An emergency command alarm unmanned aerial vehicle system

Abstract

The application relates to an emergency command alarm unmanned aerial vehicle system, and relates to the technical field of unmanned aerial vehicle systems, which comprises a machine body, the bottom surface of the machine body is fixedly connected with a connecting frame, the outer surface of the connecting frame is fixedly installed with a first control block, and the inner wall of the connecting frame is rotationally connected with a fixing frame. The application is provided with the machine body, the connecting frame, the first control block, the second control block, the fixing frame, a multifunctional camera and other components. The fixing frame is horizontally rotated through the first control block, and the multifunctional camera is vertically adjusted through the second control block. The two components cooperatively form a dead-angle-free monitoring range. In an emergency scene, the visual angle can be quickly switched. The solar panel and the monitoring block and other components are arranged, so that the emergency unmanned aerial vehicle can quickly respond, accurately identify and safely operate in a complex environment, reliable data support is provided for emergency decision-making, and the effect of reducing equipment loss and operation risk can be achieved.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) systems technology, and in particular to an UAV system for emergency command and alarm purposes. Background Technology

[0002] The alarm drone system is an intelligent equipment system that integrates functions such as flight platform, monitoring and perception, data transmission, and alarm triggering. It is mainly used to quickly detect and identify dangerous or abnormal situations in various scenarios, and issue alarm signals through preset mechanisms or manual intervention, while assisting in subsequent emergency response and command and dispatch.

[0003] Traditional emergency command relies on manual patrols, fixed monitoring equipment, or satellite remote sensing. However, manual patrols are slow and risky; fixed monitoring has limited coverage and is easily affected by terrain or damage; and satellite remote sensing has shortcomings such as poor timeliness and insufficient resolution, making it difficult to meet the needs of emergency scenarios for "real-time dynamic information".

[0004] Therefore, a new approach is needed to solve this problem. Summary of the Invention

[0005] The purpose of this application is to provide an unmanned aerial vehicle (UAV) system for emergency command and alarm purposes, which has advantages such as easy disassembly and solves (problem).

[0006] This application provides an emergency command and alarm drone system with the following technical solution: It includes a body, a connecting frame fixedly connected to the bottom surface of the body, a first control block fixedly installed on the outer surface of the connecting frame, a fixed frame rotatably connected to the inner wall of the connecting frame, an output end of the first control block fixedly connected to the fixed frame, a multi-functional camera rotatably connected to the inner wall of the fixed frame, a second control block fixedly installed on the outer surface of the fixed frame, an output end of the second control block fixedly connected to the multi-functional camera, a solar panel fixedly installed on the upper surface of the body, and a monitoring block fixedly installed on the upper surface of the body.

[0007] By adopting the above technical solutions, the fuselage is made of carbon fiber composite material, which reduces weight, lowers energy consumption, and improves endurance while ensuring structural strength. The addition of an energy management module through the solar panel allows for intelligent adjustment of the solar panel's working mode based on the fuselage's battery status, avoiding energy waste. The first and second control blocks integrate high-precision servo motors, which, together with gyroscope sensors, enable the multi-functional camera to rotate without blind spots and hover stably for shooting. The first control block can adjust the rotation of the mounting bracket inside the connecting frame, and the second control block can adjust the rotation of the multi-functional camera inside the mounting bracket. The monitoring block integrates professional monitoring equipment such as gas detectors and radiation detectors to monitor parameters such as the concentration of harmful gases and radiation dose in real time, providing data support for emergency response, according to different emergency scenarios.

[0008] Preferably, a plurality of connecting blocks are fixedly connected to the outer surface of the machine body, a propeller is fixedly installed on the inner wall of each connecting block, and a lighting lamp is fixedly installed on the bottom surface of each propeller.

[0009] By adopting the above technical solution, the propeller is composed of a connecting plate and a propeller blade. The connection between the connecting block and the fuselage adopts an elastic vibration damping structure, which can reduce the transmission of vibration generated by the high-speed rotation of the propeller to the fuselage, avoid affecting the stability of precision equipment such as cameras and monitoring blocks, and reduce energy waste caused by fuselage resonance. Multiple sets of connecting blocks can increase the power failure redundancy algorithm. When a set of propellers fails, the system automatically adjusts the speed and angle of the remaining propellers to maintain the fuselage balance and force a landing in a safe area, avoiding equipment crashes during emergency missions. The lighting can enhance the detection and imaging capabilities of the multi-functional camera.

[0010] Preferably, a control module and a signal enhancement module are fixedly installed on the outer surface of the machine body.

[0011] By adopting the above technical solutions, the control module can automatically match preset task templates according to real-time scenarios. Through the preset linkage logic of the control module, it can achieve rapid response in propeller attitude adjustment, camera angle synchronous adjustment, lighting supplementation, and real-time data transmission. By setting up a signal enhancement module, it can automatically switch to low-Earth orbit satellite communication when ground base stations are paralyzed in remote mountainous areas or disasters, thereby enhancing the control of the aircraft.

[0012] Preferably, a battery slot is provided on the bottom surface of the body, and a cover is fixedly installed on the inner wall of the battery slot.

[0013] By adopting the above technical solution, an energy management chip is integrated into the battery compartment, which is linked with the solar panel on the top of the aircraft. During daytime flight, the solar panel generates electricity to prioritize the operation of the equipment, and the excess electricity is stored in the battery. At night or in low light environments, the battery is used to provide power, maximizing the use of clean energy to extend the flight range. The cover adopts a waterproof and dustproof sealing structure, and a high and low temperature resistant silicone sealing ring is added to the connection between the cover and the battery compartment. A labyrinth-style drainage channel is designed to prevent rainwater from seeping into the battery compartment in scenarios such as heavy rain and floods, while also preventing dust and mud from clogging the interface. The cover is installed with a quick-release cover locking mechanism, which replaces the traditional screw fixation and adopts a double-action locking mechanism of pressing and rotating. Operators can open the cover and replace the battery in a short time without tools, which is especially suitable for rapid power replenishment in emergency missions.

[0014] Preferably, the outer surface of the machine body has two sliding grooves, the inner wall of each sliding groove is slidably connected to a support frame, the outer surface of each support frame is fixedly connected to a support rod, and the end of each support rod away from the corresponding support frame is fixedly connected to a foot.

[0015] By adopting the above technical solution, the support frame can be initially installed in the corresponding slide groove by sliding it horizontally along the corresponding slide groove. The legs are made of non-slip and wear-resistant material, and the bottom is equipped with a high friction coefficient rubber pad to avoid slipping when taking off and landing on muddy or slippery ground. At the same time, the edges of the legs are rounded to prevent them from scratching trapped personnel or obstacles during take-off and landing.

[0016] Preferably, each of the support frames has two connecting columns fixedly connected to its outer surface, and each connecting column has a slidably connected insert rod to its inner wall. The outer surface of each insert rod is slidably connected to the corresponding support frame.

[0017] By adopting the above technical solution, by pulling the insertion rod, the insertion rod will slide vertically along the corresponding connecting column, and it will also slide along the corresponding support frame.

[0018] Preferably, each of the slides has two slots on its inner wall, and the inner wall of each slot is inserted into a corresponding rod. Each support frame has a push plate on its outer side, and the outer surface of each push plate is fixedly connected to the corresponding rod.

[0019] By adopting the above technical solution, during the installation of the support frame, the support frame can be quickly fixed by inserting the rod into the corresponding slot, and the rod on the same side can be moved synchronously by pushing the push plate.

[0020] Preferably, each of the inserts has a spring fitted onto its outer surface, with the top end of each spring fixedly connected to the corresponding insert and the other end fixedly connected to the corresponding connecting post.

[0021] By adopting the above technical solution, during the process of pushing the push plate, the push plate will drive the corresponding insertion rod to move. At this time, the spring will be compressed. During this process, when the support frame is installed, when the slot and the corresponding insertion rod are on the same central axis, the push plate is released, and the spring will push the corresponding insertion rod into the slot under its rebound force. This allows the tripod to be quickly disassembled and assembled, facilitating replacement and maintenance.

[0022] In summary, this application includes at least one of the following beneficial technical effects:

[0023] This emergency command and alarm drone system comprises a fuselage, a connecting frame, a first control block, a second control block, a fixed frame, and a multi-functional camera. The fixed frame rotates horizontally via the first control block, while the multi-functional camera adjusts vertically via the second control block. Together, they form a comprehensive monitoring range without blind spots. In emergency scenarios, the system can quickly switch perspectives. By incorporating solar panels and monitoring blocks, the emergency drone can respond rapidly, accurately identify objects, and operate safely in complex environments, providing reliable data support for emergency decision-making and reducing equipment wear and operational risks. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the overall structure of this application;

[0025] Figure 2 This is a schematic diagram of the solar panel structure in this application;

[0026] Figure 3 This is a schematic diagram of the propeller structure of this application;

[0027] Figure 4 This is a schematic diagram of the tripod structure for this application;

[0028] Figure 5 This is a schematic diagram of the spring structure of this application.

[0029] In the picture:

[0030] 1. Body; 2. Control module; 3. Signal enhancement module; 4. Connecting frame; 5. Fixing frame; 6. First control block; 7. Second control block; 8. Multifunctional camera; 9. Battery compartment; 10. Cover; 11. Connecting block; 12. Propeller; 13. Lighting lamp; 14. Solar panel; 15. Monitoring block; 16. Slide; 17. Slot; 18. Support frame; 19. Connecting column; 20. Insert rod; 21. Spring; 22. Push plate; 23. Support rod; 24. Leg. Detailed Implementation

[0031] The following is in conjunction with the appendix Figure 1 - Appendix Figure 5 This application will be described in further detail below.

[0032] Example 1: An unmanned aerial vehicle (UAV) system for emergency command and alarm, referring to Figure 1 , Figure 2 , Figure 4 The system includes a body 1, a connecting frame 4 fixedly connected to the bottom surface of the body 1, a first control block 6 fixedly mounted on the outer surface of the connecting frame 4, a fixed frame 5 rotatably connected to the inner wall of the connecting frame 4, the output end of the first control block 6 fixedly connected to the fixed frame 5, a multi-functional camera 8 rotatably connected to the inner wall of the fixed frame 5, a second control block 7 fixedly mounted on the outer surface of the fixed frame 5, the output end of the second control block 7 fixedly connected to the multi-functional camera 8, a solar panel 14 fixedly mounted on the upper surface of the body 1, and a monitoring block 15 fixedly mounted on the upper surface of the body 1. The body 1 is made of carbon fiber composite material, which reduces weight, lowers energy consumption, and improves endurance while ensuring structural strength. The solar panel 14 can increase energy supply. The management module intelligently adjusts the working mode of the solar panel 14 based on the battery status of the main body 1 to avoid energy waste. The first control block 6 and the second control block 7 integrate high-precision servo motors, which, together with the gyroscope sensor, enable the multi-functional camera 8 to rotate without blind spots and hover for shooting. The first control block 6 can adjust the rotation of the fixing frame 5 inside the connecting frame 4, and the second control block 7 can adjust the rotation of the multi-functional camera 8 inside the fixing frame 5. The monitoring block 15 can be configured to meet the needs of different emergency scenarios. It integrates professional monitoring equipment such as gas detectors and radiation detectors to monitor parameters such as the concentration of harmful gases and radiation dose in real time, providing data support for emergency response.

[0033] Example 2: An unmanned aerial vehicle (UAV) system for emergency command and alarm purposes. Please refer to [link / reference]. Figure 1 , Figure 2 , Figure 3 Several connecting blocks 11 are fixedly connected to the outer surface of the body 1. Each connecting block 11 has a propeller 12 fixedly installed on its inner wall. Each propeller 12 has a lighting lamp 13 fixedly installed on its bottom surface. The propeller 12 is composed of a connecting plate and a spiral blade. The connection between the connecting block 11 and the body 1 adopts an elastic shock-absorbing structure to reduce the transmission of vibration generated by the high-speed rotation of the propeller 12 to the body, so as to avoid affecting the stability of precision equipment such as the multi-functional camera 8 and the monitoring block 15. At the same time, it reduces the energy waste caused by the resonance of the body. Multiple sets of connecting blocks 11 can increase the power failure redundancy algorithm. When a set of propellers 12 fails, the system automatically adjusts the speed and angle of the remaining propellers 12 to maintain the balance of the body and force it to land in a safe area to avoid equipment crashing in emergency missions. The lighting lamp 13 can enhance the detection and imaging of the multi-functional camera 8.

[0034] Please see Figure 1A control module 2 and a signal enhancement module 3 are fixedly installed on the outer surface of the aircraft 1. The control module 2 is configured to automatically match preset task templates according to real-time scenarios. Through the preset linkage logic of the control module 2, rapid responses can be achieved for propeller 12 attitude adjustment, multi-functional camera 8 angle synchronous adjustment, lighting 13 supplementary lighting, and real-time data transmission. By setting the signal enhancement module 3, it can automatically switch to low-orbit satellite communication when ground base stations are paralyzed in remote mountainous areas or disasters, thereby enhancing the control of the aircraft 1.

[0035] Please see Figure 4 , Figure 5 The bottom of the fuselage 1 has a battery compartment 9, and a cover 10 is fixedly installed on the inner wall of the battery compartment 9. The battery compartment 9 integrates an energy management chip, which is linked with the solar panel 14 on the top of the fuselage 1. During daytime flight, the solar panel 14 generates electricity to supply the equipment first, and the excess electricity is stored in the battery. At night or in low light environment, the battery is used to supply power alone, maximizing the use of clean energy to extend the flight range. The cover 10 adopts a waterproof and dustproof sealing structure. The connection between the cover 10 and the battery compartment 9 is equipped with a high and low temperature resistant silicone sealing ring and a labyrinth drainage channel is designed to prevent rainwater from seeping into the battery compartment 9 in the event of heavy rain or floods, and to prevent dust and mud from clogging the interface. The cover 10 is installed with a quick-release cover 10 locking mechanism. Instead of traditional screw fixing, it adopts a double-action locking mechanism of pressing and rotating. The operator can open the cover 10 to replace the battery in a short time without tools, which is especially suitable for rapid power replenishment in emergency missions.

[0036] Please see Figure 4 , Figure 5 Two slide grooves 16 are provided on the outer surface of the body 1. A support frame 18 is slidably connected to the inner wall of each slide groove 16. A support rod 23 is fixedly connected to the outer surface of each support frame 18. A foot 24 is fixedly connected to the end of each support rod 23 away from the corresponding support frame 18. The support frame 18 can be initially installed in the corresponding slide groove 16 by sliding the support frame 18 horizontally along the corresponding slide groove 16. The foot 24 is made of non-slip and wear-resistant material, and a high friction coefficient rubber pad is added to the bottom to avoid slipping when taking off and landing on muddy or slippery ground. At the same time, the edges of the foot 24 are rounded to prevent scratching trapped personnel or obstacles during take-off and landing.

[0037] Please see Figure 4 , Figure 5 Each support frame 18 has two connecting posts 19 fixedly connected to its outer surface. Each connecting post 19 has a sliding rod 20 slidably connected to its inner wall. The outer surface of each rod 20 is slidably connected to the corresponding support frame 18. By pulling the rod 20, the rod 20 will slide vertically along the corresponding connecting post 19 and will also slide along the corresponding support frame 18.

[0038] Please see Figure 4 , Figure 5 Each slide 16 has two slots 17 on its inner wall. The inner wall of each slot 17 is inserted into the corresponding rod 20. Each support frame 18 has a push plate 22 on its outer side. The outer surface of each push plate 22 is fixedly connected to the corresponding rod 20. During the installation of the support frame 18, the support frame 18 can be quickly fixed by inserting the rod 20 into the corresponding slot 17. Pushing the push plate 22 can drive the rod 20 on the same side to move synchronously.

[0039] Please see Figure 4 , Figure 5 Each insertion rod 20 has a spring 21 fitted on its outer surface. The top end of each spring 21 is fixedly connected to the corresponding insertion rod 20, and the other end is fixedly connected to the corresponding connecting post 19. When the push plate 22 is pushed, the push plate 22 will drive the corresponding insertion rod 20 to move. At this time, the spring 21 will be compressed. During this process, when the support frame 18 is installed, when the slot 17 and the corresponding insertion rod 20 are on the same central axis, the push plate 22 is released. The spring 21 will push the corresponding insertion rod 20 into the slot 17 under its rebound force. This allows the bracket 24 to be quickly disassembled and assembled, which is convenient for replacement and maintenance.

[0040] The implementation principle of this application embodiment is as follows: The multi-functional camera 8 is the core information acquisition component. It achieves dual-dimensional adjustment through the rotational connection between the fixed frame 5 and the connecting frame 4. The first control block 6 drives the fixed frame 5 to rotate relative to the connecting frame 4, achieving horizontal angle adjustment of the camera. The second control block 7 drives the multi-functional camera 8 to rotate relative to the fixed frame 5, achieving vertical angle adjustment of the multi-functional camera 8. Combined with the monitoring block 15, it can collect images and environmental data from the emergency scene from all directions, providing real-time information for command. The propeller 12 provides flight power for the drone, and the bottom lighting 13 can provide illumination at night or in dim environments, working in conjunction with the multi-functional camera 8 to enhance... Image clarity ensures nighttime emergency operations. The solar panel 14 on the upper surface of the body 1 can convert solar energy into electrical energy under sunlight to replenish battery power and extend battery life, making it especially suitable for long-term emergency duty scenarios. The support frame 18 can slide along the slide groove 16. During this process, by pushing the push plate 22, it will drive the corresponding insertion rod 20 to slide horizontally along the corresponding connecting post 19. The spring 21 will be compressed until the slot 17 and the corresponding insertion rod 20 are on the same central axis. At this time, the push plate 22 is released, and the spring 21 will push the corresponding insertion rod 20 into the slot 17 under its rebound force, so as to complete the quick disassembly and replacement of the tripod 24.

Claims

1. An unmanned aerial vehicle (UAV) system for emergency command and alarm, comprising an airframe (1), characterized in that: A connecting frame (4) is fixedly connected to the bottom surface of the body (1). A first control block (6) is fixedly installed on the outer surface of the connecting frame (4). A fixed frame (5) is rotatably connected to the inner wall of the connecting frame (4). The output end of the first control block (6) is fixedly connected to the fixed frame (5). A multi-functional camera (8) is rotatably connected to the inner wall of the fixed frame (5). A second control block (7) is fixedly installed on the outer surface of the fixed frame (5). The output end of the second control block (7) is fixedly connected to the multi-functional camera (8). A solar panel (14) is fixedly installed on the upper surface of the body (1). A monitoring block (15) is fixedly installed on the upper surface of the body (1).

2. The emergency command and alarm unmanned aerial vehicle system according to claim 1, characterized in that: The outer surface of the body (1) is fixedly connected with a number of connecting blocks (11), and a propeller (12) is fixedly installed on the inner wall of each connecting block (11), and a lighting lamp (13) is fixedly installed on the bottom surface of each propeller (12).

3. The emergency command and alarm unmanned aerial vehicle system according to claim 2, characterized in that: A control module (2) is fixedly installed on the outer surface of the body (1), and a signal enhancement module (3) is fixedly installed on the outer surface of the body (1).

4. The emergency command and alarm unmanned aerial vehicle system according to claim 3, characterized in that: The bottom surface of the body (1) is provided with a battery slot (9), and a cover (10) is fixedly installed on the inner wall of the battery slot (9).

5. The emergency command and alarm unmanned aerial vehicle system according to claim 4, characterized in that: Two grooves (16) are opened on the outer surface of the body (1). A support frame (18) is slidably connected to the inner wall of each groove (16). A support rod (23) is fixedly connected to the outer surface of each support frame (18). A foot (24) is fixedly connected to the end of each support rod (23) away from the corresponding support frame (18).

6. The emergency command and alarm unmanned aerial vehicle system according to claim 5, characterized in that: Two connecting columns (19) are fixedly connected to the outer surface of each of the support frames (18), and a plug rod (20) is slidably connected to the inner wall of each of the connecting columns (19). The outer surface of each plug rod (20) is slidably connected to the corresponding support frame (18).

7. The emergency command and alarm unmanned aerial vehicle system according to claim 6, characterized in that: Each of the slides (16) has two slots (17) on its inner wall. The inner wall of each slot (17) is inserted into the corresponding rod (20). Each of the support frames (18) has a push plate (22) on its outer side. The outer surface of each push plate (22) is fixedly connected to the corresponding rod (20).

8. The emergency command and alarm unmanned aerial vehicle system according to claim 7, characterized in that: Each of the insert rods (20) has a spring (21) fitted on its outer surface. The top end of each spring (21) is fixedly connected to the corresponding insert rod (20), and the other end is fixedly connected to the corresponding connecting post (19).

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