectors or screens, to simulate flight scenarios through virtual images. Alternatively, a multi-degree-of-freedom moving mechanism can be used to connect the cockpit body 100 to the ground or other fixed objects, allowing the cockpit body 100 to simulate the activity states in real driving scenarios through multi-degree-of-freedom movement.

[0038] In the embodiments of this application, the cockpit body 100 includes a main frame and a skin disposed on the outer side of the main frame. Specifically, the main frame can be formed by welding galvanized steel pipes and angle steel, while the skin can be formed by processing galvanized sheet. After processing, the skin can be fixed to the main frame by riveting.

[0039] The dashboard can be first machined from cold-rolled steel to the required shape, and then laser-cut to create openings for mounting instruments, electrical switches, and lights. The control panel can also be machined from cold-rolled steel to the required shape, and then laser-cut to create openings for mounting various instruments and equipment.

[0040] In the embodiments of this application, the control panel includes a left control panel 300 and a right control panel 310, which are respectively installed on the left and right sides of the inner bottom surface of the cockpit body 100. The landing gear control assembly, engine switch, air conditioning switch, oil injector, throttle assembly, elevator adjustment assembly, flap control assembly and other instruments and equipment can be arranged on the corresponding control panel according to the layout of a real aircraft cockpit.

[0041] Furthermore, a vibration unit is installed on the inner bottom surface of the cockpit body 100, which is used to simulate the vibration when the aircraft engine starts.

[0042] The instruments on Instrument Panel 200 include an altimeter, airspeed indicator, rate of climb / deceleration indicator, horizon indicator, turn sideslip indicator, gyrocompass, hydrocompass, radio compass, voltmeter-ammeter, tachometer, intake pressure gauge, fuel gauge, engine multimeter, cylinder head temperature gauge, air pressure gauge, angle of attack indicator, and aviation clock. These instruments are arranged on Instrument Panel 200 according to the layout of a real aircraft cockpit. Furthermore, the electrical switches and lights on Instrument Panel 200 are also based on real aircraft components and are located in the same positions as in a real cockpit.

[0043] Furthermore, the indicator lights include cabin indicator lights and external lighting lights. The cabin indicator lights include a neutral position indicator light for the adjustment plate, a generator fault indicator light, a left fuel tank remaining 10 liters indicator light, a right fuel tank remaining 10 liters indicator light, and a landing gear indicator light. The external lighting lights include a cockpit light, a left fluorescent light, and a right fluorescent light.

[0044] With the aforementioned training cockpit layout, the training cockpit will have the same layout as the real cockpit, resulting in multiple devices that need to be operated or viewed. For inexperienced pilots, although they have learned the theoretical knowledge before training, they cannot accurately and quickly apply this knowledge in the training cockpit during actual operation, leading to their inability to operate or view the correct devices according to the correct steps. To solve this problem, this application sets up an operation instruction unit inside the cockpit body 100. This operation instruction unit can issue instruction information to each corresponding device in the correct sequence. After reviewing the instruction information, the pilot can react quickly. After repeated prompts, the pilot can memorize the location and function of each device in the training cockpit, achieving the effect of assisting the pilot to quickly get started.

[0045] Specifically, the operation instruction unit can employ various display devices, such as displays or projectors. If a display screen is used, mounting holes need to be provided near each device, and the screen is then installed in the corresponding mounting holes. Under the control of the central controller, each display screen can sequentially display instruction information for each device. When a projector is used, it can be placed on the top surface of the cockpit body 100, ensuring that the projector's projection range covers all devices. When displaying instruction information, the projector controls the projection content according to the location of each device, so that the instruction information corresponding to each device is projected near the corresponding device. Regardless of the form of the operation instruction unit used, when the pilot needs to operate or view a device, it can display instruction information such as "Please operate (view) xxx here," while displaying instruction information such as "Please operate (view) xxx on the right (left, front, below)" for other devices, enabling the pilot to accurately and quickly locate the device that needs to be operated or viewed.

[0046] In one possible embodiment, the cockpit body 100 has an opening on one side, and a door panel 400 is hinged to the opening. When the door panel 400 is closed, it contacts the seat 430.

[0047] For example, the door panel 400 can be hinged to the opening of the cabin body via at least one rotating mechanism 410, and the size and shape of the door panel 400 need to match the opening so that the opening can be completely closed when the door panel 400 is closed. The rotating mechanism 410 can be a pin or a hinge, etc.

[0048] In the embodiments of this application, a locking mechanism 420 may also be provided on the inner side of the door panel 400, that is, on the side edge near the seat 430. The locking mechanism 420 may be a pin, and the pin may be provided with an elastic element so that the pin rod can automatically spring back after being pulled out, so that it can automatically be inserted into the socket provided on the edge of the cockpit body 100.

[0049] Furthermore, a cushion 440 is provided on the side of the door panel 400 facing the seat 430. Both the cushion 440 and the seat 430 can be covered with a leather surface, which can be made of imitation leather or genuine leather, to improve the pilot's comfort. When the door panel 400 is closed, the cushion 440 is positioned above the seat 430, allowing the pilot to lean against the cushion 440 when seated in the seat 430, greatly improving the pilot's comfort during training.

[0050] In one possible embodiment, the landing gear control assembly includes: a landing gear control housing 500; a landing gear control handle 510 rotatably mounted on the landing gear control housing 500; and a landing gear control sensor 530 kinetically connected to the landing gear control handle 510, the landing gear control sensor 530 being used to detect the rotation angle of the landing gear control handle 510.

[0051] For example, the landing gear control housing 500 is a hollow box with openings at both ends. One end of the landing gear control handle 510 is inserted into the landing gear control housing 500 and is rotatably connected to the inside of the landing gear control housing 500 via a pivot. The other end of the landing gear control handle 510 is outside the landing gear control housing 500 and is provided with a ball for easy operation at its end. A landing gear control timing pulley 520 is mounted on the outer surface of the landing gear control housing 500, on the shaft that rotates the landing gear control handle 510. This timing pulley 520 rotates coaxially with the shaft. A landing gear control driven pulley is also rotatably mounted on the outer surface of the landing gear control housing 500. This driven pulley is connected to the landing gear control timing pulley 520 via a gear drive or belt drive. The landing gear control sensor 530 is connected to the landing gear control timing pulley 520, rotating with the driven pulley to detect the rotation angle of the landing gear control handle 510. Once the rotation angle data is detected, the landing gear control sensor 530 transmits the data to the simulation software via UDP (User Datagram Protocol) communication.

[0052] In embodiments of this application, a nose landing gear indicator stick may also be provided on the top front side of the cockpit body 100. The nose landing gear indicator stick is movably connected to the cockpit body 100 via an electric push rod, which operates under the control of simulation software to push the nose landing gear indicator stick to move back and forth, thereby showing the pilot the nose landing gear status.

[0053] In one possible embodiment, the engine switch includes: an engine control panel 600; an engine control damper 610 rotatably connected to the engine control panel 600, the engine control damper 610 being used to provide resistance to rotation of the engine control panel 600; and an engine control sensor 620 connected to the engine control panel 600, the engine control sensor 620 being used to detect the rotation angle of the engine control panel 600.

[0054] For example, the engine switch is a fish-scale switch, and its specific installation position and shape are the same as those of the engine switch on a real aircraft. The engine control panel 600 is coaxially fixedly connected to the rotating shaft, which passes through the engine control damper 610 and is connected to the engine control sensor 620. Therefore, the engine control sensor 620 can detect the rotation angle of the engine control panel 600, and the detected rotation angle will be transmitted to the simulation software via UDP communication.

[0055] The engine control damper 610 can provide rotational damping for the engine control panel 600, simulating the rotational feel of a real engine switch while preventing accidental operation of the engine control panel 600.

[0056] In the embodiments of this application, an engine control pointer 630 can be fixedly connected to a rotating shaft. At the same time, a scale matching the engine control pointer 630 can be set at the position where the engine switch is installed on the control panel. When the engine control pointer 630 rotates synchronously with the rotating shaft, the real-time rotation angle of the engine control pointer 630 can be known in real time through the scale.

[0057] In one possible embodiment, the lubricator includes: a lubricator control lever 700; a lubricator control frame 710, on which the lubricator control lever 700 is slidably inserted along the axial direction; a lubricator control sensor 730, connected to the lubricator control lever 700, for detecting the displacement of the lubricator control lever 700; and a lubricator rebound unit 740, disposed at the end of the lubricator control lever 700, for providing a spring force to the lubricator control lever 700 after it has been pressed.

[0058] For example, the end of the fuel injector control lever 700 may be provided with a handle for easy operation, while the fuel injector rebound unit 740 includes a rebound rod and an elastic element. The rebound rod may be fixedly mounted on the control panel, and its end is coaxially slidably connected to the end of the fuel injector control lever 700, so that the fuel injector 700 can move axially along the fuel injector control lever 700 when pressed by the pilot. The elastic element may be disposed between the end of the rebound rod and the end of the fuel injector control lever 700. When the fuel injector control lever 700 is pressed down, the elastic element will be compressed to provide a rebound elastic force to the fuel injector control lever 700.

[0059] The lubricator control frame 710 can be fixedly installed on the control table and slidably connected to the lubricator control lever 700. A lubricator limiting rod 720 can be provided on the outer surface of the lubricator control lever 700. When the lubricator control lever 700 moves to the lowest position, the lubricator limiting rod 720 will contact the lubricator control frame 710, thereby limiting the displacement of the lubricator control lever 700.

[0060] In the embodiments of this application, the injector control sensor 730 may include a conductive rod and two conductive probes. The conductive rod may be disposed on the side of the injector control lever 700, while the two conductive probes need to be fixedly disposed on the injector control frame 710. When the injector control lever 700 moves to the lowest position, the conductive rod also contacts the two conductive probes, thereby connecting the two conductive probes. The connection signal will be transmitted to the simulation software via UDP communication.

[0061] In one possible embodiment, the elevator adjustment assembly includes: an elevator adjustment disc 800; an elevator adjustment damper 810 connected to the elevator adjustment disc 800, the elevator adjustment damper 810 being used to provide resistance when the elevator adjustment disc 800 rotates; and an elevator adjustment sensor 830 drivenly connected to the elevator adjustment disc 800, the elevator adjustment sensor 830 being used to detect the rotation angle of the elevator adjustment disc 800.

[0062] For example, the elevator adjustment plate 800 is coaxially connected to the rotating shaft, and the end of the rotating shaft is connected to the elevator adjustment damper 810. The elevator adjustment damper 810 provides rotational damping to the elevator adjustment plate 800, which simulates the rotational feel of a real elevator adjustment component while preventing the elevator adjustment plate 800 from being accidentally operated.

[0063] In the embodiments of this application, a first drive wheel can be provided on the rotating shaft, and an intermediate transmission assembly 820 parallel to and rotatable on the rotating shaft is provided inside the control panel. The intermediate transmission assembly 820 is preferably a rod-shaped structure, on which a first driven wheel and a second drive wheel are provided. The first driven wheel and the first drive wheel can be connected by gear transmission or belt transmission so that the rotating shaft drives the intermediate transmission assembly 820 to rotate. At the same time, an end drive rod parallel to the intermediate transmission assembly 820 can also be provided inside the control panel. A second driven wheel can be provided on the end drive rod, and the second driven wheel is connected to the second drive wheel by gear transmission or belt transmission. The elevator adjustment sensor 830 is connected to the end of the end drive rod. After the rotational speed of the elevator adjustment disk 800 is reduced by the first drive wheel, the first driven wheel, the second drive wheel and the second driven wheel, the elevator adjustment sensor 830 can detect the rotation angle of the elevator adjustment disk 800 at a certain ratio. The detected rotation angle will also be transmitted to the simulation software via UDP communication.

[0064] Furthermore, an elevator adjustment limit rod 821 can be provided at the end of the intermediate transmission assembly 820, and an elevator adjustment limit block 840 can be fixedly provided within the rotation range of the elevator adjustment limit rod 821 on the control panel. When the elevator adjustment limit rod 821 rotates together with the intermediate transmission assembly 820, after rotating to a certain angle, the elevator adjustment limit block 840 will contact the elevator adjustment limit rod 821 and limit the rotation of the elevator adjustment limit rod 821, thereby limiting the rotation angle of the elevator adjustment disc 800.

[0065] In one possible embodiment, the flap control assembly includes: a flap control housing 900; a flap control lever 910 rotatably mounted on the flap control housing 900; and a flap control sensor 930 tractively connected to the flap control lever 910, the flap control sensor 930 being used to detect the rotation angle of the flap control lever 910.

[0066] For example, the flap control housing 900 is a hollow box with openings at both ends. One end of the flap control lever 910 is inserted into the flap control housing 900 and rotatably connected inside the flap control housing 900 via a pivot. The other end of the flap control lever 910 is outside the flap control housing 900 and has a ball for easy operation at its end. A flap control synchronous wheel 920 is provided on the outer surface of the flap control housing 900, which rotates coaxially with the pivot. A flap actuation driven wheel is also rotatably provided on the outer surface of the flap control housing 900. The flap actuation driven wheel is connected to the flap control synchronous wheel 920, which can be driven by gears or belts. The flap control sensor 930 is connected to the flap control synchronous wheel 920, so that the flap control sensor 930 rotates with the flap actuation driven wheel, thereby detecting the rotation angle of the flap control lever 910. Once the rotation angle data is detected, the flap control sensor 930 will transmit the data to the simulation software via UDP communication.

[0067] Although preferred embodiments of this application have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this application.

[0068] Obviously, those skilled in the art can make various modifications and variations to this application without departing from the spirit and scope of this application. Therefore, if such modifications and variations fall within the scope of the claims of this application and their equivalents, this application also intends to include such modifications and variations.

Claims

1. A simulated aircraft flight training cockpit, characterized in that, include: Main body of the cockpit (100); An instrument panel (200) is provided on the inner bottom surface of the cockpit body (100), and the instrument panel (200) is provided with instruments, electrical switches and lighting; The control panel is located on the inner bottom surface of the main body of the cockpit (100). The control panel is equipped with landing gear control components, engine switch, air conditioning switch, oil injector, throttle assembly, elevator adjustment assembly and flap control assembly. Seat (430) is disposed on the inner bottom surface of the main body of the cabin (100); The control stick is located on the inner bottom surface of the cockpit body (100); Foot pedals are located on the inner bottom surface of the main body of the cockpit (100); An operation instruction unit is located inside the cockpit body (100). The operation instruction unit is used to generate instruction information for operating or viewing the instruments, electrical switches, lights, landing gear control components, engine switches, air conditioning switches, lubricators, throttle components, elevator adjustment components, flap control components, control sticks, and pedals. The operation instruction unit issues instruction information to each corresponding device in the correct sequence. The operation instruction unit uses a display screen or a projector. When using a display screen, mounting holes are provided near each device, and the display screen is installed in the corresponding mounting holes. Under the control of the central controller, each display screen displays instruction information for each device in sequence. When using a projector, the projector is placed on the top surface of the cockpit body (100) to ensure that the projection range of the projector can cover all devices. When displaying instruction information, the projector controls the projection content according to the position of each device so that the instruction information corresponding to each device is projected near the corresponding device.

2. The simulated aircraft flight training cockpit according to claim 1, characterized in that, The cockpit body (100) includes a main frame and a skin disposed on the outer side of the main frame.

3. The simulated aircraft flight training cockpit according to claim 2, characterized in that, A vibration unit is provided on the inner bottom surface of the cockpit body (100), which is used to simulate the vibration when the aircraft engine starts.

4. The simulated aircraft flight training cockpit according to claim 1, characterized in that, The instruments installed on the instrument panel (200) include an altimeter, airspeed indicator, rate of climb / deceleration indicator, horizon indicator, turn sideslip indicator, gyromagnetic compass, water compass, radio compass, volt-ampere meter, tachometer, intake pressure gauge, fuel gauge, engine multimeter, cylinder head temperature gauge, air pressure gauge, angle of attack indicator, and aviation clock.

5. The simulated aircraft flight training cockpit according to claim 1, characterized in that, The cockpit body (100) has an opening on one side, and a door panel (400) is hinged to the opening. When the door panel (400) is closed, it contacts the seat (430).

6. The simulated aircraft flight training cockpit according to claim 1, characterized in that, The landing gear control assembly includes: Landing gear control housing (500); The landing gear control handle (510) is rotatably mounted on the landing gear control housing (500); A landing gear control sensor (530) is connected to the landing gear control handle (510) and is used to detect the rotation angle of the landing gear control handle (510).

7. The simulated aircraft flight training cockpit according to claim 1, characterized in that, The engine switch includes: Engine control panel (600); An engine control damper (610) is rotatably connected to the engine control disc (600), and the engine control damper (610) is used to provide resistance to rotation to the engine control disc (600); An engine control sensor (620) is connected to the engine control panel (600) and is used to detect the rotation angle of the engine control panel (600).

8. The simulated aircraft flight training cockpit according to claim 1, characterized in that, The oil injector includes: Lubricator control lever (700); The injector control frame (710) is axially slidably inserted into the injector control frame (710); The injector control sensor (730) is connected to the injector control lever (700), and the injector control sensor (730) is used to detect the displacement of the injector control lever (700); The injector rebound unit (740) is disposed at the end of the injector control lever (700), and the injector rebound unit (740) is used to provide the injector control lever (700) with a spring force after being pressed.

9. A simulated aircraft flight training cockpit according to claim 1, characterized in that, The elevator adjustment assembly includes: Elevator adjustment plate (800); An elevator adjustment damper (810) is connected to the elevator adjustment plate (800), and the elevator adjustment damper (810) is used to provide resistance when the elevator adjustment plate (800) rotates; An elevator adjustment sensor (830) is connected to the elevator adjustment disk (800) for transmission. The elevator adjustment sensor (830) is used to detect the rotation angle of the elevator adjustment disk (800).

10. A simulated aircraft flight training cockpit according to claim 1, characterized in that, The flap control assembly includes: Flap control housing (900); The flap control lever (910) is rotatably mounted on the flap control housing (900); A flap control sensor (930) is connected to the flap control lever (910) and is used to detect the rotation angle of the flap control lever (910).

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