CN212921947U - Rotary folding unmanned aerial vehicle - Google Patents

Abstract

The utility model provides a rotary folding type unmanned aerial vehicle, which comprises a vehicle body, a plurality of arms and a plurality of power components, wherein the arms are arranged on the vehicle body, the arms extend outwards from the vehicle body, the power components are arranged on the axial free ends of the arms, the power components comprise motors and propellers, the motors drive the propellers to rotate, a rotating shaft is arranged on the vehicle body, the arms are connected with the rotating shaft, and the arms rotate around the rotating shaft; the unmanned aerial vehicle is characterized in that a plurality of lock catch pieces are arranged on the body, the lock catch pieces are located between the axial free ends of the booms and the rotating shaft, locking grooves are formed in the lock catch pieces, the lock catch pieces are located in the unfolding direction of the booms, the booms penetrate through openings of the locking grooves, the booms are located in the locking grooves, the booms are connected with the lock catch pieces in a clamping mode, the plurality of unfolded booms are folded through rotation, and the folded unmanned aerial vehicle is in a long strip shape, so that the size of the unmanned aerial vehicle is effectively reduced; unmanned aerial vehicle expandes the back, and the horn passes through buckle structure to be fixed in the locking inslot of hasp piece, avoids the horn position deviation to appear, leads to the emergence of flight accident.

Description

Rotary folding unmanned aerial vehicle

Technical Field

The utility model relates to an unmanned aerial vehicle field specifically relates to a rotatory foldable unmanned aerial vehicle.

Background

Along with the improvement of people's good sensitivity to unmanned aerial vehicle's use, people hope that unmanned aerial vehicle can use and use simultaneously in more scenes, when carrying out the scene switch, need transport unmanned aerial vehicle. In the transportation process, people also have higher and higher requirements on the size of the unmanned aerial vehicle, and the occupied space volume is required to be reduced in the transportation process, so that the arm of the unmanned aerial vehicle needs to be folded. But current unmanned aerial vehicle folding mechanism is comparatively complicated, complex operation, and the process of folding or expanding causes the damage to unmanned aerial vehicle easily. Unmanned aerial vehicle expandes the back, does not have on the unmanned aerial vehicle to set up horn fixed knot correspondingly and constructs, and when unmanned aerial vehicle flies in the air, no fixed horn appears the offset easily in beta structure department, leads to the emergence of unmanned aerial vehicle flight accident.

SUMMERY OF THE UTILITY MODEL

The utility model mainly aims at providing a rotatory foldable unmanned aerial vehicle that horn can be fixed.

In order to achieve the main purpose, the utility model provides a rotary folding type unmanned aerial vehicle, including fuselage, a plurality of horn and a plurality of power component, the horn sets up on the fuselage, the horn extends outward from the fuselage, the power component sets up on the axial free end of horn, the power component includes motor and screw, the motor drives the screw and rotates, is provided with the pivot on the fuselage, the horn is connected with the pivot, the horn rotates around the pivot; be provided with a plurality of hasp pieces on the fuselage, hasp piece is located between the axial free end and the pivot of horn, is provided with the locking groove on the hasp piece, and hasp piece is located the expansion direction of horn, and the horn passes the opening in locking groove, and the horn is located the locking inslot, and the horn is connected with hasp piece block.

According to the scheme, the plurality of unfolded arms are folded through rotation, and the folded unmanned aerial vehicle is in a long strip shape, so that the size of the unmanned aerial vehicle is effectively reduced, and the transportation is convenient; unmanned aerial vehicle expandes the back, and the horn passes through buckle structure to be fixed in the locking inslot of hasp piece, avoids the horn position deviation to appear, leads to the emergence of flight accident.

The further scheme is that a buckle assembly is arranged on the outer wall of the horn, the buckle assembly comprises an installation block, a spring, a bolt and a driving pin, a sliding groove is formed in the installation block along the axial direction of the bolt, the spring is arranged in the sliding groove, an axial first end of the bolt is abutted to the spring in the sliding groove, an axial second end of the bolt is located outside the sliding groove, a through groove is formed in the installation block, the through groove is located in the radial direction of the bolt, the through groove is communicated with the sliding groove, the driving pin penetrates through the through groove, the driving pin moves in the through groove, and the driving pin is; the side wall of the lock catch piece outside the locking groove is provided with a jack, the plug pin can be inserted into the jack, and the plug pin is adjacent to the side wall of the jack.

When the machine arm rotates, the machine arm penetrates through the opening to enter the locking groove, meanwhile, the rotation of the machine arm drives the buckle assembly to move, the plug pin abuts against the outer wall of the lock catch piece, the spring is compressed until the plug pin moves to the jack, and under the elastic force of the spring, the plug pin is inserted into the jack to complete the fixed connection of the machine arm and the lock catch piece; the drive driving pin moves in the sliding groove, the drive bolt moves away from the jack, the spring is compressed, and meanwhile, the driving machine arm rotates, so that the machine arm moves out of the locking groove.

The mechanical arm is sleeved with a fixed block, two groups of buckle assemblies are arranged on the fixed block, and the two groups of buckle assemblies are symmetrically arranged along the axial direction of the mechanical arm; the locking fastener is provided with two jacks, and the locking groove is positioned between the two jacks.

It is thus clear that being provided with two sets of buckle subassemblies on the fixed block and carrying out the horn and the fixed connection of hasp spare, guarantee the steadiness that horn and hasp spare are connected to two sets of buckle subassembly symmetries set up, but the drive pin that operating personnel one-hand simultaneous operation two sets of buckle subassemblies removed, makes the folding operation of horn more convenient.

The further proposal is that the rotating shaft is vertical to the machine body, the rotating shaft extends along the vertical direction, and the machine arm rotates along the horizontal direction.

It is thus clear that, when unmanned aerial vehicle horizontal direction, the horn rotates around vertical direction, the rotation range of reducible horn.

In a further embodiment, the side wall of the locking element facing the axially free end of the arm is curved.

Therefore, the rotating machine arm drives the bolt to move, the lock catch piece is located between the rotating shaft and the axial free end of the machine arm, the bolt is adjacent to the side wall, facing the axial free end of the machine arm, of the lock catch piece, and the side wall is arc-shaped, so that the bolt can move on the side wall more smoothly.

In a further embodiment, two arms are arranged between two latching elements, the openings of the latching grooves of two adjacent latching elements being arranged opposite one another.

It can be seen that two arms are located two hasp pieces, and after the folding of arm, two arms are close to for unmanned aerial vehicle after folding is rectangular shape, effectively reduces unmanned aerial vehicle volume.

The further scheme is that a spacing block is arranged between two adjacent locking fasteners and is positioned between two machine arms.

It is obvious that the setting of interval piece avoids producing the collision when two arms rotate, reduces the damage to unmanned aerial vehicle.

Drawings

Figure 1 is the utility model discloses rotatory foldable unmanned aerial vehicle embodiment structure under fold condition.

Figure 2 is the utility model discloses structure diagram after getting rid of the cover during rotatory foldable unmanned aerial vehicle embodiment fold condition.

Figure 3 is the utility model discloses rotatory foldable unmanned aerial vehicle embodiment structure under the expansion state.

Fig. 4 is an enlarged view of fig. 3 at a.

Figure 5 is the utility model discloses rotatory foldable unmanned aerial vehicle embodiment buckle subassembly's structure chart.

Fig. 6 is a cross-sectional view of the fastener assembly and catch member shown at a.

The present invention will be further explained with reference to the drawings and examples.

Detailed Description

Referring to fig. 1, the rotatory foldable unmanned aerial vehicle of this embodiment is four rotor unmanned aerial vehicles, and rotatory foldable unmanned aerial vehicle includes fuselage 1, four horn 2 and four power component 3, and four horn 2 set up on fuselage 1, and horn 2 outwards extends from fuselage 1, all is provided with a set of power component 3 on every horn 2, and power component 3 sets up on the axial free end of horn 2, and power component 3 includes motor 31 and screw 32, and motor 31 drive screw 32 rotates. In this embodiment, the body 1 includes a body 11 and a cover 12, the body 11 is provided with an accommodating cavity 13, the fixed end of the arm 2 is located in the accommodating cavity 13, and the cover 12 covers the accommodating cavity 13. A battery is arranged on one side of the machine body 1 far away from the machine cover 12, and a fan and a heat dissipation hole are arranged on the side wall of the machine body 1 corresponding to the position of the battery.

Referring to fig. 2, the body 1 is provided with four rotating shafts 4, and the four rotating shafts 4 are fixedly arranged in the accommodating cavity 13 through screws 41. In the present embodiment, the rotation shaft 4 extends in a vertical direction, and the rotation shaft 4 is perpendicular to the bottom surface of the accommodating chamber 13. Pivot 4 is connected with horn 2 is articulated, is provided with mounting hole 21 on the fixed end of horn 2, is provided with bearing 22 in the mounting hole 21, and pivot 4 is connected with bearing 22 cooperation, and setting up of bearing 22 guarantees the smooth and easy when horn 2 is rotatory folding to reduce wear guarantees the folding precision of permanent use. One machine arm 2 is correspondingly connected with a rotating shaft 4, and the machine arm 2 can rotate around the axial direction of the rotating shaft 4.

Be provided with four hasp pieces 5 on the fuselage 1, in this embodiment, fuselage 1 is the similar cuboid, and four hasp pieces 5 are located four angles departments of fuselage 1 respectively, and hasp piece 5 is located the orientation of opening of horn 2. The locking member 5 is provided with a locking groove 51. referring to fig. 3, in the present embodiment, the locking groove 51 has a U shape rotated by 90 °, and an opening 52 of the locking groove 51 is located in the rotational direction of the horn 2. When the arm 2 of the unmanned aerial vehicle is unfolded, the arm 2 rotates in the horizontal direction and passes through the opening 52 of the locking groove 51, the arm 2 is located in the locking groove 51, and the locking fastener 5 is located between the axial free end of the arm 2 and the rotating shaft 4.

Referring to fig. 4, the horn 2 is snap-fit connected to the locking piece 5. Referring to fig. 5, a fixing block 6 is sleeved outside the horn 2, two sets of buckle assemblies 7 are arranged on the fixing block 6, and the two sets of buckle assemblies are symmetrically arranged along the axial direction of the horn 2. Referring to fig. 6, the buckle assembly 7 includes a mounting block 71, a spring 72, a latch pin 73 and a driving pin 74, wherein a sliding groove 711 is provided in the mounting block 71 along an axial direction of the latch pin 73, the spring 72 is provided in the sliding groove 711, an axial first end of the latch pin 73 abuts against the spring 72 in the sliding groove 711, an axial second end of the latch pin 73 is provided outside the sliding groove 711, a through groove 712 is provided on the mounting block 71, the through groove 712 is located in a radial direction of the latch pin 73, the through groove 711 communicates with the sliding groove 712, the driving pin 74 passes through the through groove 712, the driving pin moves in the through groove 712, the driving pin 74 is fixedly connected with the latch pin 73 in the sliding groove 711, the locking member 5 is provided with two insertion holes 53 on a side wall outside the locking groove 51, the locking groove 51 is located between the two insertion holes 53, an axial second end. When unmanned aerial vehicle folded, drive horn 2 rotated, and horn 2 passed in the opening entering locking groove 51 of locking groove 51, and meanwhile, the removal of buckle subassembly 7 was driven in the rotation of horn 2, and bolt 73 butt lock catch 5's outer wall for spring 72 compresses, moves to jack 53 department until bolt 73, and under spring 72's elasticity, bolt 73 inserted jack 53, accomplishes the fixed connection of horn 2 and lock catch 5. The drive pin 74 moves within the slide channel 712 and the drive pin 73 moves away from the socket 53, compressing the spring 72 and simultaneously driving the rotation of the arm 2 so that the arm 2 moves out of the locking slot 51. In the present embodiment, when the arm 2 is located in the locking groove 51, the locking element 5 is located between the fixing block 6 and the rotating shaft 4. The side wall 54 of catch element 5 facing the axial free end of horn 2 is curved, and receptacle 53 is located in this side wall 54. The rotating arm 2 drives the pin 73 to move, the pin 73 is adjacent to the side wall 54, and the side wall 54 is arc-shaped, so that the pin 73 can move on the side wall 54 more smoothly.

In the present embodiment, two horn 2 are disposed between two adjacent locking members 5, and the openings 52 of the locking grooves 51 of the two adjacent locking members 5 are disposed oppositely. A spacing block 8 is arranged between two adjacent locking fasteners 5, and the spacing block 8 is positioned between the two machine arms 2. After the unmanned aerial vehicle is folded, the two arms 2 positioned between the two locking fasteners 5 can be parallel to each other, and the extending directions of the two arms 2 are opposite to the extending directions of the other two arms 2, so that the unfolded plurality of arms 2 are folded through rotation, and the folded unmanned aerial vehicle is in a long strip shape, so that the size of the unmanned aerial vehicle is effectively reduced, and the transportation is convenient; unmanned aerial vehicle expandes the back, and horn 2 passes through buckle subassembly 7 to be fixed in the locking groove 51 of hasp piece 5, avoids horn 2 position deviation to appear, leads to the emergence of flight accident.

Finally, it should be emphasized that the above-described embodiments are merely preferred examples of the present invention, and are not intended to limit the invention, as those skilled in the art will appreciate that various changes and modifications may be made, and any and all modifications, equivalents, and improvements made, while remaining within the spirit and principles of the present invention, are intended to be included within the scope of the present invention.

Claims (7)

1. Rotatory foldable unmanned aerial vehicle, including fuselage, a plurality of horn and a plurality of power component, the horn sets up on the fuselage, the horn is followed the fuselage outwards extends, power component sets up on the axial free end of horn, power component includes motor and screw, motor drive the screw rotates its characterized in that:

the machine body is provided with a rotating shaft, the machine arm is connected with the rotating shaft, and the machine arm rotates around the rotating shaft;

be provided with a plurality of hasp pieces on the fuselage, hasp piece is located the axial free end of horn with between the pivot, be provided with the locking groove on the hasp piece, hasp piece is located on the expansion direction of horn, the horn passes the opening in locking groove, the horn is located the locking inslot, the horn with hasp piece block is connected.

2. The rotary folding drone of claim 1, characterised in that:

a buckle assembly is arranged on the outer wall of the horn, the buckle assembly comprises an installation block, a spring, a bolt and a driving pin, a sliding groove is formed in the installation block along the axial direction of the bolt, the spring is arranged in the sliding groove, the first axial end of the bolt is abutted to the spring in the sliding groove, the second axial end of the bolt is positioned outside the sliding groove, a through groove is formed in the installation block, the through groove is positioned in the radial direction of the bolt, the through groove is communicated with the sliding groove, the driving pin penetrates through the through groove, the driving pin moves in the through groove, and the driving pin is fixedly connected with the bolt in the sliding groove;

the side wall of the lock catch piece outside the locking groove is provided with a jack, and the plug pin can be inserted into the jack.

3. The rotary folding drone of claim 2, characterised in that:

the machine arm is sleeved with a fixed block, two groups of buckle assemblies are arranged on the fixed block, and the two groups of buckle assemblies are symmetrically arranged along the axial direction of the machine arm;

the lock catch piece is provided with two jacks, and the locking groove is located between the two jacks.

4. A rotary folding drone according to any one of claims 1 to 3, characterised in that:

the pivot perpendicular to the fuselage, the pivot extends along vertical direction, the horn rotates along the horizontal direction.

5. The rotary folding drone of claim 4, characterised in that:

the side wall of the locking fastener facing the axial free end of the horn is arc-shaped.

6. The rotary folding drone of claim 4, characterised in that:

the two machine arms are arranged between the two lock catch pieces, and the openings of the locking grooves of the two adjacent lock catch pieces are oppositely arranged.

7. The rotary folding drone of claim 6, characterised in that:

and a spacing block is arranged between two adjacent locking fasteners and is positioned between the two machine arms.

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