A drone-borne time-delay detonation device

Abstract

This invention discloses a drone-borne delayed detonation device, belonging to the field of drone firefighting equipment technology. Through a separation mechanism, when the drone flies above the fire scene, it disconnects from the upper shell, allowing the upper and lower shells to fall freely. The traction rope pulls the movable rod through the hanging ring, causing the movable rod to compress the spring and move out of the sleeve rod. This causes the movable rod to disengage the positioning groove from the positioning pin, releasing the restriction of the positioning groove and positioning pin on the sleeve rod. At this time, the sleeve rod rotates under the torque generated by the release of energy under the detonation condition, and drives the drive gear to rotate through the second positioning sleeve. The drive gear drives the rotating ring to rotate in sequence through multiple driven gears. The rotating ring cuts the connecting part through the blade, throwing multiple fire extinguishing bombs out of the tank in sequence.

Description

Technical Field

[0001] This invention relates to the field of drone firefighting equipment technology, and in particular to a drone-borne delayed detonation device. Background Technology

[0002] With the widespread application of drones in forest fire prevention, high-rise fire fighting and other fields, drone-borne fire extinguishing bomb delivery devices have become an important part of fire fighting equipment. At present, domestic and foreign drone fire extinguishing bombs generally use electronic detonators or electronic delay circuits for detonation. Their triggering method relies on battery-powered electronic control modules to achieve delayed ignition function. However, in practical applications, the electronic triggering method has a high safety risk. First, the risk of battery thermal effect is prominent. When the drone operates above the fire, the ambient temperature rises sharply. The battery built into the electronic detonator is very prone to thermal runaway, which may cause the fire extinguishing bomb to explode accidentally on the rack, seriously threatening the flight safety of the drone. At the same time, the electronic components have poor environmental adaptability. The high temperature and continuous vibration in the fire working environment can easily cause the electronic components to malfunction, resulting in delayed failure or false triggering, and the triggering reliability is difficult to guarantee. Secondly, the battery poses a risk of spontaneous combustion. The core component of traditional fire extinguishing bombs relies on batteries for energy. In daily training, if the battery fails to disintegrate completely after the fire extinguishing bomb explodes in the air, the battery fragments scattered in the forest are difficult to find and clean up, and there is a risk of spontaneous combustion, which will further increase the safety hazards at the work site. Therefore, the existing electronic trigger fire extinguishing bombs have obvious shortcomings in terms of safety and environmental adaptability. Summary of the Invention

[0003] The purpose of this invention is to address the significant shortcomings of existing electronically triggered fire extinguishing bombs in terms of safety and environmental adaptability, and to propose a structure for an unmanned aerial vehicle (UAV)-borne time-delay detonation device.

[0004] To achieve the above objectives, the present invention employs the following technology: a drone-borne time-delay detonation device. It includes an upper shell that is movably mounted on a drone and a lower shell that is mounted on the upper shell. At least two canisters are mounted on the lower shell via a loading rack, and fire extinguishing bombs are installed inside the canisters. A separation mechanism is provided on the canisters, and the separation mechanism includes a rotating ring that is rotatably mounted on the canisters, and a blade is provided on the rotating ring. The fire extinguishing bomb is fixed in the tank by a positioning mechanism. The positioning mechanism includes a clip that is connected to the tank and the fire extinguishing bomb is connected by a connecting part. The upper housing is provided with at least two driving mechanisms, and the rotating ring is driven to rotate by the driving mechanisms. The lower housing is provided with a power mechanism that drives the driving mechanisms to rotate in sequence. The power mechanism includes a generator set on the lower housing. Before takeoff, the drone stores energy by rotating a preheating device and locks itself using a locking mechanism. When the drone flies above the fire, the locking mechanism unlocks, causing the preheating device to release energy with a delay and drive the second positioning sleeve to rotate. The second positioning sleeve drives the rotating ring to rotate through multiple driven gears in sequence. The rotating ring cuts the connecting part with a blade, throwing multiple fire extinguishing bombs out of the tank in sequence.

[0005] Further description of a drone-borne time-delay detonation device according to the above technology: The bottom of the tank is rotatably connected to a cover via an elastic hinge shaft. When the connection is not cut off, the fire extinguishing bomb is attached to the cover, and the cover is attached to the bottom of the tank via the elastic hinge shaft.

[0006] Further description of a drone-borne time-delay detonation device according to the above technology: The tank body has slots for inserting clips, and there are receiving cavities between adjacent slots. When the rotating ring is in the initial position, the blade is stored in the receiving cavity.

[0007] Further description of a drone-borne time-delay detonation device according to the above technology: The drive mechanism includes at least two fitting frames fixedly mounted on the upper housing, with a mounting platform rotatably mounted in the middle of the fitting frame, and a first rotating shaft mounted at each end of the mounting platform; Each of the first rotating shafts is rotatably provided with a driven gear via a first positioning sleeve. The first positioning sleeve is also provided with a fitting part, and a female shaft is installed at the end of the fitting part. The rotating ring is provided with a sub-shaft that cooperates with the main shaft via a connecting frame. When the torque generated by the release of energy is transmitted to the driven gear, it drives the rotating ring to rotate.

[0008] Further description of a drone-borne time-delay detonation device according to the above technology: The first positioning sleeve is embedded with a damping ring, and the first positioning sleeve is rotatably connected to the first rotating shaft through the damping ring to provide additional damping.

[0009] Further description of a drone-borne time-delay detonation device according to the above technology: The first rotating shaft is rotatably provided with a first positioning sleeve via a bearing. The first positioning sleeve is rotatably connected to the first rotating shaft via a bearing and does not provide additional damping. The first positioning sleeve is rotatably provided with a driven gear, and the first positioning sleeve is provided with a fitting part, the end of which is equipped with a female shaft.

[0010] Further description of a drone-borne time-delay detonation device according to the above technology: The installation platform is rotatably connected to the fitting frame via second rotating shafts at both ends. After the installation platform rotates half a revolution, it switches to the first positioning sleeve that matches the firing conditions. When the firing condition is engaged with the first positioning sleeve that provides additional damping, the damping ring slows down the energy release rate of the firing condition, thus extending the interval between fire extinguishing grenade throws. When the aforementioned conditions are met with the first positioning sleeve which does not provide additional damping, the bearing increases the rotational speed of the first positioning sleeve, and the interval between fire extinguishing grenade throws is shortened.

[0011] Further description of a drone-borne time-delay detonation device according to the above technology: The fitting frame is provided with a rotating groove, and the inner wall of the rotating groove is provided with four ratchet grooves; The second rotating shaft passes through the middle of the rotating groove and is equipped with an elastic hook. When the first positioning sleeve is switched, the elastic hook rotates half a revolution with the second rotating shaft and is embedded in the ratchet groove.

[0012] Further description of a drone-borne time-delay detonation device according to the above technology: The power mechanism also includes a telescopic rod connected to the engine condition. The telescopic rod is equipped with a drive gear by rotating a second positioning sleeve set in the lower housing. The upper part of the rim of the drive gear has teeth and is in mesh with at least one driven gear. A knob is rotatably mounted on the upper shell, and a telescopic rod passes through the middle of the knob and is fixedly connected to the drone at its top end by a traction rope.

[0013] Further description of a drone-borne time-delay detonation device according to the above technology: The telescopic rod is locked by a locking mechanism, which includes a positioning groove on the surface of the telescopic rod, with a horizontal side and an inclined side on both sides of the positioning groove. In addition, at least one slide groove is provided in the knob, and a positioning pin is movably provided in the slide groove by a spring rod. The positioning pin is provided with a flat surface and an inclined surface that cooperate with the positioning groove.

[0014] One of the above technical solutions has the following advantages or beneficial effects: 1. Through the separation mechanism, when the drone flies above the fire, it disconnects from the upper shell, and the upper and lower shells fall freely. The traction rope pulls the movable rod through the hanging ring, causing the movable rod to squeeze the spring and move out of the sleeve rod. This causes the movable rod to disengage the positioning groove from the positioning pin, and the positioning groove and positioning pin release the restriction on the sleeve rod. At this time, the sleeve rod rotates under the torque generated by the release of energy under the condition, and drives the drive gear to rotate through the second positioning sleeve. The drive gear drives the rotating ring to rotate through multiple driven gears in sequence. The rotating ring cuts the connecting part through the blade, and throws multiple fire extinguishing bombs out of the tank in sequence. Through the design of delaying the release without external power supply and only through mechanical structure, it avoids the risk of thermal runaway and spontaneous combustion when using battery-powered electronic control modules to achieve the delayed ignition function. It is compatible with the reliable triggering of drone-borne throwing fire extinguishing equipment. 2. Through the set drive mechanism, when the firing condition is engaged with the first positioning sleeve that provides additional damping, the damping ring slows down the energy release speed of the firing condition, thus extending the interval between fire extinguishing grenade throws. When the firing condition is engaged with the first positioning sleeve that does not provide additional damping, the bearing increases the rotation speed of the first positioning sleeve, thus shortening the interval between fire extinguishing grenade throws. When it is necessary to switch between the damping ring and the bearing, the fitting part is pushed, causing the fitting part to drive the mounting platform to rotate through the first rotating shaft. The mounting platform rotates half a revolution under the restriction of the second rotating shaft and the fitting frame. At this time, the driven gear connected by the damping ring disengages from the driving gear, and the driven gear connected by the bearing enters the meshing position with the driving gear, completing the switching of high and low speed paths, thus shortening the interval between fire extinguishing grenade throws. Attached Figure Description

[0015] Figure 1 A three-dimensional structural schematic diagram of a drone-borne time-delay detonation device is shown. Figure 2 A three-dimensional structural diagram of the fire extinguishing bomb during deployment is shown; Figure 3 A three-dimensional structural diagram of the loading rack and tank is shown; Figure 4 A three-dimensional structural diagram of the positioning mechanism on the fire extinguishing bomb is shown; Figure 5 A partial three-dimensional cross-sectional structural schematic diagram of the separation mechanism and the positioning mechanism is shown; Figure 6 A partial three-dimensional cross-sectional view of the slots and accommodating cavities on the tank body is shown; Figure 7 A three-dimensional structural schematic diagram of the drive mechanism is shown; Figure 8 A three-dimensional cross-sectional structural diagram of the power mechanism is shown; Figure 9 It shows Figure 8 Enlarged structural diagram at point A; Figure 10 The diagram shows the activation conditions and a partial three-dimensional structure of the telescopic rod; Figure 11 A top-view cross-sectional structural diagram of the drive mechanism and the power mechanism is shown; Figure 12 A partial three-dimensional cross-sectional structural schematic diagram of the drive mechanism is shown; Figure 13 A three-dimensional, disassembled structural diagram of the gear and damper is shown; Figure 14 A three-dimensional structural diagram showing the connection between the drive mechanism and the rotating ring is shown; Figure 15 A three-dimensional disassembled structural diagram of the gear and bearing is shown; Figure 16A three-dimensional structural schematic diagram of the mounting platform for the drive mechanism is shown; Figure 17 A three-dimensional structural diagram of the ratchet and the elastic hook is shown; Figure 18 A three-dimensional cross-sectional structural diagram of the power mechanism is shown; Figure 19 A three-dimensional cross-sectional view of the locking mechanism when it is released is shown. Figure 20 A top-view cross-sectional structural diagram of the locking mechanism is shown; Figure 21 A partial three-dimensional structural schematic diagram of the knob and locking mechanism is shown; Figure 22 A three-dimensional structural diagram of the positioning groove is shown.

[0016] Legend: 11. Upper shell; 12. Lower shell; 13. Tank body; 131. Flexible hinge shaft; 132. Cover; 133. Slot; 134. Receiving cavity; 14. Fire extinguishing bomb; 15. Loading rack; 20. Separation mechanism; 21. Rotating ring; 22. Blade; 30. Positioning mechanism; 31. Connecting part; 32. Locking device; 40. Drive mechanism; 41. Fitting frame; 411. Rotating groove; 412. Ratchet; 413. Elastic hook; 42. Driven gear; 43. Mounting platform; 431. First rotating shaft; 432. Second rotating shaft; 44. First positioning sleeve; 45. Damping ring; 46. Fitting part; 47. Female shaft; 48. Female shaft; 49. Connecting frame; 410. Bearing; 50. Power mechanism; 51. Starting condition; 52. Telescopic rod; 521. Sleeve rod; 522. Movable rod; 523. Hanging ring; 524. Spring; 53. Second positioning sleeve; 54. Drive gear; 55. Knob; 60. Locking mechanism; 61. Positioning groove; 62. Slide groove; 63. Spring rod; 64. Positioning pin. Detailed Implementation

[0017] The following will describe in detail, with reference to the accompanying drawings of the embodiments of the present invention, a UAV-borne delayed detonation device. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0018] To address the significant shortcomings of existing electronically triggered fire extinguishing bombs in terms of safety and environmental adaptability, this invention proposes a UAV-borne delayed detonation device, such as... Figure 1 - Figure 22 As shown: The device includes an upper shell 11 that is movably mounted on the drone and a lower shell 12 mounted on the upper shell 11. At least two canisters 13 are mounted on the lower shell 12 via a loading rack 15, and fire extinguishing bombs 14 are disposed inside the canisters 13. A separation mechanism 20 is provided on the canisters 13. The separation mechanism 20 includes a rotating ring 21 that is rotatably disposed on the canisters 13, and a blade 22 is provided on the rotating ring 21. The fire extinguishing bombs 14 are fixed inside the canisters 13 by a positioning mechanism 30. The positioning mechanism 30 includes a locking member 32 that is connected to the canisters 13, and the locking member 32 is connected to the fire extinguishing bombs 14 via a connecting part 31.

[0019] like Figure 2 and Figure 5 As shown, a cover 132 is rotatably connected to the bottom of the canister 13 via an elastic hinge shaft 131. When the connecting part 31 is not cut off, the fire extinguishing bomb 14 is in contact with the cover 132, and the cover 132 is in contact with the bottom of the canister 13 via the elastic hinge shaft 131. When it is necessary to install the fire extinguishing bomb 14, the cover 132 is flipped outward to open around the elastic hinge shaft 131. After the fire extinguishing bomb 14 is placed into the canister 13, the clip 32 is inserted into the clip slot 133. The clip 32 connects to the fire extinguishing bomb 14 via the connecting part 31. The cover 132 is flipped back to its original position and closed, thus sealing the bottom opening of the canister 13 with the cover 132 to prevent the fire extinguishing bomb 14 from accidentally slipping out during flight. Preferably, as shown in the figure... Figure 3 As shown, the canister 13 for filling the fire extinguishing bomb 14 is installed inside the loading rack 15 and is installed at the bottom of the lower casing 12 via the loading rack 15.

[0020] like Figure 6 As shown, the tank body 13 has a slot 133 for inserting the clip 32, and a receiving cavity 134 is provided between adjacent slots 133. When the rotating ring 21 is in the initial position, the blade 22 is stored in the receiving cavity 134 to avoid the blade 22 from contacting the connecting part 31 during flight.

[0021] When the drone flies over the fire, it rotates the rotating ring 21, causing the blade 22 on the rotating ring 21 to rotate out of the accommodating cavity 134 and cut off the connecting part 31. The fire extinguishing bomb 14 is disengaged from the clamp 32. At the same time, the cover 132 flips down and opens under the gravity of the fire extinguishing bomb 14 around the elastic hinge axis 131. The fire extinguishing bomb 14 slides out from the bottom opening of the tank 13 under the gravity and falls into the fire, thus realizing the deployment of the fire extinguishing bomb 14.

[0022] Furthermore, in order to control the rotation of the rotating ring 21, such as Figure 7 - Figure 11As shown, at least two drive mechanisms 40 are provided on the upper housing 11, such as... Figure 8 , Figure 11 and Figure 12 As shown, the rotating ring 21 is driven to rotate by the drive mechanism 40. The drive mechanism 40 includes at least two fitting frames 41 fixedly installed on the upper housing 11. Preferably, four fitting frames 41 are provided. A mounting platform 43 is rotatably provided in the middle of the fitting frame 41, and a first rotating shaft 431 is respectively installed at both ends of the mounting platform 43. Any one of the first rotating shafts 431 is rotatably provided with a driven gear 42 through a first positioning sleeve 44. A fitting part 46 is also provided on the first positioning sleeve 44, and a female shaft 47 is installed at the end of the fitting part 46. A female shaft 48 that cooperates with the female shaft 47 is provided on the rotating ring 21 through a connecting frame 49.

[0023] With this design, after the driven gear 42 receives torque, it drives the first positioning sleeve 44 to rotate around the first rotating shaft 431. The fitting part 46 on the first positioning sleeve 44 rotates accordingly. The female shaft 47 at the end of the fitting part 46 cooperates with the male shaft 48 on the connecting frame 49 to transmit the rotational torque to the rotating ring 21, thereby driving the rotating ring 21 to rotate around the tank body 13 and cut off the connecting part 31.

[0024] like Figure 8 - Figure 10 As shown, a power mechanism 50 is provided on the lower housing 12 to provide torque to the driven gear 42. The power mechanism 50 includes a firing condition 51 provided on the lower housing 12 and a telescopic rod 52 connected to the firing condition 51. The telescopic rod 52 is mounted with a driving gear 54 by rotating a second positioning sleeve 53 provided in the lower housing 12. The upper part of the rim of the driving gear 54 has teeth and is in mesh with at least one driven gear 42. Preferably, the teeth of the driving gear 54 are in mesh with the driven gear 42, and when the meshing with the driven gear 42 ends, it enters the meshing state with another driven gear 42. Through this design, it is ensured that the driving gear 54 does not interfere with other driven gears 42 in the non-meshing range, and that each driven gear 42 meshes and rotates in sequence, so as to realize the sequential and intermittent deployment of the fire extinguishing bombs 14 rather than simultaneous deployment.

[0025] Through this design, the torque generated by the release of energy from the ignition condition 51 is transmitted to the drive gear 54 through the telescopic rod 52 and the second positioning sleeve 53. The drive gear 54 drives the driven gear 42 that meshes with it to rotate. The driven gear 42 then drives the rotating ring 21 to rotate through the cooperation of the mother shaft 47 and the daughter shaft 48, so that the blade 22 cuts off the connecting part 31 and releases the fire extinguishing bomb 14.

[0026] like Figure 18As shown, a knob 55 is rotatably mounted on the upper housing 11. The telescopic rod 52 includes a sleeve rod 521 connected to the launch condition 51. A movable rod 522 is slidably nested inside the sleeve rod 521. A positioning groove 61 is provided on the movable rod 522. The movable rod 522 passes through the middle of the knob 55 and has a hanging ring 523 installed at its top. The hanging ring 523 is fixedly connected to the drone by a traction rope. The length of the traction rope is adapted to the drone's mounting height.

[0027] like Figure 20 - Figure 22 As shown, the locking mechanism 60 locks the knob 55 when it is rotated, and unlocks the drone when it flies over the fire. The locking mechanism 60 includes a positioning groove 61 on the surface of the telescopic rod 52, with a horizontal side and an inclined side on both sides of the positioning groove 61, and at least one sliding groove 62 in the knob 55. A positioning pin 64 is movably disposed in the sliding groove 62 by a spring rod 63. The positioning pin 64 has a plane and an inclined surface that cooperate with the positioning groove 61.

[0028] Before the drone takes off, by rotating the knob 55, the movable rod 522 rotates synchronously. During this process, the inclined surface of the positioning pin 64 contacts the inclined side of the positioning groove 61. The positioning pin 64 compresses the spring rod 63 and slides into the positioning groove 61. This action continues until the energy storage of the firing condition 51 is completed. At this time, the plane of the positioning pin 64 contacts the horizontal side of the positioning groove 61, and the telescopic rod 52 is locked and cannot move axially, so as to avoid the premature release of energy by the firing condition 51. All drive mechanisms 40 are in a stopped state, and the fire extinguishing bomb 14 remains fixed, waiting for the drone to fly over the fire site.

[0029] Preferably, a spring 524 is also provided inside the sleeve 521. One end of the spring 524 is connected to the inner wall of the sleeve 521, and the other end of the spring 524 is in contact with the movable rod 522. Through this design, the spring 524 applies a pushing force to the movable rod 522 inside the sleeve 521, ensuring that the positioning groove 61 can always be in contact with the positioning pin 64 during the flight of the UAV, and preventing premature unlocking.

[0030] When the drone flies over the fire, it disconnects from the upper shell 11, and the upper shell 11 and lower shell 12 fall freely. The traction rope pulls the movable rod 522 through the hanging ring 523, causing the movable rod 522 to squeeze the spring 524 and move out of the sleeve rod 521. This causes the movable rod 522 to disengage the positioning groove 61 from the positioning pin 64, and the positioning groove 61 and positioning pin 64 release the restriction on the sleeve rod 521. At this time, the sleeve rod 521 rotates under the torque generated by the release of energy from the condition 51, and drives the drive gear 54 to rotate through the second positioning sleeve 53. The drive gear 54 drives the rotating ring 21 to rotate in sequence through multiple driven gears 42. The rotating ring 21 cuts the connecting part 31 through the blade 22, and throws multiple fire extinguishing bombs 14 out of the tank 13 in sequence.

[0031] By implementing a delayed ignition design without an external power source and relying solely on mechanical structures, the design avoids the risks of thermal runaway and spontaneous combustion that exist when using battery-powered electronic control modules to achieve delayed ignition. This design ensures reliable triggering for unmanned aerial vehicle (UAV) airborne drop-type fire extinguishing equipment.

[0032] Furthermore, to prevent the drive gear 54 from rotating too fast, such as Figure 13 As shown, the first positioning sleeve 44 is embedded with a damping ring 45. The first positioning sleeve 44 is rotatably connected to the first rotating shaft 431 through the damping ring 45 to provide additional damping. Through this design, the torque released by the active gear 54 is prevented from being transmitted to the driven gear 42 at high speed, and the interval between the fire extinguishing bombs 14 being thrown is too short, so as not to effectively cover the fire scene.

[0033] Preferably, another first rotating shaft 431 is rotatably provided with a first positioning sleeve 44 via a bearing 410. The first positioning sleeve 44 is rotatably connected to the first rotating shaft 431 via the bearing 410 without providing additional damping. A driven gear 42 is rotatably provided on the first positioning sleeve 44, and a fitting part 46 is provided on the first positioning sleeve 44. A female shaft 47 is installed at the end of the fitting part 46.

[0034] In order to switch the first positioning sleeve 44, such as Figure 15 and Figure 16 As shown, the installation platform 43 is rotatably connected to the fitting frame 41 via the second rotating shaft 432 set at both ends. After the installation platform 43 rotates half a turn, it switches to the first positioning sleeve 44 that cooperates with the firing condition 51. When the firing condition 51 cooperates with the first positioning sleeve 44 that provides additional damping, the damping ring 45 slows down the energy release speed of the firing condition 51, and the interval between the fire extinguishing bombs 14 is extended. When the firing condition 51 cooperates with the first positioning sleeve 44 that does not provide additional damping, the bearing 410 increases the rotation speed of the first positioning sleeve 44, and the interval between the fire extinguishing bombs 14 is shortened, so as to realize the speed variation of the fire extinguishing bomb 14 delivery rhythm and meet the needs of different fire situations.

[0035] When it is necessary to switch between the damping ring 45 and the bearing 410, the fitting part 46 is pushed, causing the fitting part 46 to drive the mounting platform 43 to rotate through the first rotating shaft 431. The mounting platform 43 rotates half a revolution under the restriction of the second rotating shaft 432 and the fitting frame 41. At this time, the driven gear 42 connected by the damping ring 45 disengages from the driving gear 54, and the driven gear 42 connected by the bearing 410 enters the meshing position with the driving gear 54, completing the switching of high and low speed paths, so that the throwing interval of the fire extinguishing bomb 14 changes from long to short.

[0036] Furthermore, the fitting frame 41 is provided with a rotating groove 411, and the inner wall of the rotating groove 411 is provided with four ratchet grooves 412. The second rotating shaft 432 passes through the middle of the rotating groove 411 and is equipped with an elastic hook 413. When switching the first positioning sleeve 44, the elastic hook 413 rotates half a turn with the second rotating shaft 432 and is embedded in the ratchet groove 412. Through this design, the installation platform 43 is locked in the switching position by the cooperation of the elastic hook 413 and the ratchet groove 412 after rotating half a turn, ensuring that the installation platform 43 rotates into place while preventing the installation platform 43 from rotating back due to vibration, and ensuring that the switching between the high speed and low speed first positioning sleeve 44 is stable and reliable.

[0037] In one embodiment of this application, the high-speed and low-speed first positioning sleeves 44 are alternately coordinated. The second fire extinguishing bullet 14 is driven by the high-speed first positioning sleeve 44, which shortens the interval between the first and second fire extinguishing bullets 14, thus densely covering nearby fire points. The third fire extinguishing bullet 14 is driven by the low-speed first positioning sleeve 44, which lengthens the interval between the second and third fire extinguishing bullets 14, allowing time for the drone to fly to distant fire points. The fourth fire extinguishing bullet 14 is also driven by the high-speed first positioning sleeve 44, which shortens the interval between the third and fourth fire extinguishing bullets 14. Each pair of fire extinguishing bullets 14 forms a group with short intervals within the group and long intervals between groups, achieving the effect of densely suppressing localized fire points in a large-scale fire, thereby improving fire extinguishing efficiency.

[0038] Working principle: Before takeoff, fire extinguishing bombs 14 are loaded. The bottom of the canister 13 is connected to a cover 132 via a flexible hinge shaft 131. The cover 132 is flipped outward to open the bottom opening. The fire extinguishing bomb 14 is placed into the canister 13, ensuring that the fire extinguishing bomb 14 fits snugly against the cover 132 without the connecting part 31 being cut off. The locking piece 32 is inserted into the locking slot 133, and the locking piece 32 is connected to the fire extinguishing bomb 14 via the connecting part 31. The cover 132 is flipped back to its original position and closed, sealing the bottom opening of the canister 13 and preventing the fire extinguishing bomb 14 from slipping out during flight. The canister 13 for filling the fire extinguishing bomb 14 is installed at the bottom of the lower housing 12 via the loading frame 15, and the lower housing 12 is installed on the upper housing 11. Pushing the fitting part 46 causes the mounting platform 43 to rotate half a revolution around the second rotating shaft 432, switching between high-speed and low-speed paths, and the elastic hook 413 is locked in place by engaging the ratchet groove 412. Rotating the knob 55 causes the movable rod 522 to rotate synchronously. The inclined surface of the positioning pin 64 contacts the inclined side of the positioning groove 61, compresses the spring rod 63, and slides into the positioning groove 61. Continue rotating until the energy storage of the firing condition 51 is completed. At this time, the plane of the positioning pin 64 contacts the horizontal side of the positioning groove 61, and the telescopic rod 52 is locked and cannot move axially. The spring 524 in the sleeve rod 521 applies a thrust to the movable rod 522 to ensure that the positioning groove 61 is always in contact with the positioning pin 64 during flight, preventing premature unlocking. After rotating the knob 55 to the position, the locking mechanism 60 completes the locking, all drive mechanisms 40 stop, and the fire extinguishing bomb 14 remains fixed.

[0039] The drone is disconnected from the upper shell 11, and the upper shell 11 and lower shell 12 fall freely. The traction rope pulls the movable rod 522 through the hanging ring 523, and the movable rod 522 compresses the spring 524 and moves out of the sleeve rod 521. The positioning slot 61 disengages from the positioning pin 64, and the telescopic rod 52 is unlocked. The firing condition 51 releases energy, and the driving gear 54 engages with each driven gear 42 in sequence, first engaging one and then switching to the next to avoid simultaneous deployment.

[0040] Driven gear 42 drives first positioning sleeve 44 to rotate around first rotating shaft 431. The female shaft 47 at the end of fitting part 46 cooperates with the male shaft 48 on connecting frame 49, driving rotating ring 21 to rotate. Blade 22 on rotating ring 21 rotates out from receiving cavity 134, cuts off connecting part 31, and fire extinguishing bomb 14 disengages from clamp 32.

[0041] Under the influence of the gravity of the fire extinguishing bomb 14, the cover 132 flips downwards and opens around the elastic hinge axis 131, and the fire extinguishing bomb 14 slides out from the bottom of the tank 13 and falls into the fire.

[0042] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technology of the present invention and the inventive concept of the UAV-borne delayed detonation device, should be covered within the scope of protection of the present invention.

Claims

1. A time-delay detonation device for unmanned aerial vehicles (UAVs), comprising an upper shell (11) movably mounted on the UAV and a lower shell (12) mounted on the upper shell (11), wherein at least two canisters (13) are mounted on the lower shell (12) via a loading rack (15), and fire extinguishing bombs (14) are disposed within the canisters (13), characterized in that, The tank (13) is provided with a separation mechanism (20), which includes a rotating ring (21) rotatably disposed on the tank (13) and a blade (22) disposed on the rotating ring (21). The fire extinguishing bomb (14) is fixed inside the tank (13) by a positioning mechanism (30). The positioning mechanism (30) includes a clip (32) connected to the tank (13). The clip (32) and the fire extinguishing bomb (14) are connected by a connecting part (31). The upper housing (11) is provided with at least two drive mechanisms (40), and the rotating ring (21) is driven to rotate by the drive mechanism (40). The lower housing (12) is provided with a power mechanism (50) that drives the drive mechanism (40) to rotate in sequence. The power mechanism (50) includes a power condition (51) provided on the lower housing (12). Before takeoff, the drone stores energy by rotating the launch condition (51) and locks it with the locking mechanism (60). When the drone flies over the fire, the locking mechanism (60) unlocks, causing the launch condition (51) to release energy with a delay and drive the second positioning sleeve (53) to rotate. The second positioning sleeve (53) drives the rotating ring (21) to rotate in sequence through multiple driven gears (42). The rotating ring (21) cuts the connecting part (31) through the blade (22) and throws multiple fire extinguishing bombs (14) out of the tank (13) in sequence.

2. The unmanned aerial vehicle (UAV)-borne delayed detonation device according to claim 1, characterized in that, The bottom of the tank (13) is rotatably connected to the cover (132) via an elastic hinge shaft (131). When the connection part (31) is not cut off, the fire extinguishing bomb (14) is attached to the cover (132), and the cover (132) is attached to the bottom of the tank (13) via the elastic hinge shaft (131).

3. A UAV-borne delayed detonation device according to claim 1 or 2, characterized in that, The tank body (13) has a slot (133) for inserting the card (32), and a receiving cavity (134) is provided between adjacent slots (133). When the rotating ring (21) is in the initial position, the blade (22) is stored in the receiving cavity (134).

4. The unmanned aerial vehicle (UAV)-borne delayed detonation device according to claim 1, characterized in that, The drive mechanism (40) includes at least two fitting frames (41) fixedly mounted on the upper housing (11). A mounting platform (43) is rotatably provided in the middle of the fitting frame (41), and a first rotating shaft (431) is installed at both ends of the mounting platform (43). Any of the first rotating shafts (431) is provided with a driven gear (42) through the first positioning sleeve (44). The first positioning sleeve (44) is also provided with a fitting part (46), and a female shaft (47) is installed at the end of the fitting part (46). The rotating ring (21) is provided with a sub-shaft (48) that cooperates with the main shaft (47) via a connecting frame (49). When the torque generated by the release of energy under the condition (51) is transmitted to the driven gear (42), it drives the rotating ring (21) to rotate.

5. The unmanned aerial vehicle (UAV)-borne delayed detonation device according to claim 4, characterized in that, The first positioning sleeve (44) is embedded with a damping ring (45), and the first positioning sleeve (44) is rotatably connected to the first rotating shaft (431) through the damping ring (45) to provide additional damping.

6. The unmanned aerial vehicle (UAV)-borne delayed detonation device according to claim 5, characterized in that, Another first rotating shaft (431) is rotatably provided with a first positioning sleeve (44) via a bearing (410). The first positioning sleeve (44) is rotatably connected to the first rotating shaft (431) via the bearing (410) without providing additional damping. The first positioning sleeve (44) is rotatably provided with a driven gear (42), and the first positioning sleeve (44) is provided with a fitting part (46), and a female shaft (47) is installed at the end of the fitting part (46).

7. The unmanned aerial vehicle (UAV)-borne delayed detonation device according to claim 6, characterized in that, The installation platform (43) is rotatably connected to the fitting frame (41) through the second rotating shaft (432) set at both ends. After the installation platform (43) rotates half a turn, it switches to the first positioning sleeve (44) that cooperates with the launching condition (51). When the firing condition (51) is combined with the first positioning sleeve (44) that provides additional damping, the damping ring (45) slows down the energy release rate of the firing condition (51), and the interval between the throwing of the fire extinguishing bullet (14) is extended. When the firing condition (51) is engaged with the first positioning sleeve (44) which does not provide additional damping, the bearing (410) increases the rotational speed of the first positioning sleeve (44), and the interval between the throwing of the fire extinguishing bomb (14) is shortened.

8. The unmanned aerial vehicle (UAV)-borne delayed detonation device according to claim 7, characterized in that, The fitting frame (41) is provided with a rotating groove (411), and the inner wall of the rotating groove (411) is provided with four ratchet grooves (412). The second rotating shaft (432) passes through the middle of the rotating groove (411) and is equipped with an elastic hook (413). When the first positioning sleeve (44) is switched, the elastic hook (413) rotates half a revolution with the second rotating shaft (432) and is embedded in the ratchet groove (412).

9. The unmanned aerial vehicle (UAV)-borne delayed detonation device according to claim 1, characterized in that, The power mechanism (50) also includes a telescopic rod (52) connected to the power condition (51). The telescopic rod (52) is equipped with a drive gear (54) by rotating a second positioning sleeve (53) located in the lower housing (12). The drive gear (54) has teeth on the upper part of its rim and is in mesh with at least one driven gear (42). A knob (55) is rotatably mounted on the upper housing (11), and a telescopic rod (52) passes through the middle of the knob (55) and is fixedly connected to the drone by a traction rope at its top end.

10. A UAV-borne delayed detonation device according to claim 9, characterized in that, The telescopic rod (52) is locked by a locking mechanism (60), which includes a positioning groove (61) on the surface of the telescopic rod (52), with the two sides of the positioning groove (61) being a horizontal side and an inclined side, respectively. In addition, at least one slide (62) is provided in the knob (55), and a positioning pin (64) is movably provided in the slide (62) via a spring rod (63). The positioning pin (64) is provided with a plane and an inclined surface that cooperate with the positioning groove (61).

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