Portable quad-rotor unmanned aerial vehicle

Abstract

The invention discloses a portable quad-rotor unmanned aerial vehicle. The portable quad-rotor unmanned aerial vehicle comprises a fuselage main body; the vehicle arm mechanism comprises four vehicle arms, the four vehicle arms are hinged to the vehicle body, and a plurality of locking holes are formed in the outer sides of the hinged positions of the vehicle arms and the vehicle body; the locking mechanism comprises four locking assemblies, the four locking assemblies are installed on the four machine arms correspondingly, each locking assembly comprises a locking protruding head, a locking spring, a locking cylinder and a locking base, the locking bases are connected with the bottoms of the locking cylinders, locking movable cavities are formed in the locking cylinders, the bottoms of the locking springs and the bottoms of the locking protruding heads are located in the locking movable cavities, and the locking springs are located in the locking movable cavities. One end of the locking spring abuts against the locking base, the other end of the locking spring abuts against the bottom of the locking protruding head, the locking protruding head can move up and down in the locking movable cavity, and the top of the locking protruding head can enter the locking hole to be locked. Wherein the fuselage, the fuselage upper cover and the arms are formed through 3D printing, and the problems that a four-rotor unmanned aerial vehicle is high in manufacturing cost and long in manufacturing period are solved.

Description

Technical Field

[0001] The present application relates to the field of aircraft technology, and more specifically, to a portable quad-rotor drone. Background Art

[0002] With the development of the drone industry, drone technology has been widely used in both military and civilian fields. Drones generally include a fuselage and an arm, which are generally produced by mold manufacturing. However, due to the complexity of the mold and the long production cycle, the mold cost is high, which leads to a high production cost of drones. In addition, current drones are large in size and inconvenient to transport. Therefore, there is an urgent need for a drone with low manufacturing cost and easy transportation. Summary of the invention

[0003] The purpose of this application is to provide a portable quad-rotor drone to solve the problem of high manufacturing cost and inconvenient transportation of drones in the prior art. The technical solution is as follows:

[0004] The present application provides a portable quad-rotor drone, comprising:

[0005] The fuselage body comprises a fuselage and a fuselage cover, wherein the fuselage cover is detachably connected to the fuselage;

[0006] An arm mechanism, the arm mechanism comprising four arms, wherein two of the arms are respectively located on both sides of the front end of the fuselage, and the other two arms are respectively located on both sides of the rear end of the fuselage, the four arms are respectively hinged to the fuselage, and a plurality of locking holes are provided on the outer sides of the hinges between the arms and the fuselage;

[0007] A locking mechanism, wherein the locking mechanism comprises four locking assemblies, the four locking assemblies are respectively mounted on the four machine arms, the four machine arms are respectively locked by the four locking assemblies, the locking assembly comprises a locking convex head, a locking spring, a locking cylinder and a locking base, the locking base is connected to the bottom of the locking cylinder, the locking cylinder has a locking activity cavity inside, the locking spring and the bottom of the locking convex head are located in the locking activity cavity, one end of the locking spring abuts against the locking base, the other end of the locking spring abuts against the bottom of the locking convex head, the locking convex head can move up and down in the locking activity cavity, and the top of the locking convex head can enter the locking hole and lock;

[0008] Among them, the fuselage, the fuselage upper cover and the fuselage arm are all made by 3D printing.

[0009] In one embodiment, two locking holes are provided on the outer side of the hinge between the arm and the fuselage, and when the locking protrusion enters one of the locking holes, the arm is in an extended state; when the locking protrusion enters the other locking hole, the arm is folded on the side of the fuselage.

[0010] In one embodiment, one end of the four arms is hinged to the fuselage through a rotating shaft, one end of the four arms has a locking mounting groove, the four locking components are respectively installed in the four locking mounting grooves, the upper surface of the locking cylinder is flush with the upper surface of the locking mounting groove, or the upper surface of the locking cylinder is lower than the upper surface of the locking mounting groove.

[0011] In one embodiment, a motor mechanism is respectively installed at the other end of the four arms, and the motor mechanism includes a drive motor, two propellers and a propeller mounting seat. The drive shaft of the drive motor is connected to the propeller mounting seat, and the two propellers are respectively movably connected to the propeller mounting seat, and the propeller can rotate relative to the propeller mounting seat.

[0012] In one embodiment, the portable quadrotor drone also includes two antenna assemblies and two landing gear assemblies, wherein two of the arms are front arms, and the other two arms are rear arms, and the two antenna assemblies each include an antenna and an antenna articulation seat, and the antenna articulation seats of the two antenna assemblies are respectively installed on the two front arms, and the antenna is hinged to the antenna articulation seat; the two landing gear assemblies include a landing gear and a landing gear articulation seat, and the landing gear articulation seats of the two landing gear assemblies are respectively installed on the two rear arms, and the landing gear is connected to the landing gear articulation seat.

[0013] In one embodiment, the portable quadrotor drone also includes a power supply module, which includes an onboard battery and a battery fixing assembly, the onboard battery is installed on the fuselage, the battery fixing assembly is installed on the onboard battery, and the onboard battery is detachably connected to the fuselage via the battery fixing assembly.

[0014] In one embodiment, there are two battery fixing assemblies, and the two battery fixing assemblies respectively include a fixing boss, a fixing spring, a fixing cylinder and a fixing base. The fixing base is installed at the bottom of the fixing cylinder, and the interior of the fixing cylinder has a fixed cavity. The fixing spring and the bottom of the fixing boss are located in the fixed cavity. One end of the fixing spring is against the fixing base, and the other end of the fixing spring is connected to the bottom of the fixing boss. The fixing boss can move in the fixed cavity. There are fixed installation grooves on both sides of the onboard battery respectively. The fixing base and the fixing cylinder are installed in the fixed installation grooves. A fixing hole is provided at the corresponding position on the fuselage, and the top of the fixing boss can enter the fixing hole to achieve locking.

[0015] In one embodiment, the portable quadrotor drone also includes a plurality of airborne equipment brackets, a plurality of bracket slots are respectively provided on the inner walls on both sides of the fuselage, mounting plates are respectively provided at both ends of the airborne equipment brackets, the mounting plates match the bracket slots, the mounting plates are installed inside the bracket slots, and the plurality of airborne equipment brackets are spaced apart along the length direction of the fuselage.

[0016] In one embodiment, the machine cover has a plurality of airborne equipment holes, the plurality of airborne equipment holes are respectively located above the plurality of airborne equipment brackets, and a circle of sealing strips is provided on the inner walls of the plurality of airborne equipment holes.

[0017] In one embodiment, a plurality of reinforcing ribs are provided inside the fuselage, and a plurality of heat dissipation holes are provided on the fuselage.

[0018] The advantages or principles of this application are described below:

[0019] The portable quad-rotor drone of the embodiment of the present application includes a fuselage body, an arm mechanism and a locking mechanism. The fuselage body includes a fuselage and a fuselage upper cover. The arm mechanism includes four arms. The fuselage, the fuselage upper cover and the arms are all made of 3D printing, which solves the problems of high manufacturing cost and long manufacturing cycle of the drone. The locking mechanism includes four locking components, and the four arms are locked by four locking components respectively. When the portable quad-rotor drone is in use, the locking component is first installed on the arm. When the arm is rotated to the target angle, the locking protrusion of the locking component can automatically enter the corresponding locking hole and lock under the action of the locking spring. Since there are multiple locking holes, the arm can be rotated to the side of the fuselage to achieve locking, avoiding the excessive size of the quad-rotor drone during transportation, thereby facilitating the transportation of the quad-rotor drone. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of a portable quad-rotor drone in the unfolded state;

[0021] Figure 2 It is a schematic diagram of a portable quadrotor drone in a folded state;

[0022] Figure 3 This is a schematic diagram of the internal structure of a portable quadrotor drone;

[0023] Figure 4 This is another schematic diagram of the internal structure of a portable quadrotor drone;

[0024] Figure 5 It is a structural diagram of the arm mechanism;

[0025] Figure 6 is a cross-sectional view of the locking assembly;

[0026] Figure 7 This is an exploded view of the onboard battery and fuselage;

[0027] Figure 8 It is an exploded view of the onboard battery and battery fixing assembly;

[0028] Fig. 9 is a cross-sectional view of a battery fixing assembly;

[0029] Description of reference numerals:

[0030] 1. Body; 2. Arm mechanism; 3. Locking mechanism; 11. Body; 12. Body cover; 13. Locking hole; 31. Locking assembly; 311. Locking convex head; 312. Locking spring; 313. Locking cylinder; 314. Locking base; 315. Locking movable cavity; 14. Connecting hole; 21. Locking mounting groove; 316. Locking fixing plate; 317. Locking blocking plate; 318. Locking moving hole; 22. Front arm; 23. Rear arm; 4. Motor mechanism; 41. Drive motor; 42. Propeller; 43. Propeller mounting seat; 44. Motor mounting seat; 45. Hexagon socket bolt; 5. Antenna assembly; 51. Antenna; 52. Antenna articulated seat ; 53. Articulated joint; 6. Landing gear assembly; 61. Landing gear; 62. Landing gear hinge seat; 7. Power supply module; 71. Airborne battery; 72. Battery fixing assembly; 73. Power socket; 15. Battery mounting position; 721. Fixed boss; 722. Fixed spring; 723. Fixed cylinder; 724. Fixed base; 725. Fixed cavity; 726. Fixed plate; 727. Fixed blocking plate; 728. Fixed movable hole; 74. Fixed mounting slot; 16. Fixed hole; 8. Airborne equipment bracket; 17. Bracket slot; 81. Mounting card plate; 9. Airborne equipment hole position; 91. Sealing strip; 18. Reinforcement rib; 19. Heat dissipation hole position; 10. Rotating shaft. DETAILED DESCRIPTION

[0031] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "middle", "inside", etc. indicate the orientation or position relationship based on the orientation or position relationship shown in the drawings, which is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation of the present application. In addition, the terms "first", "second", etc. are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first", "second", etc. may explicitly or implicitly include one or more of the features. In the description of the present application, it should be noted that, unless otherwise clearly specified and defined, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be directly connected, or indirectly connected through an intermediate medium, or it can be the internal communication of two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present application can be understood by specific circumstances.

[0032] The preferred embodiments of the present application are described in detail below in conjunction with the accompanying drawings so that the advantages and features of the present application can be more easily understood by those skilled in the art, thereby making a clearer and more definite definition of the protection scope of the present application.

[0033] like Figures 1 to 9As shown, an embodiment of the present application provides a portable quad-rotor drone, including a fuselage body 1, an arm mechanism 2 and a locking mechanism 3. The fuselage body 1 includes a fuselage 11 and a fuselage upper cover 12, and the fuselage upper cover 12 is detachably connected to the fuselage 11. The arm mechanism 2 includes four arms, two of which are respectively located on both sides of the front end of the fuselage 11, and the other two arms are respectively located on both sides of the rear end of the fuselage 11. The four arms are respectively hinged to the fuselage 11, and a plurality of locking holes 13 are provided on the outer sides of the hinges between the arms and the fuselage 11. The locking mechanism 3 includes four locking assemblies 31, and the four locking assemblies 31 are respectively installed on the four arms, and the four arms are respectively locked by the four locking assemblies 31. The locking assembly 31 includes a locking protrusion 311, a locking spring 312, a locking cylinder 313 and a locking base 314. The locking base 314 is connected to the bottom of the locking cylinder 313. The locking cylinder 313 has a locking activity cavity 315 inside. The bottom of the locking spring 312 and the locking convex head 311 are located in the locking activity cavity 315. One end of the locking spring 312 abuts against the locking base 314, and the other end of the locking spring 312 abuts against the bottom of the locking convex head 311. The locking convex head 311 can move up and down in the locking activity cavity 315, and the top of the locking convex head 311 can enter the locking hole 13 to lock. Among them, the fuselage 11, the fuselage upper cover 12, and the fuselage arm are all made of 3D printing.

[0034] Since the fuselage 11, the upper cover 12 and the arms are all made of 3D printing, the problems of high manufacturing cost and long manufacturing cycle of the quadcopter are solved. The locking mechanism 3 includes four locking components 31, and the four arms are locked by four locking components 31 respectively. When the portable quadcopter is in use, the locking component 31 is first installed on the arm. When the arm is rotated to the target angle, the locking protrusion 311 of the locking component 31 can automatically enter the corresponding locking hole 13 and lock under the action of the locking spring 312. Since there are multiple locking holes 13, the arm can be rotated to the side of the fuselage 11 to achieve locking, avoiding the excessive size of the quadcopter during transportation, thereby facilitating the transportation of the quadcopter.

[0035] In order to achieve detachable connection between the upper cover 12 and the body 11, connection holes 14 are respectively provided at corresponding positions of the body 11 and the upper cover 12, and the upper cover 12 and the body 11 can be detachably connected by inserting screws into the connection holes 14. Preferably, there can be a plurality of connection holes 14, and the plurality of connection holes 14 are respectively located at different parts of the upper cover 12, so that the upper cover 12 and the body 11 are fixed more firmly.

[0036] In one embodiment, in order to realize the installation of the locking assembly 31 on the fuselage 11, one end of each of the four arms has a locking installation groove 21, and the four locking assemblies 31 are respectively installed in the four locking installation grooves 21. The upper surface of the locking cylinder 313 is flush with the upper surface of the locking installation groove 21, or the upper surface of the locking cylinder 313 is lower than the upper surface of the locking installation groove 21. Among them, the inner diameter of the locking installation groove 21 matches the outer diameter of the locking cylinder 313, so that the locking cylinder 313 is directly placed in the locking installation groove 21 for installation.

[0037] In one embodiment, one end of the four arms is respectively hinged to the fuselage 11 through the rotating shaft 10, and the arms can rotate relative to the rotating shaft 10. The arms of the embodiment of the present application can achieve two different states, one of which is that the arms are in an extended state relative to the fuselage 11; the other is that the arms are in a folded state relative to the fuselage 11.

[0038] In order to lock the machine arm in both the extended and folded states, two locking holes 13 are provided on the outer side of the hinge between the machine arm and the machine body 11. When the locking protrusion 311 enters one of the locking holes 13, the machine arm is in the extended state; when the locking protrusion 311 enters the other locking hole 13, the machine arm is folded on the side of the machine body 11. The locking hole 13 is located above the machine arm.

[0039] When the portable quad-rotor drone of the embodiment of the present application is used, the locking assembly 31 is first installed in the locking installation slot 21, and then the arm is installed on the fuselage 11 through the rotating shaft 10, and then the arm is rotated to the target angle, that is, the arm is rotated to the extended state, at this time, the locking protrusion 311 is opposite to the position of one of the locking holes 13, and under the action of the locking spring 312, the locking protrusion 311 moves upward, thereby entering the locking hole 13 for locking. When the arm needs to be rotated to the side of the fuselage 11 and folded, the top of the locking protrusion 311 is manually pressed to make the locking protrusion 311 move downward and disengage from the locking hole 13, and the locking spring 312 is in a compressed state. Then the arm is rotated to the target angle, that is, the arm is rotated to the folded state, at this time, the locking protrusion 311 is opposite to the position of another locking hole 13, and under the action of the locking spring 312, the locking protrusion 311 moves upward, thereby entering the other locking hole 13 for locking. During the rotation of the machine arm, due to the obstruction of the machine body 11 , the locking protrusion 311 cannot move upward under the elastic force of the locking spring 312 .

[0040] In one embodiment, the locking base 314 and the locking cylinder 313 can be connected and fixed by bolts or the like. In order to prevent the locking boss 311 from coming out of the locking cylinder 313, a locking fixing plate 316 is provided at the bottom of the locking boss 311, a locking blocking plate 317 is provided at the upper part of the locking cylinder 313, a locking moving hole 318 is provided in the middle of the locking blocking plate 317, the top of the locking boss 311 passes through the locking moving hole 318, and the locking fixing plate 316 is located below the locking blocking plate 317. The diameter of the locking fixing plate 316 is larger than the diameter of the locking moving hole 318, so that the locking fixing plate 316 can be prevented from coming out of the locking moving hole 318. Preferably, the locking cylinder 313 can be configured to be cylindrical.

[0041] In one embodiment, two of the machine arms are the front arms 22, and the other two of the machine arms are the rear arms 23, and the rear arms 23 are located below the front arms 22. When the front arms 22 and the rear arms 23 are folded, the front arms 22 are folded toward the rear of the fuselage 11, and the rear arms 23 are folded toward the front of the fuselage 11, so that the front arms 22 and the rear arms 23 are folded, and after folding, the front arms 22 and the rear arms 23 do not interfere with each other.

[0042] In one embodiment, the other ends of the four arms are respectively installed with motor mechanisms 4, which include a driving motor 41, two propellers 42 and a propeller mounting seat 43. The driving shaft of the driving motor 41 is connected to the propeller mounting seat 43, and the two propellers 42 are respectively movably connected to the propeller mounting seat 43, and the propellers 42 can rotate relative to the propeller mounting seat 43.

[0043] Specifically, a motor fixing seat 44 is fixed to the other end of the arm by bolt connection or the like, and the drive motor 41 is fixed to the motor fixing seat 44. One end of the propeller 42 is fixed to the propeller mounting seat 43 by an inner hexagonal bolt 45, and a sealing gasket is provided between the upper surface and the lower surface of the propeller 42 and the propeller mounting seat 43, and the propeller 42 is fixed to the propeller mounting seat 43 by the inner hexagonal bolt 45 and the sealing gasket. When the propeller 42 needs to be folded, the propeller 42 is manually rotated to adjust its position, and it is ready when it is adjusted to a predetermined angle. When the portable quad-rotor drone is transported, the propeller 42 can be folded up to reduce the volume for easy transportation. Under flight conditions, after the drive motor 41 drives the propeller mounting seat 43 and the propeller 42 to rotate, the propeller 42 automatically unfolds under the action of its own inertia.

[0044] In one embodiment, the portable quad-rotor drone further includes two antenna assemblies 5, each of which includes an antenna 51 and an antenna hinge seat 52. The antenna hinge seats 52 of the two antenna assemblies 5 are respectively mounted on the two front arms 22 of the machine, and the antenna 51 is hinged to the antenna hinge seat 52. Specifically, the antenna hinge seat 52 is fixed to the front arm 22 of the machine by screws, and the antenna hinge seat 52 has a hinge head 53. The antenna 51 and the hinge head 53 are connected by means of threads, buckles, and slots, so that the antenna 51 can rotate relative to the antenna hinge seat 52.

[0045] In another embodiment, the portable quad-rotor drone further includes two landing gear assemblies 6, and the two landing gear assemblies 6 include a landing gear 61 and a landing gear articulated seat 62. The landing gear articulated seats 62 of the two landing gear assemblies 6 are respectively mounted on the two rear arms 23 by screws, etc., and the landing gear 61 is connected to the landing gear articulated seat 62. Specifically, the landing gear articulated seat 62 also has an articulated head 53, and the landing gear 61 and the articulated head 53 are connected by means of threads or buckles and slots, so that the landing gear 61 can rotate relative to the landing gear articulated seat 62.

[0046] The hinged joint 53 connected to the antenna 51 and the hinged joint 53 connected to the landing gear 61 may have the same structure, and there is a certain friction force between the two hinged parts of the hinged joint 53 to prevent the parts from moving by themselves without the action of external force. When the antenna 51 or the landing gear 61 is rotated to a specific position, the friction force can be used to maintain the stability of the antenna 51 or the landing gear 61. In other embodiments, the hinged joint 53 can also be other existing hinged joints 53 with a self-locking function to maintain the antenna 51 or the landing gear 61 in a specific position. Under flight conditions, the antenna 51 and the landing gear 61 are unfolded, and the antenna 51 can also serve as the front landing gear 61; in the transportation state, the antenna 51 and the landing gear 61 can be rotated to a horizontal state and folded up, thereby reducing the volume for easy transportation.

[0047] In one embodiment, the portable quad-rotor drone further includes a power supply module 7, which includes an onboard battery 71 and a battery fixing assembly 72. The onboard battery 71 is mounted on the fuselage 11, and the battery fixing assembly 72 is mounted on the onboard battery 71. The onboard battery 71 is detachably connected to the fuselage 11 through the battery fixing assembly 72. The onboard battery 71 has a power socket 73, and the onboard battery 71 supplies power to the portable quad-rotor drone. The fuselage 11 has a battery mounting position 15, and the onboard battery 71 is mounted on the battery mounting position 15.

[0048] There are two battery fixing assemblies 72, and the two battery fixing assemblies 72 respectively include a fixing convex head 721, a fixing spring 722, a fixing cylinder 723 and a fixing base 724. The fixing base 724 is installed at the bottom of the fixing cylinder 723, and the interior of the fixing cylinder 723 has a fixing cavity 725, and the bottoms of the fixing spring 722 and the fixing convex head 721 are located in the fixing cavity 725. One end of the fixing spring 722 abuts against the fixing base 724, and the other end of the fixing spring 722 is connected to the bottom of the fixing convex head 721, and the fixing convex head 721 can move in the fixing cavity 725.

[0049] The fixed base 724 and the fixed cylinder 723 can be connected by bolts or other means. In order to prevent the fixed protrusion 721 from falling out of the fixed cylinder 723, a fixed plate 726 is provided at the bottom of the fixed protrusion 721, and a fixed blocking plate 727 is provided at the upper part of the fixed cylinder 723. The middle part of the fixed blocking plate 727 has a fixed movable hole 728. The top of the fixed protrusion 721 passes through the fixed movable hole 728, and the fixed plate 726 is located below the fixed blocking plate 727. The diameter of the fixed plate 726 is larger than the diameter of the fixed movable hole 728, so that the fixed plate 726 can be prevented from falling out of the fixed movable hole 728. Preferably, the fixed cylinder 723 can be set to be cylindrical.

[0050] There are fixing grooves 74 on both sides of the onboard battery 71, and the fixing base 724 and the fixing cylinder 723 are installed in the fixing grooves 74. A fixing hole 16 is provided at a corresponding position on the fuselage 11, and the top of the fixing boss 721 can enter the fixing hole 16 to achieve locking.

[0051] When installing the airborne battery 71, first install the fixing base 724 and the fixing cylinder 723 in the fixing installation groove 74, then press the top of the fixing protrusion 721 to move the fixing protrusion 721 into the fixing cylinder 723, and then insert the airborne battery 71 from the rear of the fuselage 11 into the battery installation position 15 on the fuselage 11. When the airborne battery 71 is installed in place, the fixing protrusion 721 of the battery fixing assembly 72 automatically springs into the corresponding fixing hole 16 on the fuselage 11 under the elastic force of the fixing spring 722 to achieve locking, thereby preventing the airborne battery 71 of the portable quad-rotor drone from falling off when in operation.

[0052] When the fixing protrusion 721 enters the fixing hole 16 and is locked, the top of the fixing protrusion 721 protrudes from the side of the fuselage 11. When the onboard battery 71 needs to be removed, the top of the fixing protrusion 721 is manually pressed to disengage the fixing protrusion 721 from the fixing hole 16, so that the onboard battery 71 can be quickly removed. The onboard battery 71 of the embodiment of the present application is easy to install and remove, thereby facilitating the charging and maintenance of the onboard battery 71.

[0053] In one embodiment, the portable quad-rotor drone further includes a plurality of airborne equipment brackets 8, and the airborne equipment brackets 8 can be detachably connected to the fuselage 11. In order to realize the detachable connection between the airborne equipment brackets 8 and the fuselage 11, a plurality of bracket card slots 17 are respectively provided on the inner walls on both sides of the fuselage 11, and mounting card plates 81 are respectively provided at both ends of the airborne equipment bracket 8, and the mounting card plates 81 match the bracket card slots 17, and the mounting card plates 81 are installed inside the bracket card slots 17. The plurality of airborne equipment brackets 8 are arranged at intervals along the length direction of the fuselage 11. When installing the airborne equipment bracket 8, the two mounting card plates 81 on the airborne equipment bracket 8 can be directly inserted into the corresponding bracket card slots 17.

[0054] Since the airborne equipment bracket 8 is provided, the airborne equipment and the like can be installed on the airborne equipment bracket 8, and then the airborne equipment and the airborne equipment bracket 8 can be installed as a whole on the fuselage 11, thereby realizing the rapid installation and removal of the airborne equipment.

[0055] The cover has a plurality of airborne equipment holes 9, which are respectively located above a plurality of airborne equipment brackets 8, and a circle of sealing strips 91 are provided on the inner walls of the plurality of airborne equipment holes 9. The airborne equipment holes 9 can be provided to meet the requirements of exposing special airborne equipment or to facilitate heat dissipation of airborne equipment. The provision of the sealing strips 91 can achieve sealing between the airborne equipment and the airborne equipment holes 9, meet the rainproof requirements of the portable quad-rotor drone, and avoid the problem that the portable quad-rotor drone is easily damaged when working in bad weather.

[0056] In one embodiment, a plurality of reinforcing ribs 18 are provided inside the fuselage 11 to improve the strength of the fuselage 11. A plurality of heat dissipation holes 19 are provided on the fuselage 11, and the plurality of heat dissipation holes 19 can be respectively located on the sides of the fuselage 11. The provision of the heat dissipation holes 19 can facilitate the heat dissipation of the airborne equipment and also help reduce the weight of the fuselage 11.

[0057] The front arm 22, rear arm 23, antenna 51, landing gear 61 and propeller 42 of the portable quadrotor drone in the embodiment of the present application are all foldable, which solves the problem of the portable quadrotor drone being too large during transportation and facilitates the carrying and transportation of the portable quadrotor drone.

[0058] The 3D printing technology used in the embodiments of the present application is the existing 3D printing technology, and there is no improvement on the 3D printing technology itself.

[0059] The implementation methods of the present application are not limited to this. According to the above content of the present application, by utilizing common technical knowledge and customary means in the field, without departing from the above basic technical ideas of the present application, the present application may also make other various forms of modification, replacement or combination, all of which fall within the scope of protection of the present application.

Claims

1. A portable quad-rotor drone, characterized in that: include: The fuselage body comprises a fuselage and a fuselage cover, wherein the fuselage cover is detachably connected to the fuselage; An arm mechanism, the arm mechanism comprising four arms, wherein two of the arms are respectively located on both sides of the front end of the fuselage, and the other two arms are respectively located on both sides of the rear end of the fuselage, the four arms are respectively hinged to the fuselage, and a plurality of locking holes are provided on the outer sides of the hinges between the arms and the fuselage; A locking mechanism, wherein the locking mechanism comprises four locking assemblies, the four locking assemblies are respectively mounted on the four machine arms, the four machine arms are respectively locked by the four locking assemblies, the locking assembly comprises a locking convex head, a locking spring, a locking cylinder and a locking base, the locking base is connected to the bottom of the locking cylinder, the locking cylinder has a locking activity cavity inside, the locking spring and the bottom of the locking convex head are located in the locking activity cavity, one end of the locking spring abuts against the locking base, the other end of the locking spring abuts against the bottom of the locking convex head, the locking convex head can move up and down in the locking activity cavity, and the top of the locking convex head can enter the locking hole and lock; Among them, the fuselage, the fuselage upper cover and the fuselage arm are all made by 3D printing.

2. The portable quad-rotor drone according to claim 1, characterized in that: Two locking holes are provided on the outer side of the hinge between the machine arm and the machine body, and when the locking protrusion enters one of the locking holes, the machine arm is in an extended state; When the locking protrusion enters the other locking hole, the machine arm is folded on the side of the machine body.

3. The portable quad-rotor drone according to claim 1, characterized in that: One end of the four arms is hinged to the fuselage through a rotating shaft, and one end of the four arms has a locking installation groove, and the four locking components are respectively installed in the four locking installation grooves, and the upper surface of the locking cylinder is flush with the upper surface of the locking installation groove, or the upper surface of the locking cylinder is lower than the upper surface of the locking installation groove.

4. The portable quad-rotor drone according to any one of claims 1 to 3, characterized in that: The other ends of the four arms are respectively installed with motor mechanisms, which include a drive motor, two propellers and a propeller mounting seat. The drive shaft of the drive motor is connected to the propeller mounting seat, and the two propellers are respectively movably connected to the propeller mounting seat, and the propeller can rotate relative to the propeller mounting seat.

5. The portable quad-rotor drone according to any one of claims 1 to 3, characterized in that: The portable quad-rotor UAV also includes two antenna assemblies and two landing gear assemblies, wherein two of the arms are front arms, and the other two arms are rear arms. The two antenna assemblies each include an antenna and an antenna hinge seat, and the antenna hinge seats of the two antenna assemblies are respectively installed on the two front arms, and the antenna is hinged to the antenna hinge seat; the two landing gear assemblies include a landing gear and a landing gear hinge seat, and the landing gear hinge seats of the two landing gear assemblies are respectively installed on the two rear arms, and the landing gear is connected to the landing gear hinge seat.

6. The portable quad-rotor drone according to any one of claims 1 to 3, characterized in that: The portable quad-rotor drone also includes a power supply module, which includes an onboard battery and a battery fixing assembly. The onboard battery is installed on the fuselage, and the battery fixing assembly is installed on the onboard battery. The onboard battery is detachably connected to the fuselage via the battery fixing assembly.

7. The portable quad-rotor drone according to claim 6, characterized in that: There are two battery fixing assemblies, and the two battery fixing assemblies respectively include a fixing convex head, a fixing spring, a fixing cylinder and a fixing base. The fixing base is installed at the bottom of the fixing cylinder. The interior of the fixing cylinder has a fixing cavity. The fixing spring and the bottom of the fixing convex head are located in the fixing cavity. One end of the fixing spring is against the fixing base, and the other end of the fixing spring is connected to the bottom of the fixing convex head. The fixing convex head can move in the fixing cavity. There are respectively fixed installation grooves on both sides of the onboard battery. The fixing base and the fixing cylinder are installed in the fixed installation grooves. A fixing hole is provided at the corresponding position on the fuselage, and the top of the fixing convex head can enter the fixing hole to achieve locking.

8. The portable quad-rotor drone according to claim 6, characterized in that: The portable quad-rotor drone also includes a plurality of airborne equipment brackets, a plurality of bracket slots are respectively provided on the inner walls on both sides of the fuselage, mounting plates are respectively provided at both ends of the airborne equipment brackets, the mounting plates match the bracket slots, the mounting plates are installed inside the bracket slots, and the plurality of airborne equipment brackets are spaced apart along the length direction of the fuselage.

9. The portable quad-rotor drone according to claim 8, characterized in that: The machine cover is provided with a plurality of airborne equipment holes, the plurality of airborne equipment holes are respectively located above the plurality of airborne equipment brackets, and a circle of sealing strips is provided on the inner walls of the plurality of airborne equipment holes.

10. The portable quad-rotor drone according to claim 1, characterized in that: A plurality of reinforcing ribs are arranged inside the fuselage, and a plurality of heat dissipation holes are arranged on the fuselage.

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