Autonomous flight fire extinguisher
By designing an autonomous flying fire extinguisher, which employs a combination of inspection sensors and a pipeline-free fire extinguishing method, the problem of short fire warning time and high deployment cost in existing fire protection technologies is solved. This enables rapid and accurate fire suppression and extinguishing, and it is suitable for various locations.
Patent Information
- Application Number
- CN202520251933.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-02-18
- Publication Date
- 2026-02-03
- Estimated Expiration
- 2035-02-18
AI Technical Summary
Existing fire protection technologies suffer from problems such as short fire warning times and the need for costly pipeline deployment, making it difficult to effectively suppress fires and hindering their widespread application.
Design an autonomous flying fire extinguisher that uses a combination of inspection sensors and a pipeline-free fire extinguishing method. It achieves accurate fire detection and simultaneous fire extinguishing through a rotor protection ring, rotor, fire extinguishing ammunition magazine, and fire extinguishing cylinder magazine.
It enables rapid and accurate detection of fires and suppression of initial fires and deflagrations without human intervention, reduces equipment costs, is suitable for various locations, and avoids the limitations of pipeline deployment.
Smart Images
Figure CN223861186U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model belongs to the technical field of fire fighting, and particularly relates to a self -flying fire extinguisher. BACKGROUND
[0002] Among various disasters, fire is one of the main disasters that most frequently and most generally threaten public safety and social development. At present, the "smoke sensing", "spraying", "fire extinguisher", "fire hydrant", "water cannon" and the like of the wisdom fire fighting are applied to all aspects of social life in large quantities, and play a very important role in protecting people's life and property safety. However, for decades, the technical innovation in the field of fire fighting has been difficult, and the traditional smoke sensing and spraying mode is still deployed in large quantities according to the regulations. These devices can be described as "effective" but "effect limited", otherwise a large number of fires would not occur. At present, the wisdom fire fighting technology and equipment are already common, but an important factor is ignored, that is, both the spraying and the water cannon need to deploy the pipeline to supply high-pressure water, which has high cost and great limitation. It is difficult to require the scenes that are not suitable for pipeline deployment, such as temples, cultural relic units and temporary nine small places. In addition, the comprehensive cost of various wisdom fire fighting devices is very high, mainly the deployment and operation and maintenance of pipelines
[0003] Although the existing technology is also based on the technology of "early warning", due to the backward technology, the interval between the early warning and the occurrence of fire is too short, which cannot give enough time to realize fire suppression and fire extinguishing, and finally a large number of fires occur. SUMMARY
[0004] The utility model is realized as follows:
[0005] The utility model provides a kind of self -flying fire extinguisher, wherein, including aircraft and aircraft platform, the aircraft is disc dish shape, periphery is provided with the anti-collision elastic protection ring, for the anti-collision protection of the aircraft;The center of the aircraft is provided with fire extinguishing agent tank, charging interface electrode, aircraft convex end locking groove and fire extinguishing agent filling port;The aircraft is provided with multiple rotor protection rings, fire extinguishing bomb bin and fire extinguishing bottle bin;The aircraft and the aircraft platform are separately arranged, the convex end locking groove on the aircraft is inserted into the center hole on the aircraft platform, and the electromagnetic lock control end of the electromagnetic lock on one side is inserted into the convex end locking groove to be connected, for locking the aircraft.
[0006] On the basis of the above technical scheme, the self -flying fire extinguisher of the utility model can also be improved as follows:
[0007] The outer circumference of the anti-collision elastic protection ring is equipped with a front light, a multi-directional obstacle avoidance sensor, an optical tracking sensor, an optical tracking correction sensor, and a flight trajectory indicator light strip.
[0008] Furthermore, the upper part of the aircraft is equipped with obstacle avoidance sensors and return-to-home alignment Hall sensors.
[0009] Furthermore, the aircraft is equipped with a main control computer, flight controller, lithium battery, high voltage generator, electromagnetic throwing controller, and fine water mist pump.
[0010] Furthermore, the rotor protection ring is equipped with a motor, blades, downlights, and a motor bracket.
[0011] Furthermore, the bottom of the aircraft is equipped with an obstacle avoidance sensor, a temperature and humidity sensor, a smoke sensor, a carbon monoxide sensor, a brightness sensor, a megaphone, a microphone, a two-dimensional gimbal, fire extinguishing bombs, fire extinguishing bottles, and fine water mist nozzles.
[0012] Furthermore, the two-dimensional gimbal is provided with a thermal imaging sensor opening, and a 360° rotating motor and a sensor bracket are provided inside, which are connected to a 180° motor. The 180° motor is equipped with a thermal imaging sensor, a visible light sensor and a three-band flame sensor.
[0013] Furthermore, the aircraft platform is connected to the mounting plate and the cabin by screws, and is equipped with an electromagnetic locking device, a laser tracking gimbal, a power supply, control components, a heat source and loading mechanism, a water injection mechanism, a laser tube, a return-to-home alignment sensor, a 360° motor for the laser tracking gimbal, a 180° motor for the laser tracking gimbal, and a 360° rotating support for the laser tracking gimbal.
[0014] Furthermore, the fire extinguishing ammunition compartment and the fire extinguishing bottle compartment are respectively loaded into the fire extinguishing ammunition and the fire extinguishing bottle. The upper part of the fire extinguishing ammunition and the fire extinguishing bottle is provided with a bayonet, and the control terminal of the internal electromagnetic throwing controller extends into the bayonet.
[0015] Furthermore, the fine water mist pump is used to control the fire extinguishing agent tank to spray, the high-pressure generator is used to control the launch of the mounted fire extinguishing bomb, and the electromagnetic throwing controller is used to control the ejection of the mounted fire extinguishing bomb and the throwing of the mounted fire extinguishing bottle.
[0016] Compared with existing technologies, the beneficial effects of the autonomous flying fire extinguisher provided by this utility model are:
[0017] 1. By adopting a combined inspection method and a combination of sensors, fires can be accurately detected within the scanning range, eliminating false alarms;
[0018] 2. It can detect fires at a straight-line distance of 50m and extinguish fires at a distance of 50 meters simultaneously, suppressing and extinguishing initial fires and deflagrations in the first instance without human intervention;
[0019] 3. No need to deploy high-pressure pipelines and booster equipment; it can extinguish fires independently or in a network based on its own fire extinguishing devices.
[0020] This invention addresses the problem that while existing technologies are also based on "early warning" systems, their outdated technology results in insufficient time for fire suppression and extinguishing due to the short interval between warning and fire occurrence, ultimately leading to numerous fires. It also solves the problem that while automatic water cannon technology allows for unattended, automated fire suppression, it requires the standardized deployment of pipelines and pressurization equipment, resulting in high costs, limited locations, and hindering widespread application. Attached Figure Description
[0021] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the description of the embodiments of this utility model will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0022] Figure 1 A schematic diagram of the disc-shaped butterfly structure of the aircraft.
[0023] Figure 2 This is a schematic diagram of the upper structure of the aircraft.
[0024] Figure 3 A schematic diagram of the internal structure of a portion of the aircraft;
[0025] Figure 4 A schematic diagram of the through-section structure of the aircraft.
[0026] Figure 5 This is a schematic diagram of the bottom structure of the aircraft.
[0027] Figure 6 A schematic diagram of the locking structure between the aircraft and the aircraft platform;
[0028] Figure 7 A schematic diagram of the structure of some detection sensors on an aircraft.
[0029] Figure 8 This is a schematic diagram of the internal structure of the aircraft platform;
[0030] The attached diagram lists the components represented by each number as follows:
[0031] 0100. Aircraft; 0101. Collision-resistant elastic protective ring; 0102. Front spotlight; 0103. Multi-directional obstacle avoidance sensor; 0104. Optical tracking sensor; 0105. Optical tracking correction sensor; 0106. Flight trajectory indicator light strip; 0107. Obstacle avoidance sensor; 0108. Return-to-home alignment Hall sensor; 0109. Fire extinguishing agent tank; 0110. Charging interface electrode; 0111. Aircraft protruding end locking slot; 0112. Fire extinguishing agent filling port; 0113. Main control computer; 011 4. Flight controller; 0115. Lithium battery; 0116. High voltage generator; 0117. Electromagnetic throwing controller; 0118. Rotor protection ring; 0119. Motor; 0120. Propeller blades; 0121. Downward spotlight; 0122. Fire extinguishing ammunition magazine; 0123. Fire extinguishing bottle magazine; 0124. Motor bracket; 0125. Downward obstacle avoidance sensor; 0126. Temperature and humidity sensor; 0127. Smoke sensor; 0128. Carbon monoxide sensor; 0129. Brightness sensor; 0130. Communicator; 01 31. Microphone; 0132. 2D Pan-Tilt Unit; 0133. Thermal Imaging Sensor Opening; 0134. Mounted Fire Extinguishing Grenade; 0135. Mounted Fire Extinguishing Bottle; 0136. Fine Water Mist Nozzle; 0137. Protruding End Locking Slot; 0138. Center Hole; 0139. Electromagnetic Locking Device; 0140. Electromagnetic Locking Device Control Terminal; 0141. 360° Rotation Motor; 0142. Sensor Bracket; 0143. 180° Motor; 0144. Thermal Imaging Sensor; 0145. Visible Light Sensor; 0146. Three-band flame sensor; 0152, mounting plate; 0153, hull; 0154, electromagnetic locking device; 0155, laser tracking gimbal; 0156, power supply; 0157, control components; 0161, loading mechanism; 0162, water injection mechanism; 0163, laser tube; 0164, return-to-home alignment sensor; 0165, 360° motor for laser tracking gimbal; 0166, 180° motor for laser tracking gimbal; 0167, 360° rotating support for laser tracking gimbal; 0200, aircraft platform. Detailed Implementation
[0032] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings.
[0033] like Figures 1-8The illustration shows an embodiment of an autonomous flying fire extinguisher provided by this utility model. In this embodiment, it includes a flying vehicle 0100 and a flying vehicle platform. The flying vehicle 0100 is disc-shaped and has an anti-collision elastic protective ring 0101 around its perimeter for anti-collision protection. The center of the flying vehicle 0100 has an extinguishing agent tank 0109, a charging interface electrode 0110, a flying vehicle protrusion end locking groove 0111, and an extinguishing agent filling port 0112. The flying vehicle 0100 has multiple rotor protection rings 0118, an extinguishing ammunition magazine 0122, and an extinguishing bottle magazine 0123 running through it. The flying vehicle 0100 is separated from the flying vehicle platform. The protrusion end locking groove 0137 on the flying vehicle 0100 is inserted into the central hole 0138 on the flying vehicle platform. The electromagnetic locking device control end 0140 on one side of the electromagnetic locking device 0139 is inserted into the protrusion end locking groove 0137 for connection, for locking the flying vehicle 0100.
[0034] In the above technical solution, the outer circumference of the anti-collision elastic protection ring 0101 is respectively provided with a front spotlight 0102, a multi-directional obstacle avoidance sensor 0103, an optical tracking sensor 0104, an optical tracking correction sensor 0105, and a flight trajectory indicator light strip 0106.
[0035] Furthermore, in the above technical solution, the upper part of the aircraft 0100 is equipped with an obstacle avoidance sensor 0107 and a return-to-home alignment Hall sensor 0108.
[0036] Furthermore, in the above technical solution, the aircraft 0100 is equipped with a main control computer 0113, a flight controller 0114, a lithium battery 0115, a high-voltage generator 0116, an electromagnetic throwing controller 0117, and a fine water mist pump.
[0037] Furthermore, in the above technical solution, the rotor protection ring 0118 is equipped with a motor 0119, a blade 0120, a downlight 0121, and a motor bracket 0124.
[0038] Furthermore, in the above technical solution, the bottom of the aircraft 0100 is equipped with an obstacle avoidance sensor 0125, a temperature and humidity sensor 0126, a smoke sensor 0127, a carbon monoxide sensor 0128, a brightness sensor 0129, a megaphone 0130, a microphone 0131, a two-dimensional gimbal 0132, a fire extinguishing bomb 0134, a fire extinguishing bottle 0135, and a fine water mist nozzle 0136.
[0039] Furthermore, in the above technical solution, the two-dimensional gimbal 0132 is provided with a thermal imaging sensor opening 0133, and a 360° rotating motor 0141 and a sensor bracket 0142 are provided inside, which are connected to a 180° motor 0143. The 180° motor 0143 is provided with a thermal imaging sensor 0144, a visible light sensor 0145 and a three-band flame sensor 0146.
[0040] Furthermore, in the above technical solution, the aircraft platform is connected to the mounting plate 0152 and the cabin 0153 by screws, and is equipped with an electromagnetic locking device 0154, a laser tracking gimbal 0155, a power supply 0156, a control component 0157, a heat source and loading mechanism 0161, a water injection mechanism 0162, a laser tube 0163, a return-to-home alignment sensor 0164, a 360° motor for the laser tracking gimbal 0165, a 180° motor for the laser tracking gimbal 0166, and a 360° rotating support for the laser tracking gimbal 0167.
[0041] Furthermore, in the above technical solution, the fire extinguishing ammunition compartment 0122 and the fire extinguishing bottle compartment 0123 are respectively loaded into the fire extinguishing ammunition 0134 and the fire extinguishing bottle 0135. The upper part of the fire extinguishing ammunition 0134 and the fire extinguishing bottle 0135 is equipped with a bayonet, and the control end of the internal electromagnetic throwing controller 0117 extends into the bayonet.
[0042] Furthermore, in the above technical solution, the fine water mist pump is used to control the fire extinguishing agent tank 0109 to spray, the high-pressure generator 0116 is used to control the launch of the mounted fire extinguishing bomb 0134, and the electromagnetic throwing controller 0117 is used to control the ejection of the mounted fire extinguishing bomb 0134 and the throwing of the mounted fire extinguishing bottle 0135.
[0043] Figure 1 This is a schematic diagram of the disc-shaped structure of the aircraft. The aircraft has a disc-shaped structure with anti-collision materials deployed around its circumference to ensure that it will not cause harm to people and environmental facilities when flying indoors. It can perform "headless flight mode" or "headed flight mode" as needed. Anti-collision sensors, laser navigation sensors, and lights are deployed on the sides.
[0044] Figure 2 This is a schematic diagram of the upper structure of the aircraft; it is equipped with an upward collision avoidance sensor and two alignment sensors for the return flight platform. These sensors can be infrared transmitters and receivers, or Hall effect sensors and magnets, to enable the aircraft to accurately return to its original position on the flight platform.
[0045] Figure 3 This is a schematic diagram of the internal structure of the aircraft; the main control computer, flight controller, electromagnetic actuator, lithium battery, fire extinguishing agent tank, fine water mist pump, etc. are all deployed inside the aircraft and are balanced according to weight.
[0046] Figure 4 This is a schematic diagram of the through-type structure of the aircraft. Fire extinguishing bombs and fire extinguishing bottles can be loaded from the top of the aircraft platform. To prevent the propellers from causing damage to people and environmental facilities during flight, a through-type protective ring is adopted. The motor, propellers, downward lighting, etc. are deployed in the center of the protective ring. The propellers can also serve as a fire extinguishing device for primary flames.
[0047] Figure 5 This is a schematic diagram of the bottom structure of the aircraft; it is equipped with a 360° rotating gimbal with built-in detection devices, smoke sensors, carbon monoxide sensors, temperature sensors, humidity sensors, brightness sensors, a loudspeaker, a microphone, etc.
[0048] Figure 6 This is a schematic diagram of the locking structure between the aircraft and the aircraft platform. The protruding part of the aircraft is inserted into the central hole of the flight platform. The control pin of the electromagnetic lock is inserted into the bayonet of the protruding end of the aircraft, locking the aircraft in place and preventing it from being moved, stolen, or dropped. When takeoff is required, the electromagnetic lock is energized to retract the control pin, releasing the restriction on the aircraft. The aircraft then flies downwards and detaches from the flight platform.
[0049] Figure 7 This is a schematic diagram of the structure of some of the detection sensors on the aircraft. The aircraft is normally fixed on the flight platform. The 360° cloud platform deployed under the aircraft drives the internal 180° detector bracket to rotate. Thermal imaging cameras, visible light cameras, and three-band flame sensors are deployed on the detector bracket to achieve all-round three-dimensional inspection and detection of the 360° perimeter and 180° vertically.
[0050] Figure 8 This is a schematic diagram of the internal structure of the aircraft platform. Normally, the aircraft is positioned below the platform. The platform's mounting plate, fixed to the ceiling and supports, is equipped with satellite signal penetration and rain protection. Inside, an electromagnetic locking control device and a laser tube gimbal are deployed. The laser tube gimbal can perform 360° and 180° rotations to ensure the laser beam maintains line-of-sight automatic tracking and navigation within the aircraft, directing it to return to base. Inside the platform, a switching power supply is installed, drawing in mains power to provide power to the aircraft and charge its lithium battery.
[0051] Specifically, the principle of this utility model is as follows: Under normal conditions, the locking groove 0111 of the central protrusion of the aircraft 0100 is restricted by the electromagnetic locking device 0154 and cannot be disengaged; the two-dimensional gimbal 0132 at the bottom of the aircraft, driven by the 360° motor 0141, rotates from 0° to 360° and then from 360° back to 0° according to the parameters set by the background system, thereby driving the sensor bracket 0142 to rotate. The sensor bracket 0142 can perform a 180° rotation, driven by the 180° motor 0143. The thermal imaging sensor 0144 and the visible light camera 0145 are mounted on the sensor bracket 0142. The three-band flame sensor 0146 rotates from 0° to 180° and then back from 180° to 0° according to the angle set by the backend system, achieving all-round fire point inspection of the surrounding area and the top and bottom. At the same time, the smoke sensor 0127 and carbon monoxide sensor 0128 deployed at the bottom detect smoke and carbon monoxide produced by combustion. The 360° motor 0165 of the laser tracking gimbal 0155 rotates to keep the laser tracking gimbal aligned with the direction of the aircraft's two-dimensional gimbal 0132, and then drives the laser tube 0163 to emit light. At this time, the 180° motor 0166 of the laser gimbal is driven to adjust the angle of the laser tube 0163. When the optical tracking sensor 0104 of aircraft 0100 receives a signal, it unlocks; aircraft 0100 takes off downwards and detaches from the aircraft platform. The three detection devices (thermal imaging, camera, and flame sensor) inside the two-dimensional gimbal 0132 of aircraft 0100 continue to track the fire point. During flight, obstacle avoidance sensors in all directions prevent aircraft 0100 from colliding with people or environmental facilities; the electromagnetic thrower 0117 retracts its control pin and throws the fire extinguishing bottle 0135 to extinguish the fire; or the high-voltage generator 0116 is activated, connecting to the fire extinguishing device 0134 through contacts to launch dry powder for fire extinguishing, and then... The electromagnetic launcher 0117 retracts its control pin, ejecting the spent casing of the fired fire extinguishing projectile 0134; or it activates the fine water mist pump to spray the fire extinguishing agent inside the fire extinguishing agent tank 0109 from the nozzle 0136 to achieve fine water mist fire extinguishing; or it lowers its flight altitude above the fire point, and under the high-speed rotation of the motor 0119, it uses the downwind force through the rotor blades 0120 to extinguish the fire by rotating to a stop; after the fire is extinguished, the aircraft 0100 locks onto the aircraft platform 0200, and the charging ring electrode below the refueling port 0122 connects to the charging circuit to power the aircraft and charge the lithium battery 0115.
Claims
1. An autonomous flying fire extinguisher, characterized in that, The system includes an aircraft (0100) and an aircraft platform. The aircraft (0100) is disc-shaped and has an elastic anti-collision protection ring (0101) around its perimeter for collision protection. At the center of the aircraft (0100) are a fire extinguishing agent tank (0109), a charging interface electrode (0110), a locking groove at the protruding end of the aircraft (0111), and a fire extinguishing agent filling port (0112). Multiple rotor guards are continuously installed throughout the aircraft (0100). The aircraft (0118), fire extinguishing ammunition compartment (0122), and fire extinguishing bottle compartment (0123) are separated from the aircraft platform. The protruding end locking groove (0137) on the aircraft (0100) is inserted into the center hole (0138) on the aircraft platform. The electromagnetic locker control end (0140) on one side of the electromagnetic locker (0139) is inserted into the protruding end locking groove (0137) for connection, which is used to lock the aircraft (0100).
2. The autonomous flying fire extinguisher according to claim 1, characterized in that, The outer circumference of the anti-collision elastic protective ring (0101) is respectively provided with a front spotlight (0102), a multi-directional obstacle avoidance sensor (0103), an optical tracking sensor (0104), an optical tracking correction sensor (0105), and a flight trajectory indicator light strip (0106).
3. The autonomous flying fire extinguisher according to claim 2, characterized in that, The upper part of the aircraft (0100) is equipped with an obstacle avoidance sensor (0107) and a return-to-home alignment Hall sensor (0108).
4. The autonomous flying fire extinguisher according to claim 3, characterized in that, The aircraft (0100) is equipped with a main control computer (0113), a flight controller (0114), a lithium battery (0115), a high-voltage generator (0116), an electromagnetic throwing controller (0117), and a fine water mist pump.
5. The autonomous flying fire extinguisher according to claim 4, characterized in that, The rotor protection ring (0118) contains a motor (0119), blades (0120), downlight (0121), and motor bracket (0124).
6. The autonomous flying fire extinguisher according to claim 5, characterized in that, The bottom of the aircraft (0100) is equipped with an obstacle avoidance sensor (0125), a temperature and humidity sensor (0126), a smoke sensor (0127), a carbon monoxide sensor (0128), a brightness sensor (0129), a megaphone (0130), a microphone (0131), a two-dimensional gimbal (0132), a fire extinguishing bomb (0134), a fire extinguishing bottle (0135), and a fine water mist nozzle (0136).
7. The autonomous flying fire extinguisher according to claim 6, characterized in that, The two-dimensional gimbal (0132) is provided with a thermal imaging sensor opening (0133), and a 360° rotating motor (0141) and a sensor bracket (0142) are provided inside, which are connected to a 180° motor (0143). The 180° motor (0143) is provided with a thermal imaging sensor (0144), a visible light sensor (0145) and a three-band flame sensor (0146).
8. The autonomous flying fire extinguisher according to claim 7, characterized in that, The aircraft platform is connected to the mounting plate (0152) and the cabin (0153) by screws. The interior is equipped with an electromagnetic locking device (0154), a laser tracking gimbal (0155), a power supply (0156), a control component (0157), a heat source and loading mechanism (0161), a water injection mechanism (0162), a laser tube (0163), a return alignment sensor (0164), a 360° motor for the laser tracking gimbal (0165), a 180° motor for the laser tracking gimbal (0166), and a 360° rotating support for the laser tracking gimbal (0167).
9. An autonomous flying fire extinguisher according to claim 8, characterized in that, The fire extinguishing ammunition compartment (0122) and the fire extinguishing bottle compartment (0123) are respectively loaded into the fire extinguishing ammunition (0134) and the fire extinguishing bottle (0135). The upper part of the fire extinguishing ammunition (0134) and the fire extinguishing bottle (0135) is provided with a bayonet, and the control end of the electromagnetic throwing controller (0117) inside extends into the bayonet.
10. An autonomous flying fire extinguisher according to claim 9, characterized in that, The fine water mist pump is used to control the fire extinguishing agent tank (0109) to spray, the high pressure generator (0116) is used to control the launch of the mounted fire extinguishing bomb (0134), and the electromagnetic throwing controller (0117) is used to control the ejection of the mounted fire extinguishing bomb (0134) and the throwing of the mounted fire extinguishing bottle (0135).