Ducted-fan drone for firefighting and fire truck

Abstract

A ducted-fan drone for firefighting and a fire truck. The ducted-fan drone for firefighting comprises: a first support beam (1) extending longitudinally, at least three ducted propulsion systems (3) being provided on each of two sides of the first support beam (1) in the width direction perpendicular to the length direction of the first support beam (1). A fire monitor (7) is provided on the first support beam (1), and can spray a fire extinguishing agent.

Description

Ductless drones and fire trucks used for firefighting

[0001] Cross-references to related applications

[0002] This application claims priority to Chinese Patent Application No. 202411620033.6, filed on November 13, 2024, entitled "Culverted Unmanned Aerial Vehicle and Fire Truck for Firefighting", the entire contents of which are incorporated herein by reference. Technical Field

[0003] This application relates to the field of ducted unmanned aerial vehicle (UAV) technology, and more specifically, to a ducted UAV and fire truck used for firefighting. Background Technology

[0004] Currently, there are some firefighting drones based on multi-rotor engines on the market, but their payload capacity is small, and they can only carry a few fire extinguishing bombs. They have a certain fire extinguishing capability for the initial stage of building fires, but for fires in super high-rise buildings, fire trucks / firefighting drones have difficulty arriving at the early stage of the fire to carry out firefighting work. When the fire is large, their actual firefighting significance is not great.

[0005] Therefore, using ducted-duct UAVs can improve payload capacity and achieve the purpose of high-altitude firefighting. However, increasing the payload capacity of ducted-duct UAVs will also increase their size, which will make it impossible for them to pass through some narrow spaces. Therefore, it is urgent to design a ducted-duct UAV that can meet the power load requirements and also pass through narrow areas, so as to improve the adaptability of ducted-duct UAVs. Summary of the Invention

[0006] This application provides a ducted drone and fire truck for firefighting, which can pass through narrow areas while meeting the power load requirements, thereby improving the adaptability of the ducted drone for firefighting.

[0007] To solve the above-mentioned technical problems, this application adopts the following technical solution:

[0008] In a first aspect, this application provides a ducted unmanned aerial vehicle (UAV) for firefighting, comprising: a longitudinally extending first support beam, with at least three ducted propulsion systems arranged on each side along both sides perpendicular to the length and width directions of the first support beam; and a fire monitor mounted on the first support beam, the fire monitor being capable of spraying fire extinguishing agent.

[0009] In the implementation of the above scheme, the ducted unmanned aerial vehicle (UAV) includes a first support beam extending longitudinally, and at least three ducted propulsion systems are arranged on each side along the length and width directions perpendicular to the first support beam. In this way, the ducted propulsion systems are arranged on the first support beam, so that the ducted UAV extends along the length direction and has a longitudinal structure, enabling the ducted UAV to pass through narrow areas. At least three ducted propulsion systems are arranged on each side along the width direction of the first support beam to meet the power load, and a fire monitor is provided on the first support beam. The fire monitor can be connected to the water hose and can spray fire extinguishing agent, enabling the ducted UAV to perform high-altitude fire extinguishing.

[0010] In one embodiment, the ducted unmanned aerial vehicle (UAV) further includes a second support beam, which is perpendicularly connected to the first support beam. At least two ducted propulsion systems are fixedly connected to one side of the first support beam, and at least two ducted propulsion systems are fixedly connected to one side of the second support beam. All of the ducted propulsion systems are inclined upwards.

[0011] In implementing the above scheme, the ducted drone also includes a second support beam, which is perpendicularly connected to the first support beam. At least two ducted propulsion systems are fixedly connected to one side of the first support beam, meaning that at least four ducted propulsion systems can be fixed on the first support beam. Similarly, at least two ducted propulsion systems are fixedly connected to one side of the second support beam, meaning that at least four ducted propulsion systems can be fixed on the second support beam. This makes the ducted drone at least an eight-ducted drone, increasing its power load. The multiple ducted propulsion systems are evenly distributed, making control easier and providing a larger power margin. The impact of a single motor failure on the entire drone is smaller. The upward tilt of the multiple ducted propulsion systems effectively increases the controllability of the ducted drone, facilitating operation and improving efficiency, thereby buying valuable time for firefighting.

[0012] In one embodiment, the first support beam is provided with at least one foldable duct propulsion system.

[0013] In the implementation of the above scheme, at least one foldable ducted propulsion system is provided on the first support beam, which can reduce the size of the ducted UAV, facilitate transportation and placement, and improve space utilization.

[0014] In one embodiment, at least four duct propulsion systems are provided on one side of the first support beam perpendicular to its length in the horizontal direction. Two of the duct propulsion systems located at both ends of the same side of the first support beam are configured as a first duct propulsion system and a second duct propulsion system. The first duct propulsion system and the second duct propulsion system can be folded along the length of the first support beam toward the duct propulsion system connected to it.

[0015] In the implementation of the above scheme, at least four ducted propulsion systems are arranged on one side of the horizontal direction perpendicular to the length direction of the first support beam. Two ducted propulsion systems located at both ends of the same side of the first support beam are configured as the first ducted propulsion system and the second ducted propulsion system. The first ducted propulsion system and the second ducted propulsion system can be folded along the length direction of the first support beam toward the ducted propulsion system connected to them, thereby reducing the space occupied in the width direction of the ducted UAV and improving space utilization. At the same time, the first ducted propulsion system and the second ducted propulsion system are folded along the length direction of the first support beam, so that the first ducted propulsion system and the second ducted propulsion system do not interfere with each other during the folding process. There is folding space around the ducted propulsion systems connected to the first ducted propulsion system and the second ducted propulsion system respectively. The folding angle of the first ducted propulsion system and the second ducted propulsion system toward the ducted propulsion system connected to them can be increased, further increasing space utilization.

[0016] In one embodiment, four duct propulsion systems are provided on one side of the first support beam, three of which are connected to the first support beam and are configured as a first duct propulsion system, a second duct propulsion system, and a third duct propulsion system, with the second duct propulsion system located between the first and third duct propulsion systems; the other duct propulsion system is connected to the second duct propulsion system and can be folded toward the second duct propulsion system along the length direction perpendicular to the first support beam.

[0017] In the implementation of the above scheme, four ducted propulsion systems are provided on one side of the first support beam, making the ducted UAV of this application an eight-ducted UAV. Three of these ducted propulsion systems are connected to the first support beam and are configured as a first, second, and third ducted propulsion system. This means that three ducted propulsion systems can be installed on one side of the first support beam, thereby reducing the length of the ducted UAV and improving space utilization. The second ducted propulsion system is located between the first and third ducted propulsion systems. The third ducted propulsion system is connected to the second ducted propulsion system and can be folded towards the second ducted propulsion system along the length direction perpendicular to the first support beam, further reducing the width of the ducted UAV and facilitating transportation. Especially when the ducted UAV is placed on a fire truck, it facilitates the placement of other components on the fire truck, allowing the fire truck to be smaller in both width and length, making it easier for the fire truck to pass through narrow areas. The ducted UAV of this application, while meeting the requirements for power load, reduces the length dimension and facilitates transportation and placement.

[0018] In one embodiment, three duct propulsion systems are provided on one side of the first support beam perpendicular to its length in the horizontal direction. Each end of the first support beam is also provided with a duct propulsion system. The two duct propulsion systems located at the ends of the first support beam can be folded toward the first support beam along its length.

[0019] In the implementation of the above scheme, three ducted propulsion systems are set on one side of the horizontal direction perpendicular to the length direction of the first support beam, and one ducted propulsion system is also set at each end of the first support beam. The two ducted propulsion systems at the ends of the first support beam can be folded towards the first support beam along the length direction of the first support beam, so that the ducted UAV of this application is an eight-ducted UAV. The three ducted propulsion systems on each side of the first support beam, compared with the four ducted propulsion systems on one side of the first support beam, can reduce the length of the first support beam, further reducing the space of the ducted UAV in length. Moreover, the two ducted propulsion systems at the ends of the first support beam can be folded towards the first support beam along the length direction of the first support beam, further reducing the space of the ducted UAV in length, which is convenient for transportation. In particular, when the ducted UAV is placed on a fire truck, it is beneficial to place other parts on the fire truck, so that the fire truck can be made smaller in length, making it easier for the fire truck to pass through narrow areas.

[0020] In one embodiment, the ducted unmanned aerial vehicle (UAV) is further provided with a folding mechanism, through which the ducted propulsion system is folded; the folding mechanism includes a first connector and a second connector that are rotatably connected, the first connector and the second connector being respectively connected to two of the ducted propulsion systems, and the folding mechanism further includes a drive assembly, which is connected to the first connector and the second connector, and the drive assembly can drive the second connector to flip relative to the first connector.

[0021] In the implementation of the above scheme, the ducted propulsion system is also equipped with a folding mechanism. By setting the folding mechanism, the ducted propulsion system can be folded along its length or width, thereby reducing the space of the ducted propulsion system and facilitating transportation and placement. The folding mechanism includes a first connector and a second connector that are rotatably connected. The first connector and the second connector are respectively connected to the two ducted propulsion systems, which allows the ducted propulsion systems to rotate and facilitate folding. The folding mechanism also includes a drive component that is connected to the first connector and the second connector. At the same time, the drive component can drive the second connector to rotate relative to the first connector, thereby causing the ducted propulsion system connected to the second connector to rotate, thus realizing the folding of the ducted propulsion system.

[0022] In one embodiment, the first connector has a first through hole, and the driving assembly includes a driving member disposed at the position of the first through hole and rotatably connected to the first connector; the second connector has a second through hole, and the driving assembly further includes a rotating member disposed at the position of the second through hole and rotatably connected to the second connector; the driving assembly further includes a connecting rod, one end of which is threadedly connected to the rotating member, and the other end of which is connected to the driving member, and the driving member is configured to drive the connecting rod to rotate.

[0023] In the implementation of the above scheme, the first connecting member has a first through hole, and the driving assembly includes a driving member, which is located at the first through hole and rotatably connected to the first connecting member, allowing the driving member to rotate relative to the first connecting member; the second connecting member has a second through hole, and the driving assembly also includes a rotating member, which is located at the second through hole and rotatably connected to the second connecting member, allowing the rotating member to rotate relative to the second connecting member; the driving assembly also includes a connecting rod, one end of which is threadedly connected to the rotating member, and the other end is connected to the driving member. When the driving member drives the connecting rod to rotate, the connecting rod is threadedly connected to the rotating member, allowing... This allows the rotating component to move towards or away from the driving component. While driving the rotating component to move, the rotating component is also rotatably connected to the second connecting component, which also causes the second connecting component to flip relative to the first connecting component, thus realizing the folding function of the ducted propulsion system. During the flipping process of the second connecting component, the driving and rotating components need to adjust their angles in real time. Therefore, the driving component and the rotating component are rotatably connected to the first and second connecting components respectively, so that while driving the rotating component to rotate, the driving component and the rotating component adjust their angles in real time. This allows the driving component to better drive the rotating component to move on the connecting rod, making it easier to control the folding mechanism and avoiding jamming.

[0024] In one embodiment, the driving member is provided with a first connecting hole, and the driving member is rotatably connected to the first connecting member through the first connecting hole. The second connecting member can be rotated around the connection position between the first connecting member and the second connecting member, and the axis of the second connecting member used for rotation is parallel to the axis of the first connecting hole. The axis of the connecting rod is perpendicular to the first connecting hole. The rotating member is provided with a second connecting hole, and the rotating member is rotatably connected to the second connecting member through the second connecting hole. The second connecting member can be rotated around the connection position between the first connecting member and the second connecting member, and the axis of the second connecting member used for rotation is parallel to the axis of the second connecting hole. The axis of the connecting rod is perpendicular to the second connecting hole.

[0025] In the implementation of the above scheme, the driving component is provided with a first connecting hole, through which it is rotatably connected to a first connecting member. This allows the driving component to rotate around the first connecting member with the first connecting hole as its axis. Simultaneously, the second connecting member can be flipped around the connection point between the first and second connecting members, with the axis of this flipped position configured as a first axis. The axis of the first connecting hole is parallel to the first axis, and the axis of the connecting rod is perpendicular to the first connecting hole. Thus, when the driving component drives the connecting rod to rotate, the second connecting member flips, and the driving component also rotates relative to the first connecting member in real time through the first connecting hole, maintaining a corresponding angle between the driving component and the rotating component for better driving of the rotating component. The rotating component is provided with a second connecting hole, through which it is rotatably connected to the second connecting member. In this way, the rotating component can rotate around the second connecting hole as an axis. At the same time, the second connecting component can be flipped around the connection position between the first and second connecting components. The axis of the flipping position can be configured as the first axis. The axis of the second connecting hole is parallel to the first axis, and the axis of the connecting rod is perpendicular to the second connecting hole. Thus, when the driving component drives the connecting rod to rotate, the second connecting component flips, and the connecting rod is threadedly connected to the rotating component. The driving angle of the driving component changes, which in turn drives the rotating component to change its angle. The rotating component also adjusts its rotation angle in real time through the second connecting hole to keep it consistent with the driving component. This allows the driving component to maintain an angle corresponding to the rotating component in real time, which facilitates the driving component to better drive the rotating component and further facilitates the folding function of the ducted propulsion system, avoiding jamming.

[0026] In one embodiment, the fire monitor includes a hose connector fixed to the first support beam. The fire monitor also includes a main water pipe and a diversion joint. The diversion joint is connected to the hose connector, with one connector connected to the main water pipe and the other connector extending in another direction.

[0027] In the implementation of the above scheme, the fire monitor includes a hose connector, which is fixed on the first support beam for easy connection with the hose. This allows the extinguishing agent in the tank to enter the fire monitor through the hose and be sprayed by the fire monitor to achieve the purpose of extinguishing the fire. The fire monitor also includes a main water pipe, which is used to guide the extinguishing agent, and a diversion connector, which is connected to the hose connector. The main water pipe is connected to the diversion connector, and the other connector of the diversion connector extends in another direction. By setting the diversion connector, the extinguishing agent can be diverted, allowing the ducted drone to install more main water pipes for fire extinguishing, thereby improving the fire extinguishing effect.

[0028] In one embodiment, the first support beam includes multiple carbon fiber plates, which are spliced ​​together to form a frame structure; the first support beam also includes multiple support members, which are connected to two adjacent carbon fiber plates and protrude from both sides of the frame structure, configured to connect with the duct propulsion system.

[0029] In the implementation of the above scheme, the first support beam includes multiple carbon fiber plates, which are spliced ​​together to form a frame structure. By splicing the carbon fiber plates into a frame structure, the overall weight of the ducted unmanned aerial vehicle (UAV) can be reduced, and its strength can be improved to meet the strength and stiffness requirements of the ducted UAV. The first support beam also includes multiple support members, which are connected to two adjacent carbon fiber plates. The support members protrude from both sides of the frame structure and are configured to connect with the ducted propulsion system. This allows the support members to connect to both the two carbon fiber plates and the two ducted propulsion systems, reducing the number of parts in the ducted UAV, lowering its weight, and facilitating control.

[0030] Secondly, this application provides a fire truck equipped with the ducted drone for firefighting described in the first aspect.

[0031] In the implementation of the above scheme, fire trucks are equipped with ducted drones, which can connect with water hoses to carry out firefighting operations. At the same time, due to the small size of the ducted drones, the space utilization of fire trucks can be improved, allowing fire trucks to pass through some narrow areas and improving adaptability. Attached Figure Description

[0032] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0033] Figure 1 is a structural schematic diagram of the ducted unmanned aerial vehicle provided in an embodiment of this application;

[0034] Figure 2 is a structural schematic diagram of the ducted unmanned aerial vehicle provided in the embodiment of this application from different perspectives;

[0035] Figure 3 is a schematic diagram of a partial explosion structure of a ducted unmanned aerial vehicle provided in an embodiment of this application;

[0036] Figure 4 is a structural schematic diagram of a ducted unmanned aerial vehicle provided in another embodiment of this application;

[0037] Figure 5 is a structural schematic diagram of a ducted unmanned aerial vehicle provided in another embodiment of this application;

[0038] Figure 6 is a structural schematic diagram of a ducted unmanned aerial vehicle provided in different embodiments of this application;

[0039] Figure 7 is a structural schematic diagram of a ducted unmanned aerial vehicle provided in another embodiment of this application;

[0040] Figure 8 is a structural schematic diagram of a ducted unmanned aerial vehicle provided in another embodiment of this application;

[0041] Figure 9 is a structural schematic diagram of the fire truck provided in an embodiment of this application;

[0042] Figure 10 is a partial structural schematic diagram of the ducted unmanned aerial vehicle provided in an embodiment of this application;

[0043] Figure 11 is a structural schematic diagram of the ducted unmanned aerial vehicle provided in the embodiments of this application from different perspectives.

[0044] Icons: 1-First support beam; 11-Carbon fiber plate; 12-Support component; 121-Support piece; 122-Support base; 13-Aluminum bracket; 2-Second support beam; 3-Duct propulsion system; 31-First duct propulsion system; 32-Second duct propulsion system; 33-Third duct propulsion system; 4-First connector; 5-Second connector; 6-Drive assembly; 61-Drive component; 611-First connecting hole; 62-Connecting rod; 63-Rotating component; 7-Fire monitor; 71-Hose connector; 72-Main water pipe; 73-Diverter connector; 74-Fuselage mounting water pipe; 75-Water pipe mount; 8-Power generation module; 9-Liquid tank; 10-Tethered cable reel; 14-Water pump system; 16-Flight control system; 17-High voltage power distribution system; 18-Limiting component. Detailed Implementation

[0045] The technical solutions in the embodiments of this application will now be described with reference to the accompanying drawings.

[0046] It should be noted that similar reference numerals and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. Furthermore, in the description of this application, terms such as "first," "second," etc., are used only to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0047] As shown in Figures 1 and 4 to 8, in a first aspect, embodiments of this application provide a ducted drone for firefighting. The ducted drone includes a first support beam 1 extending longitudinally, and at least three ducted propulsion systems 3 are provided on each side along both the length and width directions perpendicular to the first support beam 1. The ducted propulsion systems 3 are arranged on the first support beam 1, so that the ducted drone as a whole extends along the length direction and has a longitudinal structure, enabling the ducted drone to pass through narrow areas. At least three ducted propulsion systems 3 are provided on each side along the width direction of the first support beam 1 to meet the dynamic load, and a fire monitor 7 is provided on the first support beam 1. The fire monitor 7 can be connected to a water hose and can spray fire extinguishing agent, enabling the ducted drone to perform high-altitude firefighting.

[0048] Optionally, the first support beam 1 extending longitudinally means that the first support beam 1 is a long strip.

[0049] As shown in Figure 1, optionally, the ducted unmanned aerial vehicle also includes a flight control system 16 fixed on the first support beam 1. The flight control system 16 is fixed on the first support beam 1 by a shock-absorbing device, thereby improving the stability of the flight control system 16.

[0050] Optionally, the damping device may include a damping bracket and a damper.

[0051] As shown in Figure 1, optionally, the first support beam 1 is also equipped with a high-voltage power distribution system 17 and a battery box (not shown in the figure). The cable is connected to the high-voltage power distribution system 17, and the battery box is connected to the high-voltage power distribution system 17. The high-voltage power distribution system 17 includes relays and fuses, etc., and can communicate with the flight control system 16 to distribute power according to the instructions of the flight control system 16.

[0052] Optionally, the battery box can maintain a stable DC voltage; at the same time, it can provide instantaneous power replenishment and absorb the power generated by the generator during deceleration; in addition, the battery box can also ensure that the ducted drone can land smoothly after the cable is de-energized.

[0053] As shown in Figure 2, optionally, at least two ducted propulsion systems 3 are tilted, thereby increasing the controllability of the ducted UAV.

[0054] Optionally, in this embodiment of the application, three ducted propulsion systems 3 can be provided on each side along the width direction perpendicular to the length direction of the first support beam 1, so that the ducted UAV is a six-ducted UAV, or four can be provided, so that it is an eight-ducted UAV, or five can be provided, so that it is a ten-ducted UAV.

[0055] As shown in Figure 4, in one embodiment, the ducted drone also includes a second support beam 2, which is perpendicularly connected to the first support beam 1. At least two ducted propulsion systems 3 are fixedly connected to one side of the first support beam 1, which means that at least four ducted propulsion systems 3 can be fixed on the first support beam 1. At least two ducted propulsion systems 3 are fixedly connected to one side of the second support beam 2, which means that at least four ducted propulsion systems 3 can be fixed on the second support beam 2. This makes the ducted drone at least an eight-ducted drone, which increases the power load. The multiple ducted propulsion systems 3 are evenly arranged, making them easier to control. They also have a larger power margin, and the impact on the whole machine is smaller when a single motor fails. The multiple ducted propulsion systems 3 are all tilted upwards, which can effectively increase the controllability of the ducted drone, facilitate operation, improve efficiency, and thus buy effective time for firefighting.

[0056] Optionally, the first support beam 1 and the second support beam 2 have the same length. Four ducted propulsion systems 3 can be fixed on the first support beam 1, and one can be fixed on each side of one end. Four ducted propulsion systems 3 can be fixed on the second support beam 2, and one can be fixed on each side of one end. Thus, the ducted UAV in this embodiment is an eight-ducted UAV, and the eight ducted propulsion systems 3 are arranged circumferentially, which facilitates control and gives the whole device a greater power margin. When a single ducted propulsion system 3 fails, the impact on the entire ducted UAV is smaller.

[0057] Optionally, the first support beam 1 and the second support beam 2 have the same structure.

[0058] Optionally, in this embodiment, each ducted propulsion system 3 is tilted, thereby increasing the controllability of the ducted unmanned aerial vehicle.

[0059] As shown in Figures 5 to 8, in one embodiment, the first support beam 1 is provided with at least one foldable ducted propulsion system 3, which can reduce the size of the ducted UAV, facilitate transportation and placement, and improve space utilization.

[0060] As shown in Figures 6 and 8, in one embodiment, at least four ducted propulsion systems 3 are arranged on one side of the first support beam 1 perpendicular to its length in the horizontal direction. Two ducted propulsion systems 3 located at both ends of the same side of the first support beam 1 are configured as a first ducted propulsion system 31 and a second ducted propulsion system 32. The first ducted propulsion system 31 and the second ducted propulsion system 32 can be folded along the length of the first support beam 1 toward the ducted propulsion system 3 connected to it, thereby reducing the space occupied in the width direction of the ducted UAV and improving space utilization. At the same time, the first ducted propulsion system 31 and the second ducted propulsion system 32 are folded along the length of the first support beam 1, so that the first ducted propulsion system 31 and the second ducted propulsion system 32 do not interfere with each other during the folding process. There is folding space around the ducted propulsion systems 3 connected to the first ducted propulsion system 31 and the second ducted propulsion system 32 respectively. The first ducted propulsion system 31 and the second ducted propulsion system 32 are folded toward the ducted propulsion system 3 connected to them respectively, which can increase the folding angle of the first ducted propulsion system 31 and the second ducted propulsion system 32, further increasing space utilization.

[0061] As shown in Figure 6, optionally, four ducted propulsion systems 3 can be set on one side of the first support beam 1, which can be an eight-ducted UAV. As shown in Figure 8, five ducted propulsion systems 3 can also be set on one side of the first support beam 1, which can be a ten-ducted UAV.

[0062] As shown in Figure 5, in one embodiment, four ducted propulsion systems 3 are provided on one side of the first support beam 1, that is, the ducted UAV of this application is an eight-ducted UAV, of which three ducted propulsion systems 3 are connected to the first support beam 1, and the three ducted propulsion systems 3 are configured as the first ducted propulsion system 31, the second ducted propulsion system 32 and the third ducted propulsion system 33. It is equivalent to that three ducted propulsion systems 3 can be set on one side of the first support beam 1, thereby reducing the length of the ducted UAV and improving space utilization. The second ducted propulsion system 32 is located between the first ducted propulsion system 31 and the third ducted propulsion system 33. The other ducted propulsion system is connected to the second ducted propulsion system 32 and can be folded toward the second ducted propulsion system 32 along the length direction perpendicular to the first support beam 1, thereby further reducing the space of the ducted UAV in width, which is convenient for transportation. In particular, when the ducted UAV is placed on a fire truck, it is beneficial to place other parts on the fire truck, so that the fire truck can be made smaller in width and length, making it easier for the fire truck to pass through narrow areas. The ducted unmanned aerial vehicle of this application reduces the length dimension while meeting the requirements of power load, and is also convenient for transportation and placement.

[0063] As shown in Figure 5, optionally, in this embodiment of the application, another ducted propulsion system 3 is connected to the second ducted propulsion system 32, so that the thrust generated by the ducted UAV is around the center of the ducted UAV, which facilitates control.

[0064] As shown in Figure 7, in one embodiment, three ducted propulsion systems 3 are arranged on one side of the first support beam 1 perpendicular to its length in the horizontal direction. A ducted propulsion system 3 is also provided at each end of the first support beam 1. The two ducted propulsion systems 3 at each end of the first support beam 1 can be folded towards the first support beam 1 along its length, making the ducted UAV of this application an eight-ducted UAV. The arrangement of three ducted propulsion systems 3 on each side of the first support beam 1, compared to four ducted propulsion systems 3 on one side of the first support beam 1, reduces the length of the first support beam 1, further reducing the space required for the ducted UAV in length. Furthermore, the foldable propulsion systems 3 at each end of the first support beam 1 further reduce the space required for the ducted UAV in length, facilitating transportation. Especially when the ducted UAV is placed on a fire truck, it facilitates the placement of other components on the fire truck, allowing the fire truck to be made smaller and easier to pass through narrow areas.

[0065] As shown in Figure 6, in one embodiment, the ducted propulsion system 3 is also equipped with a folding mechanism. By setting the folding mechanism, the ducted propulsion system 3 can be folded along its length or width, thereby reducing the space required for the ducted propulsion system 3 and facilitating transportation and placement. The folding mechanism includes a first connecting member 4 and a second connecting member 5 that are rotatably connected. The first connecting member 4 and the second connecting member 5 are respectively connected to the two ducted propulsion systems 3, which allows the ducted propulsion system 3 to rotate, facilitating folding. The folding mechanism also includes a drive component 6, which is connected to the first connecting member 4 and the second connecting member 5. At the same time, the drive component 6 can drive the second connecting member 5 to rotate relative to the first connecting member 4, thereby causing the ducted propulsion system 3 connected to the second connecting member 5 to rotate, thus realizing the folding of the ducted propulsion system 3.

[0066] Optionally, the first connecting member 4 and the second connecting member 5 are plate-shaped structures, which can increase the connection area with the ducted propulsion system 3, thereby improving structural stability. The first connecting member 4 and the second connecting member 5 can be connected by a hinge or by a connecting shaft, thereby realizing a rotatable connection between the first connecting member 4 and the second connecting member 5.

[0067] Optionally, a limiting member 18 is provided between the first connector 4 and the second connector 5, which can separate the first connector 4 and the second connector 5 by a certain gap during normal operation of the ducted drone, so as to prevent the first connector 4 and the second connector 5 from sticking together and causing the two ducted propulsion systems 3 connected to the first connector 4 and the second connector 5 to resonate, thereby affecting the flight of the ducted drone.

[0068] Optionally, the limiting member 18 can be set on the first connecting member 4 or on the second connecting member 5.

[0069] Optionally, the first connector 4 and the second connector 5 can be provided with lugs to connect with the duct body of the duct propulsion system 3.

[0070] As shown in Figure 6, in one embodiment, the first connecting member 4 has a first through hole, and the driving assembly 6 includes a driving member 61, which is located at the first through hole and rotatably connected to the first connecting member 4, allowing the driving member 61 to rotate relative to the first connecting member 4. The second connecting member 5 has a second through hole, and the driving assembly 6 also includes a rotating member 63, which is located at the second through hole and rotatably connected to the second connecting member 5, allowing the rotating member 63 to rotate relative to the second connecting member 5. The driving assembly 6 also includes a connecting rod 62, one end of which is threadedly connected to the rotating member 63, and the other end is connected to the driving member 61. When the driving member 61 drives the connecting rod 62 to rotate, the connecting rod 62 is threadedly connected to the rotating member 63. This allows the rotating component 63 to move toward or away from the driving component 61. While driving the rotating component 63 to move, the rotating component 63 is also rotatably connected to the second connecting component 5, which also causes the second connecting component 5 to flip relative to the first connecting component 4, thus realizing the folding function of the duct propulsion system 3. During the flipping process of the second connecting component 5, the driving component and the rotating component 63 need to adjust their angles in real time. Therefore, the driving component 61 and the rotating component 63 are rotatably connected to the first connecting component 4 and the second connecting component 5, respectively. This allows the driving component 61 to drive the rotating component 63 to rotate while adjusting their angles in real time. This enables the driving component 61 to better drive the rotating component 63 to move on the connecting rod 62, making it easier to control the folding mechanism and avoiding jamming.

[0071] Optionally, the positions of the first through hole and the second through hole should be as far away as possible from the position where the first connector 4 and the second connector 5 are rotatably connected, so that the driving component 61 can easily drive the second connector 5 to rotate.

[0072] Optionally, the driving component 61 and the rotating component 63 can be rotatably connected to the first connecting component 4 and the second connecting component 5 respectively via connecting shafts.

[0073] Optionally, when the rotating part 63 is connected to the second connecting part 5, the connecting shaft cannot pass through. That is, holes can be made at both ends of the rotating part 63, and the rotating part 63 can be rotatably connected to the second connecting part 5 through the connecting shaft. If the connecting shaft passes through, it will affect the threaded connection between the connecting rod 62 and the rotating part 63, and further affect the folding function of the ducted propulsion system 3.

[0074] Optionally, the drive component 61 can be a lead screw motor, and the connecting rod 62 can be an electric lead screw. The lead screw motor is connected to the electric lead screw and can drive the electric lead screw to rotate. The first connecting hole 611 can be formed on the housing of the lead screw motor, or the drive component 61 can also include a housing connected to the lead screw motor to avoid the first connecting hole 611 affecting the normal operation of the lead screw motor.

[0075] Optionally, the rotating part 63 can be a cylindrical round nut, with a second connecting hole in the radial direction, and the hole wall is a threaded section. The electric lead screw can also be threaded.

[0076] As shown in Figure 6, in one embodiment, the driving member 61 is provided with a first connecting hole 611. The driving member 61 is rotatably connected to the first connecting member 4 through the first connecting hole 611. In this way, the driving member 61 can rotate about the first connecting member 4 with the first connecting hole 611 as the axis. At the same time, the second connecting member 5 can be flipped with the connection position between the first connecting member 4 and the second connecting member 5 as the axis. The axis of the flipped position can be configured as the first axis. The axis of the first connecting hole 611 is parallel to the first axis, and the axis of the connecting rod 62 is perpendicular to the first connecting hole 611. Thus, when the driving member 61 drives the connecting rod 62 to rotate, the second connecting member 5 flips, and the driving member 61 also rotates relative to the first connecting member 4 in real time through the first connecting hole 611, so that the driving member 61 maintains an angle corresponding to the rotating member 63 in real time, so as to better drive the rotating member 63. The rotating member 63 is provided with a second connecting hole, and the rotating member 63 is connected to the second connecting member 4 through the second connecting hole. The connecting piece 5 is rotatably connected, allowing the rotating piece 63 to rotate around the second connecting hole as an axis. Simultaneously, the second connecting piece 5 can be flipped via the connection point between the first connecting piece 4 and the second connecting piece 5, with the axis of the flipped position configured as the first axis. The axis of the second connecting hole is parallel to the first axis, and the axis of the connecting rod 62 is perpendicular to the second connecting hole. Thus, when the driving member 61 drives the connecting rod 62 to rotate, the second connecting piece 5 flips, and the connecting rod 62 is threadedly connected to the rotating piece 63. The driving angle of the driving member 61 changes, correspondingly causing the rotating piece 63 to change its angle. The rotating piece 63 also adjusts its rotation angle in real time through the second connecting hole, maintaining consistency with the driving member 61. This ensures that the driving member 61 maintains an angle corresponding to the rotating piece 63, facilitating better driving of the rotating piece 63 by the driving member 61, further facilitating the folding function of the ducted propulsion system 3 and preventing jamming.

[0077] As shown in Figures 1 and 2, in one embodiment, the fire monitor 7 includes a hose connector 71, which is fixed to the first support beam 1 for easy connection with the hose. This allows the extinguishing agent in the liquid tank 9 to enter the fire monitor 7 through the hose and be sprayed by the fire monitor 7 to achieve the purpose of extinguishing the fire. The fire monitor 7 also includes a main water pipe 72, which is used to guide the extinguishing agent. It also includes a diversion connector 73, which is connected to the hose connector 71. The main water pipe 72 is connected to the diversion connector 73, and the other connector of the diversion connector 73 extends in another direction. By setting the diversion connector 73, the extinguishing agent can be diverted, allowing the ducted drone to install more main water pipes 72 for fire extinguishing, thereby improving the fire extinguishing effect.

[0078] As shown in Figure 2, optionally, the hose connector 71 can be set on the lower end face of the first support beam 1, so as to facilitate the connection between the hose and the hose connector 71. One of the connectors of the diversion connector 73 is connected to the main water pipe 72 in the horizontal direction, and the other connector extends upward, so that another main water pipe 72 can be installed above the first support beam 1, thereby increasing the flow rate of the ducted UAV.

[0079] Optionally, a flow sensor and a water spray nozzle can be installed at the end of the main water pipe 72. The flow sensor is configured to detect the flow rate, and the water spray nozzle can change the shape of the water spray.

[0080] As shown in Figure 3, optionally, the fire monitor 7 also includes a body-mounted water pipe 74, which is located inside the first support beam 1 and connected to another connector of the diversion connector 73, so that the extinguishing agent can be diverted upward. In this way, an additional main water pipe 72 can be installed on the upper end face of the first support beam 1.

[0081] As shown in Figure 3, optionally, a water pipe hanger 75 is also provided inside the first support beam 1. The water pipe hanger 75 is located at the center of the first support beam 1. The water pipe hanger 75 is sleeved on the outer periphery of the water pipe 74 installed on the machine body, which can protect the water pipe 74 installed on the machine body and also support the first support beam 1 in the vertical direction.

[0082] As shown in Figure 3, in one embodiment, the first support beam 1 includes multiple carbon fiber plates 11, which are spliced ​​together to form a frame structure. By splicing the carbon fiber plates 11 into a frame structure, the overall weight of the ducted drone can be reduced, and the strength can be improved to meet the strength and stiffness requirements of the ducted drone. The first support beam 1 also includes multiple support members 12, which are connected to two adjacent carbon fiber plates 11. The support members 12 protrude from both sides of the frame structure and are configured to connect with the ducted propulsion system 3. This allows the support members 12 to be connected to both the two carbon fiber plates 11 and the two ducted propulsion systems 3, reducing the number of parts in the ducted drone, reducing the weight of the ducted drone, and facilitating control.

[0083] As shown in Figures 3, 10, and 11, optionally, the support member 12 includes a support plate 121 and a support base 122. The support plate 121 passes through the cross-section of the first support beam 1, reducing the occupied area and improving the structural stability of the first support beam 1. The support plate 121 has protrusions on both sides, which can be connected to two adjacent carbon fiber plates 11 in the vertical direction. The support base 122 protrudes from the first support beam 1 and can cooperate with the clamp to fix the landing gear of the ducted unmanned aerial vehicle.

[0084] Optionally, the support member 12 can also be used to fix the duct propulsion system 3, which includes a duct body. The duct body is a cylindrical structure and can be fixedly connected to the support member 12 by bolts.

[0085] Optionally, the structure of the second support beam 2 is the same as that of the first support beam 1. The connection between the first support beam 1 and the second support beam 2 can be achieved by welding or by connecting them through the support member 12.

[0086] Optionally, the first support beam 1 also includes an L-shaped aluminum bracket 13, which is used to connect the carbon fiber plates 11 in the horizontal and vertical directions.

[0087] As shown in Figure 9, in a second aspect, this application provides a fire truck equipped with a ducted drone. The ducted drone can be connected to the water hose to perform firefighting operations. At the same time, due to the small size of the ducted drone, the space utilization of the fire truck can be improved, allowing the fire truck to pass through some narrow areas and improving its adaptability.

[0088] As shown in Figure 9, optionally, the fire truck is also equipped with a power generation module 8, which is located behind the fire truck's cab. The fire truck is also equipped with a liquid tank 9, which is located at the very rear of the fire truck. Since the liquid tank 9 stores extinguishing agent and is relatively heavy, and the power generation module 8 also has a certain weight, placing the power generation module 8 behind the cab and the liquid tank 9 at the very rear of the fire truck can balance the weight of the entire fire truck and ensure stability when driving it. At the same time, the layout is reasonable and improves the space utilization of the fire truck.

[0089] As shown in Figure 9, the fire truck is also equipped with a mooring cable reel 10, which is located behind the generator module 8, shortening the distance between the two and facilitating connection between them. The fire truck is also equipped with a water pump system 14, which is located between the mooring cable reel 10 and the liquid tank 9. This reasonable layout shortens the distance between the water pump system 14 and the liquid tank 9, reduces the number of pipe connections, and makes the fire-fighting equipment structure more compact, improving space utilization and allowing the fire-fighting equipment to pass through narrow areas, thus improving fire-fighting efficiency.

[0090] The liquid tank 9, the water pump system 14, and the mooring cable reel 10 are arranged along the same length of the fire truck body and are all located below the body. The upper part of the body is configured to accommodate the ducted drone, so that the various components in the body of this embodiment are arranged reasonably, have a high degree of integration, and can improve the flow rate of the extinguishing agent.

[0091] The above are merely preferred embodiments of this application and are not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

[0092] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

[0093] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element. Industrial applicability

[0094] In summary, this application provides a ducted drone and fire truck for firefighting, which can pass through narrow areas while meeting power load requirements, thereby improving the adaptability of the ducted drone for firefighting.

Claims

1. A ducted drone for firefighting, characterized in that, include: The first support beam extends longitudinally, and at least three duct propulsion systems are provided on each of its two sides along the length and width directions perpendicular to the first support beam. The first support beam is equipped with a fire monitor, which can spray fire extinguishing agent.

2. The ducted drone for firefighting of claim 1, wherein, The ducted unmanned aerial vehicle (UAV) also includes a second support beam, which is perpendicularly connected to the first support beam. At least two ducted propulsion systems are fixedly connected to one side of the first support beam, and at least two ducted propulsion systems are fixedly connected to one side of the second support beam. All of the ducted propulsion systems are inclined upwards.

3. The ducted drone for firefighting of claim 1, wherein, The first support beam is equipped with at least one foldable duct propulsion system.

4. The ducted drone for firefighting of claim 3, wherein, At least four duct propulsion systems are provided on one side of the first support beam in a horizontal direction perpendicular to its length. Two of the duct propulsion systems located at both ends of the same side of the first support beam are configured as a first duct propulsion system and a second duct propulsion system. The first duct propulsion system and the second duct propulsion system can be folded along the length of the first support beam toward the duct propulsion system connected to them, respectively.

5. The ducted drone for firefighting of claim 3, wherein, Four duct propulsion systems are provided on one side of the first support beam, three of which are connected to the first support beam and are configured as a first duct propulsion system, a second duct propulsion system, and a third duct propulsion system. The second duct propulsion system is located between the first duct propulsion system and the third duct propulsion system. The other duct propulsion system is connected to the second duct propulsion system and can be folded toward the second duct propulsion system along the length direction perpendicular to the first support beam.

6. The ducted drone for firefighting of claim 3, wherein, Three duct propulsion systems are provided on one side of the first support beam perpendicular to its length in the horizontal direction. Each end of the first support beam is also provided with a duct propulsion system. The two duct propulsion systems located at the ends of the first support beam can be folded toward the first support beam along its length.

7. The ducted drone for firefighting according to any one of claims 3 to 6, characterized in that, The ducted unmanned aerial vehicle is also equipped with a folding mechanism, through which the ducted propulsion system is folded; The folding mechanism includes a first connector and a second connector that are rotatably connected. The first connector and the second connector are respectively connected to the two ducted propulsion systems. The folding mechanism also includes a drive assembly that is connected to the first connector and the second connector. The drive assembly can drive the second connector to flip relative to the first connector.

8. The ducted drone for firefighting of claim 7, wherein, The first connector has a first through hole, and the driving assembly includes a driving member, which is disposed at the position of the first through hole and is rotatably connected to the first connector. The second connector is provided with a second through hole, and the drive assembly further includes a rotating member, which is disposed at the position of the second through hole and is rotatably connected to the second connector; The drive assembly further includes a connecting rod, one end of which is threadedly connected to the rotating member and the other end of which is connected to the drive member, the drive member being configured to drive the connecting rod to rotate.

9. The ducted drone for firefighting of claim 8, wherein, The driving component is provided with a first connecting hole, and the driving component is rotatably connected to the first connecting component through the first connecting hole. The second connecting component can be rotated around the connection position between the first connecting component and the second connecting component. The axis of the second connecting component for rotation is parallel to the axis of the first connecting hole, and the axis of the connecting rod is perpendicular to the first connecting hole. The rotating component is provided with a second connecting hole. The rotating component is rotatably connected to the second connecting component through the second connecting hole. The second connecting component can be rotated around the connection position between the first connecting component and the second connecting component. The axis of rotation of the second connecting component is parallel to the axis of the second connecting hole. The axis of the connecting rod is perpendicular to the second connecting hole.

10. The ducted drone for firefighting according to any one of claims 1 to 6, characterized in that, The fire monitor includes a hose connector, which is fixed to the first support beam. The fire monitor also includes a main water pipe and a diversion joint, which is connected to the hose connector. One of the diversion joints is connected to the main water pipe, and the other joint extends in another direction.

11. The ducted drone for firefighting of claim 10, wherein, The first support beam comprises multiple carbon fiber plates, which are spliced ​​together to form a frame structure; The first support beam also includes multiple support members, which are connected to two adjacent carbon fiber plates. The support members protrude from both sides of the frame structure and are configured to connect with the duct propulsion system.

12. A fire apparatus characterized by, The fire truck is equipped with a ducted unmanned aerial vehicle (UAV) for firefighting as described in any one of claims 1 to 11.

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