Multi-rotor unmanned aerial vehicle long-distance self-homing precise launching fire-extinguishing bomb platform
By setting up a mechanical linkage structure between the positioning module and the triggering unit, as well as a pitch buffer bracket on the multi-rotor UAV, the problems of limited firing range and untimely linkage of the positioning mechanism were solved, achieving accurate launch and stable flight.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- SICHUAN WOLUOJIA TECH CO LTD
- Filing Date
- 2026-04-21
- Publication Date
- 2026-06-19
AI Technical Summary
Existing multi-rotor drone launch platforms suffer from reduced accuracy due to limited firing range, and the lack of instantaneous linkage between the positioning mechanism and firing poses a safety hazard. Furthermore, recoil affects the stability of the drone.
The system employs a mechanical linkage structure between the positioning module and the triggering unit, combined with an elevation buffer bracket, to achieve reliable clamping, flexible adjustment, and buffering of the fire extinguishing projectile, ensuring accurate positioning and stable launch of the launch tube at different angles.
It enables precise launch of multi-rotor drones at different firing angles, reduces the impact of recoil on the drone, and ensures firing accuracy and flight safety.
Smart Images
Figure CN122230255A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of drone firefighting technology, specifically to a multi-rotor drone long-range self-aiming precision-launching platform for fire extinguishing projectiles. Background Technology
[0002] The multi-rotor drone fire extinguishing projectile launch platform is an aerial firefighting device that mounts fire extinguishing projectile launch tubes on the belly of a multi-rotor drone. It is mainly used for long-distance firefighting operations in high-rise buildings or dangerous areas. The platform uses the drone to hover above the fire scene and launch fire extinguishing projectiles to the target area through the launch tubes, so that personnel can carry out firefighting without getting close.
[0003] However, existing launch platforms have significant drawbacks in practical use. To prevent fire extinguishing projectiles from sliding down under gravity, existing launch tubes are typically tilted upwards. This not only limits the effective firing arc, making horizontal or downward firing difficult, but also forces the projectiles to fly in a high-angle trajectory, which is curved and greatly affected by wind, making it difficult to guarantee firing accuracy. Furthermore, there is a risk of collision with the UAV rotor when launching upwards. To address this issue, some existing technologies use a positioning mechanism inside the launch tube to fix the fire extinguishing projectiles. However, such positioning mechanisms are simple in structure and lack timely mechanical linkage with the firing mechanism. This poses a safety hazard of jamming or firing failure due to the positioning component not retracting in time during firing. Moreover, the positioning mechanism needs to be manually operated during loading, which affects the loading efficiency of the fire extinguishing projectiles to some extent. In addition, the recoil generated by the fire extinguishing projectiles directly impacts the UAV, causing the fuselage to sway and become unbalanced, affecting the stability of the UAV. Therefore, based on the above problems, a multi-rotor UAV long-range self-aiming precision fire extinguishing projectile launch platform is proposed. Summary of the Invention
[0004] The purpose of this invention is to provide a long-range self-aiming precision-launching platform for fire extinguishing projectiles for multi-rotor UAVs, in order to solve the problems of reduced accuracy due to limited firing range of existing launch platforms and safety hazards caused by the lack of instantaneous linkage between the positioning mechanism and firing.
[0005] To achieve the above objectives, the present invention provides the following technical solution: A multi-rotor UAV long-range self-aiming precision-launching platform for fire extinguishing projectiles includes a UAV support frame. A pitch buffer bracket is mounted on the lower side of the upper plate of the UAV support frame. A launch tube is mounted on the lower side of the pitch buffer bracket. The launch tube includes a tube body. A positioning module is mounted on the outer right side of the launch tube. A projectile is mounted on the inner side of the tube body and the positioning module. The positioning module includes a sleeve body located on the right side of the tube body. The sleeve body includes a base sleeve fixedly connected to the right end of the tube body. The inner side of the base sleeve has several ball tracks arranged at equal angles. The inner curved surface of the base sleeve has several guide grooves communicating with the ball tracks. The inner curved surface of the base sleeve has several mounting slots located to the left of the guide grooves. The left side of the base sleeve has several slots communicating with the ball tracks. A projectile is mounted around the outside of the projectile at each of the guide grooves. The clamping block includes a guide block slidably connected to the guide groove. An elastic damping pad is fixedly connected to the side of the guide block near the projectile. A ball groove is formed on the inclined surface of the guide block. A recessed groove is formed on the side of the ball groove near the elastic damping pad and is formed inside the guide block. A magnetic block is fixedly connected to the inside of the recessed groove. Metal locking balls that are inserted into the ball groove are installed on the inside of the ball track. A locking part is installed on the left side of the sleeve body. The locking part includes a base ring fixed to the outside of the cylinder. A pull rod is slidably connected to the upper and lower holes of the base ring. A linkage ring sleeved on the outside of the cylinder is fixedly connected to the right end of the pull rod. Several locking pins that are inserted into slots are fixedly connected to the right side of the linkage ring. A spring II is sleeved on the outside of the pull rod between the base ring and the linkage ring. A trigger part is installed on the left side of the positioning module.
[0006] Preferably, the triggering part includes a base shell fixed inside the left opening of the cylinder, an elastic membrane fixedly connected inside the right opening of the base shell, a linkage frame slidably connected to the left side of the elastic membrane, pull ropes fixedly connected to both the upper and lower ends of the linkage frame, the right ends of the pull ropes fixedly connected to the pull rods, and a spring installed between the left inner wall of the base shell and the elastic membrane.
[0007] Preferably, a resetter is installed on the left side of each clamping block. The resetter includes a base fixedly connected to the mounting groove. A rail groove is opened on the inner side of the long plate of the base. A rail block is slidably connected to the inner side of the rail groove. A push block that fits against the clamping block is fixedly connected to the outer side of the rail block. A spring is fixedly connected between the push block and the short plate of the base.
[0008] Preferably, the magnetic block is in contact with the metal ball, the metal ball is disposed between the magnetic block and the pin, the right end of the pin is in contact with the metal ball, and the elastic damping pad is in close contact with the outer curved surface of the elastic body.
[0009] Preferably, a high-pressure gas cylinder is installed on the rear left side of the cylinder, and an electrically controlled valve pipe is installed between the left end of the high-pressure gas cylinder and the cylinder. A regulating valve pipe is installed on the front side of the cylinder in a connected manner. The regulating valve pipe consists of a pipe body and a regulating valve. Connecting blocks are fixedly connected to both the front and rear sides of the cylinder.
[0010] Preferably, the pitch buffer bracket includes a base frame fixed to the lower side of the upper plate of the UAV support frame. A platform is rotatably connected to the lower side of the base frame. A motor is fixedly connected to the lower front side of the base frame. The output shaft end of the motor is fixedly connected to the platform. A slide groove is opened on the lower side of the platform. A slide plate is installed on the inner side of the slide groove. A damping sleeve is fixedly connected to the inner side of each hole of the slide plate. A guide rod fixed to the inner wall of the slide groove is installed on the inner side of each damping sleeve. Several buffer springs are fixedly connected between the left inner wall of the slide groove and the left end face of the slide plate. A fixing frame sleeved on the outer side of the connecting block is fixedly connected to the lower side of the slide plate. A miniature infrared thermal imager, a laser rangefinder, and a control box are installed on the upper side of the platform.
[0011] Preferably, there is a gap between the platform and the upper plate of the UAV support frame, the buffer springs are all sleeved on the outside of the guide rod, and the miniature infrared thermal imager, laser rangefinder and projectile body are oriented in the same direction.
[0012] Compared with the prior art, the beneficial effects of the present invention are: 1. In this invention, the structure of the launch tube, positioning module, and triggering unit enables the positioning module to reliably clamp and position the projectile at both horizontal and downward angles of attack. This eliminates concerns about the projectile slipping when the launch tube adjusts its pitch angle. The triggering unit can mechanically link with the positioning module. Driven by high-pressure gas, the triggering unit simultaneously releases the positioning constraint of the positioning module on the projectile at the moment of firing, creating a rigid and instantaneous linkage between positioning release and firing operation. This enables a multi-rotor UAV long-range self-aiming precision fire extinguishing projectile platform to reliably position and rapidly fire the fire extinguishing projectile at both horizontal and downward angles of attack, avoiding the impact of limited firing range on shooting accuracy. This solves the problems of decreased accuracy due to limited firing range in existing launch platforms and safety hazards caused by the lack of instantaneous linkage between the positioning mechanism and firing. 2. In this invention, the launch tube and pitch buffer support are designed to allow the launch tube to flexibly adjust its pitch angle to adapt to different firing trajectories. When the launch tube is fired, the pitch buffer support absorbs the recoil impact by elastically deforming along the axial direction of the launch tube through its internal buffer spring. The buffer spring forms a sliding guide buffer pair with the guide rod through the damping sleeve, which greatly reduces the rigid transmission of the recoil force to the UAV. This allows the UAV to maintain a stable attitude during multi-angle launches, enabling the multi-rotor UAV long-range self-aiming precision fire extinguishing platform to launch stably across the entire firing angle range. This solves the problem of the existing launch platform causing the fuselage to sway and become unbalanced due to the direct rigid transmission of recoil force, which affects aiming accuracy and flight safety. Attached Figure Description
[0013] Figure 1 This is a schematic diagram of the overall structure of the present invention; Figure 2 For the present invention Figure 1 Another perspective structural diagram of the middle structure; Figure 3 This is a schematic diagram of the tilt buffer support structure of the present invention from an oblique upward view. Figure 4 This is a schematic diagram of the cross-sectional structure at the launching tube of the present invention; Figure 5 For the present invention Figure 4 A magnified structural diagram at point A; Figure 6 For the present invention Figure 4 A magnified structural diagram at point B; Figure 7 This is a cross-sectional structural diagram of the main body of the present invention; Figure 8 This is a schematic diagram of the structure of the clamping block of the present invention; Figure 9 This is a schematic diagram of the reset device of the present invention; Figure 10 This is a schematic diagram of the structure of the locking part of the present invention; Figure 11 This is a schematic cross-sectional view of the unfolded state of the positioning module of the present invention.
[0014] In the diagram: 1. UAV support frame; 2. Pitch buffer bracket; 21. Base frame; 22. Platform; 23. Slide groove; 24. Motor; 25. Slide plate; 26. Damping sleeve; 27. Guide rod; 28. Buffer spring; 29. Fixing frame; 3. Miniature infrared thermal imager; 4. Laser rangefinder; 5. Control box; 6. Launch tube; 61. Cylinder body; 62. Connector block; 63. High-pressure gas cylinder; 64. Electrically controlled valve pipe; 65. Adjusting valve pipe; 7. Positioning module; 71. Main body; 711. Base sleeve; 712. Guide groove; 713. Ball track; 714. Slot; 715 72. Mounting slot; 73. Metal ball clamp; 74. Clamping block; 75. Guide block; 76. Ball groove; 77. Sinking groove; 78. Magnetic block; 79. Elastic damping pad; 70. Resetter; 71. Base; 72. Rail groove; 73. Rail block; 74. Push block; 75. Spring 1; 76. Locking part; 77. Base ring; 78. Pull rod; 79. Linking ring; 70. Locking pin; 70. Spring 2; 80. Trigger part; 81. Base shell; 82. Elastic membrane; 83. Linking frame; 84. Spring 3; 85. Pull rope; 9. Elastic body. Detailed Implementation
[0015] Please see Figure 1-11 The present invention provides a technical solution: A multi-rotor UAV long-range self-aiming precision-launching platform for fire extinguishing projectiles includes a UAV support frame 1. A pitch buffer bracket 2 is mounted on the lower side of the upper plate of the UAV support frame 1. A launch tube 6 is mounted on the lower side of the pitch buffer bracket 2. The launch tube 6 includes a tube body 61. A positioning module 7 is mounted on the outer right side of the launch tube 6. A projectile 9 is mounted on the inner side of the tube body 61 and the positioning module 7. The positioning module 7 includes a sleeve body 71 located on the right side of the tube body 61. The sleeve body 71 includes a base sleeve 711 fixedly connected to the right end of the tube body 61. The inner side of the base sleeve 711 has several ball tracks 713 arranged at equal angles. The inner curved surface of the base sleeve 711 has several... The guide groove 712, which is connected to the ball track 713, has several mounting grooves 715 on the inner curved surface of the base sleeve 711 located on the left side of the guide groove 712. Several slots 714, which are connected to the ball track 713, are also provided on the left side of the base sleeve 711. Clamping blocks 73, which surround the outside of the projectile 9, are installed at each guide groove 712. Each clamping block 73 includes a guide block 731 that is slidably connected to the guide groove 712. An elastic damping pad 735 is fixedly connected to the side of the guide block 731 near the projectile 9. A ball groove 732 is provided on the inclined surface of the guide block 731. A recessed groove 733, located inside the guide block 731, is provided on the side of the ball groove 732 near the elastic damping pad 735. A magnetic block 734 is fixedly connected to the inner side of the groove 733. Metal ball catchers 72, which are inserted into the inner side of the ball track 713, are installed on the inner side of each ball track 713. A locking part 75 is installed on the left side of the sleeve body 71. The locking part 75 includes a base ring 751 fixed to the outer side of the cylinder 61. A pull rod 752 is slidably connected to the upper and lower holes of the base ring 751. A connecting ring 753, sleeved on the outer side of the cylinder 61, is fixedly connected to the right end of the pull rod 752. Several locking pins 754, which are inserted into slots 714, are fixedly connected to the right side of the connecting ring 753. A spring 755, located between the base ring 751 and the connecting ring 753, is sleeved on the outer side of each pull rod 752. (Positioning mold) A trigger part 8 is installed on the left side of block 7. The trigger part 8 includes a base shell 81 fixed inside the left opening of the cylinder 61. An elastic membrane 82 is fixedly connected inside the right opening of the base shell 81. A linkage frame 83 that is slidably connected to the base shell 81 is fixedly connected to the left side of the elastic membrane 82. Pull ropes 85 are fixedly connected to both the upper and lower ends of the linkage frame 83. The right ends of the pull ropes 85 are fixedly connected to the pull rod 752. A spring 84 is installed between the left inner wall of the base shell 81 and the elastic membrane 82. This arrangement enables the trigger part 8 to mechanically link with the positioning module 7. The trigger part 8 is driven by high-pressure gas to synchronously release the positioning constraint of the positioning module 7 on the projectile 9 at the moment of firing.Each clamping block 73 is equipped with a resetter 74 on its left side. The resetter 74 includes a base 741 fixedly connected to a mounting groove 715. A rail groove 742 is formed on the inner side of the long plate of the base 741. A rail block 743 is slidably connected to the inner side of the rail groove 742. A push block 744, which is in contact with the clamping block 73, is fixedly connected to the outer side of the rail block 743. A spring 745 is fixedly connected between the push block 744 and the short plate of the base 741. This arrangement allows the resetter 74 to push the clamping block 73 to the right and reset it the instant the locking pin 754 moves to the left and no longer restricts the metal ball 72. A magnetic block 734 is in contact with the metal ball 72, and the metal ball 72 is positioned between the magnetic block 734 and the locking pin 754. The right end of 54 is in contact with the metal ball 72, and the elastic damping pad 735 is in close contact with the outer curved surface of the projectile 9. This setting allows the locking pin 754 to lock the metal ball 72, preventing the metal ball 72 from detaching from the ball groove 732, thereby locking the clamping block 73 and keeping the elastic damping pad 735 in position for the projectile 9. A high-pressure gas cylinder 63 is installed on the rear left side of the cylinder 61. An electrically controlled valve pipe 64 is installed between the left end of the high-pressure gas cylinder 63 and the cylinder 61. A regulating valve pipe 65 is installed on the front side of the cylinder 61 in a connected manner. The regulating valve pipe 65 consists of a pipe body and a regulating valve. This setting is used for venting the projectile 9. Connecting blocks 62 are fixedly connected to both the front and rear sides of the cylinder 61.
[0016] like Figures 1-3As shown, the pitch buffer bracket 2 includes a base frame 21 fixed to the lower side of the upper plate of the UAV support 1. A platform 22 is rotatably connected to the lower side of the base frame 21. A motor 24 is fixedly connected to the lower front side of the base frame 21. The output shaft end of the motor 24 is fixedly connected to the platform 22. A slide groove 23 is opened on the lower side of the platform 22. A slide plate 25 is installed on the inner side of the slide groove 23. Damping sleeves 26 are fixedly connected to the inner side of the channels of the slide plate 25. Guide rods 27 fixed to the inner wall of the slide groove 23 are installed on the inner side of the damping sleeves 26. Several buffer springs 28 are fixedly connected between the left inner wall of the slide groove 23 and the left end face of the slide plate 25. A fixing bracket 29 sleeved on the outside of the connecting block 62 is fixedly connected to the lower side of the slide plate 25. A miniature infrared thermal imager 3, a laser rangefinder 4, and a control box 5 are installed on the upper side of the platform 22. This arrangement allows the launch tube 6 to flexibly adjust its pitch angle under the support of the pitch buffer bracket 2. The system is designed to adapt to different firing trajectories. The pitch buffer bracket 2 can absorb recoil impact by elastically deforming along the axial direction of the launch tube 6 through its internal buffer spring 28 when the launch tube 6 is fired. The buffer spring 28 forms a sliding guide buffer pair with the guide rod 27 through the damping sleeve 26, which greatly reduces the rigid transmission of the recoil force to the UAV. There is a gap between the platform 22 and the upper plate of the UAV support 1. This setting allows the platform 22 to rotate in pitch angle. The buffer springs 28 are all sleeved on the outside of the guide rod 27. This setting allows the buffer springs 28 to be positioned. The miniature infrared thermal imager 3 and the laser rangefinder 4 are aligned with the projectile 9. This setting keeps the detection optical axis of the miniature infrared thermal imager 3 and the ranging optical axis of the laser rangefinder 4 parallel and in the same direction with the launch axis of the projectile 9, ensuring that the detection target, ranging reference and the projectile 9 are aligned.
[0017] Workflow: The operation of the multi-rotor UAV long-range self-aiming precision-launching fire extinguishing projectile platform is as follows. Note: All electrical components in this application are powered by the UAV's built-in power supply. First, install and fix the UAV support frame 1 on the lower side of the multi-rotor UAV, and open the regulating valve pipe 65. Then, hold the fire extinguishing projectile flat so that it is aligned with the opening of the launch tube 6 and inserted into the tube body 61. During the insertion process, the original gas in the tube is discharged through the opened regulating valve pipe 65. As the projectile 9 continues to penetrate, its head pushes against the clamping blocks 73 of the positioning module 7, which are in the unfolded state, causing the clamping blocks 73 to move along the inclined guide groove 712. While being pressed together, they gradually retract towards the center of the projectile 9 until the elastic damping pads 735 of the clamping blocks 73 are tightly fitted with the outer curved surface of the projectile 9. When the ball groove 732 of the clamping block 73 aligns with the ball track 713, the metal ball 72 inside the ball track 713 is clamped into the ball groove 732 under the magnetic force of the magnetic block 734, simultaneously creating a gap in the ball track 713. At this time, the spring 755 of the locking part 75 pushes the linkage ring 753 and each locking pin 754 to the right and insert them into the gap in the ball track 713, limiting the metal ball 72 and keeping each clamping block 73 locked to fix the projectile 9. At the same time, the displacement of the clamping block 73 pushes the push block 744 of the reset device 74, compressing the spring 745 to store energy, completing the transition of the positioning module 7 from the unfolded to the retracted state. Finally, the regulating valve pipe 65 is closed, thus completing the rapid installation and positioning of the projectile 9. After loading, the operator can view the projectile through the external... The controller manipulates the drone to take off and move towards the fire source. The miniature infrared thermal imager 3 locks the fire source location through heat source detection, and the laser rangefinder 4 monitors the distance to the fire source in real time. The control box 5 drives the motor 24 to run based on the above information. The rotation of the output shaft of the motor 24 frequently adjusts the pitch angle of the support platform 22, thereby driving the slide plate 25, the fixing frame 29, and the launch tube 6 to make large-scale real-time angle adjustments. Due to the reliable clamping of the positioning module 7, there is no need to worry about the projectile 9 slipping off during the angle adjustment process, allowing the launch tube 6 to automatically align with the fire source. When the drone reaches the appropriate distance, the staff activates the electronic control valve 64 through the external controller, and the high-pressure gas in the high-pressure gas cylinder 63 immediately enters the cylinder 61: on the one hand, the high-pressure gas... The elastic membrane 82 of the push trigger part 8 is deformed, driving the linkage frame 83 and the pull rope 85 to move, pulling the pull rod 752 and the linkage ring 753 to make each locking pin 754 exit the gap of the ball track 713, releasing the limitation on the metal locking ball 72; at this time, the spring 745 stored in each reset device 74 releases energy instantaneously, pushing each clamping block 73 to move in the opposite direction along the inclined surface of the guide groove 712 and disengage from the contact ball 9. At the same time, the displaced clamping block 73 squeezes the metal locking ball 72 out of the ball groove 732, so that the metal locking ball 72 is completely returned to the ball track 713, realizing the synchronous reset of the positioning module 7 from the retracted to the unfolded state. On the other hand, the high-pressure gas at the same time guides the ball 9, which has lost its positioning constraint, to be ejected along the cylinder 61, completing the firing of the fire extinguishing bullet;Through the above operations, a multi-rotor UAV long-range self-aiming precision fire extinguishing platform is realized, enabling reliable positioning and rapid firing of fire extinguishing projectiles at both horizontal and downward angles of attack. This avoids the impact of limited firing range on shooting accuracy and solves the problems of decreased accuracy due to limited firing range in existing launch platforms, as well as safety hazards caused by the lack of instantaneous linkage between the positioning mechanism and firing. After the projectile 9 is launched, the recoil force drives the launch tube 6 to shift in the opposite direction of launch. This displacement is transmitted to the slide plate 25 through the fixing frame 29. The slide plate 25, together with the damping sleeve 26, slides directionally along the guide rod 27 and compresses the buffer spring 28. The buffer spring 28 effectively absorbs the recoil impact energy through elastic deformation, significantly reducing the residual impact force transmitted to the UAV and ensuring the stability of the aircraft during launch.
[0018] This article uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only for the purpose of helping to understand the method and core ideas of the present invention. The above descriptions are only preferred embodiments of the present invention. It should be noted that due to the limitations of textual expression, while there are objectively infinite specific structures, those skilled in the art can make several improvements, modifications, or changes without departing from the principles of the present invention, and can also combine the above technical features in an appropriate manner. These improvements, modifications, changes, or combinations, or the direct application of the inventive concept and technical solution to other situations without modification, should all be considered within the scope of protection of the present invention.
Claims
1. A multi-rotor UAV long-range self-aiming precision-launching platform for fire extinguishing projectiles, comprising a UAV support frame (1), characterized in that: A pitch buffer bracket (2) is installed on the lower side of the upper plate of the UAV support frame (1). A launch tube (6) is installed on the lower side of the pitch buffer bracket (2). The launch tube (6) includes a tube body (61). A positioning module (7) is installed on the outer right side of the launch tube (6). A projectile (9) is installed on the inner side of the tube body (61) and the positioning module (7). The positioning module (7) includes a sleeve body (71) located on the right side of the tube body (61). The sleeve body (71) includes a base sleeve (711) fixedly connected to the right end of the tube body (61). The inner side of the base sleeve (711) is open. The base sleeve (711) has several lanes (713) arranged at equal angles. The inner curved surface of the base sleeve (711) has several guide grooves (712) that communicate with the lanes (713). The inner curved surface of the base sleeve (711) has several mounting grooves (715) located to the left of the guide grooves (712). The left side of the base sleeve (711) has several slots (714) that communicate with the lanes (713). Each guide groove (712) is equipped with a clamping block (73) that surrounds the outside of the projectile (9). The clamping block (73) includes a guide block (731) that is slidably connected to the guide groove (712). An elastic damping pad (735) is fixedly connected to the side of the guide block (731) near the projectile (9). A ball groove (732) is provided on the inclined surface of the guide block (731). A recessed groove (733) is provided on the side of the ball groove (732) near the elastic damping pad (735) and is located inside the guide block (731). A magnetic block (734) is fixedly connected to the inside of the recessed groove (733). Metal locking balls (72) that are inserted into the ball groove (732) are installed on the inside of the ball track (713). A locking part (75) is installed on the left side of the sleeve body (71). 75) Includes a base ring (751) fixed on the outside of the cylinder (61), and a pull rod (752) is slidably connected in the upper and lower holes of the base ring (751). The right end of the pull rod (752) is fixedly connected to a linkage ring (753) sleeved on the outside of the cylinder (61). The right side of the linkage ring (753) is fixedly connected to a number of locking pins (754) for inserting slots (714). The outside of the pull rod (752) is sleeved with a spring (755) located between the base ring (751) and the linkage ring (753). A trigger part (8) is installed on the left side of the positioning module (7).
2. The multi-rotor UAV long-range self-aiming precision-launching fire extinguishing platform according to claim 1, characterized in that: The triggering part (8) includes a base shell (81) fixed inside the left opening of the cylinder (61), an elastic membrane (82) fixedly connected inside the right opening of the base shell (81), a linkage frame (83) slidably connected to the left side of the elastic membrane (82), a pull rope (85) fixedly connected to both the upper and lower ends of the linkage frame (83), the right end of the pull rope (85) fixedly connected to the pull rod (752), and a spring three (84) installed between the left inner wall of the base shell (81) and the elastic membrane (82).
3. The multi-rotor UAV long-range self-aiming precision-launching fire extinguishing platform according to claim 1, characterized in that: Each clamping block (73) is equipped with a resetter (74) on its left side. The resetter (74) includes a base (741) fixedly connected to the mounting groove (715). The long plate of the base (741) has a rail groove (742) on its inner side. The rail groove (742) is slidably connected to the inner side of the rail block (743). The outer side of the rail block (743) is fixedly connected to a push block (744) that fits against the clamping block (73). A spring (745) is fixedly connected between the push block (744) and the short plate of the base (741).
4. The multi-rotor UAV long-range self-aiming precision-launching fire extinguishing platform according to claim 1, characterized in that: The magnetic block (734) is in contact with the metal ball (72), and the metal ball (72) is disposed between the magnetic block (734) and the pin (754). The right end of the pin (754) is in contact with the metal ball (72), and the elastic damping pad (735) is in close contact with the outer curved surface of the elastic body (9).
5. The multi-rotor UAV long-range self-aiming precision-launching fire extinguishing platform according to claim 1, characterized in that: A high-pressure gas cylinder (63) is installed on the rear left side of the cylinder (61). An electric control valve pipe (64) is installed between the left end of the high-pressure gas cylinder (63) and the cylinder (61). A regulating valve pipe (65) is installed on the front side of the cylinder (61) in a connected manner. The regulating valve pipe (65) consists of a pipe body and a regulating valve. Connecting blocks (62) are fixedly connected to both the front and rear sides of the cylinder (61).
6. The multi-rotor UAV long-range self-aiming precision-launching fire extinguishing platform according to claim 5, characterized in that: The pitch buffer support (2) includes a base frame (21) fixed to the lower side of the upper plate of the UAV support frame (1). A platform (22) is rotatably connected to the lower side of the base frame (21). A motor (24) is fixedly connected to the lower front side of the base frame (21). The output shaft end of the motor (24) is fixedly connected to the platform (22). A slide groove (23) is provided on the lower side of the platform (22). A slide plate (25) is installed inside the slide groove (23). The slide plate (25) has a channel inside the channel. Damping sleeves (26) are fixedly connected to each side. Guide rods (27) fixed to the inner wall of the slide groove (23) are installed on the inner side of each damping sleeve (26). Several buffer springs (28) are fixedly connected between the left inner wall of the slide groove (23) and the left end face of the slide plate (25). A fixing frame (29) sleeved on the outside of the connecting block (62) is fixedly connected to the lower side of the slide plate (25). A miniature infrared thermal imager (3), a laser rangefinder (4) and a control box (5) are installed on the upper side of the platform (22).
7. A multi-rotor UAV long-range self-aiming precision-launching fire extinguishing platform according to claim 6, characterized in that: There is a gap between the platform (22) and the upper plate of the UAV support (1), the buffer springs (28) are all sleeved on the outside of the guide rod (27), and the miniature infrared thermal imager (3), laser rangefinder (4) and projectile (9) are oriented in the same direction.