Electric flying life-saving buoy

Abstract

The present invention discloses an electric flying life-saving float, which comprises a shell, a flight component, a flight control component and a power module. The shell is a life-saving float having a gas storage cavity. The flight component is symmetrically provided outside the shell. The flight control component and the power module are mounted inside the shell and are electrically connected to the flight component and can be controlled to operate the flight component. In the present invention, the technologies of a life-saving float and a drone are combined. During the water rescue process, it can quickly fly close to the person who has fallen into the water, which is convenient for the person who has fallen into the water to make an emergency escape, greatly improving the rescue efficiency and safety. The integrated assembly waterproof structure design simplifies the structure. While its shell fully meets the buoyancy requirements of the life-saving float, it facilitates the storage of wiring, improves the electrical waterproof function, ensures the circuit safety of the drone, enables takeoff and landing on water, and during the flight rescue, it can take off again and land on the water as needed and finally fly close to the person who has fallen into the water.

Description

Technical Field

[0001] The present invention relates to the technical field of water rescue equipment, specifically an electric flying life-saving buoy.

Background Art

[0002] In China, with the development of water areas and sea areas, the frequency of people's maritime activities has gradually increased, and accordingly, drowning accidents have occurred frequently. All the conventional methods of dropping life-saving buoys are manual, making it difficult to drop them accurately. In many areas where water rescue is needed, people cannot reach, timely rescue cannot be carried out, and rescue by helicopter is costly and has low mobility. With the development of science and technology, drones have the advantages of low usage cost, high flight speed, and short preparation time, so their applications in various fields are advancing. Considering the need for rapid response in water rescue, drones with fast reaction and high mobility are widely used in water rescue. Using a drone to carry a life-saving buoy is a common means, but in this method, it is necessary to take out the life-saving buoy and the drone from the storage location in advance, make simple adjustments, and then start the operation, which takes relatively long time for preparation. When flying near a person who has fallen into the water and dropping the life-saving buoy, errors occur, so it cannot be guaranteed that the person who has fallen into the water can receive it. The surface rescue boat submitted with patent number 201921252749.X drives the rescue boat near the person who has fallen into the water with a remote control. The disadvantage of this method is that first, it is necessary to put the rescue boat into the water and then propel it. The propulsion speed on the water is slower than that of a drone, and it is not very applicable in case of bad sea conditions or long distances. The company has already submitted a patent regarding the "flying life-saving buoy" with patent number CN213921429U, which can well solve the above technical problems, provide a new approach for water rescue, and has great application potential. However, its structure is complex, which brings some inconvenience to production and use to a certain extent. The company further develops and designs during the production and development process and submits an electric flying life-saving buoy.

Summary of the Invention

[0003] The technical problem to be solved by the present invention is that the rescue efficiency and safety of current water disaster rescue equipment are not ideal, the structure is complex, and the reliability cannot meet the requirements of long-term use. The present invention provides the following technical solutions. An electric flight rescue float ring comprising a shell, a flight component, a flight control component and a power module, The shell is a rescue float ring having a gas storage cavity, and a plurality of flight supports are provided on the outer side of the shell. The flight component comprises a motor, a propeller and an electronic speed regulator. A plurality of sets of flight components are provided and are attached one-to-one to the flight supports. The electronic speed regulator, the flight control component and the power module are installed in the shell and are electrically connected to the flight component to control the operation of the flight component.

[0004] During operation, this electric flight rescue float ring combines the technologies of an airtight rescue float ring and a drone. During the water disaster rescue process, it can quickly fly close to the person who has fallen into the water, facilitating the emergency escape of the person who has fallen into the water, and greatly improving the rescue efficiency and safety. By combining the waterproof design of the rescue float ring itself with the gas storage cavity, the structure is simplified. While the shell fully meets the buoyancy requirements of the rescue float ring, it is easy to store the wiring, improves the electrical waterproof function, ensures the circuit safety of the drone, enables water takeoff and landing, and during flight rescue, it can take off again and land on the water as needed, and finally fly close to the person who has fallen into the water. Preferably, the flight control component comprises a digital image transmission module, a digital image transmission power module, a flight control unit, a GPS (global positioning system) integrated detection module, a barometer and a remote control. The electronic speed regulator of the flight component is an integrated electronic speed regulator. The integrated electronic speed regulator is installed inside the shell, and a cooling fan is installed inside the shell corresponding to the integrated electronic speed regulator. The digital image transmission module, digital image transmission power supply module, and flight control unit are mounted on a flight control bracket provided inside the shell. The GPS integrated detection module is provided inside the shell and its outside is wrapped with aluminum foil. The barometer is mounted outside the shell. The motor is connected to the flight control unit and the power supply module via the integrated electronic speed regulator. The flight control unit is connected to the power supply module via a PMU (power management unit) module. The PMU module is used for power supply and voltage detection of the flight control unit. The digital image transmission module is connected to the digital image transmission power supply module and the flight control unit and is connected to a remote control via a wireless network.

[0005] Preferably, the shell has an elliptical cross-section, and the upper shell and the lower shell are assembled or welded to form a life-saving float with a gas storage cavity. A plurality of flight supports are integrally formed on the outside of the upper shell and / or the lower shell. The integral molding is convenient for production and assembly, has strong integrity, and high reliability.

[0006] Preferably, fixed flanges are symmetrically provided on the outside of the shell, and a tether hole is provided in the middle of the fixed flange, which makes it easy to tie a rope and is convenient for the emergency rescue of people who have fallen into the water.

[0007] Preferably, protective nets are attached to both sides of the flight support to play a role in safety protection.

[0008] Preferably, the inside of the shell is filled with foam floats to provide buoyancy support as needed.

[0009] Preferably, an imaging component is attached to the outside of the shell. The imaging component includes an imaging tripod head, an imaging module, and a transparent protective cover. The transparent protective cover is attached to the outside of the shell, and the imaging tripod head and the imaging module are built into the transparent protective cover. The imaging tripod head is a single-axis, biaxial, or triaxial imaging tripod head. The imaging module is a visible light camera or a dual-light camera. The dual-light camera can perform visible light photography and infrared night vision photography.

[0010] Preferably, the power module includes a plurality of sets of battery components. The battery components are fixed to the mounting slots provided in the shell for mounting and fixing. Preferably, a charging port, a switch hole, and a ventilation hole are respectively provided at the top of the shell. A waterproof charging terminal, a plug-in switch, and a ventilation hole seat are respectively attached to the charging port, the switch hole, and the ventilation hole. The ventilation hole seat is screwed to a waterproof breathable cover. The waterproof breathable cover has a hollow top and a waterproof breathable film attached inside. The waterproof charging terminal is used for charging the power module. The plug-in switch is a flight control switch. The waterproof breathable cover can adjust the air pressure inside the shell, exert a waterproof effect, and can be removed during inspection and maintenance to drain water through the ventilation hole.

[0011] Preferably, the flight control bracket includes a shock-absorbing mother board and a shock-absorbing support plate. The flight control unit and the visual recognition processing unit in the imaging module are attached to the shock-absorbing support plate. The shock-absorbing support plate is fixed to the shock-absorbing mother board by studs and rubber shock-absorbing balls. The digital image transmission module and the digital image transmission power module are fixed to the shock-absorbing mother board. The shock-absorbing design of the flight control bracket is beneficial to the operating stability of the flight control unit and the visual recognition processing unit in the imaging module at high-frequency vibration.

[0012] Preferably, a sealant is applied to the outer assembly seam of the upper shell and the lower shell to form an outer seal rubber ring. On the outer edge of the lower shell, buckle slots are provided over the entire length, and on the upper shell edge, buckle ribs are provided over the entire length. The buckle ribs are engaged in the buckle slots, and the upper shell and the lower shell are snap - in connected. A sealant is press - fitted into the buckle slots over the entire length to form an inner seal rubber ring, forming double waterproofing and enhancing the waterproof effect of the shell.

[0013] Preferably, a plurality of arc grooves are symmetrically provided on the outer sides of the upper shell and the lower shell. On the outer side of the upper shell, a plurality of three - prong ring frames are integrally formed corresponding to the arc grooves. The three - prong ring frame includes one motor chamber, three width - groove rods, and one fixed - plate ring. The motor chamber is a cylindrical trough shell. The motor chamber connects the upper shell and the fixed - plate ring by three width - groove rods. Two width - groove rods are connected to both ends of the arc groove of the upper shell. A wiring hole is opened in the upper shell corresponding to one width - groove rod. In the flight component, the motor is a waterproof brushless motor. The waterproof brushless motor is mounted at the center of the three - prong ring frame, and the propeller is mounted on the power output shaft of the waterproof brushless motor. On the outer side of the lower shell, a connection ring plate is attached or integrally formed corresponding to the arc groove. The connection ring plate and the three - prong ring frame together constitute a flight support.

[0014] Preferably, a navigation rescue light is provided on the shell, and the navigation rescue light is attached to the width - groove rod.

[0015] Preferably, a sealing screw kit is attached to the wiring hole. The sealing screw kit includes a jacket through seat and an inner ferrule. The jacket through seat has a plurality of cable holes. The jacket through seat is fitted outside the wiring hole and extends into the shell. The inner ferrule is fitted and attached to the jacket through seat inside the shell. The inner and outer sides of the wiring hole are sealed by a sealant, improving the waterproof performance.

[0016] Preferably, 4 or 6 sets of the flight components are provided and are attached one-to-one to the corresponding flight supports, forming a four-rotor or six-rotor flight rescue float. Currently, the flight control technology of mature four-rotor or six-rotor unmanned aerial vehicles is mature and can be applied to the rescue float structure.

[0017] Preferably, the power module is detachably attached inside the shell. An access cover corresponding to the power module is provided at the top of the shell, facilitating the immediate removal and replacement of the battery. Preferably, the shell is equipped with a voice communication device, detection (such as life-saving detection), and inspection devices (such as water quality and air quality inspections), and rescue tools (such as rescue ropes), to perform auxiliary rescue, detection, and inspection. Note that all the electronic components and flight control technologies mentioned in the present invention are all currently mature existing components and existing mature technical means. In the present invention, they are not specifically described here and are not limited at the same time. Those skilled in the art can select the corresponding existing components by referring to the content and purpose of the present invention and realize the technical solution of the present invention by the corresponding conventional technical means.

[0018] Compared with the prior art, the present invention has the following beneficial effects. 1. The present invention provides an electric flying life-saving buoy, which has a clever structure and a reasonable layout. In the present invention, the technologies of an airtight life-saving buoy and a drone are combined. During the water rescue process, it can quickly fly close to the person who has fallen into the water, facilitating the emergency escape of the person who has fallen into the water, greatly improving the rescue efficiency and safety. The integrated gas storage structure design simplifies the structure. While its shell fully meets the buoyancy requirements of the life-saving buoy, it facilitates the storage of wiring, improves the electric waterproof function, ensures the circuit safety of the drone, and enables takeoff and landing on water. During flight rescue, if necessary, it can take off again and land on the water surface, and finally fly close to the person who has fallen into the water.

[0019] 2. In the present invention, the shell structure with an air storage life-saving buoy is cleverly designed, adopting an assembled structure of an upper shell and a lower shell, with seals press-fitted inside and outside to form an inner and outer double sealing ring, thus realizing a double waterproof design for the overall structure, greatly improving the waterproof property, realizing a clever combination of the life-saving buoy and the drone, and having an amphibious function. 3. In the present invention, the number of assembled parts is simplified, with high integrity, improving the assembly efficiency while ensuring the quality rate and stability of the structure. In particular, in the present invention, the structure of integrally forming a three-pronged ring frame is used for the assembly of flight components, simplifying the structure assembly procedure. Also, in the present invention, a sealing screw kit is specially designed, and the durability is further enhanced by detailed strengthening design to ensure the safety of rescue. 4. In the present invention, furthermore, flight control components are specifically designed, adopting a mature four-rotor or six-rotor drone structure, performing modular assembly, and assembling an imaging tripod head and a dual optical imaging component corresponding to the waterproof property, thus effectively coping with the takeoff and landing flight situation on water and easily implementing accurate and rapid water emergency rescue.

Brief Description of the Drawings

[0020]

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Modes for Carrying Out the Invention

[0021] Hereinafter, with reference to specific embodiments, the technical solution of the present invention will be described in more detail.

[0022] In order to clarify the object, technical solution and advantages of the present invention, the present invention will be described in more detail below with reference to the accompanying drawings and embodiments. As can be understood, the specific embodiments described herein are used to explain the present invention and do not limit the present invention.

[0023] In the description of the present invention, it should be noted that the directions or positional relationships indicated by "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are the directions or positional relationships based on those shown in the accompanying drawings, and are only for facilitating and simplifying the description of the present invention, and do not indicate or imply that the indicated device or element must have a specific direction and be constructed and operated in a specific direction. Therefore, it cannot be understood that the present invention is limited. When the terms "first", "second", "third" are used, they are only for the purpose of description and cannot be understood as indicating or implying relative importance. Also, unless there are clear regulations and limitations, terms such as "attachment", "connection", "connection" should be understood broadly. For example, it may be a fixed connection, a detachable connection, or an integral one, a mechanical connection, an electrical connection, a direct connection, an indirect connection through an intermediate medium, or a communication inside two elements. Those skilled in the art may understand the specific meaning of the above terms in the present invention according to specific situations.

[0024] Referring to FIGS. 1 to 19, an electric flight rescue float, comprising a shell 1, a flight component 2, a flight control component 3 and a power module 4. As shown in Fig. 1, this embodiment is a four-rotor flight rescue float. Four sets of flight components 2 are provided and symmetrically arranged around the shell 1. In some embodiments, six sets of flight components 2 are provided and symmetrically arranged around the shell 1, forming a six-rotor flight rescue float.

[0025] As shown in Figs. 2 to 5, the shell 1 has an elliptical cross-section and is composed of an upper shell 11 and a lower shell 12. In this embodiment, the shell 1 is made of PP (polypropylene) plastic. In some embodiments, the shell 1 is made of PA (polyamide) or PE (Polyethylene) plastic. Four arc grooves 14 are symmetrically provided on the outer sides of the upper shell 11 and the lower shell 12. The upper shell 11 and the lower shell 12 are assembled and connected to form a rescue float with a gas storage cavity. In some embodiments, the upper shell 11 and the lower shell 12 are welded and connected. In some embodiments, the shell is filled with foam floats as needed to provide buoyancy support.

[0026] In this embodiment, referring to Fig. 4, a buckle rib 111 is provided along the entire length at the edge of the upper shell 11, and a buckle slot 121 is provided along the entire length at the outer edge of the lower shell 12. The buckle rib 111 is engaged in the buckle slot 121, and the upper shell 11 and the lower shell 12 are snap-connected. Here, a sealant is press-fitted along the entire length into the buckle slot 121 to form an inner seal rubber ring, which seals the inside to enhance waterproofness and contributes to the waterproof stability of the rescue float. In this embodiment, a sealant is applied to the outer seam of the upper shell 11 and the lower shell 12 to form an outer seal rubber ring, which seals and fixes the outside to achieve a double waterproof design.

[0027] In this embodiment, referring to FIG. 5, outside the upper shell 11, four three - prong ring frames 112 are integrally formed corresponding to the arc grooves 14. The three - prong ring frame 112 includes a motor chamber 1121, three wide - groove rods 1122, and a fixing plate ring 1123. The motor chamber 1121 is a cylindrical trough shell. The motor chamber 1121 connects the upper shell 11 and the fixing plate ring 1123 by three wide - groove rods 1122. Two wide - groove rods 1122 are connected to both ends of the arc groove 14 of the upper shell 11. The upper shell 11 is provided with a wiring hole 15 corresponding to one wide - groove rod 1122. Below the three - prong ring frame 112, a connection ring plate 13 is fitted and attached, and both ends are respectively connected to both ends of the arc groove 14 of the lower shell 12. In some embodiments, the connection ring plate 13 is integrally formed with the lower shell 12 and assembled with the three - prong ring frame 112. Four sets of flight components 2 are provided. The flight component 2 includes a waterproof brushless motor 21, a propeller 22, and an electronic speed regulator. As shown in FIG. 8, the waterproof brushless motor 21 is attached corresponding to the motor chamber 1121 at the central position of the three - prong ring frame 112. The propeller 22 is attached to the power output shaft of the waterproof brushless motor 21. In some embodiments, as the waterproof brushless motor 21, a Hurricane 4114 waterproof motor is used. Referring to FIG. 11, in this embodiment, among the four sets of flight components 2, the electronic speed regulators are all integrated together to form an integrated electronic speed regulator 23. The integrated electronic speed regulator 23 is attached to four assembly posts 231 provided in the shell by screws. The four assembly posts 231 are integrally formed with the shell 1 to facilitate assembly. Two cooling fans 232 are provided and respectively attached to the upper and lower sides of the integrated electronic speed regulator 23 to effectively dissipate heat. In some embodiments, as the integrated electronic speed regulator 23, a Hobbywing Xroror micro 60a 4in1 type electronic speed regulator is used. In some embodiments, as the propeller 22, an APC1245 type propeller 22 is used. In this embodiment, as shown in FIG. 9, on both sides of the trident ring frame 112, a protection net 113 is provided to protect the propeller 22 and avoid accidental injury to the rescue target, thereby improving safety. In this embodiment, as shown in FIGS. 8 and 9, at the arc groove positions of the fixed plate ring 1123, the connection ring plate 13, and the lower shell 12, flange strips 110 are provided. Fixing holes 1101 are provided on all the flange strips 110. The protection nets 113 on both sides are fixedly connected to the corresponding flange strips 110 respectively. In this embodiment, referring to FIG. 6, the conducting wire of the waterproof brushless motor 21 enters the inner cavity of the shell 1 through the wiring hole 15. In this embodiment, a sealing screw kit 16 is installed in the wiring hole 15. The sealing screw kit 16 includes a jacket through seat 161 and an inner ferrule 162. The jacket through seat 161 has three cable holes 1610. The jacket through seat 161 is fitted outside the wiring hole 15 and extends into the shell 1. The inner ferrule 162 is fitted and attached to the jacket through seat 161 inside the shell 1. After the wiring is completed, the wiring hole 15 is sealed with a sealant to effectively prevent water ingress and ensure the safety and durability of the life-saving float ring. On the outer sides of the upper shell 11 and the lower shell 12, fixing flanges 17 are symmetrically provided. In the middle of the fixing flanges 17, a tether hole 18 is provided.

[0028] The flight control component 3 includes a digital image transmission module 31, a digital image transmission power module 32, a flight control unit 33, a GPS integrated detection module 34, a barometer 35, and a remote control 36. Referring to FIG. 12, the barometer 35 is mounted on a mounting post (not shown) within a waterproof housing 351 provided at a corresponding position of the upper shell 11, electrically connected to the flight control unit 33, and a sealing cover 352 is connected to the bottom of the waterproof housing 351 and sealed by a sealant. A ventilation port 3511 is provided at the top of the waterproof housing 351, and the ventilation port 3511 is sealed by a waterproof breathable film 353. In some embodiments, an IBINET type waterproof breathable film is used as the waterproof breathable film 353. The GPS integrated detection module 34 is mounted within the shell 1 and electrically connected to the flight control unit. In some embodiments, the outside of the GPS integrated detection module 34 is wrapped with aluminum foil to prevent interference. The digital image transmission module 31, the digital image transmission power module 32, and the flight control unit 33 are mounted on a flight control bracket 30 provided within the shell 1. In some embodiments, an ACFLY A9 type flight controller is used as the flight control unit. In some embodiments, a GY-SPL06-3.3 type barometer is used as the barometer. In some embodiments, a cloud table h12 type digital image transmission module is used as the digital image transmission module 31. In some embodiments, an M8N type GPS integrated detection module is used as the GPS integrated detection module 34. The waterproof brushless motor 21 is connected to the flight control unit 33 and the power module 4 via an integrated electronic speed regulator 23. The flight control unit 33 is connected to the power module 4 via a PMU module 37. The PMU module 37 is used for power supply and voltage detection of the flight control unit. The digital image transmission module 31 is connected to the digital image transmission power module 32 and the flight control unit 33 and connected to the remote control 36 via a wireless network. In some embodiments, the shell 1 needs to be equipped with related rescue tools. The related rescue tools include an imaging component 8. On the side of the shell 1, a fixed port 101 is provided corresponding to the flight control bracket 30. The imaging component 8 is attached to the fixed port 101. The imaging component includes an imaging tripod head, an imaging module, and a transparent protection cover. The transparent protection cover is attached to the outside of the shell. The imaging tripod head and the imaging module are built into the transparent protection cover. The transparent protection cover plays a role in protection and waterproofing. In some embodiments, the imaging tripod head is a single-axis imaging tripod head, for example, a waterproof tripod head of the single-axis type for a cloudy table. In some embodiments, the imaging tripod head is a two-axis imaging tripod head. In some embodiments, the imaging tripod head is a three-axis imaging tripod head. In some embodiments, the imaging module is a visible light camera. In some embodiments, the imaging module is a dual-light camera. The dual-light camera can perform visible light photography and infrared night vision photography. As shown in FIGS. 13 to 14, in an embodiment using a general imaging component, the flight control bracket 30 includes a shock absorption mother board 301, a fixed support 302, and a shock absorption support plate 303. Four fixed supports 302 are provided and integrally formed with the shell 1. The shock absorption mother board 301 is attached to the fixed support 302 by screws. The flight control units 33 are respectively fixed to the shock absorption support plate 303 by bolts. The shock absorption support plate 303 is fixed to the shock absorption mother board 301 by studs 304 and rubber shock absorption balls 305, effectively preventing the influence of high-frequency vibration on the flight control units. Referring to FIGS. 15 to 19, in an embodiment using the dual-light imaging component 84 and the single-axis imaging tripod head, the imaging component 8 includes a transparent protective cover 80, a fixed sheet 81, a fixed arm 82, a tripod head motor 83, a dual-light imaging component 84, a vision sensing module 85, a dual-light camera vision recognition processing module 86, and a tripod head controller module 87. The fixed sheet 81 is attached to the fixed port 101 and sealed by a sealant to close the fixed port 101, maintaining the airtightness and waterproofness of the shell 1. A transparent protective cover 80 is attached to the outside of the fixed sheet 81 to protect the imaging component 8. The fixed arm 82 is attached to the fixed sheet 81. The dual-light imaging component 84 is attached to the fixed arm 82 by the tripod head motor 83 and connected to the flight control unit 33. The tripod head controller module 87, the vision sensing module 85, and the dual-light camera vision recognition processing module 86 are attached to the flight control bracket 30 and connected to the flight control unit 33. The dual-light camera vision recognition processing module 86 and the flight control unit 33 are respectively fixed to both sides of the shock absorption support plate 303 by studs. Further, the shock absorption support plate 303 is attached to the shock absorption mother board 301 by a rubber shock absorption ball 305. The digital image transmission module 31, the digital image transmission power module 32, the vision sensing module 85, and the tripod head controller module 87 are respectively fixed to the shock absorption mother board 301 by bolts, nuts, studs, binding ropes, or pastes. Finally, the shock absorption mother board 301 is fixed to the fixed support 302 by self-tapping screws. The rubber shock absorption ball has an elastic effect, reducing the influence of vibrations during drone flight and ensuring the normal and stable operation of the dual-light camera vision recognition processing module 86 and the flight control unit 33.

[0029] In this embodiment, referring to FIG. 10, the power supply module 4 includes two sets of battery components 41. On the upper shell 11, mounting slots 100 are provided corresponding to the battery components 41. The battery components 41 are mounted in the mounting slots 100. In some embodiments, the power supply module 4 is detachably mounted on the shell 1. At the top of the shell 1, an access cover (not shown) is provided corresponding to the power supply module 4, which facilitates quickly removing and replacing the battery. In this embodiment, referring to FIGS. 2 and 5, at the top of the shell 1, a charging port 114, a switch hole 115, and a vent hole 116 are respectively provided. On the charging port 114, the switch hole 115, and the vent hole 116, a waterproof charging terminal 5, a plug-in switch 6, and a vent hole seat 7 are respectively provided. In some embodiments, as the waterproof charging terminal 5, a 7-pin aviation plug sp13 is used. In some embodiments, a power supply wire is connected to the waterproof charging terminal 5 of the shell 1, and power is supplied in real time through the power supply wire, which is applicable to short-distance, high-speed, and high-frequency rescue. In some embodiments, as the plug-in switch 6, an Amass XT60W is used. The plug-in switch 6 and the vent hole seat 7 are mounted. The vent hole seat 7 is screwed to a waterproof breathable cover 71. The waterproof breathable cover 71 has a hollow top and a waterproof breathable membrane (not shown) is mounted inside. In some embodiments, as the waterproof breathable membrane, an IBINET type waterproof breathable membrane is used. The waterproof charging terminal 5 is used for charging the power supply module. The plug-in switch 6 is a flight control switch. During the working process, the internal components generate heat, and the pressure is released through the waterproof breathable cover 71 to adjust the air pressure inside the shell 1, avoiding excessive internal pressure during long-term work and being able to exert a waterproof effect. During inspection and maintenance, the waterproof breathable cover 71 can be removed, and drainage can be performed through the vent hole 116. In some embodiments, a navigation rescue light (not shown) is provided on the shell 1, and the navigation rescue light is attached to the width groove rod for navigation indication and rescue hints. In some embodiments, the shell 1 is equipped with a voice communication device, a detection and inspection device, and rescue tools (such as ropes and medicines) (not shown), and performs auxiliary rescue, detection, and inspection. The working principle of the present invention: In the present invention, an electric flight rescue float is provided, which has a clever structure and a reasonable layout. In the present invention, the technologies of an airtight rescue float and a drone are combined. During the water rescue process, it can quickly fly close to the person who has fallen into the water, which is convenient for the person who has fallen into the water to make an emergency escape, greatly improving the rescue efficiency and safety. The integrated gas storage structure design simplifies the structure. While its shell fully meets the buoyancy requirements of the rescue float, it is easy to store the wiring, improves the electric waterproof function, ensures the circuit safety of the drone, and enables takeoff and landing on water. During flight rescue, if necessary, it can take off again and land on the water surface, and finally fly close to the person who has fallen into the water. In the present invention, the airtight shell structure is specifically and cleverly designed, adopting a structure in which the upper shell and the lower shell are fitted, and seals are press-fitted inside and outside to form an inner and outer double sealing ring, thus realizing a double waterproof design for the overall structure and greatly improving the airtightness and waterproofness. In the present invention, the number of assembled parts is simplified, the integrity is high, while improving the assembly efficiency, the quality rate and stability of the structure are ensured. In particular, in the present invention, the structure in which the trident ring frame is integrally formed is used for the assembly of flight components, simplifying the structure assembly procedure. Also, in the present invention, a sealing screw kit is specially designed, and the durability is further enhanced by detailed strengthening design to ensure the safety of rescue. In the present invention, furthermore, the flight control components are specifically designed, adopting a mature four-rotor or six-rotor drone structure, performing modular assembly, and correspondingly designing a waterproof tripod head and a double optical imaging component, effectively coping with the water takeoff and landing flight situation and easily performing accurate and rapid water emergency rescue. Although the preferred embodiments of the present invention have been described in detail above, the present invention is not limited thereto, and various modifications can be made within the scope of knowledge of those skilled in the art without departing from the gist of the present invention.

Explanation of Signs

[0030] 1 Shell 11 Upper Shell 100 Mounting Slot 101 Fixed Port 111 Buckle Rib 112 Trifurcated Ring Frame 113 Protection Net 114 Charging Port 115 Switch Hole 116 Vent Hole 1121 Motor Chamber 1122 Width Groove Rod 1123 Fixed Plate Ring 12 Lower Shell 121 Buckle Slot 13 Connection Ring Plate 14 Arc Groove 15 Wiring Hole 16 Sealing Screw Kit 161 Jacket Through Seat 162 Inner Ferrule 17 Fixed Flange 18 Tether Hole 110 Flange Strip 1101 Fixed Hole 2 Flight Component 21 Waterproof Brushless Motor 22 Propeller 23 Integrated Electronic Speed Regulator 231 Assembly Column 232 Cooling Fan 3 Flight Control Component 30 Flight Control Bracket 301 Shock Absorbing Mother Board 302 Fixed Support 303 Shock Absorbing Support Plate 31 Digital Image Transmission Module 32 Digital Image Transmission Power Module 33 Flight Control Unit 34 GPS Integration Detection Module 35 Barometer 36 Remote Control 37 PMU Module 4 Power Module 41 Battery Component 5 Waterproof Charging Terminal 6 Plug-in Switch 7 Vent Hole Seat 71 Waterproof Vent Cover 8 Imaging Component 80 Transparent Protection Cover 81 Fixed Sheet 82 Fixed Arm 83 Tripod Head Motor 84 Dual Light Imaging Component 85 Visual Sensing Module 86 Dual Light Camera Visual Recognition Processing Module 87 Tripod Head Controller Module

Claims

1. An electric flight rescue float, comprising: a shell, a flight component, a flight control component, and a power module, wherein the shell is a rescue float having a gas storage cavity, and a plurality of flight supports are provided on the outer side of the shell; the flight component includes a motor, a propeller, and an electronic speed regulator, and a plurality of sets of flight components are provided and are attached to the flight supports one-to-one; the flight control component and the power module are mounted inside the shell and are electrically connected to the flight component to control the operation of the flight component. An electric flight rescue float, characterized in that.

2. The flight control component includes a digital image transmission module, a digital image transmission power module, a flight control unit, a GPS integrated detection module, a barometer, and a remote control; the electronic speed regulator is an integrated electronic speed regulator, the integrated electronic speed regulator is mounted inside the shell, and a cooling fan is mounted inside the shell corresponding to the integrated electronic speed regulator; the digital image transmission module, the digital image transmission power module, and the flight control unit are mounted on a flight control bracket provided inside the shell; the GPS integrated detection module is mounted inside the shell, and the barometer is mounted outside the shell; the motor is connected to the flight control unit and the power module via the integrated electronic speed regulator, and the flight control unit is connected to the power module via the PMU module; the digital image transmission module is connected to the digital image transmission power module and the flight control unit and is connected to the remote control via a wireless network. The electric flight rescue float according to claim 1, characterized in that.

3. The shell has an elliptical cross-section and is formed by assembling or welding an upper shell and a lower shell, and is a rescue float having a gas storage cavity, and a plurality of flight supports are integrally formed on the outer side of the upper shell and / or the lower shell. The electric flight rescue float according to claim 1, characterized in that.

4. A fixed flange is symmetrically provided on the outer side of the shell, and a tether hole is provided in the middle of the fixed flange. The electric flight rescue float according to claim 1, characterized in that.

5. Protective nets are attached to both sides of the flight support. The electric flight rescue float according to claim 1, characterized in that.

6. The shell is filled with a foam float. The electric flight rescue float according to claim 1, characterized in that.

7. An imaging component is attached to the outside of the shell, The imaging component includes an imaging tripod head, an imaging module, and a transparent protective cover. The transparent protective cover is attached to the outside of the shell, and the imaging tripod head and the imaging module are built into the transparent protective cover. The imaging tripod head is a single-axis, biaxial, or triaxial imaging tripod head. The imaging module is a visible light camera or a dual light camera. The power supply module includes a plurality of sets of battery components, and the battery components are fixed to mounting slots provided in the shell. At the top of the shell, a charging port, a switch hole, and a ventilation hole are respectively provided. A waterproof charging terminal, a plug-in switch, and a ventilation hole seat are respectively attached to the charging port, the switch hole, and the ventilation hole. The ventilation hole seat is screwed to a waterproof breathable cover, and the waterproof breathable cover has a hole cut out at the top and a waterproof breathable membrane attached inside. The flight control bracket includes a shock absorption mother board and a shock absorption support plate. The flight control unit and the visual recognition processing unit in the imaging module are attached to the shock absorption support plate. The shock absorption support plate is fixed to the shock absorption mother board by studs and rubber shock absorption balls. The digital image transmission module and the digital image transmission power supply module are fixed to the shock absorption mother board, and the shock absorption mother board is attached to the inner wall of the shell. The electric flight rescue float according to claim 2, characterized in that.

8. Apply a sealant to the outer seam of the assembly of the upper shell and the lower shell to form an outer seal rubber ring. A buckle slot is provided along the entire length on the outer edge of the lower shell, and a buckle rib is provided along the entire length on the upper shell edge. The buckle rib is engaged in the buckle slot, and the upper shell and the lower shell are snap-connected. A sealant is press-fitted into the buckle slot along the entire length to form an inner seal rubber ring. The electric flight rescue float according to claim 3, characterized in that...

9. A plurality of arc grooves are symmetrically provided on the outer sides of the upper shell and the lower shell. On the outer side of the upper shell, a plurality of three-pronged ring frames are integrally formed corresponding to the arc grooves. The three-pronged ring frame includes one motor chamber, three width groove rods, and one fixed plate ring. The motor chamber is a cylindrical trough shell. The motor chamber connects the upper shell and the fixed plate ring by three width groove rods. Two width groove rods are connected to both ends of the arc groove of the upper shell. A wiring hole is opened in the upper shell corresponding to one width groove rod. In the flight component, the motor is a waterproof brushless motor. The waterproof brushless motor is attached to the center of the three-pronged ring frame, and the propeller is attached to the power output shaft of the waterproof brushless motor. On the outer side of the lower shell, a connection ring plate is attached or integrally formed corresponding to the arc groove. The connection ring plate and the three-pronged ring frame together constitute a flight support. The electric flight rescue float according to claim 3, characterized in that...

10. A navigation rescue light is provided on the shell, and the navigation rescue light is attached to the width groove rod. The electric flight rescue float according to claim 9, characterized in that...

11. A sealing screw kit is attached to the wiring hole. The sealing screw kit includes a jacket through seat and an inner ferrule. The jacket through seat has a plurality of cable holes. The jacket through seat is fitted outside the wiring hole and extends into the shell. The inner ferrule is fitted and attached to the jacket through seat in the shell. The inside and outside of the wiring hole are sealed by a sealant. The electric flight rescue float according to claim 9, characterized in that...

12. Four or six sets of the flight components are provided to form a four-rotor or six-rotor flight rescue float. The electric flight rescue float according to any one of claims 1 to 11, characterized in that...

13. The power supply module is detachably attached in the shell, and an access cover is provided on the top of the shell corresponding to the power supply module. The electric flight rescue float according to claim 12, characterized in that...

14. A voice communication device, a detection and inspection device, and rescue tools are mounted on the shell. The electric flight rescue float according to claim 12, characterized by the above.

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