阅读说明：本技术 一种新型多旋翼折叠式无人机 (Novel foldable unmanned aerial vehicle of many rotors ) 是由 周敏 于 2019-11-14 设计创作，主要内容包括：本发明属于无人机技术领域,尤其是一种新型多旋翼折叠式无人机,包括无人机本体,两个无人机本体的上表面固定连接有无人机机翼,无人机机翼的两端上表面均固定连接有螺旋柱。该多旋翼折叠式无人机,通过设置轴承的内圈固定连接有螺旋杆,螺旋杆的上表面设置有折叠装置,且折叠装置包括有螺旋头,螺旋头的底部与螺旋杆的顶部固定连接,达到了螺旋翼转动时可倾斜,螺旋翼不转动时平行,防止收回时导致螺旋翼损伤,且可方便将螺旋翼个体拆下清理更换的效果,解决了现有的螺旋翼一般都是有一定的倾斜度,当折叠过后放入回位槽后,可能会对螺旋翼的表面得到刮伤,会影响螺旋翼的使用效果,而且螺旋翼长时间使用,不易拆下进行清理维护的问题。(The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a novel multi-rotor folding type unmanned aerial vehicle which comprises unmanned aerial vehicle bodies, wherein the upper surfaces of the two unmanned aerial vehicle bodies are fixedly connected with unmanned aerial vehicle wings, and the upper surfaces of the two ends of the unmanned aerial vehicle wings are fixedly connected with spiral columns. This foldable unmanned aerial vehicle of many rotors, inner circle fixedly connected with hob through setting up the bearing, the upper surface of hob is provided with folding device, and folding device is including the spiral head, the bottom of spiral head and the top fixed connection of hob, the tilting when having reached the spiral wing and having rotated, the spiral wing is parallel when not rotating, lead to the spiral wing damage when preventing to withdraw, and can conveniently pull down the effect of clearance change with the spiral wing is individual, it all has certain gradient to have solved current spiral wing, after putting into the return groove after folding, can obtain the scratch to the surface of spiral wing, can influence the result of use of spiral wing, and the spiral wing is long-time to use, the difficult problem of pulling down to clear up and maintain.)

1. The utility model provides a novel foldable unmanned aerial vehicle of many rotors, includes unmanned aerial vehicle body (1), its characterized in that: the upper surfaces of the two unmanned aerial vehicle bodies (1) are fixedly connected with unmanned aerial vehicle wings (2), the upper surfaces of two ends of each unmanned aerial vehicle wing (2) are fixedly connected with spiral columns (3), the spiral columns (3) are symmetrically distributed by taking the axis of the unmanned aerial vehicle body (1) as a symmetric center, return grooves (4) are formed in the surfaces of the spiral columns (3), bearings (5) are fixedly connected to the tops of the spiral columns (3), and spiral rods (6) are fixedly connected to the inner rings of the bearings (5);

the upper surface of hob (6) is provided with folding device, and folding device is including spiral head (7), the bottom of spiral head (7) and the top fixed connection of hob (6).

2. A novel multi-rotor folding unmanned aerial vehicle according to claim 1, wherein: the inner wall fixedly connected with first blotter (8) of returning groove (4), socket (9) have all been seted up to the upper surface of spiral head (7), socket (9) use the axis of spiral head (7) to be symmetric distribution as the center of symmetry, and are a plurality of slot (10) have all been seted up to the inner wall of socket (9).

3. A novel multi-rotor folding unmanned aerial vehicle according to claim 2, wherein: the inner wall of the slot (10) is fixedly inserted with a cross block (11), wherein mounting grooves (12) are respectively formed in the inner walls of the two slots (10), a first pressure spring (13) is fixedly connected to the inner wall of each mounting groove (12), a clamping block (14) is fixedly connected to the free end of one end of each first pressure spring (13), and clamping grooves (15) are formed in the two sides of each cross block (11).

4. A novel multi-rotor folding unmanned aerial vehicle according to claim 3, wherein: the bottom of each of the two cross blocks (11) is fixedly connected with a concave block (16) and a stop block (17) respectively, the surface of each concave block (16) is provided with a rotating cavity (18), and the inner wall of each rotating cavity (18) is provided with a rotating cavity (19).

5. The novel multi-rotor folding unmanned aerial vehicle of claim 4, wherein: the inner wall of the convolution cavity (19) is fixedly connected with a second pressure spring (20), one end free end of the second pressure spring (20) is fixedly connected with a buffer column (21), and the bottom of the buffer column (21) is fixedly connected with a second buffer pad (22).

6. The novel multi-rotor folding unmanned aerial vehicle of claim 4, wherein: the surface of the rotating cavity (18) is fixedly hinged with a rotating ball (23), the surface of the rotating ball (23) is fixedly connected with a rotating plate (24), a groove (25) is formed in the surface of one side of the rotating plate (24), a pull groove (26) is formed in the inner wall of the groove (25), and a lubricating layer (30) is fixedly connected to the surface of the rotating ball (23).

7. The novel multi-rotor folding unmanned aerial vehicle of claim 6, wherein: the inner wall of the pull groove (26) is fixedly connected with a tension spring (27), a lug (28) is fixed at the free end of one end of the tension spring (27), and a propeller (29) is fixedly connected at one end of the lug (28).

Technical Field

The invention relates to the technical field of unmanned aerial vehicles, in particular to a novel multi-rotor folding type unmanned aerial vehicle.

Background

Unmanned aircraft, also called "drone" for short, is an unmanned aircraft operated by means of radio remote control devices and self-contained program control devices, or autonomously operated by an on-board computer, either completely or intermittently.

For example, the novel multi-rotor folding unmanned aerial vehicle (application number: 201710079528.6) disclosed in the chinese patent document comprises an unmanned aerial vehicle body, a connecting shaft is fixedly connected to the top of the unmanned aerial vehicle body, wings of the unmanned aerial vehicle are hinged to the surface of the connecting shaft, positioning grooves are formed in the upper surfaces of the wings of the unmanned aerial vehicle, spiral columns are inserted into the positioning grooves, the positioning grooves are fixedly connected to the spiral columns through fixing bolts, and first and second gaskets are respectively sleeved on the surfaces of the fixing bolts, so that although the effect of rotating and folding the spiral wings is achieved, the rotating balls and the rolling balls in the rotating cavity can be lubricated, the flexibility is enhanced, so that the folding effect of the spiral wings is better, thereby reducing the volume occupied by the spiral wings, but the spiral wings generally have a certain inclination, and when the folded wings are placed in a return groove, the surfaces of the spiral wings can be scratched, thereby affecting the use, and the spiral wing is used for a long time and is not easy to be detached for cleaning and maintenance.

Disclosure of Invention

Based on the technical problems that the existing spiral wing is inclined, the spiral wing can be damaged after being folded, and the disassembly, cleaning and maintenance are inconvenient, the invention provides a novel multi-rotor folding unmanned aerial vehicle.

The invention provides a novel multi-rotor folding type unmanned aerial vehicle which comprises unmanned aerial vehicle bodies, wherein two upper surfaces of the two unmanned aerial vehicle bodies are fixedly connected with unmanned aerial vehicle wings, the upper surfaces of two ends of the unmanned aerial vehicle wings are fixedly connected with spiral columns, the spiral columns are symmetrically distributed by taking the axis of the unmanned aerial vehicle body as a symmetry center, return grooves are formed in the surfaces of the spiral columns, bearings are fixedly connected to the tops of the spiral columns, and spiral rods are fixedly connected to the inner rings of the bearings.

The upper surface of hob is provided with folding device, and folding device is including the spiral head, the bottom of spiral head and the top fixed connection of hob.

Preferably, the inner wall of the return groove is fixedly connected with a first cushion pad, the upper surface of the spiral head is provided with sockets, the sockets are symmetrically distributed by taking the axis of the spiral head as a symmetric center, and the inner walls of the sockets are provided with slots;

through above-mentioned technical scheme, through setting up first blotter, prevent to cause the damage with returning the groove collision.

Preferably, the inner walls of the slots are fixedly inserted with cross blocks, wherein the inner walls of two slots are respectively provided with a mounting groove, the inner walls of the mounting grooves are fixedly connected with a first pressure spring, a free end of one end of the first pressure spring is fixedly connected with a clamping block, and two sides of each cross block are provided with clamping grooves;

through the technical scheme, the clamping block is arranged, so that the clamping block is clamped into the clamping groove, the cross block can be pulled out only by pulling out the cross block forcibly.

Preferably, the bottoms of the two cross blocks are fixedly connected with a concave block and a stop block respectively, the surface of the concave block is provided with a rotating cavity, and the inner wall of the rotating cavity is provided with a rotating cavity.

Preferably, the inner wall of the convolution cavity is fixedly connected with a second pressure spring, a free end of the second pressure spring is fixedly connected with a buffer column, and the bottom of the buffer column is fixedly connected with a second buffer pad;

through above-mentioned technical scheme, through setting up the second blotter, through the second blotter when the second pressure spring of being convenient for pops out the cushion column, can not cause the effect of loss.

Preferably, a rotating ball is fixedly hinged to the surface of the rotating cavity, a rotating plate is fixedly connected to the surface of the rotating ball, a groove is formed in the surface of one side of the rotating plate, a pull groove is formed in the inner wall of the groove, and a lubricating layer is fixedly connected to the surface of the rotating ball;

through above-mentioned technical scheme, the inside of lubricant film is provided with graphite.

Preferably, the inner wall of the pull groove is fixedly connected with a tension spring, a free end of the tension spring is fixedly provided with a lug, and one end of the lug is fixedly connected with a propeller;

through above-mentioned technical scheme, the dog supports the screw for the screw takes the lug to slide in the recess, and when the screw did not change, the screw slowly got back to when returning the groove, the lug was pulled back by tension spring, thereby made the screw parallel.

Compared with the prior art, the invention has the beneficial effects that:

inner circle fixedly connected with hob through setting up the bearing, the upper surface of hob is provided with folding device, and folding device is including the hob, the bottom of hob and the top fixed connection of hob, the tilting when having reached the spiral wing and having rotated, the spiral wing is parallel when not rotating, lead to the spiral wing damage when preventing to withdraw, and can conveniently pull down the individual effect of clearing up the change of spiral wing, it all has certain gradient to have solved current spiral wing, after putting into the return groove after folding, can obtain the scratch to the surface of spiral wing, can influence the result of use of spiral wing, and the spiral wing uses for a long time, be difficult to pull down the problem of clearing up the maintenance.

Drawings

Fig. 1 is a schematic view of a novel multi-rotor foldable unmanned aerial vehicle according to the present invention;

fig. 2 is a cross-sectional view of a return groove structure of a novel multi-rotor folding type unmanned aerial vehicle provided by the invention;

fig. 3 is a cross-sectional view of a spiral head structure of a novel multi-rotor folding type unmanned aerial vehicle provided by the invention;

fig. 4 is a partial view of a slot structure of a novel multi-rotor folding type unmanned aerial vehicle according to the present invention;

fig. 5 is a perspective view of a cross block structure of the novel multi-rotor foldable unmanned aerial vehicle provided by the invention;

fig. 6 is a partial view of a groove structure of a novel multi-rotor folding type unmanned aerial vehicle according to the present invention;

fig. 7 is a perspective view of a bump structure of a novel multi-rotor foldable unmanned aerial vehicle according to the present invention;

fig. 8 is an enlarged view of a structure at a position a in fig. 2 of the novel multi-rotor folding type unmanned aerial vehicle provided by the invention.

In the figure: 1. an unmanned aerial vehicle body; 2. wings of the unmanned aerial vehicle; 3. a helical column; 4. returning to the groove; 5. a bearing; 6. a screw rod; 7. a screw head; 8. a first cushion pad; 9. a socket; 10. a slot; 11. a cross block; 12. mounting grooves; 13. a first pressure spring; 14. a clamping block; 15. a card slot; 16. a concave block; 17. a stopper; 18. rotating the cavity; 19. a convolute chamber; 20. a second pressure spring; 21. a buffer column; 22. a second cushion pad; 23. rotating the ball; 24. a rotating plate; 25. a groove; 26. groove drawing; 27. a tension spring; 28. a bump; 29. a propeller; 30. and a lubricating layer.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.

Referring to fig. 1-8, a novel foldable unmanned aerial vehicle of many rotors, as shown in fig. 1-4, including unmanned aerial vehicle body 1, the last fixed surface of two unmanned aerial vehicle bodies 1 is connected with unmanned aerial vehicle wing 2, the equal fixedly connected with flight column 3 of both ends upper surface of unmanned aerial vehicle wing 2, flight column 3 uses the axis of unmanned aerial vehicle body 1 to be the symmetric distribution as the center of symmetry, back groove 4 has been seted up on flight column 3's surface, flight column 3's top fixedly connected with bearing 5, the inner circle fixedly connected with hob 6 of bearing 5.

The upper surface of hob 6 is provided with folding device, and folding device is including spiral head 7, the bottom of spiral head 7 and the top fixed connection of hob 6.

Further, as shown in fig. 2-4, the inner wall of the return groove 4 is fixedly connected with a first buffer pad 8, the upper surface of the screw head 7 is provided with sockets 9, the sockets 9 are symmetrically distributed by taking the axis of the screw head 7 as a symmetric center, and the inner walls of the sockets 9 are provided with slots 10.

Further, as shown in fig. 2-4, cross blocks 11 are fixedly inserted into inner walls of the slots 10, wherein mounting grooves 12 are respectively formed in the inner walls of the two slots 10, a first pressure spring 13 is fixedly connected to the inner wall of the mounting groove 12, a clamping block 14 is fixedly connected to a free end of the first pressure spring 13, and clamping grooves 15 are respectively formed in two sides of each of the cross blocks 11.

Further, as shown in fig. 2-3 and 5, the bottoms of the two cross blocks 11 are fixedly connected with a concave block 16 and a stop block 17 respectively, the surface of the concave block 16 is provided with a rotating cavity 18, and the inner wall of the rotating cavity 18 is provided with a rotating cavity 19.

Further, as shown in fig. 1-3, a second pressure spring 20 is fixedly connected to the inner wall of the convolution chamber 19, a buffer column 21 is fixedly connected to a free end of the second pressure spring 20, and a second buffer pad 22 is fixedly connected to a bottom of the buffer column 21.

Further, as shown in fig. 2 and 8, a rotating ball 23 is fixedly hinged to the surface of the rotating cavity 18, a rotating plate 24 is fixedly connected to the surface of the rotating ball 23, a groove 25 is formed in the surface of one side of the rotating plate 24, a pull groove 26 is formed in the inner wall of the groove 25, and a lubricating layer 30 is fixedly connected to the surface of the rotating ball 23.

Further, as shown in fig. 2-3 and fig. 6-8, a tension spring 27 is fixedly connected to the inner wall of the pull groove 26, a projection 28 is fixed to a free end of the tension spring 27, and a propeller 29 is fixedly connected to an end of the projection 28.

Further, as shown in fig. 1-4, the inner ring fixedly connected with screw rod 6 through setting up bearing 5, the upper surface of screw rod 6 is provided with folding device, and folding device is including spiral head 7, the bottom of spiral head 7 and the top fixed connection of screw rod 6, the tilting when having reached the spiral wing and rotating, the spiral wing is parallel when not rotating, lead to the spiral wing damage when preventing to withdraw, and can conveniently pull down the effect of clearance change with the spiral wing individual, it all has certain gradient to have solved current spiral wing, after putting into the return tank after folding, probably obtain the scratch to the surface of spiral wing, can influence the result of use of spiral wing, and the spiral wing is used for a long time, the difficult problem of pulling down and carrying out the clearance maintenance.

The working principle is as follows: when the screw propeller is used, the cross block 11 is placed into the socket 9, the protruding part of the cross block 11 is inserted into the slot 10, meanwhile, the fixture block 14 is extruded, the fixture block 14 extrudes the first pressure spring 13, the fixture block 14 is pressed into the mounting groove 12, when the fixture block 14 and the clamping grooves 15 on the two sides of the cross block 11 are on the same axis, the first pressure spring 13 ejects the fixture block 14, the fixture block 14 is clamped into the clamping groove 15, the cross block 11 is fixed, then the screw propeller 29 is placed into the return groove 4, the screw rod 6 is controlled to rotate through a control system of the unmanned aerial vehicle, the screw rod 6 drives the screw head 7 to rotate, the screw head 7 also drives the screw propeller 29 to rotate, the screw propeller 29 is slowly separated from the return groove 4 through the action of centrifugal force along with the increasing speed, and when the rotating plate 24 and the screw propeller 29 are in horizontal line, the stop block 17 abuts against the screw, let screw 29 have certain slope, make screw 29 take lug 28 to slide to one side, and pull up tension spring 27, after unmanned aerial vehicle stops, spiral head 7 slowly stops, tension spring 27 holds screw 29 and goes back, make screw 29 parallel, and second pressure spring 20 pops out cushion column 21, cushion column 21 pops out rotor plate 24, and simultaneously, screw 29's self basis weight, put down screw 29 and rotor plate 24, get back to in the kerve 4, can not touch the inner wall of kerve 4 and cause the damage, make a side of screw 29 touch with first blotter 8, when needs clean trade maintenance, only need directly pull out cross 11 can.

The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.