Unmanned aerial vehicle, remote controller and unmanned aerial vehicle

Abstract

The utility model provides an unmanned aerial vehicle and an unmanned aerial vehicle. The rotating structure is rotatably connected to the fuselage, so that the rotating structure is selectively in a folded state or an unfolded state relative to the fuselage; wherein when the rotating structure is in the folded state, the rotating structure forms a first accommodating space of at least one part of the machine body, and / or, the rotating structure and the machine body form a second accommodating space of the remote controller.

Description

TECHNICAL FIELD

[0001] At least one embodiment of the utility model relates to unmanned plane technical field, especially a kind of unmanned plane, remote controller and unmanned aerial vehicle. BACKGROUND

[0002] When unmanned plane is transported and is stored, it can occupy smaller space, effectively improves the portability of transportation, use and storage.

[0003] The folding mode of unmanned plane is various, to reduce the space occupied when folding and storing. However, when unmanned plane is in folding state, the space between parts is not utilized, causing space waste, and the space utilization rate is poor. UTILITY MODEL CONTENT

[0004] To solve the above and other aspects at least one technical problem in the prior art, the utility model provides a kind of unmanned plane and unmanned aerial vehicle, reduce space waste, improve the space utilization rate of unmanned plane.

[0005] The first aspect of the utility model provides a kind of unmanned plane, comprising: fuselage;Rotary structure, rotatably connected to the fuselage, so that the rotary structure selectively in folding state or unfolded state relative to the fuselage;Wherein, when the rotary structure is in the folding state, the rotary structure forms the first accommodating space for accommodating at least a part of the fuselage, and / or, the rotary structure and the fuselage form the second accommodating space for accommodating remote controller.

[0006] The second aspect of the utility model provides a kind of remote controller, the remote controller is used to be connected with the above-mentioned unmanned plane and output control signal control the unmanned plane moves;When the unmanned plane is in folding state, the remote controller is accommodated in the second accommodating space of the unmanned plane.

[0007] The third aspect of the utility model provides a kind of unmanned aerial vehicle, comprising: external device;And as described above unmanned plane, the external device cooperates with the bottom of the fuselage, to be stored in the second accommodating space.

[0008] According to the technical scheme provided by the illustrative embodiment of the utility model, the rotary structure can be rotated relative to the fuselage to the unfolded state or the folding state, and when the rotary structure is in the folding state, the rotary structure forms the first accommodating space for accommodating at least a part of the fuselage, for example, the first accommodating space can accommodate the side protruding part of the fuselage. The rotary structure and the fuselage form the second accommodating space for accommodating remote controller. By fully utilizing the first accommodating space and the second accommodating space formed by the fuselage and the rotary structure, at least a part of the fuselage or remote controller and other components can be accommodated, which can reduce space waste and improve the space utilization rate of unmanned plane.

[0009] Additional aspects and advantages of the present utility model will be partially given in the following description, and some will become obvious from the following description. BRIEF DESCRIPTION OF DRAWINGS

[0010] Figure 1 is a use state diagram of a UAV in an unfolded state according to a schematic embodiment of the present utility model;

[0011] Figure 2 is a side view of a UAV in an unfolded state according to a schematic embodiment of the present utility model;

[0012] Figure 3 is a use state diagram of a UAV in a folded state according to a schematic embodiment of the present utility model;

[0013] Figure 4 is a side view of a UAV in a folded state according to a schematic embodiment of the present utility model;

[0014] Figure 5 is a three-dimensional schematic diagram of a UAV according to a schematic embodiment of the present utility model, wherein, an external device is in a separated state with the UAV;

[0015] Figure 6 is a side view of a fuselage according to a schematic embodiment of the present utility model.

[0016] In the drawings, the meanings of the reference signs are as follows:

[0017] 1, fuselage; 11, first rotating shaft; 12, second rotating shaft; 2, arm; 21, first arm; 22, second arm; 3, power device; 31, propeller; 311, blade; 32, guard ring; 4, foot stand; 5, remote controller; 51, body part; 52, operation part; 6, obstacle avoidance camera; 7, image acquisition device. DETAILED DESCRIPTION

[0018] In order to make the purpose, technical scheme and advantages of the present utility model more clear and obvious, the following will combine specific embodiments, and refer to the drawings, to make further detailed description of the present utility model.

[0019] The terms used herein are merely for describing specific embodiments, and are not intended to limit the present utility model. The terms "include", "contain" and the like used herein indicate the existence of the described features, steps, operations and / or components, but do not exclude the existence or addition of one or more other features, steps, operations or components.

[0020] All terms used herein, including technical and scientific terms, have the meanings commonly understood by one of ordinary skill in the art, unless otherwise defined. It should be further noted that the use of terms such as "first," "second," etc. herein do not connote any ordinal, precedence, or chronology, with respect to one another, but are used merely for the purpose of distinguishing between the various elements described. It will be further noted that the various elements depicted in the figures can, but not always, be associated with one another in the manner as depicted in the respective figure.

[0021] In the event a usage similar to "at least one of A, B, and C, etc." is used in the present disclosure, it is generally intended that the use represent any of the following meanings: "at least one of A, B, and C", "at least one of A, B, or C", "at least one of A, C, or B", "at least one of B, A, and C", "at least one of B, A, or C", "at least one of B, C, or A", "at least one of C, A, and B", "at least one of C, A, or B", "at least one of C, B, or A", or "at least one of A, B, and C, etc."

[0022] The unmanned aerial vehicle and unmanned aerial vehicle of the present application will be described in detail below with reference to the accompanying drawings. The features in the following embodiments and implementation modes can be combined with each other without conflict.

[0023] Embodiment one

[0024] Referring to Figure 1 , Figure 2 and Figure 3 , the present application provides an unmanned aerial vehicle, comprising a fuselage 1 and a rotating structure. The rotating structure is rotatably connected to the fuselage 1, so that the rotating structure is selectively in a folded state or an unfolded state relative to the fuselage 1. Wherein, when the rotating structure is in the folded state, the rotating structure forms a first accommodating space accommodating at least a part of the fuselage 1, and / or the rotating structure and the fuselage 1 form a second accommodating space accommodating a remote controller 5.

[0025] In some illustrative embodiments, the take-off weight of the unmanned aerial vehicle ranges from 900 grams to 1000 grams. For example, the take-off weight of the unmanned aerial vehicle can be 900 grams, 920 grams, 940 grams, 960 grams, 980 grams, 1000 grams, etc.

[0026] In some illustrative embodiments, the length dimension of the UAV in the folded state ranges from 200 mm to 250 mm, for example, 200 mm, 210 mm, 220 mm, 230 mm, 240 mm, 250 mm, etc. The width dimension and the height dimension of the UAV in the folded state can range from 80 mm to 110 mm, for example, 80 mm, 85 mm, 90 mm, 95 mm, 100 mm, 105 mm, 110 mm, etc.

[0027] In some illustrative embodiments, the rotating structure can be a rotor arm, a foot stand, a propeller, or the like. The rotating structure can selectively be in a folded state or an unfolded state relative to the body 1. When the rotating structure is in the folded state, the rotating structure forms a first accommodation space for accommodating at least a portion of the body 1. For example, the first accommodation space can accommodate a protruding component on the side of the body 1. The rotating structure and the body 1 form a second accommodation space for accommodating the remote controller 5.

[0028] According to embodiments of the present disclosure, by making full use of the first accommodation space and the second accommodation space formed by the body 1 and the rotating structure, and accommodating at least a portion of the body 1 or the remote controller 5 or the like, space waste can be reduced, and the utilization rate of the accommodation space of the UAV can be improved.

[0029] In some illustrative embodiments, at least a portion of the body 1 includes one or more of a sensor, a camera, and a gimbal of the body 1. The sensor, the camera, or the gimbal or the like is larger than the width of the body and protrudes outward from the side of the body, and can be accommodated in the first accommodation space, thereby improving the utilization rate of the accommodation space of the UAV.

[0030] In some illustrative embodiments, as shown in Figure 1 , Figure 2 and Figure 3 , the rotating structure includes a rotor arm 2, the rotor arm 2 is rotatably connected to the body 1, and the body 1 is provided with a power device 3 for providing flight power.

[0031] As shown in Figure 1 , Figure 2 and Figure 3 , in some illustrative embodiments, the rotor arm 2 is provided in two groups, and in the unfolded state, the two groups of rotor arms 2 are symmetrically arranged on both sides of the body 1 to maintain the balance of the UAV. It can be understood that the number of rotor arms 2 located on the same side of the body 1 is not limited herein. For example, the number of rotor arms 2 located on the same side of the body 1 can be one, two, three, four, five, etc. The rotor arms 2 located on the same side of the body 1 can be independent structures or can be connected to each other to form an integrated structure. For example, as shown in Figure 1 and Figure 3As shown, two arms 2 are arranged on the same side of the fuselage 1, and the two arms 2 are connected to form an integrated structure.

[0032] Referring to Figure 1 and Figure 3 , in some illustrative embodiments, the number of power devices 3 on each arm 2 is not limited here. The number on each arm 2 can be one, two, three, four, five, etc. For example, referring to Figure 1 and Figure 3 , two arms 2 are arranged on the same side of the fuselage 1, and the two arms 2 are connected to form an integrated structure, and one power device 3 is arranged on each arm 2. The power devices 3 on the two arms 2 are arranged side by side. The power device 3 includes a motor and a propeller 31 and other components to provide power for the flight of the unmanned aerial vehicle.

[0033] Referring to Figure 1 and Figure 3 , in some illustrative embodiments, the arm 2 includes, but is not limited to, a rotating shaft, a folding joint, a spring pin, and other components connected to the fuselage 1.

[0034] In some illustrative embodiments, referring to Figure 3 , in the folded state, the arm 2 is parallel to the first plane. Referring to Figure 2 , in the unfolded state, the arm 2 is substantially perpendicular to the first plane. The first plane is the plane of the roll axis and the heading axis of the unmanned aerial vehicle.

[0035] Referring to Figure 1 and Figure 2 , when the arm 2 is in the unfolded state, the arm 2 is perpendicular to the first plane (vertical plane in Figure 2 ), and the arm 2 and the fuselage 1 are substantially parallel to the horizontal plane. Referring to Figure 1 and Figure 3 , during the process of rotating the arm 2 from the unfolded state to the folded state, the arm 2 rotates downward to the fuselage 1, and the two arms 2 move closer to each other.

[0036] Referring to Figure 3 and Figure 4 , when the arm 2 is in the folded state, the arm 2 is substantially parallel to the first plane (vertical plane in Figure 2 or Figure 4 ), and the arm 2 is substantially in a vertical state. The two groups of arms 2 are arranged in relative spacing, and the arm 2 and the power device 3 form a first accommodating space accommodating at least a part of the fuselage 1. The space below the fuselage 1 and between the two groups of arms 2 forms a second accommodating space, which is substantially inverted U-shaped.

[0037] As Figure 4As shown, the upper end width of the second accommodating space is substantially equal to the lower end width. It can be understood that the upper end width of the second accommodating space can be greater than the lower end width, or the upper end width of the second accommodating space can be less than the lower end width, which is set according to actual needs.

[0038] In such an embodiment, the first accommodating space can accommodate the protruding components on the side of the body 1, such as a camera, a gimbal device, various sensors, a lighting device, and the like, as defined herein. The second accommodating space can also accommodate the remote controller 5 or other external devices below the body 1, so as to make full use of the first accommodating space and the second accommodating space formed by the body 1 and the two sets of arms 2, reduce space waste, and improve the utilization rate of the accommodating space of the unmanned aerial vehicle.

[0039] Referring to Figure 2 , Figure 3 and Figure 4 , in some illustrative embodiments, the two sets of arms 2 include a first arm 21 and a second arm 22. The first arm 21 and the second arm 22 are respectively rotatable relative to the body 1 about a first rotation shaft 11 and a second rotation shaft 12 to rotate to a folded state or an unfolded state.

[0040] Referring to Figure 2 , Figure 3 and Figure 4 , in some illustrative embodiments, the first rotation shaft 11 and the second rotation shaft 12 are substantially parallel to the roll axis of the unmanned aerial vehicle.

[0041] Specifically, referring to Figure 1 and Figure 2 , the first arm 21 and the second arm 22 are respectively located on two sides of the body 1. In the unfolded state, the first arm 21 and the second arm 22 are in a horizontal state. In the process of rotating from the unfolded state to the folded state, the first arm 21 and the second arm 22 are respectively rotated downward about the first rotation shaft 11 and the second rotation shaft 12, so that the lower ends of the first arm 21 and the second arm 22 are close to each other. In the folded state, the first arm 21 and the second arm 22 are substantially parallel to the first plane and are arranged in a spaced-apart manner.

[0042] In such an embodiment, the first arm 21 and the second arm 22 are respectively rotatable about the first rotation shaft 11 and the second rotation shaft 12 to adjust to the unfolded state or the folded state. In the folded state, the first arm 21 and the second arm 22 and the first accommodating space formed by the power device 3 can accommodate the protruding components on the side of the body 1; the space below the body 1 and the space between the first arm 21 and the second arm 22 form the second accommodating space to accommodate the lower part structure of the body 1, reduce space waste, and improve the utilization rate of the accommodating space of the unmanned aerial vehicle.

[0043] In some illustrative embodiments, referring toFigure 4 and Figure 5 As shown, the first and second rotating axes are perpendicular to the second plane of the first plane. Figure 4 The two arms intersect on the horizontal plane of the machine body 1, so that in the folded state, the end of the arm 2 is approximately parallel to the side of the remote controller 5 away from the body 1.

[0044] In detail, Figure 5 In the middle, the remote control 5 is tilted on the side away from the main body 1, intersecting with the second plane. The first rotating shaft 11 and the second rotating shaft 12 are also intersecting with the second plane, such that the first rotating shaft 11 and the second rotating shaft 12 are approximately parallel to the side of the remote control 5 away from the main body 1, so that in the folded state, the end of the arm 2 ( Figure 4 The bottom of the central arm is roughly parallel to the side of the remote controller 5 that is away from the main body 1.

[0045] According to the embodiments of this disclosure, in the folded state, the end of the arm 2 is approximately parallel to the side of the remote controller 5 away from the body 1, so that the second accommodating space formed by the space between the lower part of the body 1 and the two sets of arms 2 is adapted to the shape of the remote controller 5, so as to better store the remote controller 5, reduce space waste, and improve the space utilization of the drone.

[0046] Reference Figure 3 and Figure 4 As shown, in some illustrative embodiments, the first rotating shaft 11 and the second rotating shaft 12 are located on the sides of the fuselage 1 on both sides of the roll axis.

[0047] According to an embodiment of this disclosure, in the folded state, the first arm 21 and the second arm 22 respectively contact the sides of the fuselage 1 to prevent the first arm 21 and the second arm 22 from approaching each other, so that the first arm 21 and the second arm 22 are arranged at a distance from each other. The space below the fuselage 1 and the space between the first arm 21 and the second arm 22 form an accommodating space.

[0048] In this embodiment, by setting the first pivot 11 and the second pivot 12 on the sides of the fuselage 1 on both sides of the roll axis, the size of the drone in the height direction is further reduced, and the folded storage volume is reduced.

[0049] Reference Figure 3 and Figure 4 As shown, in some illustrative embodiments, the first rotating shaft 11 and the second rotating shaft 12 are located on the bottom surface of the fuselage 1 and are spaced apart on both sides of the roll shaft, so that the space below the fuselage 1 and the space between the first arm 21 and the second arm 22 form an accommodating space.

[0050] In this embodiment, the first pivot 11 and the second pivot 12 are located on the bottom surface of the fuselage 1, which can further reduce the size of the drone in the width direction and reduce the folded storage volume.

[0051] Referring to Figure 3 and Figure 4 , in some illustrative embodiments, when the arms 2 are in the folded state, the projection of the power device 3 on a second plane (horizontal plane in Figure 4 ) perpendicular to the first plane partially overlaps with the projection of the fuselage 1.

[0052] In detail, part of the power device 3 is located below the fuselage 1, and the right end part of the power device 3 located on the left side of the fuselage 1 and the left end part of the power device 3 located on the right side of the fuselage 1 are both located below the fuselage 1.

[0053] In such an implementation, the power device 3 can be completely located in the second accommodating space formed by the fuselage 1 and the arms 2, or at least part of the power device 3 is located in the second accommodating space formed by the fuselage 1 and the arms 2, thereby reducing the volume of the UAV in the folded state and further improving the space utilization of the accommodating space.

[0054] Referring to Figure 3 and Figure 4 , in some illustrative embodiments, when the arms 2 are in the folded state, the power device 3 is located on the side of the arms 2 facing the accommodating space.

[0055] Specifically, as shown in Figure 1 , when the arms 2 are in the unfolded state, the power device 3 is located below the arms 2. When the arms 2 are in the folded state, the power device 3 is located on the side (inner side of the arms 2 in Figure 4 ) of the two groups of arms 2 facing each other, so that the power device 3 is located in the accommodating space between the two groups of arms 2.

[0056] In such an implementation, the power device 3 is completely located in the accommodating space, effectively reducing the volume of the UAV in the folded state and effectively improving the space utilization of the accommodating space.

[0057] It can be understood that, in an alternative illustrative embodiment, when the arms 2 are in the folded state, the power device 3 can also be located on the side of the arms 2 away from the accommodating space.

[0058] Specifically, when the arms 2 are in the unfolded state, the power device 3 is located above the arms 2. When the arms 2 are in the folded state, the power device 3 is located on the side (outer side of the arms 2 in Figure 4 ) of the two groups of arms 2 away from each other, which is not shown in the figure). The lower ends of the arms 2 are close to each other, so that the power device 3 is at least partially located below the fuselage 1.

[0059] In this implementation, the power unit 3 can be located at least partially within the storage space, reducing the volume of the drone in its folded state and improving the space utilization of the storage space.

[0060] Reference Figure 2 and Figure 4 As shown, in some illustrative embodiments, the rotation angle of the robotic arm 2 from the unfolded state to the folded state is greater than or equal to 40 degrees and less than or equal to 110 degrees. For example, the rotation angle of the robotic arm 2 from the unfolded state to the folded state can be 40 degrees, 50 degrees, 60 degrees, 70 degrees, 80 degrees, 90 degrees, 100 degrees, 110 degrees, etc., and is not limited here.

[0061] In some illustrative embodiments, such as Figure 2 As shown, arm 2 is in the extended state, and arm 2 is roughly parallel to the horizontal line. Figure 4 As shown, arm 2 is in a folded state, roughly parallel to the vertical line, with an angle of 90 degrees. It can be understood that the two sets of arms 2 can continue to move closer together, increasing the angle to 110 degrees, to further reduce the folded size of the drone and improve the utilization of the storage space.

[0062] Reference Figure 3 and Figure 4 As shown, in some illustrative embodiments, the power unit 3 includes a propeller 31, the space between the plurality of blades 311 of the propeller 31 forming a partial first receiving space; and / or, in the folded state, the wide faces of the blades 311 of the power unit 3 of the two sets of arms 2 face each other.

[0063] Understandably, the power unit 3 also includes a motor and a mounting mechanism. The mounting mechanism mounts the propeller 31 onto the arm 2, so that the propeller 31 is connected to the output shaft of the motor to rotate under the drive of the motor, providing power for the drone's flight.

[0064] In some illustrative embodiments, the number of propeller blades 311 may be two, three, four, five, six, etc., and is not limited herein. The space between adjacent propeller blades 311 forms a first receiving space to accommodate components protruding from the side of the fuselage 1.

[0065] In some illustrative embodiments, in the folded state, the wide faces of the blades 311 of the power units 3 of the two sets of arms 2 face each other.

[0066] It is understandable that there may be one blade 311, and the center of the blade 311 is connected to the output shaft of the motor. Within the rotation area of ​​the blade 311, the space between the two sides of the blade 311 forms a first receiving space to accommodate the protruding parts on the side of the fuselage 1.

[0067] Specifically, as shown in Figure 3 and 4 In the folded state, the body 1 is provided with a plurality of obstacle avoidance cameras 6 on the two sides opposite to the power device 3, and the obstacle avoidance cameras 6 protrude from the side of the body 1. In the folded state, the obstacle avoidance cameras 6 extend into the space between the adjacent blades 311. In this way, the space utilization of the accommodation space is effectively improved, and the volume of the unmanned aerial vehicle in the folded state is reduced.

[0068] In some illustrative embodiments, the plurality of blades 311 are configured to rotate relative to each other to be in a folded state or a released state. In this way, the propeller 31 is a folding propeller, and the plurality of blades 311 can be folded.

[0069] In detail, during the flight of the unmanned aerial vehicle, the arm 2 is in an unfolded state. The blades 311 are in a released state and are evenly spaced and distributed, and are rotated under the driving of the motor to provide power for the flight of the unmanned aerial vehicle.

[0070] When the unmanned aerial vehicle is accommodated, the arm 2 is in a folded state, and the blades 311 are rotated so that the blades 311 are folded to further reduce the space occupied by the blades 311 during accommodation, and improve the utilization of the first accommodation space for accommodating the components protruding from the side of the body 1.

[0071] In some illustrative embodiments, the plurality of blades 311 are configured to be relatively fixed to maintain the released state. In this way, the propeller 31 is a non-folding propeller, and the shape of the propeller 31 remains unchanged. There is still a space between the blades 311 to form a first accommodation space to accommodate components protruding from the side of the body 1. Referring to Figure 3 and Figure 4 In some illustrative embodiments, the power device 3 includes a guard ring 32 connected to the arm 2 and configured to surround the periphery of the propeller 31.

[0072] In some illustrative embodiments, the guard ring 32 is annular, and the guard ring 32 surrounds the periphery of the propeller 31 and has a gap with the free end of the blade 311, so that the blade 311 can rotate normally.

[0073] In some illustrative embodiments, the guard ring 32 is installed on the arm 2 by any connection method such as welding, bolt connection or buckle connection, but is not limited thereto.

[0074] In such an embodiment, the guard ring 32 surrounds the periphery of the propeller 31, reducing the degree of damage to the propeller 31 caused by collision with obstacles. At the same time, it protects people or objects from being hit by the propeller 31, improving the safety of use.

[0075] Referring to Figures 1 to 4 In some illustrative embodiments, the thickness of the guard ring 32 is greater than the thickness of the propeller 31.

[0076] Specifically, as shown in Figure 2 the vertical direction, the size of the guard ring 32 is larger than the size of the propeller 31, the upper surface of the guard ring 32 is higher than the upper surface of the propeller 31, and the lower surface of the guard ring 32 is lower than the lower surface of the propeller 31. In this way, the propeller 31 is located within the guard ring 32, and the propeller 31 is fully protected.

[0077] Referring to Figures 1 to 4 , in some illustrative embodiments, the space between the guard ring 32 and the propeller 31 forms part of the first accommodation space.

[0078] In detail, since the thickness of the guard ring 32 is greater than the thickness of the propeller 31, there is a space between the surface of the propeller 31 and the surface of the guard ring 32. Specifically, as shown in Figure 4 , in the folded state, the width of the guard ring 32 is greater than the width of the propeller 31. The surface formed on the inner side of the propeller 31 is located outside the surface formed on the inner side of the guard ring 32, and the space between the surface formed on the inner side of the propeller 31 and the surface formed on the inner side of the guard ring 32 forms part of the first accommodation space to accommodate the obstacle avoidance camera 6 protruding from the side of the fuselage 1.

[0079] In some illustrative embodiments, the rotating structure includes a foot stand 4 rotatably connected to the fuselage 1, and the foot stand 4 is used to support the fuselage.

[0080] Referring to Figure 1 , Figure 2 , Figure 3 and Figure 5 , in some illustrative embodiments, at least two foot stands 4 are provided and arranged at the bottom of the fuselage 1. In the unfolded state, the foot stands 4 enable the UAV to land on a support surface to support the fuselage 1. In the folded state, the space between adjacent foot stands 4 forms the first accommodation space.

[0081] According to embodiments of the present disclosure, the foot stand 4 protrudes from the side of the fuselage 1, enabling the UAV to land on a support surface, increasing the area of the fuselage 1 in contact with the ground, and improving the stability of the UAV landing.

[0082] In the folded state, the foot stand 4 extends into the space between the guard ring 32 and the propeller 31 and the space between the blades 311, effectively utilizing part of the first accommodation space formed by the guard ring 32 and the propeller 31 and part of the first accommodation space formed by adjacent blades 311. At the same time, the space between adjacent foot stands 4 forms part of the first accommodation space, which can accommodate part of the remote controller 5 and / or part of the fuselage 1, thereby improving the utilization of space, reducing the volume of the UAV after folding, and facilitating storage.

[0083] In some illustrative embodiments, the image acquisition device 7 can be located at the front, rear, or bottom of the body 1 to avoid obstruction of the image acquisition device 7 in order to capture and record images.

[0084] Reference Figure 1 , Figure 3 and Figure 4 As shown, in some illustrative embodiments, the fuselage 1 is equipped with an image acquisition device 7 to capture and record images during the drone's flight. The image acquisition device 7 can be a camera, a video camera, etc.

[0085] In some illustrative embodiments, the image acquisition device 7 is mounted on the body 1 via a connecting mechanism such as a rotation mechanism or an angle adjustment mechanism. This facilitates adjustment of the angle of the image acquisition device 7, adjusts the range of image capture, and improves the flexibility of use.

[0086] Example 2

[0087] Reference Figure 5 and Figure 6 As shown, this utility model also provides a remote controller 5, which is used to communicate with the aforementioned drone and output control signals to control the drone's movement. When the drone is in a folded state, the remote controller 5 is housed in the drone's second storage space.

[0088] According to an embodiment of this disclosure, when using remote controller 5 to control the drone, remote controller 5 is in a detached state from the drone, and the drone can be moved by remote controller 5.

[0089] When storing the drone and remote controller 5, the remote controller 5 can be stored in the drone's second storage space. Making full use of the second storage space can reduce space waste and improve the utilization rate of the drone's storage space.

[0090] In some illustrative embodiments, reference is made to Figure 3 and Figure 6 As shown, the remote controller 5 is equipped with a mating part, and the drone is equipped with a mounting part that can be detachably connected to the mating part.

[0091] According to embodiments of this disclosure, the remote controller 5 is detachably connected to the drone via a mating part and a mounting part, which facilitates the assembly and disassembly of the remote controller 5 and improves the convenience of assembling the remote controller 5 onto and removing it from the drone.

[0092] In some illustrative embodiments, reference is made to Figure 3 and Figure 6 As shown, the remote controller 5 includes a main body 51 and an operation unit 52. The main body 51 is detachably connected to the drone. The operation unit 52 is located on the side of the main body 51 opposite to the fuselage 1.

[0093] According to the embodiment of the present disclosure, the operation part 52 can be a rocker, an operation key or the like, which protrudes out of the body part 51. The body part 51 cooperates with the unmanned aerial vehicle, and the operation part 52 is located on the side of the body part 51 away from the fuselage 1, so as to avoid the operation part 52 from colliding with or interfering with the unmanned aerial vehicle. The body part 51 and the operation part 52 are accommodated in the second accommodating space of the unmanned aerial vehicle, so as to facilitate the accommodation, without increasing the size of the unmanned aerial vehicle after being accommodated, and improving the utilization rate of the accommodating space of the unmanned aerial vehicle.

[0094] In some illustrative embodiments, as shown in Figure 3 and Figure 6 , the appearance surface of the body part 51 is substantially parallel to the inner wall surface of the second accommodating space.

[0095] According to the embodiment of the present disclosure, the appearance surface of the body part 51 is substantially parallel to the inner wall surface of the second accommodating space, so that the shape of the body part 51 of the remote controller 5 cooperates with the second accommodating space. When the remote controller 5 is accommodated in the second accommodating space, the friction or collision between the remote controller 5 and the unmanned aerial vehicle is reduced.

[0096] In some illustrative embodiments, as shown in Figure 3 and Figure 6 , in the folded state, the end of the arm 2 of the unmanned aerial vehicle protrudes beyond the appearance surface of the remote controller 5.

[0097] According to the embodiment of the present disclosure, when the remote controller 5 is accommodated in the second accommodating space of the unmanned aerial vehicle, the end of the arm 2 of the unmanned aerial vehicle protrudes beyond the appearance surface of the remote controller 5, so that the remote controller 5 can be completely accommodated in the second accommodating space, and the remote controller 5 can be better accommodated.

[0098] Embodiment three

[0099] As shown in Figure 6 , the utility model also provides a kind of unmanned aerial vehicle, comprising external device 5 and the unmanned aerial vehicle as described above. External device cooperates with the bottom of fuselage 1, to be accommodated in second accommodating space.

[0100] In some illustrative embodiments, the external device can be a remote controller, a camera, a gimbal sensor, a lighting device and the like, which is determined according to actual needs.

[0101] According to the embodiment of the present disclosure, the external device cooperates with the bottom of fuselage 1, so that the external device utilizes the second accommodating space, avoids increasing the folding and accommodating size of the unmanned aerial vehicle, effectively reduces the space waste, and further improves the utilization rate of the accommodating space.

[0102] As shown in Figure 3 , Figure 4 and Figure 6 , in some illustrative embodiments, the external device is detachably connected with the fuselage 1.

[0103] In some illustrative embodiments, the external device is detachably connected to the body 1 by any detachable connection mode such as magnetic connection, snap connection or screw connection, etc. so as to select to mount the external device on the body 1 or separate the external device from the body 1 according to actual needs.

[0104] In the embodiment, the external device is a remote controller. When the remote controller is needed to remotely control the flight of the UAV, the remote controller is separated from the body 1 so as to control the flight of the UAV by the remote controller. When the UAV is stored, the remote controller is mounted on the body 1 so as to be located in the accommodation space, facilitating storage.

[0105] Referring to Figs. Figure 3 , Figure 4 and Figure 6 In some illustrative embodiments, the external device is in a strip structure to cooperate with the second accommodation space.

[0106] In some illustrative embodiments, the external device has a shape substantially same as that of the body 1 and slightly smaller than the volume of the body 1 so as to be accommodated in the second accommodation space.

[0107] In such an implementation, the external device can fully utilize the second accommodation space formed by the body 1 and the two groups of arms 2, reduce space waste and improve the utilization rate of the accommodation space of the UAV.

[0108] It should be noted that the directional terms mentioned in the embodiments, such as "up", "down", "front", "back", "left", "right", etc. are only reference directions of the drawings and are not intended to limit the protection scope of the utility model. Throughout the drawings, the same elements are denoted by the same or similar reference numerals. When it is possible to cause confusion in understanding the utility model, conventional structures or configurations will be omitted.

[0109] The embodiments of the utility model have been described above. However, these embodiments are only for illustrative purposes and are not intended to limit the scope of the utility model. Although each embodiment is described above, this does not mean that the measures in each embodiment cannot be advantageously combined for use. The scope of the utility model is defined by the appended claims and their equivalents. Without departing from the scope of the utility model, those skilled in the art can make various substitutions and modifications, which should all fall within the scope of the utility model.

Claims

1. A drone, characterized in that, Comprise: a body (1); a rotating structure rotatably connected to the body (1) so that the rotating structure is selectively in a folded state or an unfolded state relative to the body (1); wherein, when the rotating structure is in the folded state, the rotating structure forms a first accommodating space accommodating at least a part of the body (1), and / or the rotating structure and the body (1) form a second accommodating space for accommodating a remote controller (5).

2. The drone of claim 1, wherein, The rotating structure comprises: an arm (2) rotatably connected to the body (1), and the arm (2) is provided with a power device (3) for providing flight power; and / or, a foot stand (4) rotatably connected to the body (1), the foot stand (4) is used for supporting the body (1).

3. The drone of claim 2, wherein, In the folded state, the arm (2) is substantially parallel to a first plane; and / or, in the unfolded state, the arm (2) is substantially perpendicular to the first plane, and the first plane is a plane where the roll axis and the heading axis of the unmanned aerial vehicle are located.

4. The drone of claim 3, wherein, When the arm (2) is in the folded state, the projection of the power device (3) and the projection of the body (1) partially overlap on a second plane perpendicular to the first plane.

5. The drone of claim 2, wherein, When the arm (2) is in the folded state, the power device (3) is located on the side of the arm (2) facing the accommodating space.

6. The drone of claim 2, wherein, The power device (3) comprises a propeller (31), and the space between at least two blades (311) of the propeller (31) forms part of the first accommodating space; And / or, The arm (2) comprises two groups, and the broad surfaces of the blades of the power devices (3) of the two groups of arms (2) are opposite in the folded state.

7. The drone of claim 6, wherein, A plurality of the blades (311) are configured to rotate relative to each other to be in a folded state or a released state.

8. The drone of claim 6, wherein, A plurality of the blades (311) are configured to be fixed relative to each other to maintain the released state.

9. The drone of claim 6, wherein, The power device (3) comprises a guard ring (32) connected to the arm (2) and configured to surround the periphery of the propeller (31).

10. The drone of claim 9, wherein, The thickness of the guard ring (32) is greater than the thickness of the propeller (31).

11. The drone of claim 10, wherein, The space between the guard ring (32) and the propeller (31) forms part of the first accommodating space.

12. The drone of any one of claims 2 to 11, wherein, The rotation angle of the arm (2) from the unfolded state to the folded state is greater than or equal to 40 degrees and less than or equal to 110 degrees.

13. The drone of claim 4, wherein, The two groups of arms (2) comprise a first arm (21) and a second arm (22), and the first arm (21) and the second arm (22) are respectively rotatable relative to the body (1) about a first rotation axis (11) and a second rotation axis (12) to rotate to the folded state or the unfolded state.

14. The drone of claim 13, wherein, The first rotation axis (11) and the second rotation axis (12) are substantially parallel to the roll axis of the unmanned aerial vehicle.

15. The drone of claim 13, wherein, The first rotation axis (11) and the second rotation axis (12) intersect the second plane so that, in the folded state, the end of the arm (2) is substantially parallel to the side of the remote controller (5) away from the body (1).

16. The drone of claim 13, wherein, The first rotation shaft (11) and the second rotation shaft (12) are located on the side surface of the fuselage (1) on both sides of the roll axis.

17. The drone of claim 13, wherein, The first rotation shaft (11) and the second rotation shaft (12) are located on the bottom surface of the fuselage (1) and are spaced apart on both sides of the roll axis.

18. The drone of claim 2, wherein, The landing legs (4) are provided in at least two and are arranged on the bottom of the fuselage (1), and in the unfolded state, the landing legs (4) enable the unmanned aerial vehicle to land on a support surface for supporting the fuselage (1). In the folded state, the space between adjacent landing legs (4) forms the first accommodating space.

19. The drone of claim 1, wherein, At least a part of the fuselage (1) includes one or more of sensors, cameras, and gimbals of the fuselage (1).

20. A remote control, characterized by The remote controller (5) is used for communication connection with the unmanned aerial vehicle of any one of claims 1 to 19 and outputs a control signal to control the movement of the unmanned aerial vehicle. In the folded state of the unmanned aerial vehicle, the remote controller (5) is accommodated in the second accommodating space of the unmanned aerial vehicle.

21. The remote control of claim 20, wherein, The remote controller (5) is provided with a matching part, and the unmanned aerial vehicle is provided with a mounting part detachably connected with the matching part.

22. The remote control of claim 20, wherein, Comprising: A body part (51) detachably connected with the unmanned aerial vehicle; An operation part (52) arranged on the side of the body part (51) away from the fuselage.

23. The remote control of claim 22, wherein, The appearance surface of the body part (51) is substantially parallel to the inner wall surface of the second accommodating space.

24. The remote control of claim 20, wherein, In the folded state, the end of the arm (2) of the unmanned aerial vehicle exceeds the appearance surface of the remote controller (5).

25. An unmanned aerial vehicle, comprising: Comprising: An external device; And The unmanned aerial vehicle according to any one of claims 1 to 19, the external device is matched with the bottom of the fuselage (1) to be accommodated in the second accommodating space.

26. The unmanned vehicle of claim 25, wherein, The external device is detachably connected with the fuselage (1).

27. The unmanned vehicle of claim 25, wherein, The external device is a strip-shaped structure to cooperate with the second accommodating space. The external device is detachably connected with the fuselage (1). The external device is a strip-shaped structure to cooperate with the second accommodating space.

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