Aircraft landing gear control panel simulation device

Abstract

The utility model discloses a simulation device for a control panel of an aircraft landing gear. The simulation device comprises a landing gear operation instruction simulation device unit and a landing gear folding and unfolding operation simulation device unit which are arranged side by side and connected through a data line, the undercarriage operation indication simulation device unit is mainly used for indicating testing and locking of aircraft states and operation actions related to the undercarriage, and the undercarriage folding and unfolding operation simulation device unit is mainly used for folding and unfolding the undercarriage. According to the utility model, the electronic circuit structure composed of the switch, the knob and the indicating lamp and the physical structure of the operating rod are utilized to simulate the operation function of the undercarriage control panel on the left console of the trafficker type, thereby simplifying the physical structure operation parts of the real machine. The use experience basically indifferent from real machine display and operation is provided for a user, and the manufacturing cost of the device is reduced.

Description

Technical Field

[0001] The utility model relates to a flight simulation device, in particular to an aircraft landing gear control panel simulation device, which is mainly used for simulating the landing gear control panel on the left control console of a Xiaolong aircraft. Background Art

[0002] The Xiaolong model is one of the classic models that are publicly available. It can provide a simulated operation basis for pilot training and flight enthusiasts to understand and experience fighter operations. Existing flight simulators are mainly in the form of flight simulation software. Its various operation panels basically use virtual buttons on the touch screen, which does not provide a good experience for users. The use of real equipment experience is costly and not suitable for widespread use. On the other hand, there is no flight simulation equipment specifically for Xiaolong fighter models on the market. Therefore, the design of flight simulation equipment with excellent operation experience and low cost is urgently needed in this field. The landing gear control panel is an important part of the aircraft landing gear system. It provides control, monitoring and protection functions for the landing gear to ensure the safe operation of the aircraft on the ground and in flight. The design of this utility model is mainly used for the simulation of the landing gear control panel on the left console of the Xiaolong model. Utility Model Content

[0003] In view of the problems existing in the above-mentioned prior art, the utility model provides an aircraft landing gear control panel simulation device mainly used for the Xiaolong model. Through low-cost structural design, it realizes the simulation of the landing gear control panel on the left control console of the Xiaolong model, which is convenient for pilot training and flight enthusiasts to experience fighter aircraft operation.

[0004] In order to achieve the above purpose, the technical solution adopted by the utility model is as follows:

[0005] A landing gear control panel simulation device for an aircraft comprises a landing gear operation indication simulation device unit and a landing gear retraction and extension operation simulation device unit which are arranged side by side and connected via a data line; the landing gear operation indication simulation device unit comprises an indication rear cover shell in the shape of a flat rectangular box, an indication cover plate which is arranged on the upper end of the indication rear cover shell and is sealed, an indication panel which is attached to the front of the indication cover plate, hollow holes for installing components which are provided on the indication cover plate and the indication panel at designated positions, a test button, a landing gear operation switch and a brightness adjustment knob which are arranged side by side horizontally at the lower position of the front of the indication panel, a landing gear position status light assembly which is arranged on the upper right position of the front of the indication panel, a landing status indicator light assembly which is arranged on the indication panel and the indication cover plate and which clamps the landing gear operation switch An operation limiter is arranged in the indicating rear cover shell for carrying and electrically connecting a test button, a landing gear operating switch, a brightness adjustment knob, a control circuit board of a landing gear position status light assembly and a landing status indicator light assembly, and an interface assembly is arranged on the indicating rear cover shell and electrically connected to the control circuit board, wherein the control circuit board is provided with a signal acquisition circuit, a status light control circuit and a data processing module, the signal acquisition circuit is used to collect input signals of the test button, the landing gear operating switch, the brightness adjustment knob and the landing gear retraction and extension operation simulation device unit and transmit them to the data processing module, the status light control circuit receives the control signal fed back by the data processing module and makes the landing gear position status light assembly and the landing status indicator light assembly light up or go out accordingly, and the interface assembly is used for power supply and signal transmission between the data processing module and the outside.

[0006] Specifically, the test button adopts a touch switch, which is placed on the control circuit board and electrically connected to the signal acquisition circuit. The touch switch is equipped with a key cap for easy key operation, and the key cap is placed in a hollow hole at a corresponding position.

[0007] Specifically, the landing gear operating switch adopts a two-position button switch, which is electrically connected to the signal acquisition circuit, and the lever of the two-position button switch extends out of the front of the indication panel through the hollow holes at the corresponding positions thereof.

[0008] Specifically, the operation limiter includes a limiter ring arranged in a corresponding hollow hole, a limiter base plate connected to the bottom of the limiter ring and fixedly connected to the indicator cover, a hinged connection portion arranged on a lateral side of the limiter ring, and an L-shaped limiter plate whose lateral end is resettably hinged to the hinged connection portion, wherein the limiter plate blocks the position of the lower side of the two-speed button switch of the column.

[0009] Specifically, the brightness adjustment knob adopts a rotary encoder of model EC11, whose rotary rod extends out of the front of the indication panel through a hollow hole at a corresponding position and an adjustment rotary cap is arranged on the rotary rod.

[0010] Specifically, the landing gear position status light assembly includes a pattern layer etched on the upper right position of the front side of the indicator panel and presenting a top-down aircraft shape, landing gear status lights arranged corresponding to the three landing gear positions on the aircraft shape, and a landing gear warning light arranged at the front end of the aircraft shape, wherein the landing gear status light and the landing gear warning light both use LED lamp beads, and are electrically connected to the status light control circuit, and the landing gear status light and the landing gear warning light are both provided with lampshades placed on the hollow holes at the corresponding positions.

[0011] Specifically, the landing status indicator light assembly includes a speed brake indicator light, a parachute indicator light and a wing indicator light which are arranged vertically side by side at the upper left position on the front side of the indicator panel. The speed brake indicator light, the parachute indicator light and the wing indicator light all use LED lamp beads, are electrically connected to the status light control circuit, and are all provided with a cover shell which covers the LED lamp beads and protrudes from the front side of the indicator panel through hollow holes at corresponding positions. The cover shell is also provided with a logo corresponding to each light.

[0012] Specifically, the data processing module uses an STM32 development board as the core, the signal acquisition circuit uses a register chip of model 74HC165 as the core, the status light control circuit uses a buffer chip of model 74HC595 as the core, and the interface component uses a USB interface or a Type-C interface.

[0013] Specifically, the landing gear retraction and extension operation simulation device unit includes an operation rear cover shell in the shape of a rectangular box, an operation cover arranged at the upper end of the operation rear cover shell and provided with an operation port, an operation fixing frame fixedly arranged in the operation rear cover shell through the operation port, an operation circuit board arranged at the lower part of the operation fixing frame, an operation interface and an operation servo arranged on the operation circuit board, an operation movable frame arranged in the operation fixing frame and connected to the rotating head of the operation servo, and an operation handle fixedly arranged on the operation movable frame and extending from the front side of the operation cover through the operation port, wherein the operation circuit board is electrically connected to the signal acquisition circuit of the control circuit board through the operation interface.

[0014] Specifically, the operating servo adopts a potentiometer.

[0015] Compared with the prior art, the utility model has the following beneficial effects:

[0016] (1) The utility model utilizes the electronic circuit structure composed of switches, knobs and indicator lights and the physical structure of the operating lever to simulate the operating functions of the landing gear control panel of the Xiaolong model, thereby simplifying the operating components of the physical structure of the landing gear control panel, and cooperates with the signal acquisition circuit, the status light control circuit and the data processing module to collect and process the operating signals of the switches. In combination with the functions of the external flight simulation system, the simulated use of the landing gear control panel of the Xiaolong model can be effectively realized, thereby providing users with a use experience that is basically the same as the display and operation of the real aircraft, greatly reducing the manufacturing cost of the device. The utility model is ingenious in design, simple in structure, low in cost, easy to use, and suitable for application in flight simulation equipment.

[0017] (2) The utility model configures an operation limiter on the landing gear operation switch to limit the normal toggle operation of the switch, so that it is in a normally closed state to keep the landing gear operation function disabled, avoid accidental touch or misoperation causing landing gear abnormality, and ensure the stability and safety of the landing gear use.

[0018] (3) The utility model uses physical electronic components to physically simulate the switch functions on the landing gear control panel. The structure combines the shell and the hollow holes thereon to ensure that the appearance of the device is consistent with the landing gear control panel of the Xiaolong model, thereby improving the user's immersive experience.

[0019] (4) The utility model adopts a 74HC165 register chip to realize the signal acquisition of the switch, a 74HC595 buffer chip to realize the signal output control of the indicator light, and an STM32 development board as the core of the data processing module, which effectively reduces the hardware cost while ensuring the performance. At the same time, the USB / Type-C interface is used as the interface for signal transmission and power supply, which can be easily connected with other flight simulation equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 The figure is a schematic diagram of the overall appearance structure of an embodiment of the utility model.

[0021] Figure 2 This is a schematic diagram of the front structure of the landing gear operation indication simulation device unit.

[0022] Figure 3 This is a schematic diagram of the indication panel structure of the landing gear operation indication simulation device unit.

[0023] Figure 4 This is a schematic diagram of the indicator rear cover structure of the landing gear operation indicator simulation device unit.

[0024] Figure 5 This is a schematic diagram of the structure of the control circuit board part of the landing gear operation indication simulation device unit.

[0025] Figure 6 Schematic diagram of the structure of the operation limiter of the landing gear operation indication simulator unit.

[0026] Figure 7 Exploded view of the simulator unit for landing gear operation instructions.

[0027] Figure 8 This is a circuit diagram of a touch switch in an embodiment of the utility model.

[0028] Fig. 9 The following is a circuit diagram of a two-speed button switch in an embodiment of the utility model.

[0029] Fig.10 This is a circuit diagram of a rotary encoder in an embodiment of the present utility model.

[0030] Fig.11 This is a circuit diagram of the LED lamp bead in the embodiment of the utility model.

[0031] Fig.12 This is a circuit schematic diagram of a register chip in an embodiment of the utility model.

[0032] Fig.13 This is a circuit schematic diagram of a buffer chip in an embodiment of the utility model.

[0033] Fig.14 This is a circuit principle interface diagram of the data processing module in the embodiment of the utility model.

[0034] Fig.15 This is a schematic diagram of the internal structure of the landing gear retraction and extension operation simulation device unit.

[0035] Fig.16 This is a schematic diagram of the structure of the operating rear cover shell of the landing gear retraction and extension operation simulation device unit.

[0036] Fig.17 This is a schematic diagram of the structure of the operation cover of the landing gear retraction and extension operation simulation device unit.

[0037] Fig.18 This is a schematic diagram of the structure of the operating movable frame part of the landing gear retraction and extension operation simulation device unit.

[0038] Fig.19 This is a circuit diagram of a potentiometer in an embodiment of the utility model.

[0039] In the above drawings, the component names corresponding to the reference numerals are as follows:

[0040] 1-indicator rear cover, 2-indicator cover, 3-indicator panel, 4-hollow hole, 5-test button, 6-landing gear operation switch, 7-brightness adjustment knob, 8-landing gear position status light assembly, 9-landing status indicator assembly, 10-operation limiter, 11-control circuit board, 13-connecting fins, 14-interface opening, 15-connecting hole, 16-screw sleeve, 17-avoidance gap, 18-touch switch, 19-key cap, 20-light-transmitting indicator, 21-two-speed button switch, 22-limiter collar, 23-limiter bottom plate, 24- Articulated connection, 25-limiting plate, 26-rotary encoder, 27-adjusting screw cap, 28-pattern layer, 29-landing gear status light, 30-landing gear warning light, 31-LED lamp beads, 32-lamp cover, 33-speed brake indicator light, 34-umbrella indicator light, 35-wing indicator light, 36-cover, 40-operating rear cover shell, 41-operating cover, 42-operating fixing frame, 43-operating port, 44-operating circuit board, 45-operating interface, 46-operating servo, 47-operating movable frame, 48-operating handle, 49-limiting block, 50-clamp. DETAILED DESCRIPTION

[0041] The present invention is further described below in conjunction with the accompanying drawings and embodiments. The implementation methods of the present invention include but are not limited to the following embodiments.

[0042] Example

[0043] like Figures 1 to 19As shown, the aircraft landing gear control panel simulator is mainly used for performing flight simulation operations on the landing gear control panel on the left control console of the Xiaolong aircraft model, including a landing gear operation indication simulator unit and a landing gear retraction and extension operation simulator unit arranged side by side and connected by a data cable; the landing gear operation indication simulator unit includes an indication rear cover shell 1 in the shape of a flat rectangular box, an indication cover plate 2 arranged on the upper end of the indication rear cover shell and sealed, an indication panel 3 attached to the front of the indication cover plate, hollow holes 4 for installing components that are opened on the indication cover plate and the indication panel at designated positions, a test button 5, a landing gear operation switch 6 and a brightness adjustment knob 7 that are arranged side by side horizontally at the lower position of the front of the indication panel, a landing gear position status light assembly 8 arranged at the upper right position of the front of the indication panel, a landing status indicator light assembly 9 arranged at the upper left position of the front of the indication panel, and a landing gear position status light assembly 10 arranged at the upper right position of the front of the indication panel. An operation limiter 10 is provided on the indicator panel and the indicator cover plate and blocks the landing gear operation switch, a control circuit board 11 is arranged in the indicator rear cover shell for carrying and electrically connecting the test button, the landing gear operation switch, the brightness adjustment knob, the landing gear position status light assembly and the landing status indicator light assembly, and an interface assembly is arranged on the indicator rear cover shell and electrically connected to the control circuit board, wherein the control circuit board is configured with a signal acquisition circuit, a status light control circuit and a data processing module, the signal acquisition circuit is used to collect the input signals of the test button, the landing gear operation switch, the brightness adjustment knob and the landing gear retraction and extension operation simulation device unit and transmit them to the data processing module, the status light control circuit receives the control signal fed back by the data processing module and makes the landing gear position status light assembly and the landing status indicator light assembly light up or go out accordingly, and the interface assembly is used for power supply and signal transmission between the data processing module and the outside. At the same time, the interface assembly is also configured with an internal signal transfer interface for electrically connecting the landing gear retraction and extension operation simulation device unit.

[0044] Specifically, the open end of the indicating rear cover shell is provided with an inwardly folded connecting fin 13 for buckling and placing the indicating cover plate. After the corresponding position of the indicating cover plate is provided with a screw hole, the indicating cover plate and the indicating rear cover shell can be connected and fixed by a cap screw; an interface opening 14 for exposing the interface component is provided on the side or / and back of the indicating rear cover shell; according to the installation requirements of the device, a plurality of connecting holes 15 for convenient external fixing can also be provided on the back of the indicating rear cover shell. The control circuit board is connected to the bottom side of the indicating cover plate by a screw sleeve 16 and maintains an installation gap with the cover plate. The two ends of the screw sleeve are respectively connected and fixed to the control circuit board and the indicating cover plate by screws. The indicating panel can be fixedly attached to the front of the indicating cover plate by bonding or screw connection. When screw connection is adopted, the connected screws can be fixed to the upper end of the screw sleeve together. The position corresponding to the cap screw on the indicating panel can be provided with a corresponding screw hole or avoidance gap according to the shape requirements. In this embodiment, it is shown in the form of avoidance gap 17.

[0045] Specifically, the test button adopts a touch switch 18, which is placed on the control circuit board and electrically connected to the signal acquisition circuit. The touch switch is equipped with a key cap 19 for easy key operation, and the key cap is placed in a hollow hole at a corresponding position. The test button is represented by the TEST symbol. After the button is pressed, it is used to detect whether the landing gear function and various functions of the landing gear control panel are normal. A light-transmitting indication part 20 marked with its symbol can be configured on the indicator panel next to the test button, and a backlight LED lamp is configured on the control circuit board at the corresponding position for backlight indication of the test button. Figure 8 The schematic diagram of the circuit of the touch switch is shown, wherein the device SW1 represents the touch switch, and the model TS-1095PS-A13B2-C3D2 can be used, and the interface K13 is used to connect the corresponding interface of the signal acquisition circuit.

[0046] Specifically, the landing gear operating switch adopts a two-position button switch 21, which is electrically connected to the signal acquisition circuit. The lever of the two-position button switch extends out of the front of the indicator panel through the hollow hole at the corresponding position. The landing gear operating switch is represented by the symbol LGOVRD. The two positions correspond to the enabling and disabling of the landing gear operating function respectively. Only when the landing gear operating function is enabled can the aircraft landing gear be retracted or lowered by operating the landing gear retraction and extension operation simulation device unit. A light-transmitting indicator 20 marked with its symbol can be configured on the indicator panel next to the landing gear operating switch, and a backlight LED lamp can be configured on the control circuit board at the corresponding position for the backlight indication of the landing gear operating switch. Fig. 9 The circuit schematic diagram of a two-position button switch is shown, wherein device U1 represents a two-position button switch, which can adopt the MT-0-102-A101-M200-RS+PJ model, and interfaces K11 and K12 are used to connect to the corresponding interfaces of the signal acquisition circuit.

[0047] Specifically, the operation limiter includes a limiter collar 22 disposed in a corresponding hollow hole, a limiter bottom plate 23 connected to the bottom of the limiter collar and fixedly connected to the indicator cover, a hinged connection portion 24 disposed on one lateral side of the limiter collar, and an L-shaped limiter plate 25 with one lateral end being resettably hinged to the hinged connection portion, wherein the limiter plate blocks the position of the lower side of the two-speed button switch. In this way, the landing gear operation switch can be kept in a normally closed state and disabled, and abnormal landing gear operation caused by accidental touch or misoperation can also be avoided. When the landing gear operation switch needs to be enabled, the limiter plate is manually operated to flip up and open, and then the switch is toggled.

[0048] Specifically, the brightness adjustment knob adopts a rotary encoder 26 of model EC11, whose rotary rod extends out of the front of the indicator panel through a hollow hole at a corresponding position and an adjustment screw cap 27 is placed on the rotary rod. The brightness adjustment knob is represented by the symbol BRT and is used to adjust the light intensity. A light-transmitting indicator 20 marked with its symbol can be configured on the indicator panel next to the brightness adjustment knob, and a backlight LED lamp can be configured on the control circuit board at the corresponding position for backlight indication of the brightness adjustment knob. Fig.10 The figure shows a circuit schematic diagram of a rotary encoder, where device CE1 represents the rotary encoder, and interfaces K9 and K10 are used to connect to corresponding interfaces of a signal acquisition circuit.

[0049] Specifically, the landing gear position status light assembly 8 includes a pattern layer 28 etched on the upper right position of the front side of the indicator panel and presenting a top-down aircraft shape, a landing gear status light 29 arranged corresponding to the three landing gear positions on the aircraft shape, and a landing gear warning light 30 arranged at the front end of the aircraft shape, wherein the three landing gear status lights are arranged in an isosceles triangle with one in front and two in the back, the landing gear status light and the landing gear warning light both use LED lamp beads 31, and are both electrically connected to the status light control circuit, and the landing gear status light and the landing gear warning light are both provided with lampshades 32 placed on the hollow holes at the corresponding positions. The three landing gear status lights are configured in green, and the landing gear warning light is configured in red. The configuration can be made by the color of the LED lamp beads or the color of the lampshade. The lampshade is elliptical, oblate or waist-shaped, and can adopt a splicing and snap-fitting structure, where the transparent lampshade shell is clamped in the hollow hole at the corresponding position, or an integrated splicing structure can be adopted, where transparent materials are spliced ​​together at the hollow hole at the corresponding position to form a light-transmitting part. Fig.11 The figure shows a circuit schematic diagram of an LED lamp bead, device LED2 is the LED lamp bead, and interface LED2 is used to connect to the corresponding interface of the status light control circuit.

[0050] Specifically, the landing status indicator light assembly 9 includes a speed brake indicator light 33, an umbrella indicator light 34 and a wing indicator light 35 arranged vertically side by side at the upper left position on the front of the indicator panel. The speed brake indicator light, the umbrella indicator light and the wing indicator light all use LED lamp beads 31, which are electrically connected to the status light control circuit. They are all provided with a cover 36 that covers the LED lamp beads and protrudes from the front of the indicator panel through hollow holes at corresponding positions. The cover is also provided with a logo corresponding to each light, such as the speed brake indicator light S / B, the umbrella indicator light D / CH, and the wing indicator light TEF. The cover adopts a full-cover shell buckled at the corresponding position on the control circuit board to ensure the targeted reflection of the light, and the protruding part of the cover is rectangular.

[0051] Specifically, the data processing module uses the STM32 development board as the core. Fig.14As shown, interfaces LATCH, CLK, and DATA12 are used to connect the signal acquisition circuit, interfaces LED_PWM, 595LATCH, 595CLK, and 595DATA are used to connect the status light control circuit, interfaces USBD+ and USBD- are used to connect the interface components for signal transmission, and interfaces VCC, GND, and 3.3V are used to connect the power supply. The signal acquisition circuit uses a register chip of model 74HC165 as the core. A 74HC165 register chip is an 8-bit input. In this solution, only one 74HC165 register chip U2 can be used, such as Fig.12 As shown, interfaces K9-K15 are used to connect corresponding rotary encoders, two-speed toggle switches, touch switches or potentiometers, and interfaces DATA12, CLK, and LATCH are used to connect corresponding interfaces of the data processing module STM32. The status light control circuit uses a 74HC595 buffer chip as the core. A 74HC595 buffer chip is 8 bits. One common output or two can be used to separate the landing gear position status light and the landing status indicator light. In this solution, two 74HC595 buffer chips U3 and U4 are cascaded, as shown in FIG. Fig.13 As shown, interfaces LED_PWM, 595LATCH, 595CLK, and 595DATA are used to connect to the corresponding interfaces of the data processing module STM32, interfaces LED1-LED4 are used to connect to the corresponding LED lamp beads of the landing gear position status lamp assembly, and interfaces LED5-LED7 are used to connect to the corresponding LED lamp beads of the landing status indicator lamp assembly. The interface assembly adopts a USB interface or a Type-C interface, which can realize signal transmission and power supply at the same time; the internal signal transfer interface can adopt a pin interface or a jumper interface.

[0052] Specifically, the landing gear retraction and extension operation simulation device unit includes an operation rear cover shell 40 in the shape of a rectangular box, an operation cover 41 arranged at the upper end of the operation rear cover shell and equipped with an operation port 43, an operation fixing frame 42 fixedly arranged in the operation rear cover shell through the operation port, an operation circuit board 44 arranged at the lower part of the operation fixing frame, an operation interface 45 and an operation servo 46 arranged on the operation circuit board, an operation movable frame 47 arranged in the operation fixing frame and connected to the rotating head of the operation servo, and an operation handle 48 fixedly arranged on the operation movable frame and extending from the front of the operation cover through the operation port, wherein the operation circuit board is electrically connected to the signal acquisition circuit of the control circuit board through the operation interface. Specifically, the operating servo adopts a potentiometer, which is electrically connected to the signal acquisition circuit through the operating interface and the corresponding jumper interface to realize the transmission of the operating signal, and a notch for exposing the operating interface is opened on the operating rear cover shell; the potentiometer is placed on the operating circuit board in a horizontal form, that is, its rotation axis is horizontally parallel to the surface of the operating circuit board, so as to facilitate the push-pull operation of the connected operating movable frame and the operating handle, simulating the actual operation process of retracting and lowering the landing gear. Fig.19 The figure shows a circuit schematic diagram of a potentiometer, wherein device KR1 represents the potentiometer, and interfaces K14 and K15 are used to electrically connect to corresponding interfaces of a signal acquisition circuit.

[0053] Specifically, the operating rear cover shell can adopt a structure of surrounding walls and a bottom plate spliced ​​together to facilitate the maintenance of the operating circuit board and the operating movable frame placed inside. The operating fixed frame adopts an installation method in which the upper part is clamped and the lower part is fixed. The clamp head 50 configured on the upper part clamps the operating port on the front of the operating cover to maintain the accurate installation position. The connecting column configured on the lower part is connected and fixed to the bottom plate of the operating rear cover shell by bolts to maintain the stable installation connection; an empty gap is also reserved in the middle of the operating fixed frame for the operating handle to extend and push and pull; and the upper clamp head surface can also be marked with text to indicate the gear position of the landing gear retracted and lowered corresponding to the push and pull operation of the operating handle; further, the text mark on the clamp head surface can be configured as a light-transmitting indicator, and a corresponding backlight LED lamp is configured at the corresponding position on the operating circuit board. The operating movable frame is a fan-shaped frame structure, which is integrally placed in the reserved gap in the operating fixed frame, and is placed with the axis of the rotating head of the operating servo as the center of the circle, so that the operating servo can be synchronously rotated when driven by the operating handle; the two ends of the fan-shaped arc edge of the operating movable frame are also provided with limit blocks 49, which are used to clamp the edge of the operating port to prevent further rotation after rotating to the set position, so as to limit the maximum forward and backward push and pull position of the operating handle. The appearance of the exposed part of the operating handle can refer to the appearance design of the operating handle of the real machine to provide users with a real operating experience.

[0054] When the utility model is used, it needs to be used in conjunction with other corresponding simulation devices, and needs to be connected to a computer with flight simulation software installed for flight simulation training or experience. Through the USB or type-C interface, external power supply and flight simulation software signal data transmission, by operating the test button, landing gear operation switch, brightness adjustment knob and operating handle and other components, the corresponding operation signal is collected by the signal acquisition circuit and transmitted to the external flight simulation system through the data processing module to realize the corresponding function. At the same time, the internal operation signal or the feedback signal of the external system is transmitted to the data processing module and then fed back to the status light control circuit to control the light and dark of the LED lamp beads of the corresponding function, so as to realize the feedback indication of the corresponding function.

[0055] The above embodiments are only preferred embodiments of the present utility model and are not intended to limit the protection scope of the present utility model. Any changes that adopt the design principles of the present utility model and are made through non-creative labor on this basis should fall within the protection scope of the present utility model.

Claims

1. An aircraft landing gear control panel simulation device, characterized in that: The invention comprises a landing gear operation indication simulation device unit and a landing gear retraction and extension operation simulation device unit which are arranged side by side and connected via a data line; the landing gear operation indication simulation device unit comprises an indication rear cover shell (1) in the shape of a flat rectangular box, an indication cover plate (2) which is arranged on the upper end of the indication rear cover shell (1) and sealed, an indication panel (3) which is attached to the front of the indication cover plate (2), hollow holes (4) which are provided on the indication cover plate (2) and the indication panel (3) at designated positions and are used for installing components, a test button (5), a landing gear operation switch (6) and a brightness adjustment knob (7) which are arranged side by side horizontally at the lower position of the front of the indication panel (3), a landing gear position status light assembly (8) which is arranged at the upper right position of the front of the indication panel (3), a landing status indicator light assembly (9) which is arranged at the upper left position of the front of the indication panel (3), and an operation limiter which is arranged on the indication panel (3) and the indication cover plate (2) and blocks the landing gear operation switch (6). (10), a control circuit board (11) arranged in the indicating rear cover shell (1) for carrying and electrically connecting a test button (5), a landing gear operating switch (6), a brightness adjustment knob (7), a landing gear position status light assembly (8) and a landing status indicator light assembly (9), and an interface assembly arranged on the indicating rear cover shell (1) and electrically connected to the control circuit board (11), wherein the control circuit board (11) is provided with a signal acquisition circuit, a status light control circuit and a data processing module, the signal acquisition circuit is used to acquire input signals of the test button (5), the landing gear operating switch (6), the brightness adjustment knob (7) and the landing gear retraction and extension operation simulation device unit and transmit them to the data processing module, the status light control circuit receives the control signal fed back by the data processing module and causes the landing gear position status light assembly (8) and the landing status indicator light assembly (9) to light up or go out accordingly, and the interface assembly is used for power supply and signal transmission between the data processing module and the outside.

2. The aircraft landing gear control panel simulation device according to claim 1, characterized in that: The test button adopts a touch switch, which is placed on the control circuit board and electrically connected to the signal acquisition circuit. The touch switch is equipped with a key cap for easy key operation, and the key cap is placed in a hollow hole at a corresponding position.

3. The aircraft landing gear control panel simulation device according to claim 1, characterized in that: The landing gear operating switch adopts a two-position button switch, which is electrically connected to the signal acquisition circuit. The lever of the two-position button switch extends out of the front of the indication panel through the hollow holes at the corresponding positions.

4. The aircraft landing gear control panel simulation device according to claim 3, characterized in that: The operation limiter (10) comprises a limiter collar (22) arranged in a corresponding hollow hole (4), a limiter base plate (23) connected to the bottom of the limiter collar (22) and fixedly connected to the indicating cover plate (2), a hinged connection portion (24) arranged on a lateral side of the limiter collar (22), and an L-shaped limiter plate (25) having one lateral end that is hinged to the hinged connection portion (24) in a reversible manner, wherein the limiter plate (25) blocks the position of the lower side of the two-speed button switch.

5. The aircraft landing gear control panel simulation device according to claim 1, characterized in that: The brightness adjustment knob adopts a rotary encoder of model EC11, a rotary rod of which extends out of the front of the indicating panel through a hollow hole at a corresponding position and an adjustment rotary cap is arranged on the rotary rod.

6. The aircraft landing gear control panel simulation device according to claim 1, characterized in that: The landing gear position status light assembly (8) comprises a pattern layer (28) etched on the right position of the upper front part of the indicator panel (3) and presenting the aircraft shape from a top view, landing gear status lights (29) arranged corresponding to the three landing gear positions on the aircraft shape, and a landing gear warning light (30) arranged at the front position of the aircraft shape, wherein the landing gear status light and the landing gear warning light both use LED lamp beads and are electrically connected to the status light control circuit, and the landing gear status light and the landing gear warning light are both provided with lampshades arranged on the hollow holes at the corresponding positions.

7. The aircraft landing gear control panel simulation device according to claim 1, characterized in that: The landing status indicator light assembly (9) comprises a speed brake indicator light (33), an umbrella indicator light (34) and a wing indicator light (35) which are arranged vertically side by side at the upper left position of the front side of the indicator panel. The speed brake indicator light, the umbrella indicator light and the wing indicator light all use LED lamp beads, are electrically connected to the status lamp control circuit, and are all provided with a cover shell which covers the LED lamp beads and protrudes from the front side of the indicator panel through hollow holes at corresponding positions. The cover shell is also provided with a logo corresponding to each lamp.

8. The aircraft landing gear control panel simulation device according to claim 1, characterized in that: The data processing module uses an STM32 development board as the core, the signal acquisition circuit uses a register chip of model 74HC165 as the core, the status light control circuit uses a buffer chip of model 74HC595 as the core, and the interface component uses a USB interface or a Type-C interface.

9. The aircraft landing gear control panel simulation device according to any one of claims 1 to 8, characterized in that: The landing gear retraction and extension operation simulation device unit comprises an operation rear cover shell (40) in a rectangular box shape, an operation cover (41) arranged at the upper end of the operation rear cover shell (40) and provided with an operation port (43), an operation fixing frame (42) fixedly arranged in the operation rear cover shell (40) through the operation port (43), an operation circuit board (44) arranged at the lower part of the operation fixing frame (42), an operation interface (45) and an operation steering gear (46) arranged on the operation circuit board (44), an operation movable frame (47) arranged in the operation fixing frame (42) and connected to the rotating head of the operation steering gear (46), and an operation handle (48) fixedly arranged on the operation movable frame (47) and extending from the front of the operation cover (41) through the operation port (43), wherein the operation circuit board is electrically connected to the signal acquisition circuit of the control circuit board through the operation interface.

10. The aircraft landing gear control panel simulation device according to claim 9, characterized in that: The operating steering gear adopts a potentiometer.

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