Integrated undercarriage of fire extinguishing unmanned aerial vehicle
By introducing shock absorption and buffer mechanisms into the landing gear of the drone, the impact problem during landing is solved, and the free delivery of fire-extinguishing bombs is achieved through electric telescopic rods and movable frames, the problem of recoil during fire extinguishing is solved, and the stability and service life of the drone is improved.
Patent Information
- Application Number
- CN202421306635.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-06-10
- Publication Date
- 2025-02-28
- Estimated Expiration
- Not applicable · inactive patent
AI Technical Summary
Existing drones are easily damaged by impact when landing, and the catapult drop during fire extinguishing causes recoil to affect flight stability.
An integrated landing gear for a fire-extinguishing drone was designed, using shock absorbing mechanisms and buffering mechanisms to reduce landing impacts, and freely deploying of fire-extinguishing bombs through electric telescopic rods and movable frames to avoid recoil.
It effectively extends the service life of the landing gear, improves the flight stability and practicality of the drone, and avoids the problem of flight instability caused by recoil.
Smart Images
Figure 00000000_0000_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to an integrated landing gear of a fire-fighting unmanned aerial vehicle. Background Art
[0002] Drones can be divided into military and civilian applications according to their application areas. Currently, they are used in aerial photography, agriculture, plant protection, micro selfies, express delivery, disaster relief, wildlife observation, infectious disease monitoring, surveying and mapping, news reporting, power inspections, disaster relief, film and television shooting, creating romance, and other fields. With the widespread use of drones, more and more people are using drones to extinguish fires. Drones are equipped with landing gears. There are at least the following disadvantages in the use of existing drones: 1. Existing drones are supported by landing gears during takeoff and landing, but drones will generate a large impact force when landing, which makes the landing gear of the drone easily damaged by impact, affecting its service life; 2. When existing drones are extinguishing fires, the fire-extinguishing bombs are released by ejection. This release method will generate recoil during the process, which is easy to affect the normal flight of the drone and reduce its practicality. Therefore, we have introduced an integrated landing gear for fire-fighting drones. Utility Model Content
[0003] The main purpose of the utility model is to provide an integrated landing gear for a fire-fighting drone, which can effectively solve the problems in the background technology.
[0004] In order to achieve the above purpose, the technical solution adopted by the utility model is:
[0005] An integrated landing gear for a fire-fighting drone comprises a drone landing gear, wherein the front lower end and the rear lower end of the drone landing gear are fixedly connected with a shock absorbing mechanism, the lower ends of two of the shock absorbing mechanisms are fixedly connected with three support rods, and legs are interspersed and fixedly connected between the lower ends of the three front support rods and the lower ends of the three rear support rods, a fire extinguishing mechanism is fixedly connected to the middle lower end of the drone landing gear, a door is provided at the middle right end of the fire extinguishing mechanism, a fixing frame is fixedly connected between the upper end of the fire extinguishing mechanism and the frame wall of the drone landing gear, and mounting holes are provided at the four corners of the upper end of the drone landing gear.
[0006] Preferably, the fire extinguishing mechanism includes a launch bin, the lower parts of the front bin wall and the rear bin wall of the launch bin are fixedly connected with guide plates, a launch port is opened in the middle part of the lower bin wall of the launch bin, the middle parts of the front mouth wall and the middle parts of the rear mouth wall of the two launch ports are interspersed and fixedly connected with electric telescopic rods, and the output ends of the two electric telescopic rods are fixedly connected with movable frames, and the lower end of the upper UAV landing gear of the launch bin is fixedly connected to the lower end of the fixed frame.
[0007] Preferably, the height of the launch chamber is smaller than the height of the support rod, the upper end surfaces of the two guide plates are inclined toward the middle, the launch port is configured as a convex structure, and the movable frame is configured as an L-shaped structure.
[0008] Preferably, the shock absorbing mechanism includes a shock absorbing frame, a fixed block is fixedly connected to the middle of the lower frame wall of the shock absorbing frame, a shock absorber is fixedly connected to the middle of the upper end of the fixed block, and the upper end of the shock absorber is fixedly connected to the lower end of the UAV landing gear, and a buffer mechanism is fixedly connected between the left frame wall of the shock absorbing frame and the left end of the fixed block and between the right frame wall of the shock absorbing frame and the right end of the fixed block.
[0009] Preferably, the buffer mechanism includes a buffer block, a connecting groove is opened in the middle of the upper end of the buffer block, a buffer rod is movably connected between the front groove wall and the rear groove wall of the connecting groove through a movable shaft, and the upper part of the outer surface of the buffer rod is movably connected to the lower end of the UAV landing gear through a connecting seat, a fixing rod is movably connected through the lower part of the right end of the buffer block, and a buffer spring is sleeved on the left and right parts of the outer surface of the fixing rod.
[0010] Preferably, the lower end surface of the buffer block contacts the lower frame wall of the shock absorbing frame, and the lower end surface of the buffer spring is higher than the lower frame wall of the shock absorbing frame.
[0011] Compared with the prior art, the utility model has the following beneficial effects:
[0012] 1. In the utility model, by setting a shock absorbing mechanism and a buffer mechanism, the landing gear generates an impact force on the shock absorbing frame when landing, and then the impact force is buffered by the buffer block sliding outward, and the shock absorbing effect of the landing gear can be enhanced by the elasticity of the buffer spring and the auxiliary shock absorption of the shock absorber, so that the landing gear of the UAV is not easily damaged by impact, and the service life of the landing gear is extended;
[0013] 2. In the utility model, by setting up a fire extinguishing mechanism, the movable frame is pulled outward by contracting the electric telescopic rod, so that the fire extinguishing bomb is launched from the opened launching port to extinguish the fire. The fire extinguishing bomb can be released freely, avoiding the recoil force generated by the catapult-type release, thereby ensuring the normal flight of the UAV, effectively improving the stability of the UAV, and also improving the practicality. BRIEF DESCRIPTION OF THE DRAWINGS
[0014] Figure 1 This is a schematic diagram of the overall structure of an integrated landing gear of a fire-fighting UAV of the utility model;
[0015] Figure 2 This is a schematic diagram of the overall structure of the shock absorbing mechanism of the integrated landing gear of a fire-fighting UAV of the utility model;
[0016] Figure 3This is a schematic diagram of the overall structure of a buffer mechanism of an integrated landing gear of a fire-fighting UAV of the utility model;
[0017] Figure 4 The utility model is a schematic diagram of the overall structure of the fire extinguishing mechanism of the integrated landing gear of a fire extinguishing UAV.
[0018] In the figure: 1. UAV landing gear; 2. shock absorbing mechanism; 3. support rod; 4. outrigger; 5. fire extinguishing mechanism; 6. cabin door; 7. mounting hole; 8. fixing frame; 21. shock absorbing frame; 22. fixing block; 23. shock absorber; 24. buffer mechanism; 241. buffer block; 242. connecting groove; 243. buffer rod; 244. fixing rod; 245. buffer spring; 51. launching cabin; 52. guide plate; 53. launching port; 54. electric telescopic rod; 55. movable frame. DETAILED DESCRIPTION
[0019] In order to make the technical means, creative features, objectives and effects achieved by the present invention easy to understand, the present invention is further described below in conjunction with specific implementation methods.
[0020] In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front end", "rear end", "two ends", "one end", "the other end" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.
[0021] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "provided with", "connected", etc. should be understood in a broad sense. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.
[0022] See also Figure 1-4 , the utility model provides a technical solution:
[0023] An integrated landing gear for a fire-fighting UAV comprises a UAV landing gear 1, wherein a shock absorbing mechanism 2 is fixedly connected to the front and rear of the lower end of the UAV landing gear 1, three support rods 3 are fixedly connected to the lower ends of the two shock absorbing mechanisms 2, legs 4 are interlaced and fixedly connected between the lower ends of the three front support rods 3 and the lower ends of the three rear support rods 3, a fire extinguishing mechanism 5 is fixedly connected to the middle of the lower end of the UAV landing gear 1, a door 6 is provided at the middle of the right end of the fire extinguishing mechanism 5, a fixing frame 8 is fixedly connected between the upper end of the fire extinguishing mechanism 5 and the frame wall of the UAV landing gear 1, and mounting holes 7 are provided at the four corners of the upper end of the UAV landing gear 1.
[0024] In this embodiment, the shock absorbing mechanism 2 includes a shock absorbing frame 21, a fixed block 22 is fixedly connected to the middle of the lower frame wall of the shock absorbing frame 21, a shock absorber 23 is fixedly connected to the middle of the upper end of the fixed block 22, and the upper end of the shock absorber 23 is fixedly connected to the lower end of the UAV landing gear 1, and a buffer mechanism 24 is fixedly connected between the left frame wall of the shock absorbing frame 21 and the left end of the fixed block 22 and between the right frame wall of the shock absorbing frame 21 and the right end of the fixed block 22; the buffer mechanism 24 includes a buffer block 241, a connecting groove 242 is opened in the middle of the upper end of the buffer block 241, and a buffer rod is movably connected between the front groove wall and the rear groove wall of the connecting groove 242 through a movable shaft 243, and the upper part of the outer surface of the buffer rod 243 is movably connected to the lower end of the UAV landing gear 1 through a connecting seat, and the lower part of the right end of the buffer block 241 is movably connected with a fixing rod 244, and the left part and the right part of the outer surface of the fixing rod 244 are both sleeved with a buffer spring 245; the lower end surface of the buffer block 241 contacts the lower frame wall of the shock absorber frame 21, so that the shock absorber frame 21 limits the buffer block 241, so that the buffer block 241 can only move left and right, and the lower end surface of the buffer spring 245 is higher than the lower frame wall of the shock absorber frame 21, so that the buffer spring 245 does not contact the shock absorber frame 21, and does not affect the contraction buffering of the buffer spring 245.
[0025] In this embodiment, the fire extinguishing mechanism 5 includes a launch chamber 51, the lower part of the front chamber wall and the lower part of the rear chamber wall of the launch chamber 51 are fixedly connected with guide plates 52, a launch port 53 is opened in the middle of the lower chamber wall of the launch chamber 51, the middle part of the front chamber wall and the middle part of the rear chamber wall of the two launch ports 53 are interspersed and fixedly connected with electric telescopic rods 54, and the output ends of the two electric telescopic rods 54 are fixedly connected with movable frames 55, and the lower end of the upper end of the UAV landing gear 1 of the launch chamber 51 is fixedly connected with the lower end of the fixed frame 8; the height of the launch chamber 51 is less than the height of the support rod 3, and the upper end surfaces of the two guide plates 52 are inclined toward the middle, so as to facilitate the diversion of the fire extinguishing bomb in the launch chamber 51 to the launch port 53, the launch port 53 is set as a convex structure, and the movable frame 55 is set as an L-shaped structure, so that the movable frame 55 is limited in the launch port 53, which can improve the stability of the movable frame 55, and the interior of the launch chamber 51 is filled with a plurality of fire extinguishing bombs.
[0026] It should be noted that the utility model is an integrated landing gear for a fire-fighting UAV. When using the fire-fighting UAV to extinguish a fire, first open the cabin door 6 to fill the launch cabin 51 with fire-extinguishing bombs, and then install and fix the UAV landing gear 1 on the UAV through the mounting hole 7. At this time, the UAV and the UAV landing gear 1 can be remotely controlled to the top of the fire location through a remote controller, and the electric telescopic rod 54 can be remotely controlled to start. The two electric telescopic rods 54 shrink at the same time, and can respectively drive the two movable frames 55 to pull outward in the launch port 53 to expose the launch port 53. Any fire-extinguishing bomb inside can be diverted to the launch port 53 through the guide plate 52, and the fire-extinguishing bomb can be freely launched from the opened launch port 53 to extinguish the fire, avoiding the use of ejection. The fire-extinguishing bomb dropped in this way produces a large recoil force on the UAV, thereby ensuring the normal flight of the UAV, effectively improving the stability of the UAV, and also improving the practicality. When the UAV lands, the outrigger 4 contacts the ground first, and the impact force generated during landing causes the support rod 3 to generate a thrust on the shock absorber frame 21, causing the buffer block 241 to slide outward on the fixed rod 244, so as to buffer and shock-absorb the impact force through the movable buffer rod 243, and then through the elasticity generated by the buffer spring 245 on the buffer block 241, and then with the auxiliary shock absorption of the shock absorber 23 and the suppression of the rebound of the buffer spring 245, the shock absorption and buffering effect of the UAV landing gear 1 can be enhanced, so that the UAV landing gear 1 is not easily damaged by impact, and the service life of the UAV landing gear 1 is effectively extended.
[0027] The above shows and describes the basic principle and main features of the utility model and the advantages of the utility model. Those skilled in the art should understand that the utility model is not limited by the above embodiments. The above embodiments and descriptions are only for explaining the principle of the utility model. Without departing from the spirit and scope of the utility model, the utility model may have various changes and improvements, which fall within the scope of the utility model to be protected. The scope of protection claimed by the utility model is defined by the attached claims and their equivalents.
Claims
1. An integrated landing gear for a fire-fighting drone, comprising a drone landing gear (1), characterized in that: The front and rear parts of the lower end of the UAV landing gear (1) are fixedly connected with a shock absorbing mechanism (2), the lower ends of the two shock absorbing mechanisms (2) are fixedly connected with three support rods (3), the lower ends of the three front support rods (3) and the lower ends of the three rear support rods (3) are interlaced and fixedly connected with a support leg (4), the middle part of the lower end of the UAV landing gear (1) is fixedly connected with a fire extinguishing mechanism (5), the middle part of the right end of the fire extinguishing mechanism (5) is provided with a cabin door (6), the upper end of the fire extinguishing mechanism (5) and the frame wall of the UAV landing gear (1) are fixedly connected with a fixing frame (8), and the four corners of the upper end of the UAV landing gear (1) are provided with mounting holes (7); The fire extinguishing mechanism (5) comprises a launch chamber (51), the lower part of the front chamber wall and the lower part of the rear chamber wall of the launch chamber (51) are both fixedly connected with a guide plate (52), the middle part of the lower chamber wall of the launch chamber (51) is provided with a launch port (53), the middle part of the front chamber wall and the middle part of the rear chamber wall of the two launch ports (53) are both interlaced and fixedly connected with electric telescopic rods (54), and the output ends of the two electric telescopic rods (54) are both fixedly connected with a movable frame (55), and the lower end of the upper UAV landing gear (1) of the launch chamber (51) is fixedly connected to the lower end of the fixed frame (8).
2. The integrated landing gear of a fire-fighting drone according to claim 1, characterized in that: The height of the launch chamber (51) is smaller than the height of the support rod (3), the upper end surfaces of the two guide plates (52) are both arranged to be inclined toward the middle, the launch port (53) is arranged to be a convex structure, and the movable frame (55) is arranged to be an L-shaped structure.
3. The integrated landing gear of a fire-fighting drone according to claim 1, characterized in that: The shock absorbing mechanism (2) comprises a shock absorbing frame (21), a fixing block (22) is fixedly connected to the middle of the lower frame wall of the shock absorbing frame (21), a shock absorber (23) is fixedly connected to the middle of the upper end of the fixing block (22), and the upper end of the shock absorber (23) is fixedly connected to the lower end of the UAV landing gear (1), and a buffer mechanism (24) is fixedly connected between the left frame wall of the shock absorbing frame (21) and the left end of the fixing block (22) and between the right frame wall of the shock absorbing frame (21) and the right end of the fixing block (22).
4. The integrated landing gear of a fire-fighting drone according to claim 3 is characterized in that: The buffer mechanism (24) comprises a buffer block (241), a connecting groove (242) is formed in the middle of the upper end of the buffer block (241), a buffer rod (243) is movably connected between the front groove wall and the rear groove wall of the connecting groove (242) via a movable shaft, and the upper part of the outer surface of the buffer rod (243) is movably connected to the lower end of the UAV landing gear (1) via a connecting seat, a fixing rod (244) is inserted and movably connected to the lower part of the right end of the buffer block (241), and a buffer spring (245) is sleeved on the left and right parts of the outer surface of the fixing rod (244).
5. The integrated landing gear of a fire-fighting drone according to claim 4 is characterized in that: The lower end surface of the buffer block (241) contacts the lower frame wall of the shock absorbing frame (21), and the lower end surface of the buffer spring (245) is higher than the lower frame wall of the shock absorbing frame (21).