An unmanned aerial vehicle

Abstract

The present invention relates to the field of aircraft, and provides an unmanned aerial vehicle including: a fuselage, an arm assembly, a power assembly and a first camera assembly. The arm assembly is installed on the fuselage; the power assembly is installed on the arm assembly to provide flight power for the unmanned aerial vehicle; at least two of the first camera assemblies are respectively installed on the arm assemblies, and at least one of the first camera assemblies is arranged on opposite sides of the fuselage. When the unmanned aerial vehicle of the present invention is flying, at least two of the first camera assemblies located on opposite sides of the fuselage can jointly complete 360-degree panoramic shooting, ensuring that 360-degree panoramic images are obtained at the same time. At least two of the first camera assemblies are installed on the arm assembly, so that the viewing angle is wide and will not be blocked by the fuselage or airborne equipment, and panoramic shooting without blind spots can be achieved.

Description

[Technical field]

[0001] The present invention relates to the field of aircraft, and in particular to an unmanned aircraft with a shooting function. [Background technology]

[0002] Unmanned aerial vehicles (UAVs) are a new type of equipment that is developing rapidly. They are flexible, quick to respond, unmanned, and require low operation. UAVs can achieve real-time image transmission and high-risk area detection by carrying multiple types of sensors or camera equipment, and are a powerful supplement to satellite remote sensing and traditional aerial remote sensing.

[0003] In current unmanned aerial vehicles, the commonly used camera components for achieving panoramic photography have a narrow viewing angle and are easily blocked by the fuselage or other onboard equipment, and cannot fully meet usage requirements. [Summary of the invention]

[0004] In order to solve the above technical problems, an embodiment of the present invention provides an unmanned aerial vehicle that can achieve panoramic shooting and has a wide shooting angle.

[0005] The embodiment of the present invention solves the technical problem by adopting the following technical solution:

[0006] An unmanned aerial vehicle comprises: a fuselage, an arm assembly, a power assembly and a first camera assembly. The arm assembly is mounted on the fuselage; the power assembly is mounted on the arm assembly to provide flight power for the unmanned aerial vehicle; at least two first camera assemblies are mounted on the arm assemblies respectively, and at least one first camera assembly is disposed on each of the two opposite sides of the fuselage.

[0007] Optionally, each of the first camera assemblies includes a first camera device, and the first camera device includes at least one lens.

[0008] Optionally, the first camera assembly includes a mounting rod and a first pan-tilt head, one end of the mounting rod is mounted on the arm assembly, the other end of the mounting rod is detachably mounted on the first pan-tilt head, and the first camera device is mounted on the first pan-tilt head.

[0009] Optionally, the first gimbal is a three-axis stabilization gimbal, comprising a first motor, a second motor and a third motor;

[0010] The stator of the third motor is detachably mounted on one end of the mounting rod away from the arm assembly, the rotor of the third motor is connected to the stator of the second motor, and the rotor of the second motor is connected to the stator of the first motor, and the first camera device is fixedly mounted on the rotor of the first motor.

[0011] Optionally, the mounting rod is a length-adjustable structure.

[0012] Optionally, the above-mentioned unmanned aerial vehicle includes at least one second camera assembly, and the second camera assembly is installed on the fuselage; when the unmanned aerial vehicle is in a flying posture, the second camera assembly is located on the lower side of the fuselage.

[0013] Optionally, each of the second camera assemblies includes a second pan-tilt head and a second camera device, the second pan-tilt head is fixedly mounted on the fuselage, and the second camera device is mounted on the second pan-tilt head.

[0014] Optionally, the arm assembly includes a drive assembly and an arm;

[0015] One ends of the two arms are hinged to each other, and the two arms are respectively located on opposite sides of the fuselage;

[0016] The driving assembly is mounted on the fuselage and connected to the two arms for driving the two arms so as to increase or decrease the angle between the two arms.

[0017] Optionally, the driving assembly comprises: a driving device, a movable part and a driving part;

[0018] The driving device is fixedly mounted on the body and is used to drive the movable part to perform reciprocating linear motion;

[0019] There are two driving members, one end of one of the driving members is hinged to one end of the movable member, one end of the other driving member is hinged to the other end of the movable member, and one end of each driving member away from the movable member is hinged to a corresponding machine arm.

[0020] Optionally, the drive assembly includes a screw;

[0021] The driving device is connected to the screw rod and is used to drive the screw rod to rotate;

[0022] The movable part is sleeved on the screw rod and can perform reciprocating linear motion along the axis of the screw rod as the screw rod rotates.

[0023] Optionally, each of the driving members comprises a main body, a first connecting portion and a second connecting portion;

[0024] Two first connection parts extend from one side of the main body, the ends of the two first connection parts are spaced apart, and the ends of the two first connection parts are hinged to a corresponding machine arm;

[0025] The two second connection parts extend from the other side of the main body, the ends of the two second connection parts are arranged at intervals, the ends of the two second connection parts are located on both sides of the movable part, and are hinged to one end of the movable part.

[0026] Optionally, each of the machine arms comprises an arm body and a mounting seat;

[0027] One end of the arm is fixed to the mounting seat;

[0028] The two mounting seats are hinged to each other, and one end of each driving member away from the movable member is hinged to a corresponding mounting seat.

[0029] Optionally, the mounting seat includes a tube body portion and a hinge portion;

[0030] One end of the arm body is inserted into and fixed to the tube body;

[0031] The two hinged parts extend from one end of the tube body, and the ends of the two hinged parts are arranged at intervals, wherein the ends of the two hinged parts of one mounting seat are alternately overlapped with the ends of the two hinged parts of the other mounting seat, and the ends of the hinged parts of the two mounting seats are hinged to each other.

[0032] Optionally, the arm assembly comprises a mounting arm, and a middle portion of each mounting arm is connected to an end of a corresponding arm away from the fuselage;

[0033] Each camera assembly is mounted on the middle portion of a corresponding mounting arm.

[0034] Optionally, the arm assembly includes a fixing rod, the fixing rod includes a rod body and a connecting member, one end of the rod body is hinged to the fuselage, the other end of the rod body is hinged to one end of the connecting member, and the other end of the connecting member is hinged to a corresponding mounting arm.

[0035] Optionally, the above-mentioned unmanned aerial vehicle includes a landing gear assembly, and the landing gear assembly includes a landing rod and a support rod;

[0036] One end of the landing rod is fixedly mounted on the mounting arm, and an acute angle is formed between the landing rod and the mounting arm;

[0037] One end of the support rod is fixedly mounted on the mounting arm, and the other end of the support rod is fixedly mounted on the landing rod and is spaced a preset distance from the end of the landing rod.

[0038] Compared with the prior art, when the unmanned aerial vehicle of the embodiment of the present invention is flying, at least two of the first camera assemblies located on opposite sides of the fuselage can jointly complete 360-degree panoramic shooting, ensuring that 360-degree panoramic images are obtained at the same time, thereby satisfying the 3D stereoscopic experience in virtual reality. At least two of the first camera assemblies are installed on the arm assembly, so that their viewing angles are wide and will not be blocked by the fuselage, and panoramic shooting without blind spots can be achieved.

Brief Description of the Drawings

[0039] One or more embodiments are exemplarily described by corresponding drawings, which do not constitute limitations on the embodiments. Elements with the same reference numerals in the drawings represent similar elements, and the figures in the drawings do not constitute proportional limitations unless otherwise stated.

[0040] Figure 1 A three-dimensional diagram of an unmanned aerial vehicle provided by one embodiment of the present invention;

[0041] Figure 2 for Figure 1 A front view of the UAV shown;

[0042] Figure 3 for Figure 1 A perspective view of a fuselage and an arm assembly of the unmanned aerial vehicle, wherein a portion of the fuselage is omitted;

[0043] Figure 4 for Figure 3 A side view of the fuselage and arm assembly is shown;

[0044] Figure 5 for Figure 4 Sectional view along line AA;

[0045] Figure 6 for Figure 3 Exploded view of the fuselage and arm assembly shown. [Specific implementation method]

[0046] For ease of understanding of the present invention, the present invention 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 terms "vertical", "horizontal", "left", "right", "inside", "outside" and similar expressions used in this specification are for illustrative purposes only.

[0047] 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 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 intended to limit the present invention. The term "and / or" used in this specification includes any and all combinations of one or more of the related listed items.

[0048] In addition, the technical features involved in different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0049] See also Figure 1 and Figure 2 One embodiment of the present invention provides an unmanned aerial vehicle 100, comprising a fuselage 10, an arm assembly 20, a power assembly 30, a first camera assembly 40, a second camera assembly 50 and a landing gear assembly 60. The arm assembly 20 is mounted on the fuselage 10, the power assembly 30 is mounted on the arm assembly 20, and is used to provide flight power for the unmanned aerial vehicle 100, two first camera assemblies 40 are respectively mounted on the arm assembly 20 and are located on opposite sides of the fuselage 10, the second camera assembly 50 is mounted on the fuselage 10, and the landing gear assembly 60 is mounted on the arm assembly 20.

[0050] The fuselage 10 includes a control circuit assembly composed of electronic components such as an MCU, and the control circuit assembly includes multiple control modules, such as a control module for controlling the folding or lowering of the arm assembly 20, a flight control module for controlling the flight attitude of the unmanned aerial vehicle 100, a positioning module for navigating the unmanned aerial vehicle 100, and a data processing module for processing environmental information obtained by related onboard equipment.

[0051] Please also read Figures 3 to 5 The body 10 defines a receiving slot 102 for partially receiving the arm assembly 20 .

[0052] The arm assembly 20 includes a driving assembly 210, an arm 220, a fixing rod 230 and a mounting arm 240. The driving assembly 210 is disposed in the receiving slot 102 of the fuselage 10, and the driving assembly 210 is connected to the arm 220, providing power to the arm 220, and driving the arm 220 to be folded or lowered. The arm 220 is connected to the mounting arm 240, and the mounting arm 240 is used to install the power assembly 30, the first camera assembly 40 and the landing gear assembly 60. The two ends of the fixing rod 230 are respectively hinged to the fuselage 10 and the mounting arm 240, and are used to apply a pulling force toward the fuselage 10 to the arm 220 and the mounting arm 240, so that the arm 220 can be stably folded or lowered.

[0053] The driving assembly 210 is installed on the fuselage 10. The driving assembly 210 includes: a driving device 212, a screw rod 214, a movable part 216 and a driving member 218. The driving device 212 is fixedly installed on the fuselage 10, and is connected to the screw rod 214, and is used to drive the screw rod 214 to rotate. One end of the screw rod 214 is fixedly connected to the rotating shaft of the driving device 212, and the other end is rotatably connected to the fuselage 10. The movable part 216 is sleeved on the screw rod 214, and can make reciprocating linear motion along the axis of the screw rod 214 as the screw rod 214 rotates. There are two driving members 218, one end of which is hinged to one end of the movable part 216, and one end of the other driving member 218 is hinged to the other end of the movable part 216.

[0054] In this embodiment, the driving device 212 includes a motor for driving the screw rod 214 to rotate, so that the movable member 216 performs reciprocating linear motion along the axis of the screw rod 214 as the screw rod 214 rotates.

[0055] It is understandable that in some other embodiments, the screw rod 214 may be omitted, the driving device 212 may be a pneumatic cylinder or a hydraulic cylinder, and the driving device 212 is connected to the movable member 216 to drive the movable member 216 to perform reciprocating linear motion.

[0056] There are two arms 220, and an angle is formed between the two arms 220. The two arms 220 are respectively located on opposite sides of the fuselage 10. Each arm 220 includes an arm body 222 and a mounting seat 224, and one end of the arm body 222 is inserted into and fixed to the mounting seat 224. The two mounting seats 224 are hinged to each other, and one end of each driving member 218 away from the movable member 216 is hinged to a corresponding mounting seat 224. When the driving device 212 is working, the driving device 212 drives the screw rod 214 to rotate, driving the movable member 216 to perform reciprocating linear motion along the axis of the screw rod 214. Under the drive of the movable member 216, the driving member 218 drives the two arms 220 to be folded or lowered, so that the angle between the two arms 220 is reduced or increased.

[0057] See also Figure 6Each of the driving members 218 includes a main body 2180, a first connecting portion 2182, and a second connecting portion 2184. The first connecting portion 2182 is rod-shaped, and two first connecting portions 2182 extend from one side of the main body 2180, and the ends of the two first connecting portions 2182 are spaced apart. Similarly, the second connecting portion 2184 is also rod-shaped, and two second connecting portions 2184 extend from the other side of the main body 2180, and the ends of the two second connecting portions 2184 are spaced apart. The ends of the two second connecting portions 2184 are located on both sides of the movable member 216 and are hinged to one end of the movable member 216.

[0058] The mounting seat 224 includes a tube body 2242, a pin 2244 and a hinged portion 2246. The tube body 2242 is provided with a mounting hole (not shown), and one end of the arm body 222 is inserted and fixed in the mounting hole. There are two pins 2244, and the two pins 2244 are respectively fixedly mounted on opposite sides of the tube body 2242, and each pin 2244 is hinged to the end of a corresponding first connecting portion 2182, so that the driving member 218 is hinged to the mounting seat 224. The hinged portion 2246 is roughly triangular plate-shaped, and there are two hinged portions 2246, which extend from one end of the tube body 2242, and the ends of the two hinged portions 2246 are spaced apart. The ends of the two hinged portions 2246 of one of the mounting seats 224 are alternately overlapped with the ends of the two hinged portions 2246 of the other mounting seat 224 , and the ends of the hinged portions 2246 of the two mounting seats 224 are hinged to each other.

[0059] The fixing rod 230 includes a rod body 232 and a connecting member 234, one end of the rod body 232 is hinged to the fuselage 10, the other end of the rod body 232 is hinged to one end of the connecting member 234, and the other end of the connecting member 234 is hinged to the mounting arm 240. When the unmanned aerial vehicle 100 is in a flying state, the power assembly 30 provides an upward pulling force to the end of the arm 220 away from the fuselage 10 and the mounting arm 240, and the fixing rod 230 provides a pulling force toward the fuselage 10 to the arm 220 and the mounting arm 240 to prevent the arm 220 from further rotating relative to the fuselage 10, so that the arm 220 is in a stable state.

[0060] There are two mounting arms 240, each of which is a substantially straight rod, and the middle portion of which is connected to the end of the arm 220 away from the fuselage 10. The two mounting arms 240 are arranged parallel to each other on opposite sides of the fuselage 10. It can be understood that in some other embodiments, the shape and arrangement of the mounting arms 240 can be changed according to actual needs, for example, the mounting arms 240 can be bent rods, etc.

[0061] Please refer to Figure 1 and Figure 2 The power assembly 30 includes a motor and a propeller mounted on the motor, and is used to provide flight power for the unmanned aerial vehicle 100. There are four power assemblies 30, and every two power assemblies 30 are mounted at opposite ends of a corresponding mounting arm 240.

[0062] It can be understood that, in some other embodiments, the number of the power assemblies 30 can be increased or decreased according to the situation, for example, reduced to 1 or 2 or increased to 6 or 8, etc. For example, when the number of the power assemblies 30 is two, the mounting arm 240 can be omitted, and each of the power assemblies 30 can be fixedly installed on one end of the arm 220 away from the fuselage 10; for example, when the number of the power assemblies 30 is 6 or 8, the number of the arms 220 and the mounting arms 240 can be increased accordingly.

[0063] There are two first camera assemblies 40, each of which includes a mounting rod 42, a first gimbal 44, and a first camera device 46. One end of the mounting rod 42 is fixedly mounted on the middle of the mounting arm 240, and the other end of the mounting rod 42 is detachably mounted on the first gimbal 44. The mounting rod 42 is a length-adjustable structure, for example, a telescopic structure, to adapt to UAVs 100 of different sizes.

[0064] The first gimbal 44 is a three-axis stabilization gimbal, which stabilizes the first camera device 46 in flight on three axes: yaw, pitch, and roll. The pitch axis is perpendicular to the roll axis, and the yaw axis is perpendicular to the pitch axis and the roll axis.

[0065] The first gimbal 44 includes: a first motor, a second motor and a third motor. The central axis of the rotor of the first motor is coaxial with the roll axis. The central axis of the rotor of the second motor is coaxial with the pitch axis, and the central axis of the rotor of the third motor is coaxial with the yaw axis. The stator of the third motor is detachably mounted on the end of the mounting rod 42 away from the mounting arm 240 through a fixing seat, and the rotor of the third motor is connected to the stator of the second motor, and the rotor of the second motor is connected to the stator of the first motor.

[0066] It can be understood that in some other embodiments, the third motor can be omitted, and the stator of the second motor can be detachably mounted on the other end of the mounting rod 42 through a fixing seat.

[0067] The first camera device 46 is fixedly mounted on the rotor of the first motor of the first pan / tilt head 44. The first camera device 46 may be a camera, a video camera, a camera head, etc., and may include at least one lens. For example, each of the first camera devices 46 includes two lenses disposed in opposite directions. The two first camera devices 46 are located in the same plane.

[0068] It is understandable that the number of the first camera assembly 40 can be at least two, and panoramic shooting can be achieved as long as at least one camera assembly 40 is disposed on each of the two opposite sides of the fuselage 10. The first camera devices 46 of at least two of the first camera assemblies 40 are located in the same plane.

[0069] It can be understood that, in some other embodiments, the first gimbal 44 may also be a single-axis gimbal; or, the first gimbal 44 is omitted, and the first camera device 46 is directly mounted on the mounting rod 42 .

[0070] The second camera assembly 50 includes a second gimbal 54 and a second camera device 56. The second gimbal 54 is mounted on the fuselage 10, and the second camera device 56 is mounted on the second gimbal 54. When the UAV 100 is flying, the second camera assembly 50 is located at the lower side of the fuselage 10.

[0071] The second gimbal 54 is a three-axis stabilization gimbal, which stabilizes the second camera device 56 in flight on three axes: yaw, pitch, and roll. The pitch axis is perpendicular to the roll axis, and the yaw axis is perpendicular to the pitch axis and the roll axis.

[0072] The second gimbal 54 includes: a first motor, a second motor and a third motor. The central axis of the rotor of the first motor is coaxial with the roll axis. The central axis of the rotor of the second motor is coaxial with the pitch axis, and the central axis of the rotor of the third motor is coaxial with the yaw axis. The stator of the third motor is mounted on the fuselage 10 through a fixing seat, the rotor of the third motor is connected to the stator of the second motor, and the rotor of the second motor is connected to the stator of the first motor. It can be understood that in some other embodiments, the third motor can be omitted, and the stator of the second motor is mounted on the fuselage 10 through a fixing seat.

[0073] The second camera device 56 is fixedly mounted on the rotor of the first motor of the second pan / tilt head 54. The second camera device 56 can be a camera, a video camera, a camera head, etc., and can include at least one lens, for example, each of the second camera devices 56 includes two back-to-back lenses.

[0074] It is understandable that the number of the second camera components 50 is not limited to one, and can be increased accordingly according to actual needs, for example, increased to 2 or 4, and 2 or 4 second camera components 50 are installed on the body 10.

[0075] It can be understood that, in some other embodiments, the second gimbal 54 may also be a single-axis gimbal; or, the second gimbal 54 is omitted, and the second camera device 56 is directly mounted on the body 10.

[0076] Please refer to Figures 3 to 5 The landing gear assembly 60 includes a landing rod 602 and a support rod 604. One end of the landing rod 602 is fixedly mounted on one end of the mounting arm 240, and an acute angle is formed between the landing rod 602 and the mounting arm 240. One end of the support rod 604 is fixedly mounted on the mounting arm 240, and the other end of the support rod 604 is fixedly mounted on the landing rod 602 and is separated from the end of the landing rod 602 by a preset distance. The support rod 604, part of the landing rod 602 and part of the mounting arm 240 form a triangle. When the unmanned aerial vehicle 100 lands, the landing gear assembly 60 can stably support the unmanned aerial vehicle 100.

[0077] It can be understood that, in some other embodiments, the landing gear assembly 60 may further include a driving device, which may be a cylinder or a hydraulic cylinder, which is mounted on the mounting arm 240, one end of the support rod 604 is mounted on the driving device, and the other end is mounted on the landing rod 602, and one end of the landing rod 602 is hinged to the mounting arm 240. When in use, the driving device can drive the support rod 604 to move linearly along the axis of its driving rod, thereby driving the landing rod 602 to rotate relative to the mounting arm 240, so that the landing rod 602 can be lowered or retracted.

[0078] When the unmanned aerial vehicle 100 is flying, the two first camera assemblies 40 located on opposite sides of the fuselage 10 can jointly complete 360-degree panoramic shooting, ensuring that 360-degree panoramic images are obtained at the same time, thereby satisfying the 3D stereoscopic experience in virtual reality. The two first camera assemblies 40 are installed on the arm assembly 20, and their viewing angles are wide, and will not be blocked by the fuselage 10 or the equipment carried, and can achieve panoramic shooting without blind spots.

[0079] In addition, the mounting rod 42 is a length-adjustable structure, and can be adapted to the UAVs 100 of different sizes.

[0080] Moreover, the driving component 210 can drive the two arms 220 to increase or decrease the angle between the two arms 220, thereby adjusting the distance between the two first camera components 40 to meet different shooting requirements.

[0081] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them. Under the concept of the present invention, the technical features in the above embodiments or different embodiments may also be combined, the steps may be implemented in any order, and there are many other changes in different aspects of the present invention as described above, which are not provided in detail for the sake of simplicity. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they may still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. An unmanned aerial vehicle (100), characterized in that: include: Body (10); An arm assembly (20), the arm assembly (20) being mounted on the fuselage (10); a power assembly (30), the power assembly (30) being mounted on the arm assembly (20) and being used to provide flight power for the unmanned aerial vehicle (100); a first camera assembly (40), at least two of the first camera assemblies (40) being respectively mounted on the arm assembly (20), and at least one of the first camera assemblies (40) being disposed on opposite sides of the body (10); at least one second camera assembly (50), the second camera assembly (50) being mounted on the fuselage (10); when the unmanned aerial vehicle (100) is in a flying posture, the second camera assembly (50) is located at the lower side of the fuselage (10); The machine arm assembly (20) comprises a driving assembly (210) and a machine arm (220); One ends of the two machine arms (220) are hinged to each other, and the two machine arms (220) are respectively located on opposite sides of the fuselage (10); The driving assembly (210) is installed on the fuselage (10), and the driving assembly (210) is connected to the two machine arms (220) and is used to drive the two machine arms (220) so that the angle between the two machine arms (220) increases or decreases; The driving assembly (210) comprises: a driving device (212), a movable part (216) and a driving part (218); The driving device (212) is fixedly mounted on the body (10) and is used to drive the movable part (216) to perform reciprocating linear motion; There are two driving members (218), one end of one of the driving members (218) is hinged to one end of the movable member (216), and one end of the other driving member (218) is hinged to the other end of the movable member (216), and one end of each driving member (218) away from the movable member (216) is hinged to a corresponding machine arm (220).

2. The unmanned aerial vehicle (100) according to claim 1, characterized in that: Each of the first camera assemblies (40) comprises a first camera device (46), and the first camera device (46) comprises at least one lens.

3. The unmanned aerial vehicle (100) according to claim 2, characterized in that: The first camera assembly (40) comprises a mounting rod (42) and a first pan-tilt head (44); one end of the mounting rod (42) is mounted on the machine arm assembly (20); the other end of the mounting rod (42) is detachably mounted on the first pan-tilt head (44); and the first camera device (46) is mounted on the first pan-tilt head (44).

4. The unmanned aerial vehicle (100) according to claim 3, characterized in that: The first gimbal (44) is a three-axis stabilization gimbal, comprising a first motor, a second motor and a third motor; The stator of the third motor is detachably mounted on one end of the mounting rod (42) away from the arm assembly (20); the rotor of the third motor is connected to the stator of the second motor, and the rotor of the second motor is connected to the stator of the first motor; the first camera device (46) is fixedly mounted on the rotor of the first motor.

5. The unmanned aerial vehicle (100) according to claim 3 or 4, characterized in that: The mounting rod (42) is a length-adjustable structure.

6. The unmanned aerial vehicle (100) according to claim 1, characterized in that: Each of the second camera assemblies (50) comprises a second pan-tilt platform (54) and a second camera device (56); the second pan-tilt platform (54) is mounted on the fuselage (10); and the second camera device (56) is mounted on the second pan-tilt platform (54).

7. The unmanned aerial vehicle (100) according to any one of claims 1 to 4, characterized in that: The drive assembly (210) includes a screw (214); The driving device (212) is connected to the screw rod (214) and is used to drive the screw rod (214) to rotate; The movable member (216) is sleeved on the screw rod (214) and can perform reciprocating linear motion along the axis of the screw rod (214) as the screw rod (214) rotates.

8. The unmanned aerial vehicle (100) according to claim 7, characterized in that: Each of the driving members (218) includes a main body (2180), a first connecting portion (2182) and a second connecting portion (2184); Two first connection parts (2182) extend from one side of the main body (2180), the ends of the two first connection parts (2182) are arranged at intervals, and the ends of the two first connection parts (2182) are hinged to a corresponding machine arm (220); The two second connection parts (2184) extend from the other side of the main body (2180), and the ends of the two second connection parts (2184) are spaced apart. The ends of the two second connection parts (2184) are located on both sides of the movable part (216) and are hinged to one end of the movable part (216).

9. The unmanned aerial vehicle (100) according to any one of claims 1 to 4, characterized in that: Each of the machine arms (220) comprises an arm body (222) and a mounting seat (224); One end of the arm body (222) is fixed to the mounting seat (224); The two mounting seats (224) are hinged to each other, and one end of each driving member (218) away from the movable member (216) is hinged to a corresponding mounting seat (224).

10. The unmanned aerial vehicle (100) according to claim 9, characterized in that: The mounting seat (224) comprises a tubular body portion (2242) and a hinge portion (2246); One end of the arm body (222) is inserted into and fixed to the tube body (2242); The two hinged portions (2246) extend from one end of the tube body portion (2242), and the ends of the two hinged portions (2246) are spaced apart, wherein the ends of the two hinged portions (2246) of one mounting seat (224) and the ends of the two hinged portions (2246) of the other mounting seat (224) are alternately overlapped, and the ends of the hinged portions (2246) of the two mounting seats (224) are hinged to each other.

11. The unmanned aerial vehicle (100) according to any one of claims 1 to 4, characterized in that: The arm assembly (20) comprises a mounting arm (240), wherein the middle portion of each mounting arm (240) is connected to an end of a corresponding arm (220) away from the fuselage (10); One of the camera assemblies (40) is mounted on the middle portion of a corresponding mounting arm (240).

12. The unmanned aerial vehicle (100) according to claim 11, characterized in that: The arm assembly (20) includes a fixing rod (230), and the fixing rod (230) includes a rod body (232) and a connecting member (234). One end of the rod body (232) is hinged to the fuselage (10), and the other end of the rod body (232) is hinged to one end of the connecting member (234), and the other end of the connecting member (234) is hinged to a corresponding mounting arm (240).

13. The unmanned aerial vehicle (100) according to claim 11, characterized in that: The invention comprises a landing gear assembly (60), wherein the landing gear assembly (60) comprises a landing rod (602) and a support rod (604); One end of the landing rod (602) is fixedly mounted on the mounting arm (240), and an acute angle is formed between the landing rod (602) and the mounting arm (240); One end of the support rod (604) is fixedly mounted on the mounting arm (240), and the other end of the support rod (604) is fixedly mounted on the landing rod (602) and is spaced a preset distance from the end of the landing rod (602).

Images