A fireproof mechanism applied to a range-extending unmanned aerial vehicle

Abstract

The application relates to the technical field of unmanned planes, in particular to a fireproof mechanism applied to a range-extending unmanned plane, which comprises an unmanned plane body, a machine cabin is arranged in the interior of the unmanned plane body, photoelectric sensors and temperature sensors are arranged on the two sides of the interior of the machine cabin, the oil tank is of a concave structure, a fireproof mechanism is arranged outside the oil tank, the fireproof mechanism comprises a fire-retardant layer arranged outside the oil tank, one side of the oil tank is fixedly connected with an oil filling port, a one-way oil valve is arranged in the interior of the oil filling port, a spraying assembly is arranged around the periphery of the unmanned plane body, and a driving device connected with the spraying assembly is arranged in the interior of the machine cabin. When the unmanned plane normally flies or falls and collides, after the generator generates an ignition state, the temperature sensor and the photoelectric sensor detect high temperature and smoke, the driving device is rapidly controlled to act on the spraying assembly, the generator and the oil tank are aimed at fire extinguishing, and the unmanned plane is cooled in time, the fire can be detected and treated in time, and the fire spreading is avoided.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more particularly to a fire protection mechanism for range-extended UAVs. Background Technology

[0002] Range-extended drones are a special type of drone that has a longer endurance than traditional drones. They are usually equipped with additional power systems, such as larger batteries or generators, to provide longer flight time and greater distance. If the drone is involved in a collision and causes turbulence, it is easy for liquid in the fuel tank to overflow, and the generator may also cause a fire.

[0003] In the prior art, patent CN211705675U discloses a fireproof and flame-retardant device for agricultural plant protection drones, including a protective frame; an oil tank mounted on the protective frame; and a flame-retardant device mounted on the surface of the oil tank. The flame-retardant device includes a shell, inside which are respectively arranged a water storage chamber, a reaction chamber, and a fire extinguishing agent storage chamber. Heat-conducting plates are provided on both sides of the shell, and one side of the heat-conducting plate penetrates through the outside of the shell and extends into the interior of the reaction chamber. Several water-guiding holes are opened on the side of the heat-conducting plate extending into the interior of the reaction chamber. Tap water is provided inside the water storage chamber, quicklime is provided inside the reaction chamber, and fire extinguishing agent is provided inside the fire extinguishing agent storage chamber.

[0004] The aforementioned structure is equipped with flame-retardant devices to extinguish fires in the drone in a timely manner. However, when the drone crashes and spontaneously combusts, the special characteristics of range-extended drones mean that the generator and fuel tank are easily ignited, causing fires to start quickly and making it impossible to deal with them in time, resulting in more serious losses. Summary of the Invention

[0005] In view of this, the purpose of this invention is to propose a fire prevention mechanism for range-extended unmanned aerial vehicles (UAVs) to solve the problem that, due to the special characteristics of range-extended UAVs, such as the generator and fuel tank being easily ignited and the rapid spread of fires, it is impossible to deal with the ignition stage of a fire in a timely manner when the UAV crashes and spontaneously combusts.

[0006] Based on the above objectives, the present invention provides a fire protection mechanism for range-extended unmanned aerial vehicles (UAVs), comprising a UAV body, a generator electrically connected to a battery inside the UAV body fixedly mounted on the UAV body, the generator being used to provide power to the battery, a support frame fixedly mounted on the bottom of the UAV body, a fuel tank connected to the generator fixedly mounted on the support frame, a cabin being opened inside the UAV body, and a ventilation opening being opened on the outside of the UAV body, the ventilation opening being connected to the cabin, and photoelectric sensors and temperature sensors being respectively installed on both sides inside the cabin. The fuel tank has a concave structure and a fireproof mechanism is provided on the outside of the fuel tank. The fireproof mechanism includes a flame-retardant layer installed on the outside of the fuel tank. A foam box is provided above the flame-retardant layer in the groove of the fuel tank. The foam box is detachably installed on the bottom of the drone body. A fuel inlet is fixedly connected to one side of the fuel tank. A one-way fuel valve is provided inside the fuel inlet. The drone body is surrounded by a jet assembly, one end of which is fixedly connected to a bent pipe, and the two ends of the bent pipe correspond to a generator and a fuel tank, respectively. The cabin is equipped with a drive unit connected to the spray assembly. Both the spray assembly and the drive unit are equipped with at least six sets. The photoelectric sensor and temperature sensor are electrically connected to the spray assembly and the drive unit. The drive unit is used to drive the spray assembly to extinguish the fire.

[0007] Preferably, the spraying assembly includes a dry powder canister and a cold air canister, which are respectively fixedly installed on the engine compartment. The bottom end of the dry powder canister is fixedly connected to a connecting pipe one, and the bottom end of the cold air canister is fixedly connected to a connecting pipe two. Both the first and second connecting pipes are fixedly connected to a spray nozzle. Multiple sets of nozzles are fixedly installed at the end of the spray nozzles. The multiple sets of nozzles penetrate the outside of the engine compartment, and the multiple sets of nozzles are connected to the bend pipe.

[0008] Preferably, a one-way solenoid valve is provided at the connection between the first connecting pipe and the spray nozzle, and a one-way solenoid valve is provided at the connection between the second connecting pipe and the third connecting pipe. The one-way solenoid valve is electrically connected to the photoelectric sensor, and the one-way solenoid valve is electrically connected to the temperature sensor.

[0009] Preferably, there are at least three sets of nozzles, the bends are inclined and distributed around the outside of the drone body, and both the nozzles and the bends are made of stainless steel.

[0010] Preferably, the drive device includes a fixed plate frame fixedly installed inside the cabin, a socket seat is sleeved on the top of the fixed plate frame, a piston rod is slidably installed on the top of the socket seat, a through rod is fixedly installed on one side of the socket seat, the through rod passes through one side of the socket seat, and a compression spring is sleeved on the outside of the through rod, one end of the compression spring is connected to the socket seat, and the other end is connected to the piston rod. A swing arm is movably installed on one side of the fixed plate frame. The end of the swing arm abuts against the sleeve seat, and a limit block is fixedly installed at the bottom of the swing arm. A stop block corresponding to the limit block is fixedly installed on the piston column. An electric telescopic rod is fixedly installed at the bottom of the fixed plate frame. The electric telescopic rod is electrically connected to the photoelectric sensor. One end of the electric telescopic rod abuts against one side of the socket. A sliding rod is fixedly installed on the other side of the bottom of the socket. A sleeve is sleeved on the outside of the sliding rod. An electromagnet is installed inside the sleeve. The electromagnet is electrically connected to the temperature sensor. A magnetic block corresponding to the electromagnet is installed inside the sliding rod.

[0011] Preferably, the top of the socket and one end of the slide rod are both inclined, the top of the stop is inclined, and the limiting block is a triangular structure.

[0012] Preferably, the magnetic poles of the magnetic block are opposite to those of the electromagnet, and the sleeve is fixedly installed on the inner wall of the cabin.

[0013] Preferably, the flame-retardant layer is filled with a flame retardant, and the flame-retardant layer is connected to the UAV body by a thread.

[0014] The beneficial effects of this invention are as follows: During normal flight of the drone or in the event of a crash, after the generator ignites, the temperature sensor and photoelectric sensor detect high temperature and smoke, and quickly control the drive device to activate the spray component. Dry powder and cold air are sprayed from both ends of the curved pipe to extinguish the fire in the generator and fuel tank, and to cool the drone in time. It can detect and deal with the fire in time. At the same time, the fuel tank is prevented from being directly ignited due to the internal one-way valve and the flame-retardant layer. If the fuel tank is destroyed in the event of continuous impact of the drone, and the foam box breaks under the impact and the foam inside overflows, the fire source will be extinguished directly, preventing the fire from spreading further. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only for this invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 This is a three-dimensional structural diagram of the entire invention; Figure 2 This is a three-dimensional structural diagram of the cabin of the present invention; Figure 3 This is a schematic diagram of the planar structure of the engine room and fuel tank of the present invention; Figure 4 This is a schematic diagram of the internal structure of the cabin of the present invention; Figure 5 For the present invention Figure 4 A magnified structural diagram of part A in the middle; Figure 6 This is a schematic diagram of the internal structure of the fire extinguishing component of the present invention.

[0017] The components in the diagram are labeled as follows: 1. UAV body; 2. Generator; 3. Fuel tank; 4. Cabin; 5. Support frame; 6. Photoelectric sensor; 7. Temperature sensor; 8. Ventilation vent; 9. Spray assembly; 10. Dry powder canister; 11. Cooling canister; 12. Connecting pipe one; 13. Connecting pipe two; 14. One-way solenoid valve one; 15. One-way solenoid valve two; 16. Spray nozzle; 17. Piston column; 18. Nozzle; 19. Bend; 20. Drive unit; 21. Fixing plate frame; 22. Socket; 23. Through rod; 24. Compression spring; 25. Electric telescopic rod; 26. Slide rod; 27. Sleeve; 28. Electromagnet; 29. ​​Magnetic block; 30. Stop block; 31. Limiting block; 32. Swing rod; 33. Fireproof mechanism; 34. Foam box; 35. Flame retardant layer; 36. Oil inlet; 37. One-way oil valve. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to specific embodiments.

[0019] like Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 and Figure 6 As shown, a fire protection mechanism for extended-range unmanned aerial vehicles (UAVs) includes a UAV body 1, a generator 2 electrically connected to a battery inside the UAV body 1 fixedly installed on the UAV body 1, the generator 2 being used to provide power to the battery, a support frame 5 fixedly installed at the bottom of the UAV body 1, a fuel tank 3 connected to the generator 2 fixedly installed on the support frame 5, a cabin 4 opened inside the UAV body 1, and a ventilation opening 8 opened outside the UAV body 1, the ventilation opening 8 being connected to the cabin 4, and photoelectric sensors 6 and temperature sensors 7 being respectively installed on both sides inside the cabin 4. The fuel tank 3 has a concave structure and a fireproof mechanism 33 is provided on the outside of the fuel tank 3. The fireproof mechanism 33 includes a flame-retardant layer 35 installed on the outside of the fuel tank 3. A foam box 34 is provided above the flame-retardant layer 35 in the groove of the fuel tank 3. The foam box 34 is detachably installed on the bottom of the drone body 1. An oil filling port 36 is fixedly connected to one side of the fuel tank 3. A one-way oil valve 37 is provided inside the oil filling port 36. The drone body 1 is surrounded by a jet assembly 9. One end of the jet assembly 9 is fixedly connected to a bent pipe 19, and the two ends of the bent pipe 19 correspond to the generator 2 and the fuel tank 3, respectively. The interior of the cabin 4 is equipped with a drive unit 20 connected to the spray assembly 9. Both the spray assembly 9 and the drive unit 20 are equipped with at least six sets. The photoelectric sensor 6 and the temperature sensor 7 are electrically connected to the spray assembly 9 and the drive unit 20. The drive unit 20 is used to drive the spray assembly 9 to extinguish the fire.

[0020] In this embodiment, when the drone crashes, the fuel tank 3 is prevented from igniting due to the internal one-way valve 37 and the flame-retardant layer 35. If the fuel tank 3 is destroyed during continuous impact, and the generator 2 and fuel tank 3 ignite, the temperature sensor 7 and photoelectric sensor 6 simultaneously detect high temperature and smoke, and quickly control the drive device 20 to activate the spray assembly 9. Dry powder and cold air are sprayed from both ends of the bend 19 to extinguish the fire in the generator 2 and fuel tank 3, and cool the drone in time. The foam box 34 breaks under the impact and the internal foam overflows, directly extinguishing the fire source and preventing further spread of the fire.

[0021] As one implementation method, such as Figure 2 , Figure 4 , Figure 5 As shown, the spray assembly 9 includes a dry powder tank 10 and a cold air tank 11, which are respectively fixedly installed on the engine compartment 4. The bottom end of the dry powder tank 10 is fixedly connected to a connecting pipe 12, and the bottom end of the cold air tank 11 is fixedly connected to a connecting pipe 13. The ends of the connecting pipe 12 and the connecting pipe 13 are both fixedly connected to a spray nozzle 16. Multiple sets of nozzles 18 are fixedly installed at the ends of the spray nozzles 16. The multiple sets of nozzles 18 penetrate the outside of the engine compartment 4 and are connected to the bend pipe 19.

[0022] In this embodiment, the smoke is monitored by the photoelectric sensor 6. In the event of a fire, the connecting pipe 12 and the connecting pipe 2 13 are opened simultaneously. The cold air in the cold air tank 11 enters the spray nozzle 16, and the dry powder in the dry powder tank 10 enters the spray nozzle 16 and mixes. The cold air and dry powder are then sprayed out through the nozzle 18 and the two ends of the bend pipe 19 to cool the generator 2 and extinguish the fire.

[0023] As one implementation method, such as Figure 3 , Figure 4 , Figure 5 As shown, a one-way solenoid valve 14 is provided at the connection between the connecting pipe 12 and the spray nozzle 16, and a one-way solenoid valve 15 is provided at the connection between the connecting pipe 13 and the connecting pipe 14. The one-way solenoid valve 14 is electrically connected to the photoelectric sensor 6, and the one-way solenoid valve 15 is electrically connected to the temperature sensor 7.

[0024] In this embodiment, the smoke generated by the flame is detected by the photoelectric sensor 6, which controls the one-way solenoid valve 14 to open. At the same time, the high temperature generated by the generator 2 is transmitted to the temperature sensor 7 through the engine compartment 4, and the temperature sensor 7 controls the one-way solenoid valve 25 to open. Different sprays are generated in different states.

[0025] As one implementation method, such as Figure 2 , Figure 3 , Figure 4 , Figure 5 As shown, there are at least three sets of nozzles 18, and the bends 19 are set at an angle and are distributed around the outside of the drone body 1. Both nozzles 18 and bends 19 are made of stainless steel.

[0026] In this embodiment, stainless steel nozzles 18 and bends 19 are used to increase the structural strength of the external spray assembly 9 and prevent damage when the drone crashes. The two sets of external nozzles 18 correspond to the fuel tank 3 and the generator 2, and the middle nozzle is a divergent type to prevent flames from remaining in a distant area during firefighting.

[0027] As one implementation method, such as Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 and Figure 6 As shown, the drive unit 20 includes a fixed plate frame 21 fixedly installed inside the engine compartment 4. A socket 22 is sleeved on the top of the fixed plate frame 21. A piston rod 17 is slidably installed on the top of the socket 22. A through rod 23 is fixedly installed on one side of the socket 22. The through rod 23 passes through one side of the socket 22, and a compression spring 24 is sleeved on the outside of the through rod 23. One end of the compression spring 24 is connected to the socket 22, and the other end is connected to the piston rod 17. A swing arm 32 is movably installed on one side of the fixed plate frame 21. The end of the swing arm 32 abuts against the sleeve seat 22, and a limit block 31 is fixedly installed at the bottom of the swing arm 32. A stop block 30 corresponding to the limit block 31 is fixedly installed on the piston column 17. An electric telescopic rod 25 is fixedly installed at the bottom of the fixed plate frame 21. The electric telescopic rod 25 is electrically connected to the photoelectric sensor 6. One end of the electric telescopic rod 25 abuts against one side of the socket 22. A slide rod 26 is fixedly installed on the other side of the bottom of the socket 22. A sleeve 27 is sleeved on the outside of the slide rod 26. An electromagnet 28 is installed inside the sleeve 27. The electromagnet 28 is electrically connected to the temperature sensor 7. A magnetic block 29 corresponding to the electromagnet 28 is installed inside the slide rod 26.

[0028] In this embodiment, by pulling the socket 22 to move on the fixed plate 21, the piston rod 17 on the socket 22 moves at the same time. When the movement is made, after the limiting block 31 at the bottom of the swing rod 32 contacts the stop block 30, the socket 22 continues to move. The internal compression spring 24 is compressed between the socket 22 and the piston rod 17, and the cold air or dry powder inside the piston rod 17 is pushed out to extinguish the fire.

[0029] As one implementation method, such as Figure 6 As shown, the top of the socket 22 and one end of the slide rod 26 are both set with slopes, the top of the stop block 30 is set with slopes, and the limit block 31 has a triangular structure.

[0030] In this embodiment, once the temperature exceeds a certain threshold, the inclined surface of one end of the swing rod 32 contacts the inclined surface of the socket 22, and the swing rod 32 tilts upward. The limiting block 31 disengages from the stop block 30, and under the compression of the compression spring 24, the stored force pushes out the cold air or dry powder inside the piston column 17. The cold air or dry powder is then sprayed out through both ends of the nozzle 18 and the connecting bend 19. The fire extinguishing speed is faster in the stored state. As one implementation method, such as Figure 5 and Figure 6 As shown, the magnetic poles of the magnetic block 29 are opposite to those of the magnetic field of the electromagnet 28. The sleeve 27 is fixedly installed on the inner wall of the cabin 4, and a spring connects the slide rod 26 and the sleeve 27.

[0031] In this embodiment, as the temperature increases, the resistance of the temperature sensor 7 usually decreases, resulting in a larger current flowing through the electromagnet 28. The electromagnet 28 inside the sleeve 27 attracts the slide rod 26 to move. At this time, the slide rod 26 pulls the socket 22 to move on the fixed plate 21, driving the spray assembly 9 to spray out.

[0032] As one implementation method, such as Figure 3 As shown, the flame retardant layer 35 is filled with flame retardant, and the flame retardant layer 35 is connected to the UAV body 1 by threads.

[0033] In this embodiment, the internal one-way valve 37 prevents the internal liquid from flowing back out of the oil tank 3, and the flame-retardant layer 35 prevents the oil tank 3 from being ignited. The flame-retardant layer 35 wraps around the oil tank 3, improving protection.

[0034] Working principle: During normal flight of the UAV body 1, the generator 2 runs continuously. The high temperature generated by the generator 2 is transferred to the temperature sensor 7 through the cabin 4. The temperature sensor 7 controls the one-way solenoid valve 15 to open, and the cold air in the cold air tank 11 enters the spray nozzle 16. When the temperature is higher, the resistance of the temperature sensor 7 usually decreases, and the current flowing through the electromagnet 28 is larger. The electromagnet 28 in the sleeve 27 attracts the slide rod 26 to move. At this time, the slide rod 26 pulls the socket 22 to move on the fixed plate 21, and the movable part on the socket 22... The piston rod 17 moves simultaneously. When the limit block 31 at the bottom of the rocker arm 32 contacts the stop block 30, the socket 22 continues to move. The internal compression spring 24 is compressed between the socket 22 and the piston rod 17 until the temperature exceeds a certain threshold. After the inclined surface of one end of the rocker arm 32 contacts the inclined surface of the socket 22, the rocker arm 32 tilts upward, the limit block 31 disengages from the stop block 30, and the compressed spring 24 stores the cold air inside the piston rod 17 and pushes it out. The cold air is sprayed out through the nozzle 18 and the two ends of the bend pipe 19 to cool the generator 2. If a spontaneous combustion occurs due to an internal fault in generator 2, the smoke generated by the flames is detected by photoelectric sensor 6. Photoelectric sensor 6 controls one-way solenoid valve 14 to open. At the same time, the high temperature generated by generator 2 is transmitted to temperature sensor 7 through engine compartment 4. Temperature sensor 7 controls one-way solenoid valve 25 to open. Similarly, electric telescopic rod 25 pushes socket 22 to move, accelerating the charging time of piston column 17, enabling fire extinguishing at the fastest speed. Dry ice and cold air from inside nozzle 16 are sprayed out simultaneously, passing through both ends of bend pipe 19, targeting generator 2 for fire extinguishing and cooling. When the drone crashes, the fuel tank 3 is prevented from igniting due to the internal one-way valve 37 and the flame-retardant layer 35. If the fuel tank 3 is destroyed during continuous impact and a fire breaks out in the generator 2 and fuel tank 3, as above, during the ignition stage, the temperature sensor 7 monitors the fire. During the combustion stage, the temperature sensor 7 and the photoelectric sensor 6 detect high temperature and smoke simultaneously, and quickly control the drive device 20 to activate the spray assembly 9. Dry powder and cold air are sprayed from both ends of the bend pipe 19 to extinguish the fire in the generator 2 and fuel tank 3, and cool the drone in time. At the same time, the foam box 34 breaks under the impact and the foam inside overflows, directly extinguishing the fire source and preventing it from spreading further.

[0035] Those skilled in the art should understand that the discussion of any of the above embodiments is merely exemplary and is not intended to imply that the scope of the invention (including the claims) is limited to these examples; within the framework of the invention, the technical features of the above embodiments or different embodiments can also be combined, the steps can be implemented in any order, and there are many other variations of the different aspects of the invention as described above, which are not provided in the details for the sake of brevity.

[0036] This invention is intended to cover all such substitutions, modifications, and variations that fall within the broad scope of the appended claims. Therefore, any omissions, modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this invention should be included within the scope of protection of this invention.

Claims

1. A fire protection mechanism for a range-extended unmanned aerial vehicle (UAV), comprising a UAV body (1), wherein a generator (2) electrically connected to a battery inside the UAV body (1) is fixedly installed on the UAV body (1), the generator (2) being used to provide power to the battery, and a support frame (5) is fixedly installed at the bottom of the UAV body (1), wherein a fuel tank (3) connected to the generator (2) is fixedly installed on the support frame (5), characterized in that, The UAV body (1) has a cabin (4) inside and a vent (8) outside. The vent (8) is connected to the cabin (4). Photoelectric sensors (6) and temperature sensors (7) are respectively installed on both sides of the cabin (4). The fuel tank (3) has a concave structure and a fireproof mechanism (33) is provided on the outside of the fuel tank (3). The fireproof mechanism (33) includes a flame-retardant layer (35) installed on the outside of the fuel tank (3). A foam box (34) is provided above the flame-retardant layer (35) in the groove of the fuel tank (3). The foam box (34) is detachably installed on the bottom of the drone body (1). An oil filling port (36) is fixedly connected to one side of the fuel tank (3). A one-way oil valve (37) is provided inside the oil filling port (36). The drone body (1) is surrounded by a jet assembly (9), one end of which is fixedly connected to a bend (19), and the two ends of the bend (19) correspond to the generator (2) and the fuel tank (3) respectively. The cabin (4) is equipped with a drive device (20) connected to the spray assembly (9). Both the spray assembly (9) and the drive device (20) are equipped with at least six sets. The photoelectric sensor (6) and the temperature sensor (7) are electrically connected to the spray assembly (9) and the drive device (20). The drive device (20) is used to drive the spray assembly (9) to extinguish the fire. The drive device (20) includes a fixed plate frame (21) fixedly installed inside the cabin (4). A socket (22) is sleeved on the top of the fixed plate frame (21). A piston column (17) is slidably installed on the top of the socket (22). A through rod (23) is fixedly installed on one side of the socket (22). The through rod (23) passes through one side of the socket (22), and a compression spring (24) is sleeved on the outside of the through rod (23). One end of the compression spring (24) is connected to the socket (22), and the other end is connected to the piston column (17). A swing arm (32) is movably installed on one side of the fixed plate frame (21). The end of the swing arm (32) abuts against the sleeve seat (22), and a limit block (31) is fixedly installed at the bottom of the swing arm (32). A stop block (30) corresponding to the limit block (31) is fixedly installed on the piston column (17). An electric telescopic rod (25) is fixedly installed at the bottom of the fixed plate frame (21). The electric telescopic rod (25) is electrically connected to the photoelectric sensor (6). One end of the electric telescopic rod (25) abuts against one side of the socket (22). A slide rod (26) is fixedly installed on the other side of the bottom of the socket (22). A sleeve (27) is sleeved on the outside of the slide rod (26). An electromagnet (28) is provided inside the sleeve (27). The electromagnet (28) is electrically connected to the temperature sensor (7). A magnetic block (29) corresponding to the electromagnet (28) is provided inside the slide rod (26). The magnetic poles of the magnetic block (29) are opposite to those of the electromagnet (28). The sleeve (27) is fixedly installed on the inner wall of the cabin (4). The top of the socket (22) and one end of the slide rod (26) are both set with slopes, the top of the stop block (30) is set with slopes, and the limiting block (31) has a triangular structure.

2. The fire protection mechanism for extended-range unmanned aerial vehicles according to claim 1, characterized in that, The spraying assembly (9) includes a dry powder tank (10) and a cold air tank (11) respectively fixedly installed on the engine compartment (4). The bottom end of the dry powder tank (10) is fixedly connected to a connecting pipe (12), and the bottom end of the cold air tank (11) is fixedly connected to a connecting pipe (13). The ends of the connecting pipe (12) and the connecting pipe (13) are both fixedly connected to a spray nozzle (16). The ends of the spray nozzle (16) are fixedly installed with multiple sets of nozzles (18). The multiple sets of nozzles (18) penetrate the outside of the engine compartment (4), and the multiple sets of nozzles (18) are connected to the bend pipe (19).

3. A fire protection mechanism for extended-range unmanned aerial vehicles according to claim 2, characterized in that, A one-way solenoid valve (14) is provided at the connection between the first connecting pipe (12) and the spray nozzle (16), and a one-way solenoid valve (15) is provided at the connection between the second connecting pipe (13). The one-way solenoid valve (14) is electrically connected to the photoelectric sensor (6), and the one-way solenoid valve (15) is electrically connected to the temperature sensor (7).

4. A fire protection mechanism for extended-range unmanned aerial vehicles according to claim 2, characterized in that, There are at least three sets of nozzles (18), the bends (19) are inclined and distributed around the outside of the UAV body (1), and both the nozzles (18) and the bends (19) are made of stainless steel.

5. A fire protection mechanism for extended-range unmanned aerial vehicles according to claim 1, characterized in that, The flame-retardant layer (35) is filled with flame retardant, and the flame-retardant layer (35) is connected to the UAV body (1) by threads.

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