An alarm monitoring system for flight training

Abstract

The utility model discloses an alarm monitoring system for flight training, including fuselage, the both sides of fuselage are provided with the wing, the both sides of one end of fuselage are provided with tail fin, the top of fuselage is provided with the hatch cover away from the tail fin one end, and the vertical tail is provided with the fuselage near the tail fin one end, the both sides of fuselage are all set up and are provided with the air intake, and the air intake is located the top of wing, and the top of fuselage is provided with disc radar, and the inside of disc radar is provided with control module, and the bottom of fuselage is provided with visual assembly, and visual assembly includes base, body and visual module group, and base is fixedly connected with fuselage, and body is detachably connected with base, and visual module group is embedded in the inside of body. The utility model visual assembly integrates high definition camera and infrared imager, realizes all scene monitoring in combination with disc radar, and each module is connected with control module data real -time interaction, and alarm device integrates sound, light alarm, and the sound frequency and light color of optimization, improve warning recognition, and effectively guarantee flight training safety.

Description

Technical Field

[0001] This utility model relates to the field of aerospace technology, specifically to an alarm monitoring system for flight training. Background Technology

[0002] Flight training alarm monitoring systems are key safety equipment in aviation flight training. They mainly collect flight environment data, identify potential risks, and promptly send alarm signals to pilots to help avoid accidents and ensure the safety of personnel and equipment during training. They are of great significance for improving the quality and safety of flight training.

[0003] Furthermore, current alarm monitoring systems for flight training suffer from poor environmental adaptability; single vision components perform poorly in complex environments; low functional integration, poor coordination between modules, and delayed early warnings; insufficient airframe sealing and ease of maintenance; and problems with limited alarm methods and low recognition accuracy, making it difficult to meet training safety requirements. Therefore, there is an urgent need to design an alarm monitoring system for flight training to solve these problems. Utility Model Content

[0004] The purpose of this invention is to provide an alarm monitoring system for flight training to address the aforementioned shortcomings in the prior art.

[0005] To achieve the above objectives, this utility model provides the following technical solution: An alarm monitoring system for flight training includes a fuselage, wings on both sides of the fuselage, tail fins on both sides at one end of the fuselage, a hatch at the top of the fuselage away from the tail fins, and a vertical tail at the end of the fuselage near the tail fins. Air intakes are provided on both sides of the fuselage, and the air intakes are located above the wings. A disc radar is provided on the top of the fuselage, and a control module is provided inside the disc radar. A vision component is provided on the bottom of the fuselage. The vision component includes a base, a body, and a vision module. The base is fixedly connected to the fuselage, and the body is detachably connected to the base. The vision module is embedded inside the body.

[0006] Preferably, the vision module includes a high-definition camera and an infrared imager. The high-definition camera is used at least to acquire color visual images in a visible light environment, and the infrared imager is used at least to acquire infrared visual images in a low light or nighttime environment. Both the high-definition camera and the infrared imager are electrically connected to the control module.

[0007] Preferably, the disc radar includes a radar antenna and a signal processing unit. The radar antenna is used to transmit radar waves and receive reflected echoes. The signal processing unit is used to process the reflected echoes to generate environmental data containing obstacle distance and speed information. The disc radar is electrically connected to the control module.

[0008] Preferably, the control module is also connected to an alarm device, which includes a sound alarm and a light alarm. The sound alarm is located inside the machine body and is used to emit a buzzing alarm sound at a preset frequency. The light alarm is located on the top of the machine body and uses red LED beads to emit a flashing alarm light.

[0009] Preferably, a sealing strip is provided on the inner side of the hatch cover. When the hatch cover is closed, the sealing strip fits tightly against the edge of the hatch on the side of the fuselage, thereby sealing the internal space of the fuselage.

[0010] Preferably, the hatch cover is provided with a locking mechanism, which includes a latch and a latch. The latch is located at the free end of the hatch cover, and the latch is located at a corresponding position on the fuselage.

[0011] In the above technical solution, the alarm monitoring system for flight training provided by this utility model has the following beneficial effects: (1) The vision component integrates a high-definition camera and an infrared imager, combined with a disc radar, to achieve full-scene monitoring. Furthermore, each module is connected to the control module, and data is exchanged in real time, which greatly improves the reliability of monitoring and the timeliness of early warning, thus giving pilots more time to respond to emergencies.

[0012] (2) The sealing strip and locking mechanism of the hatch cover improve the sealing and stability, and the visual components are designed to be detachable for easy maintenance; the alarm device integrates sound and light alarms, optimizes the sound frequency and light color, improves the warning recognition, and effectively ensures flight training safety. Attached Figure Description

[0013] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this utility model. For those skilled in the art, other drawings can be obtained based on these drawings.

[0014] Figure 1 This is a three-dimensional structural view of an embodiment of an alarm monitoring system for flight training according to the present invention.

[0015] Figure 2 This is a three-dimensional view of the visual component structure provided in an embodiment of an alarm monitoring system for flight training according to the present invention.

[0016] Figure 3 This is an enlarged view of the visual component structure provided in an embodiment of an alarm monitoring system for flight training according to this utility model.

[0017] Figure 4 This is a structural flowchart of an embodiment of an alarm monitoring system for flight training according to the present invention.

[0018] 1. Fuselage; 2. Wing; 3. Tail; 4. Vertical tail; 5. Air intake; 6. Door cover; 7. Circular radar; 8. Vision module; 81. Base; 82. Airframe; 83. Vision module. Detailed Implementation

[0019] To enable those skilled in the art to better understand the technical solution of this utility model, the present utility model will be further described in detail below with reference to the accompanying drawings.

[0020] like Figure 1-4 As shown in the figure, an alarm monitoring system for flight training provided by this utility model includes a fuselage 1, wings 2 on both sides of the fuselage 1, tail fins 3 on both sides of one end of the fuselage 1, a hatch cover 6 on the top of the fuselage 1 away from the tail fins 3, and a vertical tail 4 on the end of the fuselage 1 near the tail fins 3; air inlets 5 are provided on both sides of the fuselage 1, the air inlets 5 are located above the wings 2, a disc radar 7 is provided on the top of the fuselage 1, a control module is provided inside the disc radar 7, and a vision component 8 is provided on the bottom of the fuselage 1. The vision component 8 includes a base 81, a body 82 and a vision module 83. The base 81 is fixedly connected to the fuselage 1, the body 82 is detachably connected to the base 81, and the vision module 83 is embedded inside the body 82.

[0021] In this embodiment, the fuselage 1 is made of a lightweight aluminum alloy frame and carbon fiber skin composite structure. The overall streamlined design reduces air resistance. Wings 2 are provided on both sides of the fuselage 1. The wings 2 on both sides of the fuselage 1 are hinged to the main frame of the fuselage 1 through titanium alloy hinges. An angle adjustment mechanism is provided at the root of the wings 2. Tail wings 3 are provided on both sides of one end of the fuselage 1. The tail wings 3 on both sides of the tail of the fuselage 1 are symmetrically fixed to the mounting bracket of the tail section of the fuselage by high-strength bolts. A servo motor of model SERVO-2000 is embedded inside. A hatch cover 6 is provided at the top of the fuselage 1 away from the tail fin 3. The hatch cover 6 is connected to the edge of the hatch on the top of the fuselage 1 by a hinge. The hinge is made of 304 stainless steel to ensure wear resistance for long-term use. A vertical tail 4 is provided at one end of the fuselage 1 near the tail 3. The vertical tail 4 is vertically installed on the center line of the tail of the fuselage 1 near the wing 2 and is rigidly connected to the frame of the fuselage 1 by welding. A GPS-M8N satellite positioning module is installed on the top of the vertical tail 4, which can obtain the aircraft's position information in real time. Air inlets 5 are provided on both sides of the fuselage 1. The air inlets 5 are located above the wings 2. Specifically, the air inlets 5 are located above the leading edge of the wings 2. They have a flat elliptical structure with their major axis parallel to the span of the wings 2. They are equipped with honeycomb-shaped flow-rectifying grilles inside, which can rectify the intake airflow. A disc radar 7 is installed on the top of the fuselage 1. The disc radar 7 is installed at the center of the top of the fuselage 1 and is connected to the frame of the fuselage 1 by a fixing rod, which can effectively reduce the impact of vibration during flight on the radar measurement accuracy. The disc radar 7 has an internal control module. The control module uses a microcontroller of model MCU-STM32H743 as its core, and integrates a 16-bit AD converter and a high-speed DMA controller. It can simultaneously process multiple sensor data from the radar and vision component 8. The bottom of the body 1 is provided with a vision component 8, which includes a base 81, a body 82 and a vision module 83. The base 81 is fixedly connected to the body 1, and the body 82 is detachably connected to the base 81. The vision component 8 is installed at the central axis position at the bottom of the body 1. The base 81 is fixedly connected to the mounting flange at the bottom of the body 1 by four countersunk bolts. The base 81 and the body 82 are connected by a quick-release buckle structure, which can complete the disassembly and assembly of the vision component within 30 seconds. The vision module 83 is embedded inside the body 82, and the vision module 83 is embedded in a sealed cavity inside the body 82.

[0022] Specifically, the vision module 83 includes a high-definition camera and an infrared imager. The high-definition camera is used to acquire color visual images in visible light environments. The high-definition camera is a 12-megapixel industrial camera of model CAM-HD1200, equipped with an 8mm fixed-focus lens, a frame rate of up to 30fps, and supports autofocus. The infrared imager is used to acquire infrared visual images in low light or nighttime environments. Both the high-definition camera and the infrared imager are electrically connected to the control module. The infrared imager uses an uncooled focal plane array detector of model IR-640 with a resolution of 640×512 and a detection wavelength range of 8-14μm. It can achieve clear imaging within a range of 50 meters in completely dark environments.

[0023] Specifically, the disc radar 7 includes a radar antenna and a signal processing unit. The radar antenna is used to transmit radar waves and receive reflected echoes. The radar antenna is a 24GHz millimeter-wave radar of model R-24G with a beamwidth of 90° horizontally and 30° vertically. The detection range can reach 100 meters and it can track 32 targets simultaneously. The signal processing unit is used at least to process the reflected echoes and generate environmental data containing obstacle distance and speed information. The disc radar 7 is electrically connected to the control module. The signal processing unit uses a DSP-TMS320 digital signal processor, which can process the reflected echoes in real time and generate environmental data containing obstacle distance, speed, and azimuth angle. The data update frequency is 10Hz.

[0024] Specifically, the control module is also connected to an alarm device, which includes a sound alarm and a light alarm. The sound alarm is installed inside the body 1 and is used to emit a buzzer alarm sound at a preset frequency. The sound alarm uses a piezoelectric buzzer of model Buzzer-12V, which can emit a 3kHz buzzer alarm sound of 85dB. The light alarm is located on the top of the unit 1 and uses red LED beads to emit flashing alarm lights. The light alarm uses 6 high-brightness red LED beads of model LED-R5, which are arranged in a ring on the warning light holder on the top of the unit 1, and the flashing frequency is 1Hz.

[0025] Specifically, a sealing strip is provided on the inside of the hatch cover 6. When the hatch cover 6 is closed, the sealing strip fits tightly against the edge of the hatch on the side of the fuselage 1, thus sealing the internal space of the fuselage 1.

[0026] Specifically, the hatch cover 6 is equipped with a locking mechanism, which includes a latch and a buckle. The latch is located at the free end of the hatch cover 6, and the buckle is located at the corresponding position on the fuselage 1. When the hatch cover 6 is closed, the latch and the buckle engage to lock and fix the hatch cover 6.

[0027] Working steps: 1. Open the hatch cover 6 on the top of fuselage 1 to enter the cockpit, check all internal components to ensure that all equipment is in normal condition, and close the internal seal of fuselage 1. 2. Start the power supply system of the fuselage 1, and activate the circular radar 7, vision component 8 and control module in sequence. Wait for the radar antenna of the circular radar 7 to start emitting radar waves and the high-definition camera and infrared imager inside the fuselage 82 of the vision component 8 to start normally. 3. The radar antenna of the disc radar 7 continuously transmits radar waves. After receiving the echoes reflected from surrounding obstacles, the signal processing unit processes the echoes to generate environmental data containing the distance and speed of the obstacles, which is then transmitted to the control module in real time. IV. The high-definition camera of the vision component 8 in visible light environment or infrared imager in low light or nighttime environment collects visual images of the flight environment and transmits them to the control module via the airframe 82. 5. The control module performs synchronous analysis of radar data and visual images. If no risk is identified, it continues to receive and process data. 6. If obstacles or other risks are detected, immediately send a command to the alarm device to trigger the sound alarm 1 to emit a preset frequency buzzer alarm sound inside the body 1, and at the same time activate the red LED light on the top of the body 1 to emit a flashing alarm light. VII. Alarm Response and Handling After triggering an alarm, the pilot receives the audible and visual alarm signals, combines the cockpit instrument data with visual observation, judges the type and distance of the risk, and adjusts the flight attitude in a timely manner, such as changing altitude or heading, to avoid the risk. 8. The control module continuously monitors changes in risk; if the risk is eliminated, the alarm will automatically stop. 9. If the risk has not been eliminated, keep the alarm status active and continue to update obstacle data until the pilot completes the avoidance maneuver and the risk signal disappears; 10. After the flight training is completed and the aircraft lands, shut down the power supply system of fuselage 1, and then shut down the control module, circular radar 7, and vision component 8 in sequence. After the equipment is completely powered off, open the hatch cover 6.

[0028] The foregoing description only illustrates certain exemplary embodiments of the present invention. Undoubtedly, those skilled in the art can modify the described embodiments in various ways without departing from the spirit and scope of the present invention. Therefore, the above drawings and descriptions are illustrative in nature and should not be construed as limiting the scope of protection of the claims of the present invention.

Claims

1. An alarm monitoring system for flight training, comprising an airframe (1), characterized in that, The fuselage (1) is provided with wings (2) on both sides, and tail fins (3) are provided on both sides of one end of the fuselage (1). A hatch cover (6) is provided on the top of the fuselage (1) away from the tail fins (3), and a vertical tail (4) is provided on the end of the fuselage (1) close to the tail fins (3). Air inlets (5) are provided on both sides of the fuselage (1). The air inlets (5) are located above the wings (2). A disc radar (7) is provided on the top of the fuselage (1). A control module is provided inside the disc radar (7). A vision component (8) is provided on the bottom of the fuselage (1). The vision component (8) includes a base (81), a body (82), and a vision module (83). The base (81) is fixedly connected to the fuselage (1). The body (82) is detachably connected to the base (81). The vision module (83) is embedded inside the body (82).

2. The alarm monitoring system for flight training according to claim 1, characterized in that, The vision module (83) includes a high-definition camera and an infrared imager. The high-definition camera is used at least to acquire color visual images in visible light environments, and the infrared imager is used at least to acquire infrared visual images in low light or nighttime environments. Both the high-definition camera and the infrared imager are electrically connected to the control module.

3. The alarm monitoring system for flight training according to claim 1, characterized in that, The disc radar (7) includes a radar antenna and a signal processing unit. The radar antenna is used to transmit radar waves and receive reflected echoes. The signal processing unit is used to process the reflected echoes and generate environmental data containing obstacle distance and speed information. The disc radar (7) is electrically connected to the control module.

4. The alarm monitoring system for flight training according to claim 1, characterized in that, The control module is also connected to an alarm device, which includes a sound alarm and a light alarm. The sound alarm is located inside the body (1) and is used to emit a buzzing alarm sound at a preset frequency. The light alarm is located on the top of the body (1) and uses red LED beads to emit a flashing alarm light.

5. The alarm monitoring system for flight training according to claim 1, characterized in that, The inner side of the hatch cover (6) is provided with a sealing strip. When the hatch cover (6) is closed, the sealing strip is tightly fitted with the hatch edge on the side of the fuselage (1) to achieve the sealing of the internal space of the fuselage (1).

6. The alarm monitoring system for flight training according to claim 1, characterized in that, The hatch cover (6) is provided with a locking mechanism, which includes a latch and a buckle. The latch is located at the free end of the hatch cover (6), and the buckle is located at the corresponding position on the fuselage (1).

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