Unmanned aerial vehicle capable of preventing electronic interference

Abstract

The utility model provides an electronic interference prevention unmanned aerial vehicle, relates to the technical field of unmanned aerial vehicles, and aims to solve the technical problem that the unmanned aerial vehicle controlled by optical fibers is unreasonable in structural layout and easy to cut lines. The electronic interference prevention unmanned aerial vehicle comprises a fuselage, an optical fiber winding mechanism and a plurality of rotor wings connected to the peripheral side of the fuselage, and in the height direction of the fuselage, each rotor wing is higher than the bottom of the fuselage; the optical fiber winding mechanism is arranged at the bottom of the fuselage close to the rear end, one end of an optical fiber in the optical fiber winding mechanism is in communication connection with a control unit of the unmanned aerial vehicle, and the other end obliquely extends downwards in the direction away from the rear end of the fuselage. The optical fiber of the unmanned aerial vehicle capable of preventing electronic interference can be prevented from being influenced by other parts of the unmanned aerial vehicle through reasonable arrangement of the optical fiber winding mechanism.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to an electronic interference-proof unmanned aerial vehicle. Background Art

[0002] The statements in this section merely provide background technology related to the present invention and do not necessarily constitute prior art.

[0003] Among the countermeasures against UAVs, electronic interference with UAV control signals is relatively common. Common anti-electronic interference measures for UAVs include avoiding interference segments through frequency hopping and autonomous flight through image recognition. However, frequency hopping is ineffective for full-band interference, and autonomous flight through image recognition cannot control UAVs in real time, which will cause information asymmetry for real-time information and thus cause mission failure. Utility Model Content

[0004] The utility model aims to provide an unmanned aerial vehicle that is resistant to electronic interference and solves the technical problem that the optical fiber for real-time control of the unmanned aerial vehicle is easily affected by other components or parts of the unmanned aerial vehicle.

[0005] In order to achieve the above purpose, the utility model provides the following technical solutions:

[0006] The utility model provides an anti-electronic interference unmanned aerial vehicle, comprising a fuselage, an optical fiber winding mechanism, and a plurality of rotors connected to the periphery of the fuselage, wherein in the height direction of the fuselage, each of the rotors is higher than the bottom of the fuselage;

[0007] The optical fiber winding mechanism is arranged at the bottom of the fuselage near the rear end. One end of the optical fiber in the optical fiber winding mechanism is communicatively connected to the control unit of the unmanned aerial vehicle, and the other end extends obliquely downward in a direction away from the rear end of the fuselage.

[0008] According to at least one embodiment of the utility model, the unmanned aerial vehicle further comprises a rack for mounting a throwable payload object, the rack being arranged at a bottom portion of the fuselage near the middle;

[0009] The hanger is located in front of the optical fiber winding mechanism, and the height of the hanger protruding from the fuselage is less than or equal to the height of the optical fiber winding mechanism protruding from the fuselage.

[0010] According to at least one embodiment of the utility model, the mounting bracket is provided with at least one mounting portion having a first pin hole, the bottom of the fuselage is provided with at least one pair of mounting points having a second pin hole adapted to at least one of the mounting portions, each of the mounting portions is detachably connected to a corresponding pair of the mounting points via a pin shaft, and the mounting portion is located between the pair of the mounting points.

[0011] According to at least one embodiment of the present utility model, the unmanned aerial vehicle further comprises a pod mounting interface, wherein the pod mounting interface is arranged at a bottom portion of the fuselage near the front end; and / or,

[0012] The unmanned aerial vehicle also includes an image acquisition device, which is arranged at the front end of the fuselage.

[0013] According to at least one embodiment of the utility model, the optical fiber winding mechanism includes a base, a spool, and a driving device for driving the spool to rotate; the base includes a bottom plate and a first support plate and a second support plate located on the bottom plate and arranged opposite to each other;

[0014] The bobbin is located between the first support plate and the second support plate, and two end plates of the bobbin are respectively opposite to the first support plate and the second support plate;

[0015] The optical fiber winding mechanism also includes a magnetic brake mechanism, which includes a magnetic part and a non-magnetic part that are relatively arranged, one of the magnetic part and the non-magnetic part is arranged on the first support plate, and the other is arranged on the end plate opposite to the first support plate.

[0016] According to at least one embodiment of the present utility model, the unmanned aerial vehicle further comprises a plurality of tripods, the plurality of tripods correspond one-to-one to the plurality of rotors, and each of the tripods is coaxial with the corresponding rotor;

[0017] Each of the tripods is foldably connected to the rotor, and when the tripod is folded, the axial direction of the tripod is parallel to the length direction of the fuselage.

[0018] According to at least one embodiment of the present utility model, each of the legs is further provided with a shock absorbing structure at the end away from the rotor; and / or,

[0019] The unmanned aerial vehicle further comprises at least one antenna, and each of the antennas is embedded in a corresponding tripod.

[0020] According to at least one embodiment of the utility model, the unmanned aerial vehicle further comprises a battery, wherein the battery is arranged on a side of the fuselage opposite to the optical fiber winding mechanism, and the battery is adapted to at least a portion of the fuselage.

[0021] According to at least one embodiment of the present utility model, the top of the body further has a battery groove and a battery female interface close to the battery groove, the battery female interface protrudes from the surface of the top of the body, and the bottom of the battery groove is further provided with two positioning grooves;

[0022] The bottom surface of the battery has a boss that matches the battery groove, and the boss is also provided with clips that match the two positioning grooves respectively. The bottom surface of the battery has a recessed portion near one end for accommodating the battery mother interface, and the bottom surface of the recessed portion is formed with a battery sub-interface that is adapted to the battery mother interface.

[0023] According to at least one embodiment of the present invention, the number of the rotors is four and the rotors are rotors with foldable blades, two of the rotors are symmetrically arranged on both sides of the fuselage and close to the front end of the fuselage; the other two rotors are symmetrically arranged on both sides of the fuselage and close to the rear end of the fuselage;

[0024] Each of the rotors is connected to the fuselage via a foldable arm, and two fixing clips for preventing the arms from rotating are respectively provided on both sides of the fuselage near the middle; when the arms are folded, each folded arm is respectively inserted into the C-shaped slot of the corresponding fixing clip.

[0025] One or more technical solutions provided in the exemplary embodiments of the present utility model can achieve at least one of the following beneficial effects.

[0026] The anti-electronic interference unmanned aerial vehicle of the exemplary embodiment of the utility model sets the optical fiber winding mechanism at the bottom of the fuselage near the rear end. The optical fiber in the optical fiber winding mechanism can transmit the ground control signal to the control unit inside the fuselage. The signal transmission through the optical fiber can avoid electronic interference, and then the unmanned aerial vehicle can be controlled in real time. The setting position of the optical fiber winding mechanism can make the optical fiber connected to the ground controller extend to the rear and lower part of the fuselage, thereby avoiding the rotor higher than the bottom of the fuselage, thereby reducing the possibility of the optical fiber being affected by other components and improving the reliability of the real-time control of the unmanned aerial vehicle. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] The accompanying drawings illustrate exemplary embodiments of the present invention and are used to explain the principles of the present invention together with the description thereof, wherein these drawings are included to provide a further understanding of the present invention, and the accompanying drawings are included in and constitute a part of this specification;

[0028] Figure 1 is an axonometric structural schematic diagram of an optical fiber winding mechanism according to an embodiment of the utility model;

[0029] Figure 2 It is a schematic diagram of a three-dimensional exploded structure of an optical fiber winding mechanism according to an embodiment of the utility model;

[0030] Figure 3 is a schematic diagram of a longitudinal cross-sectional structure of an optical fiber winding mechanism according to an embodiment of the utility model;

[0031] Figure 4 is a schematic diagram of the axonometric structure of an unmanned aerial vehicle (unfolded) according to an embodiment of the utility model;

[0032] Figure 5 is a schematic diagram of a three-dimensional exploded structure of an unmanned aerial vehicle according to an embodiment of the utility model;

[0033] Figure 6 is a schematic diagram of the axonometric structure of an unmanned aerial vehicle from another viewing angle according to an embodiment of the utility model;

[0034] Figure 7 is a schematic diagram of the isometric structure of a battery according to an embodiment of the utility model;

[0035] Figure 8 is a schematic diagram of the isometric structure of a battery from another viewing angle according to an embodiment of the utility model;

[0036] Fig. 9 It is a schematic diagram of the axonometric structure of an unmanned aerial vehicle (folded) according to an embodiment of the utility model.

[0037] Reference numerals:

[0038] 11. optical fiber; 12. slip ring; 121. second rotating part; 122. second fixed part; 13. optical signal module; 14. control board;

[0039] 20, bobbin; 21, end plate; 211, magnetic part; 212, non-magnetic part;

[0040] 30. Motor; 31. First fixed part; 32. First rotating part; 33. Output shaft;

[0041] 41. Reciprocating screw rod; 42. Guide rod; 43. Line straightener; 431. Steering member; 44. Tension sensor;

[0042] 51. first synchronous wheel; 52. second synchronous wheel; 53. synchronous belt;

[0043] 61. First support plate; 62. Second support plate; 63. Bottom plate; 631. Protective wire coil; 64. Wire box; 65. Waterproof box;

[0044] 71. Fixing fixture; 72. Arm; 73. Tripod; 74. Rotor; 75. Battery groove; 751. Positioning slot; 76. Mounting point;

[0045] 80, rack; 81, load object; 82, mounting part; 83, pin shaft;

[0046] 90. Battery; 91. Recessed portion; 911. Battery sub-interface; 92. Buckle; 93. Boss; 921. Button. DETAILED DESCRIPTION

[0047] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0048] In the field of unmanned aerial vehicles, frequency hopping or autonomous flight is usually used to prevent electronic interference. By controlling the frequency hopping to avoid electronic interference, when facing interference with the full-band interference mode, the unmanned aerial vehicle will be in a state of losing signal and cannot be controlled; and by building a three-dimensional map and placing it inside the unmanned aerial vehicle, presetting the route and target task, this method cannot control the unmanned aerial vehicle in real time, and cannot complete the corresponding task when the target task is uncertain. The information faced by the unmanned aerial vehicle is real-time, and the information gap will cause the target task to be unable to be reliably completed.

[0049] In the exemplary embodiment of the utility model, optical fiber guidance is adopted to prevent electronic interference, and the unmanned aerial vehicle is controlled by ground personnel to perform the target task. Due to the unreasonable structure layout of the unmanned aerial vehicle, the optical fiber is easily affected by other components of the unmanned aerial vehicle.

[0050] In view of the above problems, the unmanned aerial vehicle provided by the exemplary embodiment of the utility model sets the optical fiber winding mechanism at the bottom of the fuselage near the rear end, so that the optical fiber extending to the ground avoids other components of the unmanned aerial vehicle as much as possible, thereby improving control reliability.

[0051] It should be noted that the optical fiber winding mechanism provided by the exemplary embodiment of the utility model is not only applicable to unmanned aerial vehicle guidance for preventing electronic interference, but also applicable to other aircraft that require optical fiber guidance.

[0052] Figure 4 is a schematic diagram of the axonometric structure of an unmanned aerial vehicle (unfolded) according to an embodiment of the utility model; Figure 5 is a schematic diagram of a three-dimensional exploded structure of an unmanned aerial vehicle according to an embodiment of the utility model; Figure 6 FIG. 1 is a schematic diagram of the axonometric structure of an unmanned aerial vehicle from another perspective according to an embodiment of the present utility model. Figure 4-Figure 6 As shown, an exemplary embodiment of the utility model also provides an unmanned aerial vehicle, including a fuselage, a fiber optic winding mechanism, and a plurality of rotors 74 connected to the periphery of the fuselage. In the height direction of the fuselage, each rotor 74 is higher than the bottom of the fuselage, and the fiber optic winding mechanism is arranged at the bottom of the fuselage near the rear end.

[0053] The unmanned aerial vehicle adopts a layout in which a plurality of rotors 74 are arranged on the circumference. Since the blades of the rotors 74 may cut the optical fiber 11, the optical fiber winding mechanism is arranged at the bottom of the fuselage near the rear end. It should be noted that the fiber outlet of the wire box 64 of the optical fiber winding mechanism is located at the rear end of the bottom of the wire box 64, and the rear end and front end of the fuselage mentioned above refer to the rear end and front end of the unmanned aerial vehicle when flying forward. Based on this, during the flight, the optical fiber winding mechanism arranged at the bottom of the fuselage near the rear end is difficult to intersect with the optical fiber 11 because the blades of the rotors 74 are located at the upper part of the fuselage, and the optical fiber 11 extends downward along the lower rear of the fuselage towards the ground, thereby preventing the optical fiber 11 from being cut as much as possible.

[0054] In some embodiments, Figure 5 and Figure 6 As shown, the unmanned aerial vehicle also includes a rack 80 for mounting a throwable payload object 81, and the rack 80 is arranged at the bottom of the fuselage near the middle; the rack 80 is located in front of the optical fiber winding mechanism, and the height of the rack 80 protruding from the fuselage is less than or equal to the height of the optical fiber winding mechanism protruding from the fuselage, that is, the bottom of the rack 80 is higher than or flush with the bottom of the optical fiber winding mechanism, and the rack 80 is away from the optical fiber 11 that is tilted backward and extends downward from the optical fiber winding mechanism, so that the rack 80 has no effect on the extended optical fiber 11.

[0055] Exemplarily, the mounting bracket 80 is provided with at least one mounting portion 82 having a first pin hole, and the bottom of the fuselage is provided with at least one pair of mounting points 76 having a second pin hole adapted to the at least one mounting portion 82, each mounting portion 82 is detachably connected to the corresponding pair of mounting points 76 via a pin shaft 83, and the mounting portion 82 is located between the pair of mounting points 76.

[0056] The unmanned aerial vehicle can carry different payloads 81 through a detachable pylon 80 to perform various target tasks. Some payloads 81 are throwable. In order to reduce the change in the center of gravity of the unmanned aerial vehicle after the payload 81 is thrown, which may cause the flight instability, the pylon 80 is arranged at the bottom of the fuselage near the middle to minimize the impact of the change in the center of gravity.

[0057] Due to the multi-target mission of the unmanned aerial vehicle, the pylon 80 needs to be quickly disassembled to adapt to the target mission. Exemplarily, two mounting parts 82 are respectively arranged on the surface of the pylon 80 facing the fuselage at positions close to the front end and the rear end, and the two mounting parts 82 have a first pin hole for the pin shaft 83 to pass through. Correspondingly, two pairs of mounting points 76 are provided at the bottom of the fuselage, respectively adapted to the two mounting parts 82, specifically, the two mounting points 76 in each pair of mounting points 76 have coaxial second pin holes, and when the corresponding mounting part 82 is located between the two mounting points 76 in the pair of mounting points 76, the first pin hole is coaxial with the second pin holes of the two mounting points 76, so that the pin shaft passes through the two mounting points 76 and the mounting part 82, and the two form a quickly detachable connection.

[0058] In some embodiments, Figure 4-Figure 6 As shown, the unmanned aerial vehicle further includes a plurality of tripods 73, the plurality of tripods 73 correspond to the plurality of rotors 74 one by one, and each tripod 73 is coaxial with the corresponding rotor 74; the unmanned aerial vehicle further includes at least one antenna, and each antenna is embedded in a corresponding tripod 73. The plurality of tripods 73 are located on the side opposite to the optical fiber extension side of the optical fiber winding mechanism, that is, the tripods 73 are all away from the extension direction of the optical fiber 11 extending from the optical fiber winding mechanism, so that the tripods 73 will not affect the effect of winding and unwinding the optical fiber.

[0059] Exemplarily, the number of rotors 74 of the UAV is 4, and the number of tripods 73 is also 4. The tripods 73 are arranged under the corresponding rotors 74 to support the UAV when the UAV is docked on the ground. The bottom of each tripod 73, that is, the end away from the rotor, is also provided with a corrugated shock-absorbing structure to prevent the UAV from vibrating too much when falling and causing damage to components. Exemplarily, the shock-absorbing structure can also be a rubber shock-absorbing pad or the like. An extended-range backup antenna can be set in one or more of the four tripods 73. When the optical fiber 11 of the UAV scrapes the ground, the extended-range backup antenna can flip the UAV fuselage through one-key flipping of the UAV under the condition of good wireless extended-range signal. The blades of the rotor 74 are located at the bottom of the UAV, such as Figure 6 As shown, the optical fiber 11 can be cut by the blades of the rotor 74 to achieve the recovery of the unmanned aerial vehicle. The self-destruction of the unmanned aerial vehicle can also be achieved by using the extended range backup antenna. Since the optical fiber can transmit a large amount of data information in real time, the unmanned aerial vehicle can be self-destructed and abandoned to avoid exposing itself after completing the target mission.

[0060] like Figure 5As shown, the battery 90 of the unmanned aerial vehicle is arranged on the side of the fuselage opposite to the optical fiber winding mechanism, for example, the battery 90 of the unmanned aerial vehicle is arranged on the top of the fuselage, the battery 90 is adapted to a part of the fuselage, and the battery 90 does not extend beyond the peripheral side of the fuselage, for example, the outer contour of the battery does not exceed the maximum size of the fuselage, that is, the length, width and height of the battery (excluding the handle) do not exceed the length, width and height of the fuselage, so that it will not have a potential impact on the extended optical fiber 11 of the optical fiber winding mechanism. At the same time, the location of the battery of the unmanned aerial vehicle can balance the weight of the hanger, pod and optical fiber winding mechanism at the bottom of the fuselage, and the layout is more reasonable, and the battery can be quickly replaced.

[0061] For example, a battery handle is provided on the top of the battery 90, that is, on the surface of the battery 90 away from the fuselage, to facilitate replacement of the battery 90. At the same time, the battery handle can also provide a carrying capacity for the entire unmanned aerial vehicle, making it easy to move the entire unmanned aerial vehicle. For example, a battery switch is also provided on the rear end surface of the battery 90 for turning the power on and off, and a power indicator light is also provided near the power source for indicating the battery power.

[0062] Exemplarily, the battery 90 is installed on the top of the UAV and adopts a lithium-ion battery, which is lightweight and can provide the UAV with a hovering endurance of 100 minutes.

[0063] Figure 7 is a schematic diagram of the isometric structure of a battery according to an embodiment of the utility model; Figure 8 FIG. 1 is a schematic diagram of the isometric structure of a battery from another perspective according to an embodiment of the present utility model. Figure 7 , Figure 8 and Figure 5 As shown, the top of the fuselage also has a battery groove 75 and a battery female interface near the battery groove 75, the battery female interface protrudes from the surface of the top of the fuselage, and the bottom of the battery groove 75 is also provided with two positioning grooves 751; the bottom surface of the battery has a boss 93 matching the battery groove 75, and the boss 93 is also provided with buckles 92 matching the two positioning grooves 751 respectively, and the bottom surface of the battery has a recessed portion 91 for accommodating the battery female interface near one end, and the bottom surface of the recessed portion 91 is formed with a battery sub-interface 911 adapted to the battery female interface.

[0064] The battery mother interface of the fuselage is raised on the surface of the top of the fuselage. The battery mother interface is raised near the front end of the fuselage, and the battery sub-interface 911 formed on the bottom surface of the recessed part 91 on the battery 90 is adapted to the battery mother interface. The embedded interface setting can be waterproof. After the boss 93 on the bottom surface of the battery 90 is embedded in the battery groove 75, it can prevent the battery 90 from moving left and right and forward and backward after being installed on the fuselage, so that a fixed connection can be formed more stably. Further, by setting two positioning grooves 751 on the bottom surface of the battery groove 75, correspondingly, two buckles 92 are set on the boss 93 of the battery 90. When the battery 90 is installed on the fuselage, the two buckles 92 are respectively inserted into the two positioning grooves 751 to form a detachable connection. Further, a button 921 connected to the corresponding buckle 92 is also provided on the rear end surface of the battery 90. When the battery 90 needs to be removed, the button 921 is pressed to push the corresponding buckle 92 to disengage from the positioning groove 751.

[0065] Fig. 9 1 is a schematic diagram of the axonometric structure of an unmanned aerial vehicle (folded) according to an embodiment of the present utility model. Figure 5 and Fig. 9 As shown, there are four rotors 74 and the rotors 74 are rotors 74 with foldable blades. Two rotors 74 are symmetrically arranged on both sides of the fuselage and close to the front end of the fuselage; the other two rotors 74 are symmetrically arranged on both sides of the fuselage and close to the rear end of the fuselage; each rotor 74 is connected to the fuselage through a foldable arm 72, and two fixing clips 71 are respectively arranged on both sides of the fuselage near the middle, and each tripod 73 is foldably connected to the rotor 74; when the unmanned aerial vehicle is folded, each folded arm 72 is fixed in the C-shaped slot of the corresponding fixing clip 71, and the axial direction of each arm 72 and the axial direction of the tripod 73 are along the length direction of the fuselage.

[0066] like Figure 5As shown, four rotors 74 are symmetrically arranged on both sides of the fuselage, with two rotors 74 on each side, respectively close to the front and rear ends of the fuselage, that is, the entire unmanned aerial vehicle is roughly H-shaped. Among them, the blades of each rotor 74 can be folded to reduce the occupied space. The arm 72 can also be folded and connected to the fuselage, that is, the arm 72 is hingedly connected to the fuselage, and the arm 72 is rotated toward the middle position of the fuselage, and then fixed to one side of the fuselage by the corresponding fixing clamp 71, that is, the extension direction of each arm 72 is fixed to one side of the fuselage along the preset direction. Thereby, the occupied space of the arm 72 is compressed. At the same time, the tripod 73 arranged below the rotor 74 is also hingedly connected to the rotor 74, which can also be folded by rotation, that is, when the arm 72 is folded toward the middle of the fuselage, the tripod 73 is folded toward the front or rear end of the fuselage, that is, the extension direction of the tripod 73 is also a preset direction. After folding, the tripod 73 and the corresponding arm 72 can be arranged parallel to the length direction of the fuselage. When the propellers, the tripod 73 and the arms 72 of the UAV are folded, the UAV is compact and small in size and can be put into a backpack for easy carrying by one person for off-road travel.

[0067] In some embodiments, the outer shell of the unmanned aerial vehicle fuselage is made of lightweight plastic material, which has the characteristics of light weight, high hardness, and low unit cost, and can effectively protect the control unit inside the fuselage. The arm 72 is made of T800 carbon fiber material, which has high strength and light weight; the blades of the rotor 74 are made of carbon-added plastic material, which has high strength, low unit cost, and is easy to mass produce; the brushless motor that provides power for the rotor 74 provides 2.5 times the weight of the whole machine; the motor seat that carries the brushless electrode is made of 7075 aluminum alloy, which can not break in a high vibration environment, and the built-in electric adjustment control board is conducive to the heat dissipation of the electric adjustment. The base, the wire box 64, and the waterproof box 65 can all be injection molded with lightweight plastic materials, which have the characteristics of low cost and light weight. Based on this, the unmanned aerial vehicle of the exemplary embodiment of the utility model has the characteristics of light weight and low cost, and the use of optical fiber to collect data in real time can be used as a disposable unmanned aerial vehicle.

[0068] In some embodiments, a pod interface is further provided at the front bottom portion of the fuselage of the unmanned aerial vehicle of the exemplary embodiment of the utility model, and the pod can be replaced according to the requirements of the target mission. For example, a high-magnification 8M camera gimbal can be set at this position. Since optical fiber is used for signal transmission, a high-definition camera can be used. The high-magnification 8M camera gimbal is installed at the front bottom portion of the fuselage to obtain a wider viewing angle, and can track multiple targets in real time over a long distance.

[0069] In some embodiments, the front end of the fuselage of the unmanned aerial vehicle of the exemplary embodiment of the utility model is also provided with an image acquisition device, which can be a high-definition resolution fisheye camera. Since it is located in front of the fuselage, it can provide the operator with a wide first-person perspective.

[0070] As can be seen from the above, by arranging a battery 90 on the top of the fuselage, arranging a pod, a hanger 80 and a fiber optic winding mechanism in sequence from the front end to the rear end on the bottom of the fuselage, and arranging four rotors 74 on the sides of the fuselage through four arms 72, forming an H-shaped distribution, the unmanned aerial vehicle is easy to operate as a whole, foldable and portable. For example, the battery 90 is detachable and can be used as a fulcrum for moving the entire machine, and the power switch is convenient; the optical fiber 11 in the fiber optic winding mechanism is not easily cut by the rotor 74; after the load object 81 on the hanger 80 is thrown, the change in the center of gravity has little effect on the flight stability.

[0071] In some embodiments, Figure 5 and Figure 6 As shown, two heat dissipation ports are provided on both sides of the fuselage for dissipating the heat of the control unit inside the fuselage of the unmanned aerial vehicle. The heat dissipation ports are respectively close to the sides of the fuselage where the fixing clamps 71 are located. For example, the heat dissipation ports can be covered with a waterproof and breathable membrane, which can dissipate the heat of the fuselage while being waterproof, so as to ensure the normal operation of the fuselage control unit.

[0072] For example, Figure 6 As shown, four communication interfaces are provided at the bottom of the fuselage around a pair of mounting points 76 to meet the requirements of multi-target tasks, for example, the fuselage and the load object 81 form a communication connection through the communication interface.

[0073] Figure 1 is an axonometric structural schematic diagram of an optical fiber winding mechanism according to an embodiment of the utility model; Figure 2 It is a schematic diagram of the three-dimensional exploded structure of the optical fiber winding mechanism according to the embodiment of the utility model. Figure 3 FIG. 1 is a schematic diagram of a longitudinal cross-sectional structure of an optical fiber winding mechanism according to an embodiment of the present utility model. Figure 1-Figure 3 As shown, an optical fiber winding mechanism provided by an exemplary embodiment of the utility model, an optical fiber 11 is used to connect to an unmanned aerial vehicle for transmission of control signals, the optical fiber winding mechanism includes a base, a slip ring 12, a spool 20 and a driving device for driving the spool 20 to rotate, the spool 20 has a hollow cavity; the driving device includes a first fixed portion 31, a first rotating portion 32 and an output shaft 33 connected to the first rotating portion 32, the first fixed portion 31 is arranged on the base, and the first rotating portion 32 is fixed in the cavity; the slip ring 12 includes a second fixed portion 122 and a second rotating portion 121 electrically connected to the second fixed portion 122, the second fixed portion 122 is fixed on the base, the second rotating portion 121 is fixed in the cavity and connected to the end of the output shaft 33 away from the first rotating portion 32; the optical fiber 11 is communicatively connected to the second fixed portion 122.

[0074] In practical applications, the driving device can be an outer rotor motor 30, which includes a first fixed part 31, a first rotating part 32 and an output shaft 33 connected to the first rotating part 32; the first fixed part 31 is fixedly arranged on the second support plate 62, and the first rotating part 32 is fixedly arranged in the hollow cavity of the bobbin 20; the optical fiber winding mechanism also includes a slip ring 12, which includes a second fixed part 122 and a second rotating part 121, the second rotating part 121 is arranged in a part of the cavity close to the first support plate 61, the second fixed part 122 is arranged on the first support plate 61, and the end of the output shaft 33 away from the first rotating part 32 is connected to the second rotating part 121.

[0075] When the first rotating part 32 is fixedly disposed in the hollow cavity of the bobbin 20, the first rotating part 32 is fixedly connected to the bobbin 20 by, for example, gluing. The end of the output shaft 33 away from the first rotating part 32 is connected to the second rotating part 121, and the second rotating part 121 is also fixedly disposed in the hollow cavity of the bobbin 20, for example, by gluing. In this way, the bobbin 20 can be rotatably disposed between the first support plate 61 and the second support plate 62. Since the slip ring 12 includes a second fixed portion 122 and a second rotating portion 121, the second fixed portion 122 is fixed on the first support plate 61, the second fixed portion 122 and the second rotating portion 121 move relative to each other and can be connected in communication, the optical fiber 11 on the spool 20 can form a communication connection with the outside through the slip ring 12, for example, it can form an electrical connection with the control board 14, and form a communication and electrical connection with the control unit inside the unmanned aerial vehicle through the control board 14. For example, a cable outlet is provided on the bottom plate 63, and the cable of the control board 14 communicates with the control unit inside the unmanned aerial vehicle through the cable outlet, or is electrically connected to the battery 90 of the unmanned aerial vehicle. In order to reduce the wear of the above-mentioned cable, a protective coil 631 is also coated on the edge of the cable outlet to prevent the cable from being cut. Based on this, part of the motor 30 is arranged in the hollow cavity of the bobbin, so that the entire structure is compact and the space occupied is reduced. At the same time, without affecting the communication between the optical fiber 11 and the unmanned aerial vehicle, the output shaft 33 of the motor 30 cooperates with the second rotating part 121 of the slip ring 12 to jointly support the bobbin 20 and rotate the bobbin 20.

[0076] like Figure 1 and Figure 2As shown, when the optical fiber 11 needs to be wound onto the spool 20 for winding, the optical fiber 11 transmits a control signal to the driving device, and the driving device drives the spool 20 to rotate forward, and at this time, the reciprocating screw 41 rotates forward synchronously with the spool 20 through the synchronization mechanism. Since the cooperation between the line adjuster 43 and the reciprocating screw 41 is similar to a ball screw, it converts the rotary motion of the reciprocating screw 41 into the linear motion of the line adjuster 43, and the reciprocating screw 41 drives the line adjuster 43 to reciprocate along the axial direction of the spool 20. It should be pointed out that if there is no restriction, the line adjuster 43 will also rotate on the reciprocating screw 41. Therefore, the other end of the line adjuster 43 is slidably set on the guide rod 42 to prevent the line adjuster 43 from rotating, and can only reciprocate along the direction limited by the guide rod 42. Based on this, the optical fiber 11, driven by the line aligner 43 and the driving device, is wound evenly along the axial direction of the bobbin 20 while being wound on the bobbin 20, so as to prevent the optical fiber 11 from being concentrated at one position of the bobbin 20 and causing jamming. When the optical fiber 11 needs to be unwound on the bobbin 20, the optical fiber 11 transmits a control signal to the driving device, and the driving device drives the bobbin 20 to rotate in the opposite direction, and the reciprocating screw 41 rotates in the opposite direction synchronously. Therefore, during the unwinding process, the optical fiber 11 will also move along the axial direction of the bobbin 20, so that the optical fiber 11 will not stop at an axial position of the bobbin 20, which will cause difficulty in unwinding when the tension of the optical fiber 11 is too large.

[0077] Exemplarily, the line aligner 43 has a through hole for the optical fiber 11 to pass through, and the axis of the through hole extends along the tangent direction of the spool 20. The line aligner 43 is located between the spool 20 and the ground controller, that is, the line aligner 43 is located in front of the spool 20. When the axis of the through hole of the line aligner 43 extends along the tangent direction of the spool 20, the optical fiber 11 can be smoothly wound onto the spool 20 or unwound from the spool 20.

[0078] like Figure 1 and Figure 2 As shown, the line aligner 43 includes a steering member 431, the end of which has a crescent-shaped depression, and the end of the steering member 431 with the depression is stuck in the spiral groove of the reciprocating screw 41. The steering member 431 can penetrate the line aligner 43 and its end with the crescent-shaped depression is embedded in the spiral groove of the reciprocating screw 41. Through the end with the depression, when the reciprocating screw 41 rotates, the rotational motion is converted into the linear motion of the line aligner 43. When the steering member 431 slides to one end of the spiral groove, the reciprocating screw 41 continues to rotate, and the spiral groove drives the end of the steering member 431 with the depression to move linearly in the opposite direction, and this cycle is repeated, so that the line aligner 43 reciprocates along the axial direction of the reciprocating screw 41, so as to achieve the purpose of uniform winding or unwinding of the optical fiber 11.

[0079] like Figure 2As shown, in some embodiments, the line shunter 43 also includes a tension sensor 44 for detecting the tension of the optical fiber 11, and the tension sensor 44 is connected to the drive device for communication. The tension sensor 44 has a through hole for the optical fiber 11 to pass through, and the through hole is located on the side of the line shunter 43 facing away from the spool 20 and below the through hole. The axis of the through hole extends along the tangential direction of the spool 20 so that the optical fiber 11 can avoid the tension sensor 44 from generating additional resistance to the optical fiber 11 as much as possible. The optical fiber 11 passes through the through hole of the tension sensor 44 and the through hole of the line shunter 43 in sequence and is wound onto the spool 20. When the tension sensor 44 obtains a signal that the pulling force of the optical fiber 11 is too large, the control board 14 processes the information and controls the motor 30 to increase or decrease the rotation speed in the corresponding direction to prevent the optical fiber 11 from being torn off; and when the tension sensor 44 obtains a signal that the pulling force of the optical fiber 11 is too small or there is no tension, the control board 14 processes the information and controls the motor 30 to increase or decrease the rotation speed in the corresponding direction to prevent the optical fiber 11 from being not tightened and causing the wire to explode.

[0080] like Figure 2 and Figure 3 As shown, the base includes a first support plate 61 and a second support plate 62 that are arranged opposite to each other, and a bottom plate 63 connected to the corresponding ends of the first support plate 61 and the second support plate 62; the spool 20 is located between the first support plate 61 and the second support plate 62, and the two end plates 21 of the spool 20 are respectively opposite to the first support plate 61 and the second support plate 62; the optical fiber winding mechanism also includes a magnetic brake mechanism, the magnetic brake mechanism includes a magnetic portion 211 and a non-magnetic portion 212 that are arranged opposite to each other, one of the magnetic portion 211 and the non-magnetic portion 212 is arranged on the first support plate 61, and the other is arranged on the end plate 21 opposite to the first support plate 61.

[0081] Exemplarily, the bobbin 20 is in a dumbbell shape, which can prevent the occurrence of line running. For example, the end plates 21 at both ends of the bobbin 20 are tapered structures with a gradually decreasing cross section from the end to the middle of the bobbin 20. The two end plates 21 are respectively opposite to the first support plate 61 and the second support plate 62. The bobbin 20 is rotatably arranged between the first support plate 61 and the second support plate 62. The bottom plate 63 serves to connect the first support plate 61 and the second support plate 62. The first support plate 61 and the second support plate 62 can be at a certain distance from both ends of the bottom plate 63.

[0082] Considering that the optical fiber winding mechanism releases too much wire due to inertial rotation during high-speed pay-off, that is, the wire explodes, a magnetic brake mechanism is set on the optical fiber winding mechanism. The working principle of the magnetic brake mechanism is: adjustment is made through the electromagnetic damping phenomenon. According to Lenz's law, the magnetic lines of induction are cut when the wire cup rotates to generate a force opposite to the direction of movement of the wire cup, thereby slowing down the rotation speed of the wire cup to match the wire output speed, thereby effectively avoiding wire explosion.

[0083] For example, there are multiple magnetic parts 211, and the multiple magnetic parts 211 surround the cavity of the bobbin 20 and are circumferentially distributed on the end plate 21 opposite to the first support plate 61; an annular non-magnetic conductive part 212 is provided on the first support plate 61, opposite to the multiple magnetic parts 211. Exemplarily, the non-magnetic conductive part 212 can be an aluminum ring, and the magnetic part 211 can be a magnet or an electromagnet. When the two rotate relative to each other, the magnetic field will generate eddy currents through the aluminum ring, and the generation of eddy currents will cause the temperature inside the aluminum ring to rise. This process will convert electrical energy into thermal energy, causing the aluminum ring to heat up, and the bobbin 20 will gradually reduce the speed to match the unwinding speed.

[0084] In order to be waterproof, a wire box 64 is also provided on the base to seal with the bottom plate 63, and a sealing ring is also provided between the bottom plate 63 and the wire box 64 to seal and waterproof the two. The entire wire box 64 and the bottom plate 63 form a relatively closed box body, and other components of the optical fiber winding mechanism are enclosed in the box body. It should be noted that the wire box 64 is provided with a long strip of fiber outlet, and the fiber outlet is arranged on the side wall of the wire box 64 in front of the spool 20 near the bottom, so that the optical fiber 11 connected to the ground control equipment does not bend significantly when entering the wire box 64, and the length direction of the fiber outlet is parallel to the axial direction of the spool 20, so that the optical fiber 11 can be not bent between the fiber outlet and the line straightener 43, and the service life of the optical fiber 11 is not reduced, so that the optical fiber 11 on the spool 20 can be connected to the ground control equipment, and the ground control equipment is, for example, a computer of the ground personnel and other equipment. It should be noted that the front of the above-mentioned spool 20 refers to the side of the reciprocating screw 41 of the spool 20. Exemplarily, the edge of the cable outlet is also covered with a cable protection sleeve having a certain elasticity to prevent the sharp edge from cutting the optical fiber.

[0085] It should also be noted that an optical signal module 13 is fixedly provided at the middle position of the output shaft 33. The optical fiber 11 on the spool 20 is connected to the second rotating part 121 of the slip ring 12 through the optical signal module 13. The optical signal module 13 is used to convert the optical signal transmitted by the optical fiber 11 so that it can be recognized by the control board 14.

[0086] For example, in order to make the control board 14 waterproof, a waterproof box 65 is further provided inside the bottom plate 63 of the base, and its enclosed space can accommodate the control board 14. The control board 14 is respectively connected to the motor 30 and the second fixing portion 122 of the slip ring 12 in communication, and is also connected to the power supply and / or internal control unit of the unmanned aerial vehicle through the outlet of the bottom plate 63. That is, the position of the waterproof box 65 on the bottom plate 63 corresponds to the outlet, and the fixing method between the waterproof box 65 and the bottom plate 63 can be sealed with glue to prevent water from entering.

[0087] The synchronous mechanism can be in various forms. The exemplary embodiment of the present invention adopts gear transmission or synchronous wheels and synchronous belts. The following description will take synchronous wheels and synchronous belts as examples.

[0088] For example, the synchronization mechanism includes a first synchronization wheel 51, a second synchronization wheel 52 and a synchronization belt 53 that transmits and connects the first synchronization wheel 51 and the second synchronization wheel 52; the first synchronization wheel 51 is arranged on the end plate 21 opposite to the bobbin 20 and the second support plate 62, the second synchronization wheel 52 is arranged on the reciprocating screw 41, and the reciprocating screw 41 is rotatably arranged on the first support plate 61 and the second support plate 62.

[0089] The first synchronous wheel 51 is arranged on the end plate 21 opposite to the bobbin 20 and the second support plate 62. The first synchronous wheel 51 has a relatively large inner diameter and can be wrapped around the outside of the first rotating part 32 of the motor 30, or directly fixed to the outside of the first rotating part 32 of the motor 30. The second synchronous wheel 52 is arranged near the end of the reciprocating screw 41, and the first synchronous wheel 51 and the second synchronous wheel 52 are connected by a synchronous belt 53. Exemplarily, the two ends of the reciprocating screw 41 are rotatably arranged on the first support plate 61 and the second support plate 62 through corresponding bearings. It should be noted that the two ends of the above-mentioned guide rod 42 can also be rotatably arranged on the first support plate 61 and the second support plate 62 through corresponding bearings, so that the line shunter 43 can move smoothly on the guide rod 42.

[0090] Exemplarily, the optical fiber 11 is a high-toughness optical fiber with a diameter of 0.13 mm, a length of 12 km, and a weight of 1.5 kg. It can lift five times its own weight and is lightweight while preventing disconnection in mid-air.

[0091] As can be seen from the above, the optical fiber 11 is used for the transmission of control signals of the unmanned aerial vehicle, and the wireless control is converted into wired control, which has the characteristics of light weight, stable signal transmission without interference, low signal loss and long transmission distance, high toughness and not easy to be broken. The unmanned aerial vehicle with the optical fiber winding mechanism can carry a 12KM optical fiber to communicate with the ground control equipment, and transmit high-quality, high-speed and highly stable signals, so that the target information can be obtained in real time and the target task can be reliably completed. The optical fiber winding mechanism adopts an anti-jamming and anti-explosion wire mechanism, which can realize the rapid release and recovery of the optical fiber, and can complete multiple target tasks in open areas.

[0092] Those skilled in the art should understand that the above embodiments are only for the purpose of clearly illustrating the present invention, and are not intended to limit the scope of the present invention. For those skilled in the art, other changes or modifications may be made based on the above disclosure, and these changes or modifications are still within the scope of the present invention.

Claims

1. An unmanned aerial vehicle that is resistant to electronic interference, characterized in that: It comprises a fuselage, an optical fiber winding mechanism, and a plurality of rotors connected to the periphery of the fuselage, wherein each of the rotors is higher than the bottom of the fuselage in the height direction of the fuselage; The optical fiber winding mechanism is arranged at the bottom of the fuselage near the rear end. One end of the optical fiber in the optical fiber winding mechanism is communicatively connected to the control unit of the unmanned aerial vehicle, and the other end extends obliquely downward in a direction away from the rear end of the fuselage.

2. The unmanned aerial vehicle according to claim 1, characterized in that: The unmanned aerial vehicle further comprises a rack for mounting a throwable payload object, wherein the rack is arranged at a bottom portion of the fuselage near the middle; The hanger is located in front of the optical fiber winding mechanism, and the height of the hanger protruding from the fuselage is less than or equal to the height of the optical fiber winding mechanism protruding from the fuselage.

3. The unmanned aerial vehicle according to claim 2, characterized in that: The mounting bracket is provided with at least one mounting portion having a first pin hole, and the bottom of the fuselage is provided with at least one pair of mounting points having a second pin hole adapted to at least one of the mounting portions, each of the mounting portions is detachably connected to a corresponding pair of mounting points via a pin shaft, and the mounting portion is located between a pair of mounting points.

4. The unmanned aerial vehicle according to claim 1, characterized in that: The unmanned aerial vehicle further comprises a pod mounting interface, wherein the pod mounting interface is arranged at a position near the front end of the bottom of the fuselage; and / or, The unmanned aerial vehicle also includes an image acquisition device, which is arranged at the front end of the fuselage.

5. The unmanned aerial vehicle according to claim 1, characterized in that: The optical fiber winding mechanism comprises a base, a spool and a driving device for driving the spool to rotate; the base comprises a bottom plate and a first support plate and a second support plate located on the bottom plate and arranged opposite to each other; The bobbin is located between the first support plate and the second support plate, and two end plates of the bobbin are respectively opposite to the first support plate and the second support plate; The optical fiber winding mechanism also includes a magnetic brake mechanism, which includes a magnetic part and a non-magnetic part that are relatively arranged, one of the magnetic part and the non-magnetic part is arranged on the first support plate, and the other is arranged on the end plate opposite to the first support plate.

6. The unmanned aerial vehicle according to claim 1, characterized in that: The unmanned aerial vehicle further comprises a plurality of tripods, the plurality of tripods correspond to the plurality of rotors one by one, and each of the tripods is coaxial with the corresponding rotor; Each of the tripods is foldably connected to the rotor, and when the tripod is folded, the axial direction of the tripod is parallel to the length direction of the fuselage.

7. The unmanned aerial vehicle according to claim 6, characterized in that: Each of the legs is further provided with a shock absorbing structure at the end away from the rotor; and / or, The unmanned aerial vehicle further comprises at least one antenna, and each of the antennas is embedded in a corresponding tripod.

8. The unmanned aerial vehicle according to claim 1, characterized in that: The unmanned aerial vehicle further comprises a battery, which is arranged on a side of the fuselage opposite to the optical fiber winding mechanism, and the battery is adapted to at least a part of the fuselage.

9. The unmanned aerial vehicle according to claim 8, characterized in that: The top of the fuselage also has a battery groove and a battery female interface close to the battery groove, the battery female interface protrudes from the surface of the top of the fuselage, and the bottom of the battery groove is also provided with two positioning grooves; The bottom surface of the battery has a boss that matches the battery groove, and the boss is also provided with clips that match the two positioning grooves respectively. The bottom surface of the battery has a recessed portion near one end for accommodating the battery mother interface, and the bottom surface of the recessed portion is formed with a battery sub-interface that is adapted to the battery mother interface.

10. The unmanned aerial vehicle according to claim 6, characterized in that: The number of the rotors is four and the rotors are rotors with foldable blades, two of the rotors are symmetrically arranged on both sides of the fuselage and close to the front end of the fuselage; the other two rotors are symmetrically arranged on both sides of the fuselage and close to the rear end of the fuselage; Each of the rotors is connected to the fuselage via a foldable arm, and two fixing clamps for preventing the arms from rotating are respectively provided on both sides of the fuselage near the middle; When the machine arms are folded, each of the folded machine arms is respectively inserted into a C-shaped slot of the corresponding fixing fixture.

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