An aircraft early warning device and system

Abstract

This utility model discloses an aircraft early warning device and system, including a housing, a communication control board, a display screen, a sound outlet, an audio warning component, and a light warning component. The communication control board and the audio warning component are disposed inside the housing, while the display screen, the sound outlet, and the light warning component are disposed on the housing. The communication control board is connected to the display screen, the audio warning component, and the light warning component, and is also used to connect to an external aircraft monitoring system. The audio warning component is located behind the sound outlet. Using this utility model, the status data of the aircraft monitoring system can be monitored in real time, and fault information can be displayed intuitively to personnel, reducing manual intervention and improving the efficiency and timeliness of fault handling.

Description

Technical Field

[0001] This utility model relates to the field of airborne equipment technology, and in particular to an aircraft early warning device and system. Background Technology

[0002] In the civil aviation sector, fault monitoring and early warning of aircraft monitoring systems primarily rely on the Central Maintenance Computer System (CMCS) and the Aircraft Condition Monitoring System (ACMS). These systems monitor various aircraft parameters in real time through sensors and data acquisition equipment, and generate fault information when anomalies are detected.

[0003] However, existing monitoring systems rely on manual review of reports or emails periodically, lacking intuitive alarm mechanisms and making real-time early warning difficult. This can lead to delays in transmitting fault information to relevant personnel, increasing time delays in fault handling. Furthermore, the manual intervention required to obtain and process fault information increases the workload of maintenance personnel. Utility Model Content

[0004] The purpose of this utility model embodiment is to provide an aircraft early warning device and system that can monitor the status data of the aircraft monitoring system in real time, intuitively display fault information to the staff, reduce manual intervention, and improve the efficiency and timeliness of fault handling.

[0005] To achieve the above objectives, this utility model provides an aircraft early warning device, comprising: a housing, a communication control board, a display screen, a sound outlet, an audio warning component, and a light warning component;

[0006] The communication control board and the audio warning component are located inside the housing, while the display screen, the sound outlet, and the light warning component are located on the housing.

[0007] The communication control board is connected to the display screen, the audio warning component, and the light warning component respectively, and the communication control board is also used to connect to an external aircraft monitoring system;

[0008] The audio warning component is located behind the sound outlet.

[0009] As an improvement to the above solution, the light warning component is a multi-segment foldable light pole; the multi-segment foldable light pole includes a base fixing segment, a middle adjustment segment, a top light-emitting segment, and a rotatable connecting component;

[0010] The base fixing section is fixedly connected to the housing, the base fixing section and the intermediate adjustment section are movably connected through the rotatable connecting component, and the intermediate adjustment section and the top light-emitting section are movably connected through the rotatable connecting component.

[0011] As an improvement to the above solution, the light warning component includes a light-transmitting cover, a base, a focusing lens, and an LED; wherein, the light-transmitting cover covers the base and forms a receiving cavity, the focusing lens and the LED are disposed inside the receiving cavity, the LED is disposed on the base, and the focusing lens is disposed between the LED and the light-transmitting cover.

[0012] As an improvement to the above solution, the aircraft warning device further includes an arc-shaped reflector, which is located behind the audio warning component and opposite to the sound-emitting surface of the audio warning component, with the concave surface of the arc-shaped reflector facing the audio warning component.

[0013] As an improvement to the above solution, the aircraft early warning device also includes a cooling fan; the cooling fan is located above the communication control board.

[0014] As an improvement to the above solution, the aircraft early warning device also includes a temperature sensor, which is located above the communication control board.

[0015] As an improvement to the above solution, the aircraft early warning device further includes a heat dissipation hole, a movable baffle, and a drive mechanism. The heat dissipation hole is located on the housing, and the movable baffle is connected to the drive mechanism. The movable baffle is located at the heat dissipation hole.

[0016] As an improvement to the above solution, the communication control board includes a Raspberry Pi main control board and an interface expansion board. The Raspberry Pi main control board and the interface expansion board are connected through GPIO ports. The Raspberry Pi main control board is connected to the display screen and the audio warning component; the interface expansion board is connected to the light warning component.

[0017] As an improvement to the above solution, the aircraft early warning device further includes a USB interface, an Ethernet interface, and a power interface. The USB interface and the Ethernet interface are connected to the Raspberry Pi main control board; the power interface is connected to the interface expansion board.

[0018] This utility model embodiment also provides an aircraft early warning system, including an aircraft monitoring system and an aircraft early warning device as described in any of the above.

[0019] Compared with existing technologies, the aircraft early warning device and system disclosed in this utility model can acquire fault information collected by the aircraft monitoring system in real time and immediately trigger audible and visual alarms when a fault occurs, ensuring that maintenance personnel can obtain fault information in a timely manner and reducing the time delay in fault handling. Through the automated early warning device, the need for manual intervention is reduced; maintenance personnel do not need to periodically check reports or emails, as the system automatically displays fault information through an audible and visual alarm mechanism, reducing the risk of human negligence. The audible and visual alarms, achieved through full-color light pillars and speakers, can intuitively display fault information, improve the perception of fault information, and ensure that maintenance personnel can notice potential problems in a timely manner. Attached Figure Description

[0020] Figure 1 This is a first structural schematic diagram of the aircraft early warning device provided in this embodiment of the utility model;

[0021] Figure 2 This is a second structural schematic diagram of the aircraft early warning device provided in this embodiment of the present invention;

[0022] Figure 3 This is a first structural schematic diagram of the light warning component in an embodiment of this utility model;

[0023] Figure 4 This is a second structural schematic diagram of the light warning component in an embodiment of this utility model;

[0024] Figure 5 This is a schematic diagram of the heat dissipation component in an embodiment of this utility model;

[0025] Figure 6 This is a schematic diagram of the third structure of the aircraft early warning device provided in this embodiment of the present invention;

[0026] Figure 7 This is a schematic diagram of the fourth structure of the aircraft early warning device provided in this embodiment of the present invention;

[0027] Figure 8 This is a fifth structural schematic diagram of the aircraft early warning device provided in this embodiment of the present invention;

[0028] Figure 9 This is a sixth structural schematic diagram of the aircraft early warning device provided in this embodiment of the present invention;

[0029] Figure 10 This is a seventh structural schematic diagram of the aircraft early warning device provided in this embodiment of the utility model;

[0030] Figure 11 This is a schematic diagram of the hardware structure connection of the aircraft early warning device provided in this embodiment of the utility model;

[0031] In the diagram, 10 is the aircraft early warning device; 11 is the housing; 12 is the communication control board; 121 is the Raspberry Pi main control board; 122 is the interface expansion board; 13 is the display screen; 14 is the sound outlet; 15 is the audio warning component; 16 is the light warning component; 161 is the base fixing section; 162 is the middle adjustment section; 163 is the top light-emitting section; 164 is the rotatable connecting component; 165 is the light-transmitting cover; 166 is the base; 167 is the focusing lens; 168 is the LED; 17 is the heat dissipation component; 171 is the cooling fan; 172 is the heat dissipation hole; 173 is the movable baffle; 174 is the drive mechanism; 18 is the interface component; 181 is the USB interface; 182 is the Ethernet interface; and 183 is the power interface. Detailed Implementation

[0032] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0033] See Figure 1 and Figure 2 , Figure 1 This is a first structural schematic diagram of the aircraft early warning device provided in this embodiment of the present invention. Figure 2 This is a second structural schematic diagram of the aircraft early warning device provided in this embodiment of the present invention. This embodiment of the present invention provides an aircraft early warning device 10, including: a housing 11, a communication control board 12, a display screen 13, a sound outlet 14, an audio warning component 15, and a light warning component 16. The communication control board 12 and the audio warning component 15 are disposed inside the housing 11, while the display screen 13, the sound outlet 14, and the light warning component 16 are disposed on the housing 11. The communication control board 12 is connected to the display screen 13, the audio warning component 15, and the light warning component 16, and the communication control board 12 is also used to connect to an external aircraft monitoring system. The audio warning component 15 is located behind the sound outlet 14.

[0034] In this embodiment, the aircraft monitoring system monitors various parameters of the aircraft in real time through sensors and data acquisition equipment, and generates fault information when an anomaly is detected. The aircraft early warning device 10 is used to acquire fault information from the external aircraft monitoring system, process and display the fault information, and issue corresponding audible and / or visual alarms to alert personnel.

[0035] Specifically, the communication control board 12 is used to collect fault information of the aircraft monitoring system and generate corresponding control commands, control the light warning component 16 to produce lights of corresponding color or brightness, control the audio warning component 15 to emit corresponding alarm sounds or preset voice broadcasts, and can also control the display screen to display corresponding fault information.

[0036] Optionally, the communication control board 12 adopts a Linux-based ARM architecture microcomputer - Raspberry Pi - as the core of device control, realizing functions such as network communication, code execution, signal processing and control screen display, and integrating multiple components such as power management, audio warning components and light warning components.

[0037] Optionally, the audio warning component 15 can be a speaker, buzzer, or audio equipment. For example, the audio warning component 15 is a stereo dual-speaker, powered and driven by the display screen, and plays sound via an HDMI interface. Warning sounds or customized voice announcements can be played according to software settings. A groove for the sound outlet 14 is cut at the speaker mounting location on the device housing, and the sound outlet 14 is arranged in a honeycomb pattern.

[0038] Optionally, the light warning component 16 can be in the form of a full-color light column, a multi-color LED module, or a color-changing light strip. For example, the light warning component 16 is a full-color light column, specifically a 5V powered full-color light strip with an aluminum alloy shell and a milky white PC light-transmitting cover. It uses the WS2812B protocol and supports software programming to control the color. The full-color light column generates different colors and patterns of light according to different warning types to alert on-duty personnel.

[0039] Optionally, the display screen 13 can be a touch screen or an LCD screen. For example, the display screen 13 uses a 7-inch capacitive touch screen with a resolution of 1024*600, an HDMI interface, is powered separately via USB, and is connected to the communication control board via a USB interface to achieve screen touch control functionality.

[0040] The technical means employed in this embodiment enable real-time acquisition of fault information collected by the aircraft monitoring system. Upon the occurrence of a fault, an audible and visual alarm is immediately triggered, ensuring that maintenance personnel can obtain fault information promptly and reducing time delays in fault handling. The automated warning device reduces the need for manual intervention; maintenance personnel do not need to periodically check reports or emails, as the system automatically displays fault information through an audible and visual alarm mechanism, reducing the risk of human error. The use of full-color LED lights and speakers to achieve audible and visual alarms provides a clear visual display of fault information, improving the perceptibility of fault information and ensuring that maintenance personnel can promptly notice potential problems.

[0041] As a preferred embodiment, the present invention is further implemented based on the above embodiments, see [link to details]. Figure 3 This is a first structural schematic diagram of the light warning component in this utility model embodiment. The light warning component 16 is a multi-segment foldable lamp post. The multi-segment foldable lamp post includes a base fixing segment 161, a middle adjustment segment 162, a top light-emitting segment 163, and a rotatable connecting component 164.

[0042] The base fixing section 161 is fixedly connected to the housing 11. The base fixing section 161 and the intermediate adjustment section 162 are movably connected through the rotatable connecting component 164. The intermediate adjustment section 162 and the top light-emitting section 163 are movably connected through the rotatable connecting component 164.

[0043] In this embodiment, the light warning component 16 can be improved into a multi-segment foldable light column structure, which can be connected by hinges and other rotatable connecting components to achieve angle adjustment, adapting to the installation requirements of different computer room spaces.

[0044] Specifically, the multi-section foldable lamp post is divided into three functional sections, from bottom to top: the base fixing section, the middle adjustment section, and the top light-emitting section. Each section can be axially rotated and folded through hinges, and can be folded and unfolded within a certain length range to adapt to different installation spaces.

[0045] Optionally, the top light-emitting section is equipped with a lamp column for emitting light of different colors and brightness. For example, the top light-emitting section integrates multiple full-color LED beads arranged in a ring to ensure 360° illumination without blind spots.

[0046] Optionally, the rotatable connecting component 164 is a damping hinge with adjustable torque. The rotation axis of the damping hinge is perpendicular to the axis of the lamp post, supporting bidirectional rotation from 0° to 180°. In the 0° state, the lamp post is fully extended and vertical, suitable for open server room spaces. In the 90° state, the middle adjustment section is folded horizontally, and the top light-emitting section can be directed towards the view of the on-duty personnel, suitable for scenarios where it is installed on the side of a server rack. In the 180° state, the lamp post is fully folded, fitting snugly against the main body of the warning device, suitable for confined spaces, such as embedded server racks.

[0047] By employing the technical means of this embodiment, through the redundant design of segmented folding and damping hinges, the light warning function is retained, and the installation and adaptation problem of different machine room spaces is solved through mechanical structure, thereby enhancing the practicality of the aircraft warning device.

[0048] As a preferred embodiment, the present invention is further implemented based on the above embodiments, see [link to details]. Figure 4This is a second structural schematic diagram of the light warning component in an embodiment of the present utility model. The light warning component 16 includes a light-transmitting cover 165, a base 166, a focusing lens 167, and an LED bead 168. The light-transmitting cover 165 covers the base 166 and forms a receiving cavity. The focusing lens 167 and the LED bead 168 are disposed inside the receiving cavity. The LED bead 168 is disposed on the base 166, and the focusing lens 167 is disposed between the LED bead 168 and the light-transmitting cover 165.

[0049] In this embodiment, a focusing lens array can be added inside the light warning component 16 to enable clear color differentiation of the light even at a distance, solving the problem of light dispersion in traditional light strips. The focusing lens 167 is a plano-convex lens, wherein the flat surface of the focusing lens 167 faces the lamp bead 168, and the convex surface faces the light-transmitting cover 165, thereby effectively focusing the light emitted by the lamp bead 168 and emitting it through the light-transmitting cover 165.

[0050] Preferably, in an embodiment where the light warning component 16 is a multi-segment foldable lamp post, the light-transmitting cover 165, the base 166, the focusing lens 167, and the lamp beads 168 can be specifically disposed in the top light-emitting segment 163.

[0051] Optionally, multiple condenser lenses 167 and LED chips 168 can be configured, and there is a one-to-one correspondence between condenser lenses 167 and LED chips 168.

[0052] For example, inside the top light-emitting section, eight sets of focusing lenses are evenly arranged along the vertical axis of the lamp post. Each set of lenses corresponds to one full-color LED, with a spacing of 1.2cm between the LEDs. The lenses are arranged in an array to form a ring distribution, ensuring that the light converges horizontally in a 360° direction, covering all angles that maintenance personnel may observe, while avoiding light waste in the vertical direction. Through the curved surface design of the lenses, the divergent light emitted by the LEDs is focused into a narrow 30° beam, effectively improving the luminous intensity.

[0053] By employing the technical means of this embodiment, the reliability and applicability of the luminous alarm are significantly improved through the precise matching of the focusing lens array and the LED beads. Especially for the large space and strong interference environment of aviation computer rooms, it solves the defect of the diffused light of traditional light poles and improves the intuitiveness of the warning.

[0054] As a preferred embodiment, based on the above embodiments of the present invention, the aircraft warning device 10 further includes an arc-shaped reflector (not shown in the figure), the arc-shaped reflector is disposed behind the audio warning component 15, opposite to the sound-emitting surface of the audio warning component 15, and the concave surface of the arc-shaped reflector faces the audio warning component 15.

[0055] In this embodiment, by designing an acoustic cavity structure, such as adding an arc-shaped reflector inside the housing, the directionality of the warning sound is enhanced, and it can be adjusted to propagate towards the maintenance personnel's duty area, solving the problem of the wide diffusion range and weak directionality of traditional loudspeaker warning sounds, and also avoiding interference with other work areas.

[0056] Specifically, the arc-shaped reflector is installed inside the housing of the warning device, located directly behind the speaker and opposite to the speaker's sound direction. The arc-shaped reflector adopts a single arc-shaped curved surface design, with the curvature optimized based on the acoustic reflection principle. The overall structure is a semi-enclosed structure with the concave surface facing the speaker, forming a directional guiding channel for sound waves.

[0057] Optionally, the arc-shaped reflector can be adjusted at a certain angle around the horizontal axis, that is, in the direction parallel to the central axis of the speaker, by means of the cooperation of the bracket waist-shaped hole and screws, thereby precisely adjusting the sound output direction of the speaker.

[0058] By employing the technical means of this embodiment, the directional guidance of the arc-shaped reflector and the adjustable angle structure effectively solve the problem of weak directionality of warning sounds in multi-equipment environments in aviation equipment rooms, thereby enhancing the effectiveness of fault early warning.

[0059] As a preferred embodiment, the present invention is further implemented based on the above embodiments, see [link to details]. Figures 6 to 10 , Figure 6 This is a schematic diagram of the third structure of the aircraft early warning device provided in this embodiment of the present invention. Figure 7 This is a fourth structural schematic diagram of the aircraft early warning device provided in this embodiment of the present invention, used to show the front structure of the aircraft early warning device. Figure 8 This is a fifth structural schematic diagram of the aircraft early warning device provided in this embodiment of the invention, used to show the right side structure of the aircraft early warning device. Figure 9 This is a sixth structural schematic diagram of the aircraft early warning device provided in this embodiment of the invention, used to show the rear structure of the aircraft early warning device. Figure 10 This is a seventh structural schematic diagram of the aircraft early warning device provided in this embodiment of the present invention, used to show the left side structure of the aircraft early warning device. The aircraft early warning device 10 also includes a heat dissipation component 17, which includes a cooling fan 171; the cooling fan 171 is located above the communication control board 12.

[0060] In this embodiment, in order to prevent the communication control board 12 from continuously working and generating heat, thus affecting the safe and stable operation of the device, a heat dissipation component 17 is provided to dissipate heat and cool down the communication control board 12.

[0061] Specifically, the heat dissipation component 17 includes a cooling fan 171, which can start and run continuously after the aircraft early warning system is powered on. The cooling fan 171 can also be connected to the communication control board 12 and controlled to start or stop through the communication control board 12.

[0062] In a preferred embodiment, the heat dissipation component 17 further includes a temperature sensor (not shown in the figure), which is located above the communication control board 12. The temperature sensor is used to monitor the CPU temperature of the communication control board 12 in real time. The temperature sensor is connected to the communication control board 12.

[0063] As an example, the cooling fan 171 is used for active cooling of the device, has dimensions of 30*30*10MM, uses a 5V power supply, and is controlled to start and stop via a GPIO pin. A temperature sensor monitors the CPU temperature of the communication control board in real time. When the CPU temperature exceeds a preset temperature threshold, the GPIO pin of the communication control board outputs a control signal to trigger the cooling fan to start. When the CPU temperature falls below the preset temperature threshold, the GPIO pin of the communication control board triggers the cooling fan to shut down.

[0064] In a preferred embodiment, the heat dissipation component 17 further includes heat dissipation holes 172, which are disposed on the housing 11.

[0065] In this embodiment, the heat dissipation hole 172 is specifically located on the back of the housing 11 of the aircraft early warning device, and heat dissipation is provided for the internal structure by opening the hole on the back of the device.

[0066] Optionally, each heat dissipation hole is slot-shaped, and adjacent heat dissipation holes are staggered.

[0067] Optionally, a dust filter can be added to the back of the heat dissipation vents to prevent dust from entering the device.

[0068] For a preferred embodiment, see Figure 5 This is a schematic diagram of the structure of the heat dissipation component in this embodiment of the present utility model. The heat dissipation component 17 also includes a movable baffle 173 and a driving mechanism 174. The movable baffle 173 and the driving mechanism 174 are connected. The movable baffle 173 can movably cover the heat dissipation hole 172. The driving mechanism 174 is connected to the communication control board 12.

[0069] Based on the existing heat dissipation hole structure, an adaptive dustproof heat dissipation structure is improved. By designing a movable baffle 173 and a driving mechanism 174 at the heat dissipation hole, the CPU temperature of the communication control board 12 is monitored in real time by the temperature sensor. When the CPU temperature exceeds a preset temperature threshold, the GPIO pin of the communication control board triggers the driving mechanism 174 to drive the movable baffle 173 to open. When the CPU temperature is lower than the preset temperature threshold, the GPIO pin of the communication control board triggers the driving mechanism 174 to drive the movable baffle 173 to close. This not only enhances heat dissipation efficiency but also reduces dust entry.

[0070] Optionally, the movable baffle 173 can be configured as a louver, grille, or other form.

[0071] The technical approach employed in this embodiment involves incorporating a heat dissipation structure into the aircraft early warning system. A cooling fan cools the communication control board, and a temperature sensor monitors the CPU temperature to control the fan's operation, effectively balancing heat dissipation performance and energy conservation. Furthermore, by installing ventilation holes and movable baffles, the temperature sensor also monitors the CPU temperature to control the opening and closing of the baffles, effectively balancing heat dissipation performance and dust prevention.

[0072] As a preferred embodiment, the present invention is further implemented based on the above embodiments, see [link to details]. Figure 11 This is a schematic diagram of the hardware structure connection of the aircraft early warning device provided in this embodiment of the utility model. The communication control board 12 includes a Raspberry Pi main control board 121 and an interface expansion board 122. The Raspberry Pi main control board 121 and the interface expansion board 122 are connected through a GPIO port. The Raspberry Pi main control board 121 is connected to the display screen and the audio warning component; the interface expansion board 122 is connected to the light warning component.

[0073] In a preferred embodiment, the aircraft early warning device further includes an interface component 18, which includes a USB interface 181, an Ethernet interface 182, and a power interface 183. The USB interface 181 and the Ethernet interface 182 are connected to the Raspberry Pi main control board 121, and the power interface 183 is connected to the interface expansion board 122.

[0074] In this embodiment, the Raspberry Pi main control board 121 is a Raspberry Pi 4th Generation B Raspberry Pi 44B. The Raspberry Pi 4B is a microcomputer developed by the Raspberry Pi Foundation, abbreviated as RPi. Based on the Debian GNU / Linux operating system, it boasts powerful computing capabilities and rich expansion interfaces, and is widely used in fields such as the Internet of Things, embedded systems, education, and entertainment. The Raspberry Pi 4B is equipped with a high-performance 64-bit quad-core Broadcom BCM2711 processor with a clock speed of 1.5GHz, supports dual-band 2.4 / 5.0GHz Wi-Fi and Bluetooth 5.0, and features a Gigabit Ethernet interface and a USB 3.0 port. It supports dual displays with 4K resolution output via a pair of micro-HDMI ports and has hardware video decoding capabilities for 4Kp60. Furthermore, the Raspberry Pi 4B supports Power over Ethernet (PoE) functionality, implemented through a separate PoE HAT plugin.

[0075] The interface expansion board 122 serves as the control interface between the main control board and various external devices. It integrates power management, signal distribution, and level conversion circuits to realize the relevant control of external devices such as lamp posts and fans.

[0076] The Ethernet interface 182 connects the wired network interface of the main control board to the outside of the early warning device via a Category 6 gigabit RJ45 network interface extension cable, thereby enabling wired network connection and access to the data interface of the aircraft monitoring system.

[0077] The power interface 183 can be a TYPE-C interface, powered by a 5V power supply.

[0078] Optionally, the interface expansion board is connected to the Raspberry Pi main control board via a 2*20P dual-row female connector, connecting to 40 GPIOs of the main control board to achieve signal expansion and level conversion. The interface expansion board is connected to the full-color LED column using a three-wire single-bus transmission protocol. The interface expansion board is connected to the cooling fan using an amplifier circuit driven by a MOSFET. The interface expansion board is connected to the power interface by connecting the two wires of the Type-C power interface to the terminals on the interface expansion board, providing power to the main control board and other devices.

[0079] The technical approach employed in this embodiment utilizes a Raspberry Pi-based early warning device to automatically acquire and process warning information from the aircraft monitoring system, reducing manual intervention. Through system integration and interface development, seamless integration with aircraft monitoring systems and other systems is achieved, ensuring real-time data sharing and processing, and improving the efficiency and collaborative capabilities of fault handling.

[0080] This utility model embodiment also provides an aircraft early warning system, including an aircraft monitoring system and an aircraft early warning device as described in any of the above embodiments.

[0081] It should be noted that the aircraft monitoring system is used to monitor various parameters of the aircraft in real time through sensors and data acquisition equipment, and to generate fault information when an anomaly is detected. The structure and working principle of the aircraft early warning device can be referred to the specific content of the above embodiments, and the working principles and beneficial effects of the two correspond one-to-one, so they will not be described again.

[0082] The above description is the preferred embodiment of this utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of this utility model, and these improvements and modifications are also considered to be within the protection scope of this utility model.

Claims

1. An aircraft warning device, characterized in that include: Housing, communication control board, display screen, sound outlet, audio warning components, and light warning components; The communication control board and the audio warning component are located inside the housing, while the display screen, the sound outlet, and the light warning component are located on the housing. The communication control board is connected to the display screen, the audio warning component, and the light warning component respectively, and the communication control board is also used to connect to an external aircraft monitoring system; The audio warning component is located behind the sound outlet.

2. The aircraft warning device of claim 1, wherein The light warning component is a multi-segment foldable light pole; the multi-segment foldable light pole includes a base fixing segment, a middle adjustment segment, a top light-emitting segment, and a rotatable connecting component; The base fixing section is fixedly connected to the housing, the base fixing section and the intermediate adjustment section are movably connected through the rotatable connecting component, and the intermediate adjustment section and the top light-emitting section are movably connected through the rotatable connecting component.

3. The aircraft warning device of claim 1, wherein, The light warning component includes a light-transmitting cover, a base, a focusing lens, and LED beads; wherein, the light-transmitting cover covers the base and forms a receiving cavity, the focusing lens and the LED beads are disposed inside the receiving cavity, the LED beads are disposed on the base, and the focusing lens is disposed between the LED beads and the light-transmitting cover.

4. The aircraft warning device of claim 1, wherein, The aircraft warning device also includes an arc-shaped reflector, which is located behind the audio warning component and opposite to the sound-emitting surface of the audio warning component, with the concave surface of the arc-shaped reflector facing the audio warning component.

5. The aircraft warning device of claim 1, wherein, The aircraft early warning device also includes a cooling fan; the cooling fan is located above the communication control board.

6. The aircraft warning device of claim 5, wherein, The aircraft early warning device also includes a temperature sensor, which is located above the communication control board.

7. The aircraft warning device of claim 6, wherein The aircraft early warning device also includes a heat dissipation hole, a movable baffle, and a drive mechanism. The heat dissipation hole is located on the housing, and the movable baffle is connected to the drive mechanism. The movable baffle is located at the heat dissipation hole.

8. The aircraft warning device of claim 1, wherein, The communication control board includes a Raspberry Pi main control board and an interface expansion board. The Raspberry Pi main control board and the interface expansion board are connected via GPIO ports. The Raspberry Pi main control board is connected to the display screen and the audio warning component; the interface expansion board is connected to the light warning component.

9. The aircraft warning device of claim 8, wherein, The aircraft early warning device also includes a USB interface, an Ethernet interface, and a power interface. The USB interface and the Ethernet interface are connected to the Raspberry Pi main control board; the power interface is connected to the interface expansion board.

10. An aircraft warning system characterized by, It includes aircraft monitoring systems and aircraft early warning devices as described in any one of claims 1 to 9.

Images