CN219162861U - Aircraft front panel analogue means - Google Patents

Abstract

The utility model discloses an aircraft front panel simulation device which comprises a main warning lamp module, an emergency brake handle, a status lamp module, a resistance umbrella switch module, an air pressure altimeter adjusting knob module and a digital clock module, wherein the main warning lamp module is arranged at the left upper position of a front panel, the emergency brake handle is arranged at the left side of the main warning lamp module in parallel, the status lamp module is arranged at the right upper position of the front panel, the resistance umbrella switch module is arranged at the left side of the front panel, and the air pressure altimeter adjusting knob module and the digital clock module are arranged at the right side of the front panel. The utility model utilizes the electronic circuit structure to design the main alarm lamp module, the emergency brake handle, the status lamp module, the drag parachute switch module, the air pressure altimeter adjusting knob module and the digital clock module on the front panel of the personal computer type, simplifies the operation parts of the physical structure of the personal computer on the basis of simulating the display and operation functions of the modules, provides the use experience basically indiscriminate with the operation of the personal computer for a user, and reduces the manufacturing cost of the device.

Description

Aircraft front panel analogue means

Technical Field

The utility model relates to flight simulation equipment, in particular to an aircraft front panel simulation device which is mainly used for front panel simulation of a owl dragon model.

Background

With the rapid development of civil aviation industry in China, the opening of airspace in China and the relaxation of personal flight driving license, various flight experience devices and flight simulators become interesting, and model simulation is gradually expanded from civil models to fighter models. The Xiaolong model is one of the disclosed classical models, and can provide a simulation operation basis for pilot training and flight lovers to know and experience fighter operations.

The existing flight simulator is mainly in a flight simulation software form, various operation panels are basically in a virtual key mode of a touch screen, experience is poor for users, and the mode of using real machine equipment experience is high in cost and not suitable for wide use; on the other hand, there is no flight simulation device on the market that is specific to the owl fighter model. Therefore, there is a need in the art to design a flight simulation device with excellent operational experience and low cost, and the design of the present utility model is mainly used for front panel simulation of the koilon model.

Disclosure of Invention

Aiming at the problems existing in the prior art, the utility model provides the aircraft front panel simulation device mainly used for the owl dragon model, the front panel simulation of the owl dragon model is realized through the low-cost structural design, and the training of pilots and the experiencing of fighter operations by flight lovers are facilitated.

In order to achieve the above purpose, the technical scheme adopted by the utility model is as follows:

the utility model provides an aircraft front panel analogue means, includes the main alarm lamp module that lays in the upper left position of front panel, sets up in the emergent brake handle of main alarm lamp module left side position side by side, lays in the status light module of upper right position of front panel, lays in the drag parachute switch module of front panel left side position to and lay in the atmospheric pressure altimeter adjust knob module and the digital clock module of front panel right side position, main alarm lamp module, emergent brake handle, status light module, drag parachute switch module, atmospheric pressure altimeter adjust knob module and digital clock module all are connected through contact pin interface and are supplied power and data transmission with external controller.

Specifically, the main alarm lamp module comprises a main alarm upper cover and a main alarm back cover which are mutually buckled and connected, a main alarm lamp cover arranged on the front upper position of the main alarm upper cover, a fire alarm lamp cover and a flight control alarm lamp cover which are arranged on the front lower position of the main alarm upper cover and are arranged side by side, a main alarm circuit board arranged in a cavity formed by the main alarm upper cover and the main alarm back cover, a main alarm LED lamp arranged on the main alarm circuit board and corresponding to the position of the main alarm lamp cover, a fire alarm LED lamp arranged on the main alarm circuit board and corresponding to the position of the fire alarm lamp cover, a flight control alarm LED lamp arranged on the main alarm circuit board and corresponding to the position of the flight control alarm lamp cover, and a main alarm pin interface arranged on the main alarm circuit board and used for connecting an external controller, wherein the main alarm LED lamp, the fire alarm LED lamp and the flight control LED lamp are electrically connected with the main alarm pin interface, and the main alarm pin interface is connected with an external cable through a notch arranged on the main alarm back cover.

Specifically, emergent brake handle includes the emergency brake base, swing joint emergency brake handle head on the emergency brake base, and the emergency brake button switch of setting up in the emergency brake base and with the emergency brake handle head matching to and dispose on the emergency brake base and with the emergency brake contact pin interface of emergency brake button switch electricity connection, wherein the emergency brake contact pin interface is used for the electricity to connect external controller.

Specifically, the status light module comprises a status upper cover and a status back cover which are mutually buckled and connected, a plurality of status lampshades which are regularly arranged on the front surface of the status upper cover and used for indicating the status information of the airplane, a status circuit board which is arranged in a cavity formed by the status upper cover and the status back cover, status LED lamps which are arranged on the status circuit board and correspond to each status lampshades one to one, and a status contact pin interface which is arranged on the status circuit board and used for being electrically connected with an external controller, wherein the status circuit board is provided with a status indication circuit, and the status contact pin interface is electrically connected with each status LED lamp through the status indication circuit and is connected with a cable outside a notch arranged on the status back cover.

Specifically, the status LED lamp includes a PITCH TRM lamp, a ROLL TRIM lamp, a YAW TRIM lamp, an a/a lamp, an a/G1 lamp, an a/G2 lamp, an EFCS lamp, a No3 TANK lamp, a No1 TANK lamp, a WING D/T lamp, a CTR D/T lamp, a START lamp, an AB lamp, a COMBAT lamp, an EMG HYD lamp, an NWS lamp, and an advisony lamp.

Specifically, the drag parachute switch module comprises a drag parachute upper cover and a drag parachute back cover which are mutually buckled and connected, a drag parachute circuit board which is arranged in a cavity formed by the drag parachute upper cover and the drag parachute back cover, a drag parachute button switch which is arranged on the drag parachute circuit board and extends out of the front face of the drag parachute upper cover through a mounting hole arranged on the drag parachute upper cover, and a drag parachute contact pin interface which is arranged on the drag parachute circuit board and is used for electrically connecting an external controller, wherein the drag parachute contact pin interface is electrically connected with the drag parachute button switch and is connected with an external wiring cable through a notch arranged on the drag parachute back cover.

Specifically, the air pressure altimeter adjusting knob module comprises an adjusting knob upper cover and an adjusting knob back cover which are mutually buckled and connected, an adjusting knob circuit board arranged in a cavity formed by the adjusting knob upper cover and the adjusting knob back cover, an adjusting rotary encoder arranged on the adjusting knob circuit board and extending out of the front face of the adjusting knob upper cover through a hole arranged on the adjusting knob upper cover, and an adjusting knob contact pin interface arranged on the adjusting knob circuit board and used for being electrically connected with an external controller, wherein the adjusting knob contact pin interface is electrically connected with the adjusting rotary encoder and is connected with a cable outside a notch arranged on the adjusting knob back cover.

The digital clock module comprises a clock upper cover and a clock back cover which are mutually buckled and connected, a clock display area and a clock key area which are arranged on the front surface of the clock upper cover and form hollow holes, a digital clock circuit board which is arranged in a cavity formed by the clock upper cover and the clock back cover, a clock liquid crystal board which is arranged on the digital clock circuit board and matched with the hollow holes of the clock display area, a clock key switch with a lamp and a clock button sub-switch which are arranged on the digital clock circuit board and matched with the clock key area, and a digital clock pin interface which is arranged on the digital clock circuit board and used for being electrically connected with an external controller, wherein a liquid crystal display circuit which is electrically connected with the clock liquid crystal board and a key acquisition circuit which is electrically connected with the clock key switch with the lamp and the clock button sub-switch are arranged on the digital clock circuit board, and an external wiring cable which is arranged on the clock back cover is arranged on the digital clock circuit board.

Compared with the prior art, the utility model has the following beneficial effects:

(1) The utility model utilizes the electronic circuit structure to design the main alarm lamp module, the emergency brake handle, the status lamp module, the drag parachute switch module, the air pressure altimeter adjusting knob module and the digital clock module on the front panel of the Xiaolong model, simplifies the operation components of the physical structure of the real machine on the basis of simulating the display and operation functions of the modules, and can effectively realize the simulation use of the front panel of the Xiaolong model by connecting the contact pin interface with the controller of the flight simulation system, thereby providing the use experience which is basically indiscriminate with the display and operation of the real machine for users and greatly reducing the manufacturing cost of the device. The utility model has the advantages of ingenious design, simple structure, low cost and convenient use, and is suitable for being applied to flight simulation equipment.

(2) According to the utility model, the display and operation devices such as the LED lamp, the toggle switch, the key switch, the rotary encoder, the liquid crystal panel and the like are respectively designed in a targeted manner according to the actual display and operation modes of each module, so that the low cost of the replacement of the electronic device is ensured, and each display, indication and operation function is accurately simulated and realized, thereby reliably realizing the display and operation functions of the front panel of the real machine and improving the immersive experience of a user.

Drawings

Fig. 1 is a schematic layout structure of an embodiment of the present utility model.

Fig. 2 is a schematic view showing an external structure of a main warning lamp module according to an embodiment of the present utility model.

Fig. 3 is a schematic diagram of an exploded structure of an alarm lamp module according to an embodiment of the present utility model.

Fig. 4 is a schematic circuit diagram of an embodiment of the main warning lamp module according to the present utility model.

Fig. 5 is a schematic structural view of an emergency brake handle according to an embodiment of the present utility model.

Fig. 6 is a schematic circuit diagram of an emergency brake handle according to an embodiment of the present utility model.

Fig. 7 is a schematic diagram of an external structure of a status light module according to an embodiment of the utility model.

Fig. 8 is an exploded view of a status light module according to an embodiment of the present utility model.

Fig. 9 is a schematic circuit diagram of a status LED lamp section in an embodiment of the present utility model.

Fig. 10 is a schematic circuit diagram of a status indication circuit according to an embodiment of the present utility model.

FIG. 11 is a schematic circuit diagram of a status pin interface according to an embodiment of the present utility model.

FIG. 12 is a schematic view showing the external structure of a drag parachute opening and closing module according to an embodiment of the present utility model.

FIG. 13 is a schematic view of the structure of a circuit board portion of a drag parachute according to an embodiment of the present utility model.

FIG. 14 is a schematic circuit diagram of a drag parachute switching module in an embodiment of the present utility model.

FIG. 15 is a schematic view showing the external structure of an air pressure altimeter adjusting knob module according to an embodiment of the present utility model.

Fig. 16 is a schematic view of a circuit board portion of an adjusting knob according to an embodiment of the present utility model.

FIG. 17 is a schematic circuit diagram of an air pressure altimeter adjustment knob module according to an embodiment of the present utility model.

Fig. 18 is a schematic diagram showing an external structure of a digital clock module according to an embodiment of the present utility model.

Fig. 19 is a schematic diagram of a digital clock circuit board according to an embodiment of the present utility model.

Fig. 20 is a schematic circuit diagram of a key acquisition circuit according to an embodiment of the present utility model.

Detailed Description

The utility model will now be further described with reference to the accompanying drawings and examples, embodiments of which include, but are not limited to, the following examples.

Examples

As shown in fig. 1 to 20, the aircraft front panel simulation device is mainly used for performing flight simulation operation on a front panel of a owl dragon type, is integrally arranged around a front control panel UFCP and three multi-functional display panels MFDs, and specifically comprises a main warning lamp module 10 arranged at the left upper position of the front panel, an emergency brake handle 20 arranged at the left side of the main warning lamp module side by side, a status lamp module 30 arranged at the right upper position of the front panel, a resistance umbrella switch module 40 arranged at the left side of the front panel, and an air pressure altimeter adjusting knob module 50 and a digital clock module 60 arranged at the right side of the front panel, wherein the main warning lamp module, the emergency brake handle, the status lamp module, the resistance umbrella switch module, the air pressure altimeter adjusting knob module and the digital clock module are all connected with an external controller through a pin interface for power supply and data transmission. The external controller adopts an STM32 development board as a core and can be integrated in the UFCP, so that each function of the flight simulation system can be more stably constructed.

Specifically, the main alarm lamp module 10 includes a main alarm upper cover 101 and a main alarm back cover 102 that are fastened to each other, a main alarm lamp cover 103 disposed on the main alarm upper cover and located on the front side, a fire alarm lamp cover 104 and a flight alarm lamp cover 105 disposed on the main alarm upper cover and located side by side, a main alarm circuit board 106 disposed in a cavity formed by the main alarm upper cover and the main alarm back cover, a main alarm LED lamp 107 disposed on the main alarm circuit board and corresponding to the position of the main alarm lamp cover, a fire alarm LED lamp 108 disposed on the main alarm circuit board and corresponding to the position of the fire alarm lamp cover, a flight alarm LED lamp 109 disposed on the main alarm circuit board and corresponding to the position of the flight alarm lamp cover, and a main alarm pin interface 110 disposed on the main alarm circuit board and used for connecting an external controller, wherein the main alarm LED lamp, the fire alarm LED lamp and the flight alarm LED lamp are electrically connected to the main alarm pin interface, and the main alarm pin interface passes through an external cable 1 wiring gap on the main alarm back cover. Fig. 4 is a schematic circuit diagram of a main alarm lamp module, wherein a main alarm LED lamp is implemented by adopting three LED lamp beads of an LED23, an LED22 and an LED19 in parallel, a fire alarm LED lamp and a flight alarm LED lamp are implemented by adopting one LED lamp bead, an interface LED19, an LED20 and an LED21 are connected with a CN2 main alarm pin interface, and corresponding alarm indication such as primary alarm, fire alarm, flight control fault alarm and the like can be implemented after the interface LED19, the LED20 and the LED21 are connected with an external controller through a cable.

Specifically, the emergency brake handle 20 comprises an emergency brake base 21, an emergency brake handle head 22 movably connected to the emergency brake base, an emergency brake key switch arranged in the emergency brake base and matched with the emergency brake handle head, and an emergency brake pin interface arranged on the emergency brake base and electrically connected with the emergency brake key switch, wherein the emergency brake pin interface is used for electrically connecting an external controller. As shown in fig. 6, a schematic circuit diagram of an emergency brake handle is shown, a device K5 is a sudden brake key switch, an interface K11 is connected with a CN1 sudden brake pin interface and is connected with an external controller through a cable, during emergency brake operation, a sudden brake handle head is pushed and pressed inwards to trigger the sudden brake key switch, and a switch signal is transmitted to the external controller through K11 and CN1 to realize a corresponding emergency brake function.

Specifically, the status light module 30 includes a status upper cover 31 and a status back cover 32 that are fastened to each other, a plurality of status light covers 33 regularly arranged on the front surface of the status upper cover for indicating status information of the aircraft, a status circuit board 34 disposed in a cavity formed by the status upper cover and the status back cover, status LED lights 35 disposed on the status circuit board and corresponding to each status light cover one by one, and status pin interfaces 36 disposed on the status circuit board for electrically connecting to an external controller, wherein the status circuit board is configured with status indication circuits, and the status pin interfaces are electrically connected to each status LED light through the status indication circuits and are connected to cables through notches 1 disposed on the status back cover. Specifically, the status LED lamps include a PITCH TRM lamp (PITCH TRIM neutral position), a ROLL TRIM lamp (lateral TRIM neutral position), a YAW TRIM lamp (heading TRIM neutral position), an a/a lamp (air-to-air configuration), an a/G1 lamp (air-to-ground 1 configuration), an a/G2 lamp (air-to-ground 2 configuration), an EFCS lamp (analog backup on), a No3 TANK lamp (No 1 TANK oil off), a No1 TANK lamp (No 1 TANK oil off), a WING D/T lamp (WING TANK oil off), a CTR D/T lamp (fuselage TANK oil off), a START lamp (generator on), an AB lamp (boost on), a COMBAT lamp (COMBAT mode), an EMG HYD lamp (emergency hydraulic pump on), a NWS lamp (front wheel steering on), and an advisony lamp (strapdown attitude system fault). As shown in fig. 9, which is a schematic circuit diagram of a status LED lamp portion, the devices LED1 to LED18 are 18 status LED lamps, and the interfaces LED1 to LED18 are used for respectively connecting status indication circuits. Fig. 10 is a schematic circuit diagram of a status indication circuit, in which three 8-bit buffer chips with the model number of 74HC595D are adopted as cascade output signals of each status LED lamp, each bit output of the 8-bit buffer chips corresponds to one status LED lamp, interfaces LED 1-LED 18 are respectively connected with 18 status LED lamps, QH' pins of a previous buffer chip are connected with SER pins of a next buffer chip to realize cascade output, and interfaces DATA, RCK, SCK, 595DATA2 are connected with a status pin interface CN21, as shown in fig. 11. The state pin interface CN21 is connected to an external controller through a cable to realize corresponding state indication.

Specifically, the drag parachute opening and closing module 40 includes a drag parachute upper cover 41 and a drag parachute back cover 42 fastened and connected to each other, a drag parachute circuit board 43 disposed in a cavity formed by the drag parachute upper cover and the drag parachute back cover, a drag parachute button switch 44 disposed on the drag parachute circuit board and extending out of the front surface of the drag parachute upper cover through a mounting hole 46 disposed on the drag parachute upper cover, and a drag parachute pin interface 45 disposed on the drag parachute circuit board and used for electrically connecting to an external controller, wherein the drag parachute pin interface is electrically connected with the drag parachute button switch and is connected with an external wiring cable through a notch disposed on the drag parachute back cover. As shown in fig. 14, which is a schematic circuit diagram of a drag parachute switch module, a device K1 is a drag parachute button switch, interfaces K12 and K13 are connected with a CN3 drag parachute contact pin interface and are connected with an external controller through a cable, and an operation signal of the drag parachute button switch is transmitted to the external controller through CN3 to realize drag parachute release. While the backlight can also be configured for the module via the interface VCC I.

Specifically, the air pressure altimeter adjusting knob module 50 includes an adjusting knob upper cover 51 and an adjusting knob back cover 52 which are fastened and connected with each other, an adjusting knob circuit board 53 arranged in a cavity formed by the adjusting knob upper cover and the adjusting knob back cover, an adjusting rotary encoder 54 arranged on the adjusting knob circuit board and extending out of the front surface of the adjusting knob upper cover through a hole 56 arranged on the adjusting knob upper cover, and an adjusting knob pin interface 55 arranged on the adjusting knob circuit board and used for electrically connecting an external controller, wherein the adjusting knob pin interface is electrically connected with the adjusting rotary encoder and is connected with an external cable through a notch arranged on the adjusting knob back cover. As shown in fig. 17, which is a schematic circuit diagram of an air pressure altimeter adjusting knob module, a device CE2 is an adjusting rotary encoder, an EC11 type rotary encoder can be adopted, interfaces K14 and K15 are connected with a K3 adjusting knob pin interface, and are connected with an external controller through a cable, and an operating signal of the adjusting rotary encoder is transmitted to the external controller through the K3 interface to realize adjustment of the air pressure altimeter. While the backlight can also be configured for the module via the interface VCC I.

Specifically, the digital clock module 60 includes a clock upper cover 61 and a clock back cover 62 that are fastened to each other, a clock display area and a clock key area that are disposed on the front surface of the clock upper cover and form hollow holes, a digital clock circuit board 63 disposed in a cavity formed by the clock upper cover and the clock back cover, a clock liquid crystal board 64 disposed on the digital clock circuit board and matching with the hollow holes of the clock display area, a clock switch 65 and a clock switch 66 with a lamp and disposed on the digital clock circuit board and matching with the clock key area, and a digital clock pin interface disposed on the digital clock circuit board and used for electrically connecting with an external controller, wherein a liquid crystal display circuit electrically connected with the clock liquid crystal board and a key acquisition circuit electrically connected with the clock switch with the lamp and the clock switch are disposed on the digital clock circuit board, and the digital clock pin interface is electrically connected with the liquid crystal display circuit and the key acquisition circuit and passes through a notch external connection cable disposed on the clock back cover. The key collection circuit adopts a register chip with the model of 74HC165D, as shown in FIG. 20, interfaces K1-K4 are used for connecting four clock key switches with lamps, and interfaces 165DATA, 165SCK9 and 165SH/LD are used for connecting digital clock pin interfaces. The liquid crystal display circuit can adopt a conventional liquid crystal display circuit, and is not described herein. When the clock is used, UTC time display and local time display can be realized through the clock liquid crystal panel according to signals from an external controller, the clock toggle switch can realize the function switch of the module, and the displayed time can be regulated and calibrated through the clock button switch with the lamp.

When the intelligent aerodrome type front panel is used, the intelligent aerodrome type front panel is required to be matched with other corresponding simulation equipment, and a computer provided with flight simulation software is required to be connected for flight simulation training or experience, especially the intelligent aerodrome type front panel is matched with UFCP and MFD for use, so that simulation display and operation of the aerodrome type front panel are realized together.

The above embodiments are only preferred embodiments of the present utility model, and not intended to limit the scope of the present utility model, but all changes made by adopting the design principle of the present utility model and performing non-creative work on the basis thereof shall fall within the scope of the present utility model.

Claims (8)

1. The utility model provides an aircraft front panel analogue means, its characterized in that, including setting up the main alarm lamp module in the upper left position of front panel, set up the emergent brake handle in main alarm lamp module left side position side by side, lay in the status light module in the upper right position of front panel, lay in the resistance umbrella switch module of front panel left side position to and lay in the air pressure altimeter adjust knob module and the digital clock module of front panel right side position, main alarm lamp module, emergent brake handle, status light module, resistance umbrella switch module, air pressure altimeter adjust knob module and digital clock module all are connected through contact pin interface and external controller and are supplied power and data transmission.

2. The aircraft front panel simulation device according to claim 1, wherein the main alarm lamp module comprises a main alarm upper cover and a main alarm back cover which are mutually buckled and connected, a main alarm lamp cover arranged on the front upper position of the main alarm upper cover, a fire alarm lamp cover and a flight control alarm lamp cover which are arranged on the front lower position of the main alarm upper cover and are arranged side by side, a main alarm circuit board arranged in a cavity formed by the main alarm upper cover and the main alarm back cover, a main alarm LED lamp arranged on the main alarm circuit board and corresponding to the position of the main alarm lamp cover, a flight control alarm LED lamp arranged on the main alarm circuit board and corresponding to the position of the fire alarm lamp cover, and a main alarm pin interface arranged on the main alarm circuit board and used for being connected with an external controller, wherein the main alarm LED lamp, the fire alarm LED lamp and the flight control alarm LED lamp are electrically connected with the main alarm pin interface, and the main alarm pin interface passes through an external cable notch arranged on the main alarm back cover.

3. The aircraft front panel simulation device of claim 1, wherein the emergency brake handle comprises an emergency brake base, an emergency brake handle head movably connected to the emergency brake base, an emergency brake key switch disposed in the emergency brake base and matched with the emergency brake handle head, and an emergency brake pin interface disposed on the emergency brake base and electrically connected to the emergency brake key switch, wherein the emergency brake pin interface is used for electrically connecting an external controller.

4. The aircraft front panel simulation device according to claim 1, wherein the status light module comprises a status upper cover and a status back cover which are fastened and connected with each other, a plurality of status light covers which are regularly arranged on the front surface of the status upper cover and are used for indicating status information of the aircraft, a status circuit board which is arranged in a cavity formed by the status upper cover and the status back cover, status LED lights which are arranged on the status circuit board and are in one-to-one correspondence with each status light cover, and a status pin interface which is arranged on the status circuit board and is used for electrically connecting an external controller, wherein the status circuit board is provided with a status indication circuit, and the status pin interface is electrically connected with each status LED light through the status indication circuit and passes through a notch external wiring cable which is arranged on the status back cover.

5. The aircraft front panel simulation device of claim 4, wherein the status LED lamp comprises a PITCH TRM lamp, a ROLL TRIM lamp, a YAW TRIM lamp, an a/a lamp, an a/G1 lamp, an a/G2 lamp, an EFCS lamp, a No3 TANK lamp, a No1 TANK lamp, a WING D/T lamp, a CTR D/T lamp, a START lamp, an AB lamp, a COMBAT lamp, an EMG HYD lamp, an NWS lamp, and an advisony lamp.

6. The aircraft front panel simulation device according to claim 1, wherein the drag parachute switch module comprises a drag parachute upper cover and a drag parachute back cover which are mutually buckled and connected, a drag parachute circuit board arranged in a cavity formed by the drag parachute upper cover and the drag parachute back cover, a drag parachute button switch arranged on the drag parachute circuit board and extending out of the front face of the drag parachute upper cover through a mounting hole arranged on the drag parachute upper cover, and a drag parachute contact pin interface arranged on the drag parachute circuit board and used for electrically connecting an external controller, wherein the drag parachute contact pin interface is electrically connected with the drag parachute button switch and is connected with an external wiring cable through a notch arranged on the drag parachute back cover.

7. The aircraft front panel simulation device according to claim 1, wherein the barometer adjustment knob module comprises an adjustment knob upper cover and an adjustment knob back cover that are fastened to each other, an adjustment knob circuit board disposed in a cavity formed by the adjustment knob upper cover and the adjustment knob back cover, an adjustment knob encoder disposed on the adjustment knob circuit board and protruding out of a front surface of the adjustment knob upper cover through a hole provided in the adjustment knob upper cover, and an adjustment knob pin interface disposed on the adjustment knob circuit board for electrically connecting to an external controller, wherein the adjustment knob pin interface is electrically connected to the adjustment knob encoder and is connected to a cable outside through a notch provided in the adjustment knob back cover.

8. The aircraft front panel simulation device according to claim 1, wherein the digital clock module comprises a clock upper cover and a clock back cover which are mutually buckled and connected, a clock display area and a clock key area which are arranged on the front surface of the clock upper cover and form hollowed holes, a digital clock circuit board arranged in a cavity formed by the clock upper cover and the clock back cover, a clock liquid crystal board arranged on the digital clock circuit board and matched with the hollowed holes of the clock display area, a clock key switch with a lamp and a clock button switch arranged on the digital clock circuit board and matched with the clock key area, and a digital clock pin interface arranged on the digital clock circuit board and used for being electrically connected with an external controller, wherein a liquid crystal display circuit electrically connected with the clock liquid crystal board and a key acquisition circuit electrically connected with the clock key switch with a lamp are arranged on the digital clock circuit board, and the digital clock pin interface is electrically connected with the liquid crystal display circuit and the key acquisition circuit through a notch external wiring cable arranged on the clock back cover.

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