Unmanned aerial vehicle

Abstract

The embodiment of the utility model relates to the technical field of unmanned aerial vehicles, and discloses an unmanned aerial vehicle which comprises a vehicle body, a wing module, a lifting module, a first driving module and a second driving module. The lifting module is mounted on the body; the first driving module comprises a first switching motor and a first propeller motor, the first switching motor is mounted on the wing module, the first propeller motor is connected with the first switching motor, and the first switching motor is used for driving the first propeller motor to swing between a horizontal state and a vertical state; the second driving module comprises a second switching motor and a second propeller motor, the second switching motor is installed on the wing module, the second propeller motor is connected with the second switching motor, and the second switching motor is used for driving the second propeller motor to swing between the horizontal state and the vertical state. According to the embodiment of the utility model, the first driving module and the second driving module can provide lifting power for the unmanned aerial vehicle.

Description

Technical Field

[0001] The embodiment of the utility model relates to the technical field of unmanned aerial vehicles, and in particular to a unmanned aerial vehicle. Background Art

[0002] Existing drones generally include a lifting module and a horizontal flight module. The lifting module is used to drive the drone to lift vertically, while the horizontal flight module is used to provide power for the drone to move forward. Since the drone needs to overcome its own gravity to lift vertically during the take-off phase, the power provided by the lifting module determines the weight of the drone.

[0003] With the development of drones, the functions of drones are increasing, which leads to the weight of drones becoming heavier. In order to enable drones to perform vertical take-off and landing normally, people generally use more propeller motors as lifting modules to provide greater power for the lifting and landing of drones.

[0004] However, using more propeller motors will make the structure of the drone complicated. Therefore, it is necessary to design a drone that can increase the lifting power. Utility Model Content

[0005] The main technical problem solved by the embodiments of the utility model is to provide a drone, which can increase the power of the drone during lifting and lowering without increasing the number of propeller motors.

[0006] In order to solve the above technical problems, the technical solution adopted in the embodiment of the utility model is: to provide a drone, including a fuselage, a wing module, a lifting module, a first driving module and a second driving module, the wing module is installed on the fuselage; the lifting module is installed on the fuselage; the first driving module includes a first switching motor and a first propeller motor, the first switching motor is installed on the wing module, the first propeller motor is connected to the first switching motor, and the first switching motor is used to drive the first propeller motor to swing between a horizontal state and a vertical state; the second driving module includes a second switching motor and a second propeller motor, the second switching motor is installed on the wing module, the first switching motor and the second switching motor are respectively located on both sides of the fuselage, the second propeller motor is connected to the second switching motor, and the second switching motor is used to drive the second propeller motor to swing between a horizontal state and a vertical state; wherein, when the first propeller motor and the second propeller motor are in a horizontal state, the first propeller motor and the second propeller motor can provide the drone with forward power; when the first propeller motor and the second propeller motor are in a vertical state, the first propeller motor and the second propeller motor can provide the drone with lifting power.

[0007] Optionally, the UAV also includes a tail module, which includes a first tail panel, a second tail panel, a first tail rudder and a second tail rudder. The first tail panel and the second tail panel are both connected to the tail of the fuselage. The first tail rudder is rotatably arranged on the first tail panel, and the second tail rudder is rotatably arranged on the second tail panel.

[0008] Optionally, the first driving module further includes a first mounting seat, the first mounting seat is connected to the first switching motor, and the first propeller motor is mounted on an end of the first mounting seat away from the first switching motor.

[0009] Optionally, the second driving module further includes a second mounting seat, the second mounting seat is connected to the second switching motor, and the second propeller motor is mounted on an end of the second mounting seat away from the second switching motor.

[0010] Optionally, the wing module includes a wing body, a first wing rod and a second wing rod, the wing body is mounted on the fuselage, the first wing rod and the second wing rod are both mounted on the wing body, the first wing rod and the second wing rod are respectively located on both sides of the fuselage, the first switching motor is mounted on one end of the first wing rod, and the second switching motor is mounted on one end of the second wing rod.

[0011] Optionally, the wing module further includes a first yaw plate and a second yaw plate, both of which are rotatably arranged on the wing body, and the first yaw plate and the second yaw plate are respectively located on both sides of the fuselage.

[0012] Optionally, a first circuit board electrically connected to the first drive module is provided in the first wing rod; the wing module also includes a first heat sink, the first heat sink is connected to the first circuit board, the first heat sink is installed on the first wing rod, and at least part of the first heat sink is exposed to the outside.

[0013] Optionally, a plurality of first grooves are provided on the surface of the first heat dissipation plate exposed to the outside.

[0014] Optionally, a second circuit board electrically connected to the second drive module is provided in the second wing rod; the wing module also includes a second heat sink, which is connected to the second circuit board and installed on the second wing rod, and at least part of the second heat sink is exposed to the outside.

[0015] Optionally, the lifting module includes a third propeller motor and a fourth propeller motor, both of which are installed on the fuselage, and both of which can provide lifting power for the drone.

[0016] The beneficial effects of the embodiments of the utility model are as follows: different from the prior art, the embodiments of the utility model install both the lifting module and the wing module on the fuselage, install the first switching motor on the wing module, and connect the first propeller motor to the first switching motor so that the first switching motor can drive the first propeller motor to switch between a horizontal state and a vertical state; install the second switching motor on the wing module, the second motor and the first motor are respectively located on both sides of the fuselage, and the second motor is connected to the first switching motor so that the second switching motor can drive the second propeller motor to switch between a horizontal state and a vertical state; when the first propeller motor and the second propeller motor are in a horizontal state, the first propeller motor and the second propeller motor can provide the drone with forward power; when the first propeller motor and the second propeller motor are in a vertical state, the first propeller motor, the second propeller motor and the lifting module can all provide the drone with lifting power, and the lifting power of the drone can be increased without increasing the number of propeller motors. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the specific embodiments of the utility model or the technical solutions in the prior art, the following is a brief introduction to the drawings required for the specific embodiments or the prior art description. In all the drawings, similar elements or parts are generally identified by similar reference numerals. In the drawings, each element or part is not necessarily drawn according to the actual scale.

[0018] Figure 1 It is a structural schematic diagram of the drone provided in the embodiment of the utility model when the first propeller motor is in a horizontal state;

[0019] Figure 2 yes Figure 1 A magnified view of the area shown in middle A;

[0020] Figure 3 yes Figure 1 A magnified view of the area shown in part B;

[0021] Figure 4 is a schematic structural diagram of the drone provided in the embodiment of the utility model when the first propeller motor is in a vertical state;

[0022] Figure 5 yes Figure 4 Enlarged view of the area shown in middle C;

[0023] Figure 6 It is a partial structural schematic diagram of the first driving module, the second driving module and the wing module provided in the embodiment of the utility model in a disassembled state;

[0024] Figure 7 yes Figure 6 Enlarged view of the area shown in middle E;

[0025] Figure 8 yes Figure 4 Enlarged view of the area shown in D in the middle;

[0026] Fig. 9 yes Figure 6 Enlarged view of the area shown in part F;

[0027] Fig.10 It is a schematic diagram of the local structure of the UAV provided in the embodiment of the utility model when the first yaw plate is deflected upward;

[0028] Fig.11 It is a schematic diagram of the local structure of the UAV provided in the embodiment of the utility model when the first yaw plate is deflected downward;

[0029] Fig.12 It is a schematic diagram of the local structure of the UAV provided in the embodiment of the utility model when the first tail rudder and the second tail rudder are both deflected upward;

[0030] Fig.13 It is a schematic diagram of the local structure of the UAV provided in the embodiment of the utility model when the first tail rudder and the second tail rudder are both deflected downward;

[0031] Fig.14 It is a schematic diagram of the local structure of the UAV provided in an embodiment of the utility model when the first tail rudder is deflected upward and the second tail rudder is deflected downward. DETAILED DESCRIPTION

[0032] In order to facilitate the understanding of the utility model, the utility model is described in more detail below in conjunction with the accompanying drawings and specific embodiments. It should be noted that when an element is described as "fixed to" another element, it can be directly on another element or there can be one or more centered elements therebetween. When an element is described as "connected" to another element, it can be directly connected to another element or there can be one or more centered elements therebetween. The orientation or positional relationship indicated by the terms "upper", "lower", "inner", "outer", "vertical", "horizontal", etc. used in this specification is based on the orientation or positional relationship shown in the accompanying drawings, only for the convenience of describing the utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the utility model. In addition, the terms "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0033] Unless otherwise defined, all technical and scientific terms used in this specification have the same meaning as those commonly understood by those skilled in the art in the technical field of the present invention. The terms used in the specification of the present invention are only for the purpose of describing specific embodiments and are not used to limit the present invention. The term "and / or" used in this specification includes any and all combinations of one or more related listed items.

[0034] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0035] See also Figure 1 , Figure 2 and Figure 3 The UAV 100 includes: a fuselage 1, a first drive module 2, a second drive module 3, a wing module 4 and a lifting module 5. The wing module 4 is mounted on the fuselage 1, and the wing module 4 is roughly symmetrically arranged relative to the fuselage 1. The first drive module 2 and the second drive module 3 are both mounted on the wing module 4, and the first drive module 2 and the second drive module 3 are respectively located on both sides of the fuselage 1, and the first drive module 2 and the second drive module 3 are roughly symmetrically arranged relative to the fuselage 1. The lifting module 5 is mounted on the fuselage 1, and the lifting module 5 is used to provide power for the lifting of the UAV 100.

[0036] For the first driving module 2 mentioned above, please refer to Figure 2 , Figure 4 , Figure 5 , Figure 6 and Figure 7 The first driving module 2 includes a first switching motor 21 and a first propeller motor 22. The first switching motor 21 is installed on the wing module 4. The first propeller motor 22 is connected to the first switching motor 21. The first switching motor 21 is used to drive the first propeller motor 22 to swing between a horizontal state and a vertical state. Figure 5 In the vertical state shown in FIG, the first propeller motor 22 can provide the UAV 100 with lifting power. When the first switching motor 21 drives the first propeller motor 22 to swing to Figure 2 When in the horizontal state shown in , the first propeller motor 22 can provide the drone 100 with forward power.

[0037] For the second drive module 3 mentioned above, please refer to Figure 3 , Figure 4 , Figure 6 , Figure 8 and Fig. 9, the second driving module 3 includes a second switching motor 31 and a second propeller motor 32. The second switching motor 31 is installed on the wing module 4, and the second switching motor 31 and the first switching motor 21 are respectively located on both sides of the fuselage 1, and the minimum distance between the second switching motor 31 and the fuselage 1 is substantially equal to the minimum distance between the first switching motor 21 and the fuselage 1. The second propeller motor 32 is connected to the second switching motor 31 so that the second switching motor 31 can drive the second propeller motor 32 to swing between a horizontal state and a vertical state. Among them, when the second propeller motor 32 is in Figure 8 In the vertical state shown in FIG, the second propeller motor 32 can provide the UAV 100 with lifting power. When the second switching motor 31 drives the second propeller motor 32 to swing to Figure 3 When in the horizontal state shown in , the second propeller motor 32 can provide the drone 100 with forward power.

[0038] In this embodiment, the first propeller motor 22 is driven to switch between the horizontal state and the vertical state by the first switching motor 21, and the second propeller motor 32 is driven to switch between the horizontal state and the vertical state by the second switching motor 31. When the drone 100 is lifting, the first propeller motor 22 and the second propeller motor 32 can be adjusted to the vertical state, so that the first propeller motor 22, the second propeller motor 32 and the lifting module 5 jointly provide the drone 100 with lifting power, which is conducive to increasing the load of the drone 100 without increasing the propeller motors, and can also make the drone 100 take off. When the drone 100 rises to a set height, the first propeller motor 22 and the second propeller motor 32 can be switched to the horizontal state, so that the first propeller motor 22 and the second propeller motor 32 can jointly provide power for the drone 100 to move forward, so that the drone 100 can fly forward.

[0039] In some embodiments, see Figure 1 , Figure 7 and Fig. 9The wing module 4 includes a wing body 41, a first wing rod 42 and a second wing rod 43. The wing body 41 is mounted on the fuselage 1, and the wing body 41 is roughly symmetrical with respect to the fuselage 1. The first wing rod 42 and the second wing rod 43 are both mounted on the wing body 41, and the first wing rod 42 and the second wing rod 43 are respectively located on both sides of the fuselage 1, and the first wing rod 42 and the second wing rod 43 are roughly symmetrical with respect to the fuselage 1. The first switching motor 21 is mounted on one end of the first wing rod 42, and the first switching motor 21 is at least partially accommodated inside the first wing rod 42. The second switching motor 31 is mounted on one end of the second wing rod 43, and the second switching motor 31 is at least partially accommodated in the second wing rod 43. In this embodiment, by accommodating at least part of the first switching motor 21 in the first wing rod 42 and accommodating at least part of the second switching motor 31 in the second wing rod 43, it is beneficial to reduce the resistance of the first switching motor 21 and the second switching motor 31 to the forward movement of the drone 100.

[0040] In some embodiments, see Figure 7 The first driving module 2 also includes a first mounting seat 23, one end of the first mounting seat 23 is connected to the first switching motor 21, and the first propeller motor 22 is installed at one end of the first mounting seat 23 away from the first switching motor 21. The first switching motor 21 is used to drive the first mounting seat 23 to swing relative to the first wing rod 42, thereby driving the first propeller motor 22 to swing relative to the first wing rod 42, thereby realizing the switching of the first propeller motor 22 between the horizontal state and the vertical state.

[0041] It can be understood that in addition to connecting the first switching motor 21 and the first propeller motor 22 through the first mounting bracket 23, other methods can also be used. For example, they can be connected through an L-shaped connecting rod, with one end of the L-shaped connecting rod connected to the first switching motor 21 and the other end fixed to the first propeller motor 22, so that the first switching motor 21 can drive the first propeller motor 22 to switch between the horizontal state and the vertical state through the L-shaped connecting rod.

[0042] In some embodiments, see Fig. 9 The second driving module 3 also includes a second mounting seat 33, one end of the second mounting seat 33 is connected to the second switching motor 31, and the second propeller motor 32 is installed at one end of the second mounting seat 33 away from the second switching motor 31. The second switching motor 31 is used to drive the second mounting seat 33 to swing relative to the second wing rod 43, thereby driving the second propeller motor 32 to swing relative to the second wing rod 43, thereby realizing the switching of the second propeller motor 32 between the horizontal state and the vertical state.

[0043] It can be understood that in addition to connecting the second switching motor 31 and the second propeller motor 32 through the second mounting bracket 33, other methods can also be used. For example, the connection can be made through an L-shaped connecting rod, with one end of the L-shaped connecting rod being connected to the second switching motor 31 and the other end being fixed to the second propeller motor 32, so that the second switching motor 31 can drive the second propeller motor 32 to switch between the horizontal state and the vertical state through the L-shaped connecting rod.

[0044] In some embodiments, see Figure 1 , Fig.10 and Fig.11 The wing module 4 also includes a first yaw plate 44 and a second yaw plate 45. The first yaw plate 44 and the second yaw plate 45 are both rotatably arranged on the wing body 41. The first yaw plate 44 and the second yaw plate 45 are respectively located on both sides of the fuselage 1. The first yaw plate 44 and the second yaw plate 45 are used to control the steering of the drone 100.

[0045] Specifically, the first yaw plate 44 and the second yaw plate 45 are substantially symmetrically arranged relative to the fuselage 1, the first yaw plate 44 can swing up and down around the wing body 41, and the second yaw plate 45 can also swing up and down around the wing body 41. When the first yaw plate 44 deflects upward relative to the wing body 41, and the second yaw plate 45 deflects downward relative to the wing body 41, as shown in FIG. Fig.10 As shown in FIG. 1 , the lift of one side of the wing body 41 with the first yaw plate 44 is reduced, and the lift of one side of the wing body 41 with the second yaw plate 45 is increased, so that the UAV 100 generates a counterclockwise moment F1 in its forward direction, thereby causing the UAV 100 to deflect in the counterclockwise direction, and then the UAV 100 can turn left; when the first yaw plate 44 deflects downward relative to the wing body 41, and the second yaw plate 45 deflects upward relative to the wing body 41, as shown in FIG. Fig.11 As shown, the lift on one side of the wing body 41 having the first yaw plate 44 increases, and the lift on one side of the wing body 41 having the second yaw plate 45 decreases, so that the drone 100 generates a clockwise moment F2 in its forward direction, thereby causing the drone 100 to deflect in the clockwise direction, and further allowing the drone 100 to turn right.

[0046] In some embodiments, the wing module 4 further includes at least two motors (not shown), and the first yaw plate 44 is connected to one of the motors so that the motor can drive the first yaw plate 44 to swing relative to the wing body 41. The second yaw plate 45 is connected to another motor so that the motor can drive the second yaw plate 45 to swing relative to the wing body 41.

[0047] In some embodiments, see Figure 1 , Fig.12 and Fig.13 The UAV 100 further includes a tail module 6, which includes a first tail panel 61, a second tail panel 62, a first tail rudder 63, and a second tail rudder 64. The first tail panel 61 and the second tail panel 62 are both connected to the tail portion 12 of the fuselage 1, the first tail rudder 63 is rotatably disposed on the first tail panel 61, and the second tail rudder 64 is disposed on the second tail panel 62. The first tail rudder 63 and the second tail rudder 64 can control the UAV 100 to fly upward or downward.

[0048] Specifically, the first tail fin plate 61 and the second tail fin plate 62 are connected in a V shape, the first tail rudder 63 can swing around the first tail fin plate 61, and the second tail rudder 64 can swing around the second tail fin plate 62. When the first tail rudder 63 deflects upward relative to the first tail fin plate 61, and the second tail rudder 64 also deflects upward relative to the second tail fin plate 62, as shown in FIG. Fig.12 As shown, the tail module 6 generates negative lift to make the drone 100 generate a nose-up moment, so that the drone 100 can climb upward; when the second tail rudder 64 deflects downward relative to the second tail plate 62, and the second tail rudder 64 also deflects downward relative to the second tail plate 62, as shown in FIG. Fig.13 As shown, the tail module 6 generates positive lift to cause the drone 100 to generate a diving moment, thereby allowing the drone 100 to dive downward.

[0049] It is worth noting that the first tail rudder 63 and the second tail rudder 64 can not only control the drone 100 to climb up or dive down, but also balance the power of the drone 100 when the first propeller motor or the second propeller motor 32 fails, so that the drone 100 can continue to fly smoothly. Fig.11 and Fig.14 , when the first propeller motor 22 fails during flight and cannot work, the first tail rudder 63 can be deflected upward relative to the first tail wing plate 61, and the second tail rudder 64 can be deflected downward relative to the second tail wing plate 62. In this way, when the drone 100 moves forward, the tail module 6 can balance the power difference between the second propeller motor 32 and the first propeller motor 22, thereby reducing the risk of the drone 100 turning to the side with weak power. In this way, even if the first propeller motor 22 fails during flight, only the power output of the second propeller motor 32 can ensure that the drone 100 can continue to fly forward, so that the first propeller motor 22 can return normally when it fails. Similarly, not shown in the figure, when the second propeller motor 32 fails, the first tail rudder 63 can be deflected downward relative to the first tail wing plate 61, and the second tail rudder 64 can be deflected upward relative to the second tail wing plate 62, which can also balance the power difference between the first propeller motor 22 and the second propeller motor 32, ensuring that the drone 100 can continue to fly forward normally.

[0050] In some embodiments, the tail module 6 further includes two motors (not shown), and the first tail rudder 63 is connected to one of the motors so that the motor can drive the first tail rudder 63 to rotate relative to the first tail plate 61. The second tail rudder 64 is connected to the other motor so that the motor can drive the second tail rudder 64 to rotate relative to the second tail plate 62.

[0051] In some embodiments, see Figure 5 and Figure 7 , the first wing rod 42 has a first circuit board 421, the first circuit board 421 is connected to the first drive module 2, and the first circuit board 421 is used to control the operation of the first drive module 2, including but not limited to adjusting the speed of the first propeller motor 22 and switching the first propeller motor 22 between a horizontal state and a vertical state. The first circuit board 421 has electronic devices that are easy to heat up, such as capacitors, Moss tubes, etc. In order to ensure the normal operation of the first circuit board 421, it is necessary to set a relevant heat dissipation structure for the first circuit board 421. In the present application, the wing module 4 also includes a first heat sink 46, the first heat sink 46 is connected to the first circuit board 421, so that the heat in the first circuit board 421 can be conducted to the first heat sink 46, the first heat sink 46 is installed on the first wing rod 42, and the first heat sink 46 is at least partially exposed to the outside world. When the drone 100 is flying, an airflow can be generated on the surface of the first heat sink 46 exposed to the outside world, so that the first heat sink 46 can conduct heat to the outside air, realize heat dissipation of the first circuit board 421, thereby reducing the risk of failure of the first circuit board 421.

[0052] For the first heat sink 46 mentioned above, please refer to Figure 5 and Figure 7 The first heat sink 46 is mounted on the surface of the first wing bar 42 facing the second wing bar 43, and the surface of the first heat sink 46 exposed to the outside is provided with a first groove 461, and the opening of the first groove 461 faces the outside of the first wing bar 42, that is, the opening of the first groove 461 faces the second wing bar 43. In this embodiment, by providing the first groove 461, the area of ​​the first heat sink 46 in contact with the outside can be increased, which is conducive to improving the heat dissipation efficiency of the first heat sink 46.

[0053] In some embodiments, see Figure 5 The first heat sink 46 is installed at a position of the first wing rod 42 close to the first propeller motor 22 so that the airflow generated by the first propeller motor 22 during operation can blow to the surface of the first heat sink 46, thereby accelerating the heat dissipation speed of the first heat sink 46.

[0054] In some embodiments, see Fig. 9, the second wing rod 43 has a second circuit board 431, the second circuit board 431 is connected to the second drive module 3, and the second circuit board 431 is used to control the operation of the second drive module 3, including but not limited to adjusting the speed of the second propeller motor 32 and switching the second propeller motor 32 between a horizontal state and a vertical state. The second circuit board 431 has electronic devices that are easy to heat up, such as capacitors, Moss tubes, etc. In order to ensure the normal operation of the second circuit board 431, it is also necessary to set a relevant heat dissipation structure for the second circuit board 431. In the present application, the wing module 4 also includes a second heat sink 47, which is connected to the second circuit board 431 so that the heat in the second circuit board 431 can be conducted to the second heat sink 47, the second heat sink 47 is installed on the second wing rod 43, and the second heat sink 47 is at least partially exposed to the outside world. When the drone 100 is flying, an airflow can be generated on the surface of the second heat sink 47 exposed to the outside world, so that the second heat sink 47 can conduct heat to the outside air, thereby achieving heat dissipation of the second circuit board 431, thereby reducing the risk of failure of the second circuit board 431.

[0055] In some embodiments, see Fig. 9 The second heat dissipation component is provided with a second groove 471, and the opening of the second groove 471 faces outside the second wing rod 43, so that the contact area between the second heat dissipation component and the external air can be increased, which is beneficial to improving the heat dissipation efficiency of the second heat dissipation component.

[0056] In some embodiments, see Fig. 9 The second heat sink 47 is installed at a position of the second wing rod 43 close to the second propeller motor 32 so that the airflow generated by the second propeller motor 32 during operation can blow to the surface of the second heat sink 47, thereby accelerating the heat dissipation speed of the second heat sink 47.

[0057] For the above mentioned lifting module 5, see Figure 4The lifting module 5 includes a third propeller motor 51 and a fourth propeller motor 52. The third propeller motor 51 and the fourth propeller motor 52 are both installed on the fuselage 1, and the third propeller motor 51 is located near the head 11 of the fuselage 1, and the fourth propeller motor 52 is located near the tail 12 of the fuselage 1. The third propeller motor 51 and the fourth propeller motor 52 are both used to provide lifting power for the drone 100. When the drone 100 needs to be lifted, the third propeller motor 51 and the fourth propeller motor 52 can be started, and the first propeller motor 22 and the second propeller motor 32 can be adjusted to a vertical state, so that the first propeller motor 22, the second propeller motor 32, the third propeller motor 51 and the fourth propeller motor 52 can all provide lifting power for the drone 100, which can increase the load capacity of the drone 100, and there is no need to set up additional propeller motors for lifting.

[0058] In an embodiment of the utility model, the lifting module 5 and the wing module 4 are both installed on the fuselage 1, the first switching motor 21 is installed on the wing module 4, the first propeller motor 22 is connected to the first switching motor 21, so that the first switching motor 21 can drive the first propeller motor 22 to switch between a horizontal state and a vertical state, and the second switching motor 31 is installed on the wing module 4, the second motor and the first motor are respectively located on both sides of the fuselage 1, and the second motor is connected to the first switching motor 21, so that the second switching motor 31 can drive the second propeller motor 32 to switch between a horizontal state and a vertical state. When the first propeller motor 22 and the second propeller motor 32 are in a horizontal state, the first propeller motor 22 and the second propeller motor 32 can provide the drone 100 with forward power, and when the first propeller motor 22 and the second propeller motor 32 are in a vertical state, the first propeller motor 22, the second propeller motor 32 and the lifting module 5 can all provide the drone 100 with lifting power, and the lifting power of the drone 100 can be increased without increasing the number of propeller motors.

[0059] The above description is only an embodiment of the present invention, and does not limit the patent scope of the present invention. Any equivalent structure or equivalent process transformation made by using the contents of the specification and drawings of the present invention, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present invention.

Claims

1. A drone, characterized in that: include: body; Wing modules, mounted on the fuselage; A lifting module is installed on the fuselage; A first driving module, comprising a first switching motor and a first propeller motor, wherein the first switching motor is mounted on the wing module, the first propeller motor is connected to the first switching motor, and the first switching motor is used to drive the first propeller motor to swing between a horizontal state and a vertical state; A second driving module comprises a second switching motor and a second propeller motor, wherein the second switching motor is installed on the wing module, the first switching motor and the second switching motor are respectively located on both sides of the fuselage, the second propeller motor is connected to the second switching motor, and the second switching motor is used to drive the second propeller motor to swing between a horizontal state and a vertical state; Among them, when the first propeller motor and the second propeller motor are in a horizontal state, the first propeller motor and the second propeller motor can provide the drone with forward power; when the first propeller motor and the second propeller motor are in a vertical state, the first propeller motor and the second propeller motor can provide the drone with lifting power.

2. The drone according to claim 1, characterized in that: The drone also includes a tail module, which includes a first tail panel, a second tail panel, a first tail rudder and a second tail rudder. The first tail panel and the second tail panel are both connected to the tail of the fuselage. The first tail rudder is rotatably arranged on the first tail panel, and the second tail rudder is rotatably arranged on the second tail panel.

3. The drone according to claim 1, characterized in that: The first driving module further includes a first mounting seat, the first mounting seat is connected to the first switching motor, and the first propeller motor is mounted on an end of the first mounting seat away from the first switching motor.

4. The drone according to claim 1, characterized in that: The second driving module also includes a second mounting seat, the second mounting seat is connected to the second switching motor, and the second propeller motor is installed at an end of the second mounting seat away from the second switching motor.

5. The drone according to claim 1, characterized in that: The wing module includes a wing body, a first wing rod and a second wing rod, the wing body is installed on the fuselage, the first wing rod and the second wing rod are both installed on the wing body, the first wing rod and the second wing rod are respectively located on both sides of the fuselage, the first switching motor is installed at one end of the first wing rod, and the second switching motor is installed at one end of the second wing rod.

6. The drone according to claim 5, characterized in that: The wing module further includes a first yaw plate and a second yaw plate, wherein the first yaw plate and the second yaw plate are both rotatably disposed on the wing body, and the first yaw plate and the second yaw plate are respectively located on both sides of the fuselage.

7. The drone according to claim 5, characterized in that: A first circuit board electrically connected to the first drive module is provided in the first wing rod; The wing module further includes a first heat dissipation plate, which is connected to the first circuit board, mounted on the first wing rod, and at least part of the first heat dissipation plate is exposed to the outside.

8. The drone according to claim 7, characterized in that: A plurality of first grooves are arranged on the surface of the first heat dissipation plate exposed to the outside.

9. The drone according to claim 5, characterized in that: A second circuit board electrically connected to the second drive module is provided in the second wing rod; The wing module further includes a second heat dissipation plate, which is connected to the second circuit board, mounted on the second wing rod, and at least part of the second heat dissipation plate is exposed to the outside.

10. The drone according to any one of claims 1 to 9, characterized in that: The lifting module includes a third propeller motor and a fourth propeller motor, and the third propeller motor and the fourth propeller motor are both installed on the fuselage. The third propeller motor and the fourth propeller motor can provide lifting power for the drone.

Images