CN206914622U - A kind of folding multi-rotor unmanned aerial vehicle - Google Patents

Abstract

The utility model discloses a foldable multi-rotor unmanned aerial vehicle, which comprises a fuselage, a fuselage arm and a landing gear. The fuselage includes an upper shell and a lower shell of the fuselage. The GPS bracket of the device; a plurality of arms are evenly hinged around the fuselage through the folded parts that are installed between the upper shell of the fuselage and the lower shell of the fuselage; the landing gear includes at least three independently arranged support rods and the The hinge at the top and the support rod are evenly distributed around the fuselage and are hinged to the machine arm through the hinge; meanwhile, the length of the support rod is greater than the length of the machine arm from the hinge to the motor installation end on the machine arm. The arms are folded through the folding parts, and the landing gear is folded through the hinges, so that the entire UAV can be folded and stored when transported or not in use. The length of the mounting end of the upper motor can still be supported by a support rod when the drone is in a folded state.

Description

A foldable multi-rotor UAV

technical field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a foldable multi-rotor unmanned aerial vehicle.

Background technique

Drone technology has advanced by leaps and bounds in recent years. Due to its low cost, good maneuverability, strong survivability, and no risk of casualties, UAVs occupy an extremely important position in modern military warfare, and they also have very broad prospects in the civilian field. Currently, they are used in aerial photography, agriculture, Plant protection, micro selfie, express transportation, disaster rescue, observing wild animals, monitoring infectious diseases, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, making romance and other occasions have been widely used, greatly expanding the UAV itself. use and value.

The current UAVs mainly include fixed-wing UAVs and rotary-wing UAVs, and multi-rotor UAVs have gradually become the mainstream of UAV development. General multi-rotor UAVs have a large arm extension space, which is not convenient for transportation and disassembly.

The patent document whose publication number is CN106477024A discloses a foldable eight-rotor drone, including a motor, a propeller, an arm, an upper fuselage shell, a lower fuselage shell, a landing gear cross bar, a landing gear vertical bar, and a battery box and the electric adjustment box; the upper shell of the fuselage is closed and connected to the lower shell of the fuselage, and the upper shell of the fuselage is a smooth and streamlined surface; the upper shell of the fuselage is connected with eight arms, and the arms include the first arm connector and the second arm Connecting piece, the lower ends of the first machine arm connecting piece and the second machine arm connecting piece are hinged through the rotating shaft, and also include the locking piece of the machine arm; the outer end of the machine arm is connected with the motor, propeller and electric adjustment box; the vertical rod of the landing gear The upper end is connected to the bottom side of the fuselage lower shell, and the landing gear cross bar is connected to the lower end of the landing gear vertical bar through a tee piece.

This invention realizes the folding of the machine arm by setting the first machine arm connecting piece and the second machine arm connecting piece, but this folding method still cannot fully fold the machine arm, and the landing gear of the landing gear cross bar and the landing gear vertical bar The structure is cumbersome and cannot be folded, causing the UAV of the invention to occupy a large space after being folded.

Utility model content

The purpose of this utility model is to provide a foldable multi-rotor UAV. The landing gear of the UAV can be folded together with the arm, so as to realize the maximum folding of the whole UAV, which is convenient for transportation and carrying.

In order to achieve the above object, the multi-rotor folding unmanned aerial vehicle provided by the utility model includes a fuselage, a fuselage arm and a landing gear. The fuselage includes a fuselage upper shell and a fuselage lower shell. The GPS bracket of the navigator; a plurality of arms are evenly hinged around the fuselage through the folded parts that are installed between the upper shell of the fuselage and the lower shell of the fuselage; the landing gear includes at least three independently arranged support rods and the support The hinge at the top of the rod, the support rod is evenly distributed around the fuselage and is hinged with the machine arm through the hinge; meanwhile, the length of the support rod is greater than the length of the machine arm from the hinge to the motor installation end on the machine arm.

In the above technical solution, the fuselage is divided into an upper shell and a lower shell for easy installation and disassembly.

The arms are folded through the folding parts, and the landing gear is folded through the hinges, so that the entire UAV can be folded and stored when transported or not in use. The length of the mounting end of the upper motor can still be supported by a support rod when the drone is in a folded state.

The specific solution is that the folding part includes a fixed part abutted between the upper shell of the fuselage and the lower shell of the fuselage and a movable part movably connected with the fixed part through a rotating shaft; the movable part is provided with a sleeve for connecting the machine arm; A first locking mechanism for fixing the movable part is provided between the fixed part and the movable part when the movable part drives the arm in an open state; the lower shell of the fuselage is provided with a second escape part for the movable part to move.

The machine arm folding part is arranged between the fuselage upper shell and the fuselage lower shell, so that the whole machine arm can be folded around the fuselage, and at the same time, the fixing of the machine arm when stretching is realized through the first locking mechanism. The folder has a simple structure and is applicable to various types of drones. The second avoidance part of the lower shell of the fuselage provides space for the movement of the rotating part to avoid hitting the fuselage.

A further specific solution is that the fixed part includes two fixed plates arranged at intervals and attached to the upper and lower fuselage shells and the lower shell of the fuselage respectively, and a connecting plate lapped on the top of the two fixed plates; the movable part is arranged between the two fixed plates, The rotation shaft passes through the lower part of the fixed plate.

A further specific solution is that the first locking mechanism includes a locking block arranged on the movable part away from the end of the rotating shaft, a threaded hole is provided on the locking block, and a through hole corresponding to the threaded hole is provided on the connecting plate ; The upper shell of the fuselage is provided with a first avoidance part for screwing. The screw cooperates with the threaded hole on the locking block through the through hole on the connecting plate to realize the locking function, thereby realizing the fixing of the machine arm when extending. The fuselage can be avoided when the screws of the first locking mechanism are tightened through the first avoiding portion of the upper shell of the fuselage.

Another specific solution is that the hinge includes a fixed ring for being sleeved on the machine arm, a mounting block for installing the fixed ring, and a rotating block that is movably connected with the mounting block through a rotating shaft, and one side of the rotating block is provided with a A sleeve for installing the support rod; a second locking mechanism for fixing the rotating block when the rotating block drives the supporting rod to be in a supporting state is provided between the rotating block and the mounting block.

By setting the landing gear as a support bar hinged with the arm, it can be folded relative to the arm, and at the same time, the arm can also be folded, and the arm and the support bar can be folded at the same time, occupying less space during transportation or carrying . The structure of the hinge connecting the support rod and the arm is simple, and it is easy to realize the folding of the support rod. The rotating block is locked by the locking mechanism, so that the structure of the landing gear is more stable.

A further specific solution is that a cavity is provided in the rotating block; the second locking mechanism includes a locking member that is slidably installed in the cavity and is provided with a buckle, and a buckle that is arranged on the mounting block for locking the buckle. Piece.

A further specific solution is that the cavity is provided with a spring supporting the locking member, and guide grooves are provided on both sides of the cavity to cooperate with the buckle to slide; the clamping block is provided with a clamping groove that can accommodate the buckle; the locking member It has a pressing portion extending out of the cavity.

When the support bar needs to be opened, press and hold the pressing part of the locking part, and at the same time turn the rotating block to make the support bar in a vertical state, then release the pressing part of the locking part, and push it outward under the elastic force of the spring to make the locking part The buckle is snapped into the clamping groove along the guide groove, and the support rod is opened and locked at this moment. When the support rod needs to be folded, the pressing part of the locking member is also pressed to make the buckle withdraw along the locking groove, and then the support rod is rotated along the rotation axis to be folded and folded.

The preferred solution is that the support rod has an outward angle along the vertical direction when it is in the supporting state, a cushion block with a sloped bottom is provided at the bottom end, and a wedge block is provided between the fixing ring and the mounting block to maintain the angle. This design makes the support more stable.

Another specific scheme is that the GPS bracket includes a chassis fixed on the upper casing of the fuselage, a pole vertically arranged on the chassis, and a mounting plate installed on the top of the pole and used to install the GPS navigator; There is an installation slot for installing the pole; the pole is trapezoidal with a narrow top and a wide bottom, the bottom end has a mounting bar fixed in the installation groove, and the top end has a threaded hole for installing the mounting plate, and the pole is equipped with a lightening A number of hollows under its own weight; a boss is provided at the bottom of the mounting plate, a fixing groove is arranged inside the boss, and a through hole corresponding to the threaded hole is provided at the bottom of the groove.

The GPS bracket has a stable structure, is not easily affected by weather, and firmly supports the GPS navigator, so that the signal transmission of the GPS navigator is more stable.

A further specific plan is that the chassis is provided with a number of arc holes for fixing and adjusting its own direction; the arc holes are provided with steps for easy installation of screws; The positioning holes are provided at both ends with threaded holes for fastening the mounting strips; the edge of the mounting plate is provided with a surrounding edge for installing and protecting the GPS navigator, and the surrounding edge is provided with a gap for passing the line.

The stability of the GPS bracket is further increased by setting the positioning holes and the rotating shaft matched with the positioning holes.

Compared with the prior art, the beneficial effects of the utility model are:

The utility model folds and sets the arms and the landing gear of the drone to make it more convenient for transportation and storage, and can be applied to various fields of drones, including agricultural drones or industrial drones.

Description of drawings

Fig. 1 is the front view of the utility model embodiment;

Fig. 2 is the top view of the utility model embodiment;

Fig. 3 is the perspective view of the utility model embodiment;

Fig. 4 is a perspective view of an embodiment of the utility model omitting one of the arms;

Fig. 5 is a front view of the arm folder of the embodiment of the present invention;

Fig. 6 is a perspective view of the arm folder of the embodiment of the present invention;

Fig. 7 is the front view of the landing gear hinge of the embodiment of the present invention;

Fig. 8 is a perspective view of the landing gear hinge of the embodiment of the present invention;

Fig. 9 is a front view of one implementation of the landing gear support rod of the embodiment of the present invention;

Fig. 10 is a front view of another embodiment of the landing gear support rod of the embodiment of the present invention;

Fig. 11 is the front view of the GPS bracket of the utility model embodiment;

Fig. 12 is a perspective view of the GPS bracket of the utility model embodiment;

Fig. 13 is a perspective view of the chassis of the GPS bracket of the utility model embodiment;

Fig. 14 is a perspective view of a pole of a GPS bracket according to an embodiment of the present invention;

Fig. 15 is a perspective view of the mounting plate of the GPS bracket according to the embodiment of the present invention.

detailed description

Below in conjunction with embodiment and accompanying drawing, the utility model is further described.

Example

Referring to FIGS. 1 to 3 , the foldable multi-rotor UAV includes a fuselage 1 , an arm 2 , a landing gear 3 and a GPS bracket 4 . The fuselage 1 is disc-shaped, and includes a fuselage upper shell 11 and a fuselage lower shell 12 . A plurality of machine arms 2 are evenly distributed around the disc-shaped fuselage 1, and are hinged with the fuselage 1 through a machine arm folder 5. The landing gear 3 includes more than three support rods 31 and the hinges 32 that the support rods 31 are hinged on the machine arm 2 or the fuselage 1. In this embodiment, the support rods 31 are respectively hinged on the machine arm 2, the bottom end of each support rod 31 is provided with a spacer 33. The GPS support 4 is arranged on the top of the fuselage 1, and the top of the GPS support 4 is equipped with a GPS navigator.

This embodiment is provided with eight machine arms 2 and three support rods 31 in total, and three support rods 31 are hinged on the first, third and sixth machine arms at intervals respectively, and are approximately evenly arranged to ensure that no one The stability of the aircraft during take-off and landing. Simultaneously, the length of support bar 31 is greater than the length of machine arm 2 from hinge 32 to the motor mounting end on the machine arm, so design is for when machine arm 2 and landing gear 3 draw in state, landing gear can still lift to whole unmanned aerial vehicle to the supporting role. In addition, in order to reduce the weight of the entire drone, the fuselage 1, the arm 2 and the support rod 31 are all made of carbon fiber, and the upper shell 11 and the lower shell 12 of the fuselage are hollowed out.

Referring to Fig. 3 to Fig. 6, the arm folding part 5 between the machine arm 2 and the fuselage 1 includes a fixed part 51 and a movable part 52, and the fixed part 51 and the movable part 52 are movably connected by a rotating shaft 53, and are connected between the fixed part 51 and the movable part 52. A first locking mechanism is provided between the movable parts 52 .

The fixing part 51 includes two fixed plates 511 arranged at intervals and attached to the fuselage upper shell 11 and the fuselage lower shell 12 up and down respectively, and a connecting plate 512 lapped on the top of the two fixed plates 511. The fixed plate 511 is fixed on the fuselage by screws. Between the shell 11 on the body and the lower shell 12 of the fuselage. The movable part 52 is disposed between the two fixed plates 511 , and the rotating shaft 53 passes through the lower part of the fixed plates 511 . A second escape portion 14 for moving the movable part 52 is provided on the lower shell 12 of the fuselage.

The movable part 52 includes a bottom plate 521 and an assembly plate 522 connected in an L shape. The rotating shaft 53 is arranged on the bottom plate 521 on the side away from the assembly plate 522. One side of the assembly plate 521 is provided with a sleeve for connecting the machine arm 2. Barrel 54. Threaded holes are provided on the peripheral surfaces of the machine arm 2 and the sleeve 54 for mounting screws, so that one end of the machine arm 2 is fixed in the sleeve 54, and the other end of the machine arm 2 is equipped with a propeller. In order to reduce the weight of the whole drone, a plurality of hollow parts 55 are provided on the fixed part 51 and the movable part 52 .

The locking mechanism includes a locking block 56 fixed on the upper part of the assembly plate. The locking block is provided with a threaded hole 57 , and the connecting plate 512 is provided with a through hole corresponding to the threaded hole 57 . When the movable part 52 drives the machine arm 2 to rotate to the open state, the locking block 56 is inserted into the fixing part 51, the threaded hole 57 is aligned with the through hole 58, and the locking screws are inserted into the through hole 58 and the threaded hole 57 in turn to tighten , A first escape portion 13 for screwing is provided on the upper casing 11 of the fuselage.

Referring to FIGS. 7 to 9 , the hinge 32 includes a fixed ring 321 , a mounting block 322 and a rotating block 323 . The fixing ring 321 is used to fix the machine arm, and is installed on one side of the mounting block 322 by screws. The rotating block 323 and the other side of the mounting block 322 are movably connected by the rotating shaft 324. The rotating block 323 is provided with a sleeve 325 for installing the support rod 31 on the side away from the mounting block 322, and the peripheral surface of the sleeve 325 is provided with a to the set screw 326 that fixes the support rod 31. A second locking mechanism for fixing the rotating block 323 is provided between the rotating block 323 and the mounting block 322 when the rotating block 323 drives the support rod 31 to be in a supporting state.

A cavity is provided on the rotating block 323 , and the locking mechanism includes a locking member 328 slidably installed in the cavity and provided with a buckle 329 , and a locking mechanism for locking the buckle 329 on the mounting block 322 . block 3221, at the same time, a spring 327 supporting the locking member 328 is provided in the cavity, guide grooves 3231 that cooperate with the buckle 329 to slide are set on both sides of the cavity, and a buckle that can accommodate the buckle 329 is provided on the clamping block 3221 Tight groove 3222. In order to adapt to the shape of the spring 327, the locking member 328 is a hollow cylinder, and a pressing portion adapted to fingers is provided at the pressing end of the locking member 328.

When the support rod 31 needs to be opened, press the pressing part of the locking member 328, and rotate the rotating block 323 at the same time, so that the supporting rod 31 is in a vertical state, then release the locking member 328, and push it outward under the elastic force of the spring 327 , so that the buckle 329 snaps into the clamping groove 3222 along the guide groove 3231 , and at this moment, the support rod 31 is opened and locked. When the support rod 31 needs to be folded, the pressing part of the locking block 328 is also pressed, so that the buckle 329 withdraws along the locking groove 3222, and then the support rod 31 is rotated along the rotating shaft 324 to be folded and folded.

The above support rods 31 are in a vertical state when they are opened. In order to make the support rods 31 more stable when they are opened, the support rods 31 can be inclined at a certain angle. Referring to FIG. A wedge-shaped pad is provided between the mounting block 322 , so that the mounting block 322 is inclined at a certain angle in the vertical direction relative to the fixing ring 321 . When the undercarriage 3 is opened, the three support rods 31 are tilted around, so that the support is more stable.

11 to 15, the GPS bracket 4 includes a chassis 41, a pole 42 and a mounting plate 43, the pole 42 is vertically fixed on the chassis 41, and the mounting plate 43 is fixed on the top of the pole 42 for installing a GPS navigator.

The chassis 41 is provided with some arc holes 411, and steps are arranged in the arc holes 411, which is convenient for installing screws. At the same time, the angle of the entire GPS bracket 4 can be rotatably adjusted through the arc-shaped hole 411, thereby adjusting the signal receiving direction of the GPS navigator, so as to find the best direction. The chassis 41 is provided with a mounting groove 412 for installing the pole 42 along the diameter direction. The middle part of the mounting groove 412 is provided with a positioning hole 413 aligned with the raised rotating shaft on the fuselage. The threaded hole 414 is used for fastening the pole 42 .

The pole 42 is a trapezoid with a narrow top and a wide bottom, and its thickness is between 5-8 mm. The bottom end has a mounting bar 421 matching the mounting groove 412 . The mounting bar 421 is provided with a through hole 422 corresponding to the threaded hole 414 . A top end of the pole 42 is provided with a threaded hole 423 for installing the mounting plate 43 . A number of hollows are provided on the pole 42 to reduce its own weight, and all the hollows are symmetrically arranged along the center line of the pole 42 for the sake of visual appearance.

The bottom end of the mounting plate 43 is provided with a boss 431, and the boss 431 is provided with a fixing groove 432 for accommodating and fixing the top of the strut 42. The bottom of the groove is provided with a through hole 433 corresponding to the threaded hole 423. A surrounding edge 434 for installing and protecting the GPS navigator is provided on the edge of the mounting plate 43, and a gap 435 for passing wires is provided on the surrounding edge 434.

The foldable multi-rotor drone of this embodiment can be applied to various fields of drones, including agricultural drones and industrial drones. At the same time, the above descriptions are only examples of the preferred implementation of the present utility model, and are not intended to limit the present utility model. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present utility model shall be included in the Within the protection scope of the present utility model.

Claims (10)

1. a kind of folding multi-rotor unmanned aerial vehicle, including fuselage, horn and undercarriage, it is characterised in that：

The fuselage includes fuselage upper casing and fuselage lower casing, and the GPS for installing GPS navigation device is provided with the fuselage upper casing Support；

Multiple horns to the folded piece between the fuselage upper casing and the fuselage lower casing by being uniformly hinged on institute State around fuselage；

The undercarriage includes at least three support bars being independently arranged and is arranged on the hinge part of the supporting bar top, described Support bar is evenly distributed on around fuselage and is hinged by the hinge part with the horn；

The length of the support bar is more than length of the horn from the hinge part to motor installation end on horn.

2. multi-rotor unmanned aerial vehicle according to claim 1, it is characterised in that：

Described folded piece includes being connected to the fixture between the fuselage upper casing and the fuselage lower casing and fixing with this The movable part that part is flexibly connected by rotary shaft；

The movable part is provided with the sleeve for being used for inserting the horn；

It is provided between the fixture and the movable part when the movable part drives the horn to be in open configuration to described The first retaining mechanism that movable part is fixed；

The fuselage lower casing is provided with the second relief portion being used for for movable part activity.

3. multi-rotor unmanned aerial vehicle according to claim 2, it is characterised in that：

Described fixture includes two and is arranged at intervals and touch the fixation of the fuselage upper casing and the fuselage lower casing respectively up and down Plate, and it is overlapped on the connecting plate on two fixed plate tops；

Described movable part is arranged between two fixed plates, and rotary shaft is passed through by the bottom of fixed plate.

4. multi-rotor unmanned aerial vehicle according to claim 3, it is characterised in that：

The first described retaining mechanism includes the latch segment being arranged far from the movable part of described rotary shaft one end, the latch segment On offer a screwed hole, a through hole corresponding with the screwed hole is offered on described connecting plate；

Described fuselage upper casing is provided with the first relief portion for twisting nail.

5. multi-rotor unmanned aerial vehicle according to claim 1, it is characterised in that：

Described hinge part include be used for be set on the horn retainer ring, for the mounting blocks of the retainer ring are installed with And the moving block being flexibly connected with the mounting blocks by rotary shaft, and described moving block side is provided with and is used to install the branch The sleeve of strut；

It is provided between the moving block and the mounting blocks when the moving block drives the support bar to be in holding state to institute State the second retaining mechanism that moving block is fixed.

6. multi-rotor unmanned aerial vehicle according to claim 5, it is characterised in that：

A cavity is provided with described moving block；

The second described retaining mechanism includes being slidably mounted in cavity and the locking member provided with buckle, and is arranged on the peace It is used for the clamping block for blocking the buckle on dress block.

7. multi-rotor unmanned aerial vehicle according to claim 6, it is characterised in that：

The spring for supporting the locking member is provided with described cavity, the both sides of cavity set the guiding for coordinating the buckle to slide Groove；

The clamping slot of the buckle can be accommodated by being offered on described clamping block；

Described locking member has the press section extended to outside cavity.

8. according to the multi-rotor unmanned aerial vehicle described in claim 5 to 7 any claim, it is characterised in that：

Described support bar vertically has outside angle in holding state, and its bottom is provided with a bottom surface as inclined-plane Cushion block, a wedge for keeping the angle is provided between the retainer ring and the mounting blocks.

9. multi-rotor unmanned aerial vehicle according to claim 1, it is characterised in that：

Chassis that described GPS supports include being fixed on the fuselage upper casing, the pole that is vertically set on the chassis with And it is installed on the pole top and the mounting disc for installing GPS navigation device；

The chassis is diametrically offering the mounting groove for installing the pole；

For the pole to be up-narrow and down-wide trapezoidal, bottom has the mounting bar being fixed in the mounting groove, and top, which is provided with, to be used for The screwed hole of the mounting disc is installed, and the pole is provided with to mitigate some hollow outs of own wt；

The bottom of the mounting disc is provided with boss, and fixing groove is provided with boss, and bottom land offers corresponding with the screwed hole logical Hole.

10. multi-rotor unmanned aerial vehicle according to claim 9, it is characterised in that：

Described chassis is provided with some for fixing and adjusting the arcuate socket in itself direction；

The step for being easily installed screw is provided with the arcuate socket；

The middle part of the mounting groove is provided with the positioning hole with raised rotary shaft contraposition on fuselage, and both ends, which are provided with, fastens the mounting bar Screwed hole；

The edge of the mounting disc is provided with the surrounding edge for being used for installing and protect GPS navigation device, is offered on the surrounding edge for leading to line Breach.