Portable quad-rotor unmanned aerial vehicle

Abstract

The utility model provides a portable four-rotor unmanned aerial vehicle which comprises a vehicle body, four vehicle arms and four rotor assemblies, and one end of each vehicle arm is provided with one rotor assembly; a containing space is formed in the fuselage body, a first resistance reduction structure is formed at the front end of the fuselage body, and second resistance reduction structures are formed on the two sides of the fuselage body; a supporting structure is arranged at the bottom of the vehicle body, and the other end of each vehicle arm is connected with the supporting structure in a locking mode through a first locking piece. The four-rotor unmanned aerial vehicle has the advantages that wind resistance in the flying process can be effectively reduced, and therefore the flying speed of the four-rotor unmanned aerial vehicle can be increased; according to the four-rotor unmanned aerial vehicle, all the vehicle arms can be folded by simply disassembling the first locking pieces, and therefore the four-rotor unmanned aerial vehicle can be conveniently stored and transported.

Description

[Technical field]

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a portable four-rotor unmanned aerial vehicle. [Background technology]

[0002] At present, quad-rotor drones have been used in various fields such as commerce, life, and military. When a traditional quad-rotor drone is in flight or idle, the four rotors are all in an extended state, which occupies a large space and is not convenient for storage and transportation.

[0003] In order to facilitate the storage and transportation of quad-rotor drones, quad-rotor drones with folding functions have emerged. For example, the Chinese utility model patent with application number CN202222610335.8 discloses a quad-rotor drone wingspan folding structure, which can fold the wings of the drone when in use, thereby improving the overall storage efficiency. However, the above existing quad-rotor drones have the following defects: the fuselage is large in size, and the folding structure occupies most of the space of the fuselage, which limits the layout of other core components to a certain extent. At the same time, the wind resistance of the whole machine is large, making it difficult to achieve stable high-speed flight. [Contents of the utility model]

[0004] In view of the above-mentioned technical problems, the purpose of the utility model is to provide a portable quad-rotor drone that can reduce wind resistance while making the entire structure more compact.

[0005] The utility model is implemented as follows: a portable quad-rotor drone comprises a fuselage body, four arms and four rotor assemblies, one end of each of the arms being provided with a rotor assembly; an accommodating space is formed in the fuselage body, a first drag reduction structure is formed at the front end of the fuselage body, and a second drag reduction structure is formed on both sides of the fuselage body; a supporting structure is provided at the bottom of the fuselage body, and the other end of each of the arms is locked and connected to the supporting structure through a first locking member.

[0006] Furthermore, the first drag reduction structure is formed with a front windward surface located at the front end, a first side windward surface located on one side, a second side windward surface located on the other side, and an upper windward surface located at the top; the front windward surface is gradually inclined backward from bottom to top; the first side windward surface and the second side windward surface are both gradually inclined outward from front to back, and a first transition curved surface gradually expanding from inside to outside is formed between the first side windward surface and the second side windward surface and the fuselage body; the upper windward surface is gradually inclined backward from top to bottom, and a second transition curved surface gradually expanding from bottom to top is formed between the upper windward surface and the fuselage body.

[0007] Furthermore, a lower windward surface which is gradually inclined backward from top to bottom is formed at the front end of the bottom of the first drag reduction structure, and a notch is formed on the lower windward surface.

[0008] Furthermore, it also includes a camera device, which is installed inside the first drag reduction structure, and the shooting end of the camera device extends to the front windward surface.

[0009] Furthermore, both the first side windward surface and the second side windward surface are provided with connecting slots connected to the interior of the first drag reduction structure, and the connecting slots extend along the length direction of the fuselage body to the first transition curved surface.

[0010] Furthermore, the second drag reduction structure is formed with a first inclined surface at the top, a second inclined surface at the middle, and a vertical plane at the bottom; the first inclined surface gradually inclines inward from top to bottom, and the second inclined surface gradually inclines outward from top to bottom, and a third transition curved surface is formed between the second inclined surface and the vertical plane.

[0011] Furthermore, the support structure includes a detachable chassis and a support mainboard, and the other end of each of the arms is arranged between the detachable chassis and the support mainboard;

[0012] The inner side of the fuselage body is provided with a mounting part, and the supporting mainboard is locked and connected with the mounting part through a second locking member; the detachable chassis and the supporting mainboard are locked and connected with each other through a third locking member.

[0013] Furthermore, the four arms are grouped in pairs, and among the two arms in the same group, the upper surface of the other end of any one of the arms is formed with a first assembling step, and the lower surface of the other end of the other arm is formed with a second assembling step; the two arms in the same group are assembled together through the first assembling step and the second assembling step, and are locked and connected with the support structure through the first locking piece.

[0014] Furthermore, it also includes a control device, which is arranged on the top of the supporting structure.

[0015] Furthermore, it also includes an antenna, which is installed at the tail of the fuselage body and is electrically connected to the control device.

[0016] By adopting the technical solution of the utility model, at least the following beneficial effects are achieved:

[0017] 1. A first drag reduction structure is formed at the front end of the fuselage body, and a second drag reduction structure is formed on both sides of the fuselage body, which can effectively reduce the wind resistance during flight, thereby helping to increase the flight speed of the quadrotor drone.

[0018] 2. The other end of each arm is locked and connected to the support structure through the first locking member, so that when the quad-rotor drone is not in use, each arm can be folded by simply disassembling the first locking member, thereby facilitating the storage and transportation of the quad-rotor drone.

[0019] 3. A storage space is formed in the fuselage body, and the supporting structure is located at the bottom of the fuselage body, which is convenient for storing various core components in the storage space and making the overall structure of the entire quadcopter more compact and beautiful. The fuselage body can also be used to protect various core components to ensure that they are not easily damaged during use.

[0020] 4. By designing a supporting structure including a detachable chassis and a supporting mainboard, and using a second locking component to lock the supporting mainboard to the body of the machine, and using a third locking component to lock the detachable chassis to the supporting mainboard, the detachable chassis can be easily disassembled and replaced during specific use, thereby being able to better adapt to various scenarios and mounting requirements.

Brief Description of the Drawings

[0021] The present invention will be further described below in conjunction with the embodiments with reference to the accompanying drawings.

[0022] Figure 1 This is a top three-dimensional structural diagram of a portable four-rotor drone of the utility model;

[0023] Figure 2 This is a bottom three-dimensional structural diagram of a portable four-rotor drone of the utility model;

[0024] Figure 3 This is an exploded view of a portable four-rotor drone of the utility model;

[0025] Figure 4 It is a top structural diagram of the fuselage body in the utility model;

[0026] Figure 5 It is a bottom structural diagram of the fuselage body in the utility model;

[0027] Figure 6 It is a connection structure diagram of two machine arms of the same group in the utility model.

[0028] Description of reference numerals:

[0029] Quadrotor drone 100;

[0030] Fuselage body 1, accommodating space 11, first drag reduction structure 12, front windward surface 121, first side windward surface 122, second side windward surface 123, upper windward surface 124, first transition curved surface 125, second transition curved surface 126, lower windward surface 127, notch 128, connecting notch 129, second drag reduction structure 13, first inclined surface 131, second inclined surface 132, vertical plane 133, third transition curved surface 134, mounting portion 14;

[0031] Arm 2, first assembly step 21, second assembly step 22;

[0032] Rotor assembly 3, drive motor 31, propeller 32;

[0033] Support structure 4, a removable chassis 41, supporting main board 42;

[0034] A first locking member 51, a second locking member 52, and a third locking member 53;

[0035] Camera device 6;

[0036] Control device 7;

[0037] Antenna 8. [Specific implementation method]

[0038] In order to better understand the technical solution of the present invention, the technical solution of the present invention will be described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0039] It should be noted that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicate positions or positional relationships based on the positions or positional relationships shown in the drawings, and are only for the convenience of describing these embodiments and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation. In addition, the terms "first", "second", etc., etc. are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, features defined as "first", "second", etc. may explicitly or implicitly include one or more of the features.

[0040] See also Figures 1 to 6As shown, a preferred embodiment of a portable quad-rotor drone 100 of the utility model, the quad-rotor drone 100 includes a fuselage body 1, four arms 2 and four rotor assemblies 3, one end of each of the arms 2 is provided with a rotor assembly 3, so as to utilize the rotor assembly 3 to provide the quad-rotor drone 100 with the power required for flight; wherein, the rotor assembly 3 specifically includes a drive motor 31 and a propeller 32, the drive motor 31 is fixedly mounted on one end of the arm 2, the propeller 32 is connected to the output end of the drive motor 31, and when working, the drive motor 31 outputs power to drive the propeller 32 to rotate, thereby providing the power required for flight;

[0041] A accommodating space 11 is formed in the fuselage body 1 to facilitate the arrangement of various required core components inside the fuselage body 1, which can not only protect the various core components, but also make the structure of the entire quad-rotor drone 100 more compact; a first drag reduction structure 12 is formed at the front end of the fuselage body 1, and a second drag reduction structure 13 is formed on both sides of the fuselage body 1, and the first drag reduction structure 12 and the second drag reduction structure 13 are both used to reduce wind resistance to increase the flight speed of the quad-rotor drone 100; a support structure 4 is provided at the bottom of the fuselage body 1, and the other end of each of the arms 2 is locked and connected to the support structure 4 through a first locking member 51.

[0042] By adopting the above technical solution of the utility model, at least the following beneficial effects are achieved:

[0043] 1. A first drag reduction structure 12 is formed at the front end of the fuselage body 1, and a second drag reduction structure 13 is formed on both sides of the fuselage body 1, which can effectively reduce the wind resistance during flight, thereby helping to increase the flight speed of the quad-rotor drone 100.

[0044] 2. The other end of each arm 2 is locked and connected to the support structure 4 through the first locking member 51, so that when the quad-rotor drone 100 is not in use, each arm 2 can be folded by simply disassembling the first locking member 51, thereby facilitating the storage and transportation of the quad-rotor drone 100.

[0045] 3. A accommodating space 11 is formed in the fuselage body 1, and the supporting structure 4 is located at the bottom of the fuselage body 1, which is convenient for storing various core components in the accommodating space 11 and making the overall structure of the entire quad-rotor drone 100 more compact and beautiful, and can also use the fuselage body 1 to protect various core components and ensure that they are not easily damaged during use.

[0046] As a preferred embodiment of the present invention, please refer to Figure 4 and Figure 5As shown, the first drag reduction structure 12 is formed with a front windward surface 121 located at the front end, a first side windward surface 122 located at one side, a second side windward surface 123 located at the other side, and an upper windward surface 124 located at the top; the front windward surface 121 is gradually tilted backward from bottom to top; the first side windward surface 122 and the second side windward surface 123 are gradually tilted outward from front to back, and a first transition curved surface 125 gradually expanding from inside to outside is formed between the first side windward surface 122 and the second side windward surface 123 and the fuselage body 1; the upper windward surface 124 is gradually tilted backward from top to bottom, and a second transition curved surface 126 gradually expanding from bottom to top is formed between the upper windward surface 124 and the fuselage body 1. By adopting the above structural design, the front end of the entire first drag reduction structure 12 is small and the rear end is large, which is conducive to the smooth flow of airflow, can effectively reduce wind resistance, and thus is conducive to improving the flight speed of the quad-rotor drone 100.

[0047] Furthermore, a lower windward surface 127 which is gradually inclined backward from top to bottom is formed at the bottom front end of the first drag reduction structure 12, and a notch 128 is formed on the lower windward surface 127. In this way, during the flight of the quad-rotor drone 100, the airflow at the front end can flow smoothly along the inclined front windward surface 121 and the lower windward surface 127, thereby further reducing wind resistance.

[0048] In a preferred embodiment of the present invention, in order to achieve image capture, the quad-rotor drone 100 also includes a camera device 6, which is installed inside the first drag reduction structure 12, and the shooting end of the camera device 6 extends to the front windward surface 121.

[0049] Since the front field of view of the quad-rotor drone 100 is good, by arranging the camera device 6 in the first drag reduction structure 12 and extending the shooting end of the camera device 6 to the front windward surface 121, the camera device 6 can be better utilized for image capture, and the first drag reduction structure 12 can be used to protect the camera device 6.

[0050] Furthermore, the first side windward surface 122 and the second side windward surface 123 are both provided with a connecting slot 129 connected to the inside of the first drag reduction structure 12, and the connecting slot 129 extends along the length direction of the fuselage body 1 to the first transition curved surface 125. Since the camera device 6 and the like will generate heat during operation, by forming the connecting slot 129 on the first side windward surface 122 and the second side windward surface 123, the external cold air flow can enter the inside of the first drag reduction structure 12 through the connecting slot 129 during the flight of the quad-rotor drone 100, thereby having a certain cooling effect on the camera device 6 and the like.

[0051] As a preferred embodiment of the present invention, please refer to Figure 4 and Figure 5 As shown, the second drag reduction structure 13 is formed with a first inclined surface 131 located at the upper part, a second inclined surface 132 located in the middle part and a vertical plane 133 located at the lower part; the first inclined surface 131 gradually inclines inward from top to bottom, and the second inclined surface 132 gradually inclines outward from top to bottom, so that an inwardly recessed area is formed between the first inclined surface 131 and the second inclined surface 132, which is conducive to the smooth passage of airflow, thereby reducing wind resistance, and a third transition curved surface 134 is formed between the second inclined surface 132 and the vertical plane 133.

[0052] In a preferred embodiment of the present utility model, the support structure 4 includes a detachable chassis 41 and a support main board 42, and the other end of each of the arms 2 is disposed between the detachable chassis 41 and the support main board 42;

[0053] The inner side of the fuselage body 1 is provided with a mounting portion 14, and the supporting main board 42 is locked and connected with the mounting portion 14 through a second locking member 52; in the specific implementation of the utility model, the mounting portions 14 can be provided on both sides of the bottom of the front end of the fuselage body 1 and both sides of the bottom of the rear end, and the four corners of the supporting main board 42 are locked and connected with the mounting portion 14 through the second locking member 52, so as to ensure that the supporting main board 42 can be reliably connected with the fuselage body 1;

[0054] The detachable chassis 41 and the supporting main board 42 are locked together by the third locking member 53. When the utility model is implemented, the middle parts of both ends of the detachable chassis 41 can be locked together with the supporting main board 42 by the third locking member 53. As a specific implementation of the utility model, the second locking member 52 and the third locking member 53 are both screws or bolts.

[0055] The utility model designs a support structure 4 including a detachable chassis 41 and a supporting main board 42, and utilizes a second locking component 52 to lock and connect the supporting main board 42 to the fuselage body 1, and utilizes a third locking component 53 to lock and connect the detachable chassis 41 to the supporting main board 42, so that the detachable chassis 41 can be easily disassembled and replaced during specific use, thereby being able to better adapt to various different scenarios and mounting requirements.

[0056] In the preferred embodiment of the present utility model, please refer to Figure 2 and Figure 6As shown, the four arms 2 are grouped in pairs, and in the two arms 2 in the same group, the upper surface of the other end of any one of the arms 2 is formed with a first assembling step 21, and the lower surface of the other end of the other arm 2 is formed with a second assembling step 22; the two arms 2 in the same group are assembled together through the first assembling step 21 and the second assembling step 22, and are locked and connected with the support structure 4 through the first locking member 51, and the first locking member 51 can be a bolt. When the utility model is implemented in a specific way, in the two arms 2 of the same group, in addition to being locked and connected together at the positions of the first assembling step 21 and the second assembling step 22 using a first locking component 51, the first locking component 51 sequentially passes through the detachable chassis 41, one arm 2 of the same group, and the other arm 2 of the same group and is locked to the supporting main board 42; it is also necessary to rotatably set a rotating shaft (not shown) at a position close to the first assembling step 21 or the second assembling step 22 on each of the arms 2, and then use a first locking component 51 for locking, and the first locking component 51 will sequentially pass through the inside of the detachable chassis 41 and the rotating shaft and be locked to the supporting main board 42. In this way, when the arm 2 needs to be folded, it is only necessary to remove the first locking component 51 at the positions of the first assembling step 21 and the second assembling step 22, so that the arm 2 can be rotated to achieve folding, and each time folding is required, it is only necessary to remove the two first locking components 51, which is very convenient to operate.

[0057] In a preferred embodiment of the utility model, the quad-rotor drone 100 further includes a control device 7, which is arranged on the top of the support structure 4, so as to support the control device 7 by the support structure 4, and hide the entire control device 7 inside the fuselage body 1. In the specific implementation of the utility model, the control device 7 is equipped with a battery to provide the required power supply, and the camera device 6 is electrically connected to the control device 7, so as to control the camera device 6 to work by the control device 7.

[0058] In a preferred embodiment of the present invention, the quad-rotor drone 100 further includes an antenna 8 , which is mounted at the tail of the fuselage body 1 , and is electrically connected to the control device 7 .

[0059] Although the specific implementation methods of the present invention are described above, those skilled in the art should understand that the specific embodiments described are only illustrative and are not intended to limit the scope of the present invention. Equivalent modifications and changes made by those skilled in the art in accordance with the spirit of the present invention should be included in the scope of protection of the claims of the present invention.

Claims

1. A portable quad-rotor drone, comprising a fuselage, four arms and four rotor assemblies, wherein one end of each arm is provided with a rotor assembly; characterized in that: A accommodating space is formed in the fuselage body, a first drag reduction structure is formed at the front end of the fuselage body, and a second drag reduction structure is formed on both sides of the fuselage body; a supporting structure is arranged at the bottom of the fuselage body, and the other end of each of the arms is locked and connected to the supporting structure through a first locking component.

2. A portable quad-rotor drone as claimed in claim 1, characterized in that: The first drag reduction structure is formed with a front windward surface located at the front end, a first side windward surface located on one side, a second side windward surface located on the other side, and an upper windward surface located at the top; the front windward surface is gradually inclined backward from bottom to top; the first side windward surface and the second side windward surface are both gradually inclined outward from front to back, and a first transition curved surface gradually expanding from inside to outside is formed between the first side windward surface and the second side windward surface and the fuselage body; the upper windward surface is gradually inclined backward from top to bottom, and a second transition curved surface gradually expanding from bottom to top is formed between the upper windward surface and the fuselage body.

3. A portable quad-rotor drone as claimed in claim 2, characterized in that: The bottom front end of the first drag reduction structure is formed with a lower windward surface which is gradually inclined backward from top to bottom, and a notch is formed on the lower windward surface.

4. A portable quad-rotor drone as claimed in claim 2, characterized in that: It also includes a camera device, which is installed inside the first drag reduction structure, and a shooting end of the camera device extends to the front windward surface.

5. A portable quad-rotor drone as claimed in claim 4, characterized in that: The first side windward surface and the second side windward surface are both provided with a connecting slot connected to the interior of the first drag reduction structure, and the connecting slot extends along the length direction of the fuselage body to the first transition curved surface.

6. A portable quad-rotor drone as claimed in claim 1, characterized in that: The second drag reduction structure is formed with a first inclined surface at the top, a second inclined surface at the middle, and a vertical plane at the bottom; the first inclined surface gradually inclines inward from top to bottom, the second inclined surface gradually inclines outward from top to bottom, and a third transition curved surface is formed between the second inclined surface and the vertical plane.

7. A portable quad-rotor drone as claimed in claim 1, characterized in that: The support structure includes a detachable chassis and a support mainboard, and the other end of each of the arms is arranged between the detachable chassis and the support mainboard; The inner side of the fuselage body is provided with a mounting part, and the supporting mainboard is locked and connected with the mounting part through a second locking member; the detachable chassis and the supporting mainboard are locked and connected with each other through a third locking member.

8. The portable quad-rotor drone according to claim 1, characterized in that: The four arms are grouped in pairs, and among the two arms in the same group, the upper surface of the other end of any one of the arms is formed with a first assembling step, and the lower surface of the other end of the other arm is formed with a second assembling step; the two arms in the same group are assembled together through the first assembling step and the second assembling step, and are locked and connected with the supporting structure through the first locking piece.

9. The portable quad-rotor drone according to claim 1, characterized in that: Also included is a control device, which is disposed on top of the support structure.

10. A portable quad-rotor drone as claimed in claim 9, characterized in that: It also includes an antenna, which is installed at the tail of the fuselage body and is electrically connected to the control device.

Images