Flight device with flame generator

Abstract

The utility model discloses a flight device carrying a flame generator, which comprises an aircraft, two hitching arms, a storage battery, a flame generator and a driving component, the bottom end of the aircraft is provided with two connecting frames, and the two connecting frames are oppositely arranged and extend towards the lower part of the aircraft; the two hanging arms are connected to the lower ends of the two connecting frames in a one-to-one opposite mode, first fixing plates are arranged at the lower ends of the two hanging arms so that an installation gap can be defined between the two first fixing plates, the storage battery is arranged in the installation gap, and the two sides of the storage battery are connected with the two first fixing plates correspondingly. The lower ends of the two first fixing plates are both connected with second fixing plates, a rotating shaft is arranged between the two second fixing plates in a penetrating mode, the flame generator is arranged on the rotating shaft, and the driving assembly is arranged between the two second fixing plates and used for driving the rotating shaft to rotate so as to adjust the flame direction of the flame generator. According to the deicing device, deicing operation can be carried out by carrying the flame generator, the operation efficiency is improved, and the use cost is reduced.

Description

Technical Field

[0001] This utility model relates to the field of flight devices, specifically to a flight device carrying a flame generator. Background Technology

[0002] In power transmission systems, high-voltage cables serve as crucial carriers for power transmission, and their safe and stable operation is paramount. However, in cold climates, high-voltage cables are highly susceptible to icing. Icing not only increases cable weight, causing sagging or even breakage, but can also trigger electrical faults such as flashovers and short circuits, seriously threatening the safe and stable operation of the power system. Therefore, timely and effective removal of icing from high-voltage cables is a vital task for ensuring the reliable operation of the power system.

[0003] Currently, a common method in existing high-voltage cable de-icing technologies is to use an aircraft carrying an iron rod for de-icing operations. Specifically, an aircraft (such as a drone) carries an iron rod, which is then swung by a specific mechanical device during flight. The impact force of the swinging iron rod against the surface of the high-voltage cable breaks the ice layer on the cable surface, thereby achieving the purpose of de-icing.

[0004] However, although the de-icing method of using an aircraft to swing and strike an iron bar can break the ice layer on the surface of high-voltage cables to some extent, its de-icing effect is not ideal due to limitations in the striking force generated by the swinging iron bar. From the perspective of the aircraft, its load-bearing capacity is limited, and the weight and size of the iron bar carried are usually strictly limited to ensure flight safety and stability. This results in relatively low kinetic energy that the iron bar can gain during swinging, thus limiting the striking force. At the same time, the flight attitude and stability of the aircraft also affect the swing amplitude and frequency of the iron bar, further weakening the striking force. Therefore, it can only remove the outer layer of ice during striking, and is difficult to effectively treat the ice layer attached to the cable surface.

[0005] Therefore, it is necessary to make further improvements to the existing technology. Utility Model Content

[0006] This invention aims to at least partially solve one of the technical problems in related technologies. Therefore, the purpose of this invention is to provide a flying device carrying a flame generator.

[0007] To achieve the above objectives, an embodiment of the present invention provides a flight device carrying a flame generator, comprising a flight vehicle, two mounting arms, a battery, a flame generator, and a drive assembly.

[0008] The aircraft has two connecting frames at its bottom, which are arranged opposite each other and extend downwards from the aircraft.

[0009] The two hook arms are connected one to one to the lower end of the two connecting frames. The lower end of each hook arm is provided with a first fixing plate to define an installation gap between the two first fixing plates.

[0010] The battery is located within the installation gap, and its two sides are respectively connected to the two first fixing plates.

[0011] A second fixing plate is connected to the lower end of each of the two first fixing plates, and a rotating shaft passes through the two second fixing plates. The flame generator is mounted on the rotating shaft.

[0012] The drive assembly is located between the two second fixed plates and is used to drive the rotating shaft to rotate in order to adjust the flame direction of the flame generator.

[0013] In addition, the flight device carrying a flame generator according to the above embodiments of the present invention may also have the following additional technical features:

[0014] According to one embodiment of the present invention, the flame generator includes a sleeve and a flame generator body.

[0015] The sleeve is fixedly fitted onto the rotating shaft.

[0016] The flame generator body is connected to the sleeve and is electrically connected to the battery.

[0017] According to one embodiment of the present invention, the drive assembly includes a mounting plate, a motor, and a transmission belt.

[0018] The mounting plate is connected between the two second fixing plates.

[0019] The motor is mounted on the mounting plate.

[0020] One end of the transmission belt is fitted onto the output shaft of the motor, and the other end is fitted onto the rotating shaft to transmit the power of the motor to the rotating shaft.

[0021] According to one embodiment of the present invention, both connecting frames are U-shaped, and the ends of both connecting frames are connected to the bottom surface of the aircraft.

[0022] According to one embodiment of the present invention, both of the upper ends of the hook arms are provided with downwardly bent portions to form a hooking gap between the bent portions and the hook arms, and the upper ends of the hook arms are hooked to the lower end of the connecting frame through the hooking gap.

[0023] According to one embodiment of the present invention, the upper end of the hook arm is further provided with a closure member. The closure member is L-shaped, with one end pivotally connected to the upper end face of the hook arm and the other end detachably connected to the side of the hook arm, so as to seal the lower opening of the hook gap.

[0024] According to one embodiment of the present invention, an adjustable screw is vertically inserted through the closure member, the upper end of the adjusting screw extends into the hook gap, and a pressure plate is connected to the upper end of the adjusting screw. The pressure plate and the end of the adjusting screw are movably connected so that the pressure plate can be adjusted to rise or fall by the adjusting screw to press against the surface of the connecting frame.

[0025] According to one embodiment of the present invention, a fixing screw is provided on the outer surface of the other end of the closure member, and a threaded hole corresponding to the fixing screw is provided on the hook arm, and the end of the fixing screw is connected to the threaded hole.

[0026] According to one embodiment of the present invention, a rubber gasket is provided on the bottom surface of the tablet.

[0027] According to one embodiment of the present invention, a camera assembly is provided in the middle of the bottom surface of the aircraft for capturing images of the surrounding environment.

[0028] According to the embodiments of this utility model, the flying device carrying a flame generator integrates the aircraft, mounting arm, battery, flame generator, and drive assembly into one unit to form a fully functional flying de-icing device. It can carry a flame generator for de-icing operations without the need for additional complex auxiliary equipment, thereby improving work efficiency and reducing operating costs. The drive assembly is set between the second fixed plates to drive the rotating shaft to rotate. The flame generator is installed on the rotating shaft. The flame direction of the flame generator can be easily adjusted through the drive assembly. The flame jet direction can be flexibly adjusted according to different de-icing needs or cable routing, thereby improving the targeting and effectiveness of de-icing operations.

[0029] Additional aspects and advantages of this invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0030] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0031] Figure 1 This is a schematic diagram of the overall structure in an embodiment of this utility model;

[0032] Figure 2 This is another schematic diagram of the overall structure in an embodiment of this utility model;

[0033] Figure 3 This is a schematic plan view of the overall structure in an embodiment of this utility model;

[0034] Figure 4 This is a schematic diagram of the connection between the mounting arm and the flame generator in an embodiment of this utility model;

[0035] Figure 5 This is a partial enlarged view of the mounting arm in an embodiment of this utility model.

[0036] Icon labels:

[0037] Aircraft 10;

[0038] Connector 11;

[0039] 20mm hook arm;

[0040] First fixing plate 21;

[0041] Second fixing plate 22;

[0042] Shaft 23;

[0043] Bending section 24;

[0044] Enclosure 25;

[0045] Fixing screw 251;

[0046] Adjusting screw 26;

[0047] Tablet compression 27;

[0048] Rubber gasket 271;

[0049] 30 batteries;

[0050] Flame generator 40;

[0051] Sleeve 41;

[0052] Flame generator body 42;

[0053] Driver component 50;

[0054] Mounting plate 51;

[0055] Motor 52;

[0056] 53 transmission belts;

[0057] Camera component 60.

[0058] The realization of the purpose, functional features and advantages of this utility model will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0059] The embodiments of this utility model are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this utility model, and should not be construed as limiting this utility model. All other embodiments obtained by those skilled in the art based on the embodiments of this utility model without inventive effort are within the scope of protection of this utility model.

[0060] In the description of this utility model, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "circumferential", "radial", etc., indicating the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model.

[0061] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this utility model, "a plurality of" means two or more, unless otherwise explicitly specified.

[0062] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0063] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0064] The following describes in detail, with reference to the accompanying drawings, a flight device carrying a flame generator 40 according to an embodiment of the present invention.

[0065] Reference Figures 1 to 5 As shown, a flight device carrying a flame generator 40 according to an embodiment of the present invention includes a flight vehicle 10, two mounting arms 20, a battery 30, a flame generator 40, and a drive assembly 50.

[0066] The aircraft 10 has two connecting frames 11 at its bottom end, which are arranged opposite to each other and extend downwards from the aircraft 10.

[0067] The two hanging arms 20 are connected one to one to the lower ends of the two connecting frames 11. The lower ends of the two hanging arms 20 are provided with first fixing plates 21 to define the installation gap between the two first fixing plates 21.

[0068] The battery 30 is disposed within the installation gap and connected to the two first fixing plates 21 on both sides. Advantageously, a connecting frame 11 is provided at the bottom of the aircraft 10, and a mounting arm 20 is connected to the lower end of the connecting frame 11. The battery 30 is housed by defining the installation gap through the first fixing plates 21, making full use of the space under the aircraft device. This results in a compact and rationally laid-out structure, helping to reduce the size and weight of the device and improve flight flexibility and stability. Furthermore, the connection of the battery 30 to the two first fixing plates 21 on both sides ensures the battery 30 remains stable during flight, reducing the risk of loosening or damage due to vibration and other factors, thus improving the safety and reliability of the device.

[0069] The lower ends of the two first fixing plates 21 are each connected to a second fixing plate 22, and a rotating shaft 23 passes through the two second fixing plates 22. The flame generator 40 is mounted on the rotating shaft 23.

[0070] The drive assembly 50 is disposed between the two second fixed plates 22 and is used to drive the rotating shaft to rotate in order to adjust the flame direction of the flame generator 40.

[0071] Based on the above, by integrating the aircraft 10, the mounting arm 20, the battery 30, the flame generator 40, and the drive assembly 50 into one unit, a fully functional in-flight de-icing device is formed. It can carry the flame generator 40 for de-icing operations without the need for additional complex auxiliary equipment, thereby improving operational efficiency and reducing operating costs. The drive assembly 50 is set between the second fixed plates 22 to drive the rotating shaft to rotate. The flame generator 40 is installed on the rotating shaft 23. The flame direction of the flame generator 40 can be easily adjusted through the drive assembly 50. The flame jet direction can be flexibly adjusted according to different de-icing needs or cable routing, thereby improving the targeting and effectiveness of de-icing operations.

[0072] Preferably, in one embodiment of the present invention, the flame generator 40 includes a sleeve 41 and a flame generator body 42.

[0073] The sleeve 41 is fixedly sleeved on the rotating shaft 23.

[0074] The flame generator body 42 is connected to the sleeve and is electrically connected to the battery 30.

[0075] Thus, the sleeve 41 is fixedly fitted onto the rotating shaft 23, providing a stable mounting position for the flame generator body 42 and ensuring that it will not shake during operation. At the same time, because it is mounted on the rotating shaft 23, when the rotating shaft 23 is driven to rotate by the drive assembly 50, the flame generator body 42 can flexibly adjust the flame direction to adapt to different cable positions and de-icing requirements, achieving an organic combination of stable installation and flexible rotation.

[0076] Preferably, in one embodiment of the present invention, the drive assembly 50 includes a mounting plate 51, a motor 52, and a transmission belt 53.

[0077] The mounting plate 51 is connected between the two second fixing plates 22.

[0078] The motor 52 is mounted on the mounting plate 51.

[0079] One end of the transmission belt 53 is sleeved on the output shaft of the motor 52, and the other end is sleeved on the rotating shaft 23, so as to transmit the power of the motor 52 to the rotating shaft 23.

[0080] Thus, by connecting the mounting plate 51 between the two second fixing plates 22, a stable mounting base is provided for the motor 52, making the entire drive assembly 50 compact and rationally laid out, which is beneficial for installation in equipment with limited space. The power from the output shaft of the motor 52 is transmitted to the rotating shaft 23 via the transmission belt 53. This transmission method is simple and reliable, effectively realizing power transmission and ensuring the normal operation of related components. Of course, to ensure transmission stability, transmission gears are respectively installed on the output end of the motor 52, i.e., the rotating shaft 23, and the transmission is connected by a toothed transmission belt 53.

[0081] Preferably, in one embodiment of the present invention, both connecting frames 11 are U-shaped, and the ends of both connecting frames 11 are connected to the bottom surface of the aircraft 10.

[0082] In this way, the U-shaped structure can rationally plan the space to a certain extent, avoiding excessive interference with other components. Within the limited space at the bottom of the aircraft 10, a relatively compact and efficient layout can be achieved, which helps to improve the utilization rate of the internal space of the aircraft 10 and provides more possibilities for the placement of other important equipment or systems. It can also more securely connect related components to the aircraft 10, reducing loosening or shaking caused by factors such as vibration and airflow impact during flight, and improving the overall structural stability.

[0083] Preferably, in one embodiment of the present invention, both of the upper ends of the hanging arms 20 are provided with downwardly bent portions 24 to form a hanging gap between the bent portions 24 and the hanging arms 20, and the upper ends of the hanging arms 20 are hung on the lower end of the connecting frame 11 through the hanging gap.

[0084] Thus, the design of the mounting gap allows the mounting arm 20 and the connecting frame 11 to be connected by a mounting method. During installation, simply align the upper end of the mounting arm 20 with the mounting gap to easily complete the mounting operation without complicated installation tools or cumbersome installation steps. When disassembly is required, the mounting arm 20 can also be easily and quickly removed from the connecting frame 11, greatly improving the efficiency of equipment maintenance and parts replacement.

[0085] Preferably, in one embodiment of the present invention, the upper end of the hook arm is further provided with a closure member 25. The closure member 25 is L-shaped. One end of the closure member 25 is pivotally connected to the upper end face of the hook arm 20, and the other end is detachably connected to the side of the hook arm 20, so as to close the lower opening of the hook gap.

[0086] Thus, one end of the closure 25 is pivotally connected to the upper end face of the hook arm 20, and the other end is detachably connected to the side of the hook arm 20. This connection method not only ensures that the closure 25 can be flexibly installed and removed, but also seals the opening of the hook gap, ensuring the stability of the hook arm 20 connection.

[0087] Preferably, in one embodiment of the present invention, an adjustable screw 26 is vertically inserted through the closure member 25, the upper end of the adjusting screw 26 extends into the hook gap, and a pressure plate 27 is connected to the upper end of the adjusting screw 26. The pressure plate 27 and the end of the adjusting screw 26 are movably connected so that the pressure plate 27 can be adjusted to rise or fall by the adjusting screw 26 to press against the surface of the connecting frame 11.

[0088] Thus, by rotating the adjusting screw 26, the lifting height of the pressure plate 27 can be precisely controlled, thereby adjusting the pressure of the pressure plate 27 on the surface of the connecting frame 11. This allows the tightness of the connection between the mounting arm 20 and the connecting frame 11 to be flexibly adjusted according to actual needs, ensuring a stable and reliable connection under different flight conditions and load conditions, effectively preventing safety hazards caused by loosening or shaking. Since the connecting frame 11 may have certain dimensional deviations during actual manufacturing and use, or different requirements for connection tightness in different installation environments, this adjustment structure can adapt well to these changes. By adjusting the position and pressure of the pressure plate 27, dimensional deviations can be compensated for, meeting the connection requirements under different installation environments and working conditions, and improving the versatility and adaptability of the entire mounting structure.

[0089] Preferably, in one embodiment of the present invention, a fixing screw 251 is provided on the outer surface of the other end of the closure member 25, and a threaded hole corresponding to the fixing screw 251 is provided on the hook arm 20, and the end of the fixing screw 251 is connected to the threaded hole.

[0090] Thus, the engagement of the fixing screw 251 with the threaded hole is a common and reliable connection method. Through this connection, the closure 25 can be firmly fixed to the mounting arm 20, preventing the closure 25 from loosening or falling off due to vibration, airflow impact, or other factors during the flight of the aircraft 10. This ensures that the closure 25 always effectively seals the lower opening of the mounting gap, guaranteeing the stability and safety of the mounting structure.

[0091] Preferably, in one embodiment of the present invention, the bottom surface of the pressure plate 27 is provided with a rubber gasket 271.

[0092] Thus, the aircraft 10 will vibrate during flight. The rubber pad 271 has good elasticity and cushioning performance, which can absorb and disperse this vibration energy, reduce the impact on the mounting arm 20 and the connecting frame 11, reduce the risk of component wear and fatigue damage caused by vibration, and extend the service life of the components.

[0093] Meanwhile, the rubber gasket 271 is relatively soft, which can prevent the pressure plate 27 from directly and rigidly contacting the surface of the connecting frame 11, preventing the pressure plate 27 from causing scratches, wear and other damage to the surface of the connecting frame 11, protecting the surface quality of the connecting frame 11, and also reducing corrosion and other problems that may be caused by surface damage, thus improving the durability of the entire structure.

[0094] Preferably, in one embodiment of the present invention, a camera component 60 is provided at the center of the bottom surface of the aircraft 10 for capturing the surrounding environment.

[0095] Thus, through the camera component 60, the aircraft 10 can acquire real-time image information of the surrounding environment, helping operators or flight control systems to understand the situation around the aircraft 10 in a timely manner, including terrain, obstacle positions, other flying objects, etc., thereby making more accurate and reasonable flight decisions and improving flight safety and reliability.

[0096] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0097] The above description is only a preferred embodiment of the present utility model and does not limit the patent scope of the present utility model. All equivalent structural transformations made under the inventive concept of the present utility model using the contents of the present utility model specification and drawings, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present utility model.

Claims

1. A flying device carrying a flame generator, characterized in that, The utility model relates to an aircraft, which comprises two connecting frames arranged oppositely and extending downward from the bottom of the aircraft, two hanging arms connected to the lower ends of the connecting frames oppositely, each of the hanging arms being provided with a first fixing plate at the lower end to define an installation gap together with the first fixing plates, a storage battery arranged in the installation gap and connected to the first fixing plates at both sides, a flame generator arranged on a rotating shaft penetrating between the second fixing plates and connected to the storage battery, and a driving assembly arranged between the second fixing plates to drive the rotating shaft to rotate and adjust the flame direction of the flame generator. The flame generator comprises a sleeve member fixedly sleeved on the rotating shaft and a flame generator body connected to the sleeve member and electrically connected to the storage battery. The driving assembly comprises an installation plate connected between the second fixing plates, a motor mounted on the installation plate, and a transmission belt sleeved on the output shaft of the motor at one end and on the rotating shaft at the other end to transmit the power of the motor to the rotating shaft. Each of the connecting frames is U-shaped, and the end of each of the connecting frames is connected to the bottom surface of the aircraft. Each of the hanging arms is provided with a downwardly bent bending portion at the upper end to form a hanging gap between the bending portion and the hanging arm, and the upper end of the hanging arm is hung on the lower end of the connecting frame through the hanging gap. The upper end of the hanging arm is further provided with a closure member in the form of an L-shaped member, one end of which is pivotally connected to the upper end surface of the hanging arm, and the other end of which is detachably connected to the side surface of the hanging arm to close the lower end opening of the hanging gap.

2. The flight device carrying a flame generator according to claim 1, characterized in that, An adjustable adjusting screw is vertically penetrated through the closure member, the upper end of the adjusting screw extending into the hanging gap, and a pressing plate is connected to the upper end of the adjusting screw, the pressing plate being movably connected to the end of the adjusting screw to be lifted and lowered by the adjusting screw to press against the surface of the connecting frame. The other end of the closure member is provided with a fixing screw, and the hanging arm is provided with a threaded hole corresponding to the fixing screw. The bottom surface of the pressing plate is provided with a rubber gasket.

3. The flight carrying a flame generator device according to claim 1, characterized in that, A camera assembly is arranged in the middle of the bottom surface of the aircraft to take pictures of the surrounding environment. ​ ​ ​ 4. The flight device carrying a flame generator according to claim 1, characterized in that, ​ 5. The flight device carrying a flame generator according to claim 4, characterized in that, ​ 6. The flight device carrying a flame generator according to claim 5, characterized in that ​ 7. The flight device carrying a flame generator according to claim 6, characterized in that ​ 8. The flight device carrying a flame generator according to claim 6, characterized in that, ​ 9. The flight carrying a flame generator according to claim 7, characterized in that, ​ 10. The flight carrying a flame generator device according to claim 1, characterized in that, ​

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