CN210011875U - Foldable six-shaft multi-rotor flight body - Google Patents
Foldable six-shaft multi-rotor flight body Download PDFInfo
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- CN210011875U CN210011875U CN201920420302.2U CN201920420302U CN210011875U CN 210011875 U CN210011875 U CN 210011875U CN 201920420302 U CN201920420302 U CN 201920420302U CN 210011875 U CN210011875 U CN 210011875U
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Abstract
The utility model discloses a many rotors of folding six flight bodies belongs to the unmanned aerial vehicle field. The folding power assembly comprises a base assembly, a folding assembly and a power assembly. The folding assembly comprises a contraction fixing rod, a sliding sleeve ring sleeved on the contraction fixing rod, a plurality of first cantilever rods, a plurality of second cantilever rods and a plurality of third cantilever rods, a first connecting rod and a second connecting rod, wherein the first cantilever rods, the second cantilever rods and the third cantilever rods are sequentially hinged to the top of the contraction fixing rod, the first connecting rod is connected with the hinged positions of the sliding sleeve ring and the first cantilever rods, the hinged positions of the sliding sleeve ring and the second cantilever rods, and the second connecting rod is connected with the hinged positions of the first cantilever rods, the hinged positions of the second cantilever rods and. The utility model discloses a downward movement slip lantern ring drives head rod and second connecting rod downstream, draws and states first cantilever bar, second cantilever bar and third cantilever bar and fold in vertical direction, and the cantilever length who has solved current six many rotor crafts is too big, needs great storage space, is difficult for depositing and the problem of transportation.
Description
Technical Field
The utility model belongs to the unmanned aerial vehicle field, especially a folding six many rotors flight body.
Background
Unmanned aerial vehicle aircraft wide distribution is in each field, according to the application, can divide into military use and civilian use. Wherein the military unmanned aerial vehicle is divided into a scout and a target drone. In the civil aspect, the unmanned aerial vehicle is combined with various industries, for example, the unmanned aerial vehicle is widely applied to the fields of aerial photography, agricultural plant protection, express transportation, field rescue, field observation, topographic mapping, news shooting, electric power inspection, emergency disaster relief, movie and television shooting, the use of the unmanned aerial vehicle is greatly expanded, and the unmanned aerial vehicle technology is actively applied and developed in various countries.
Among them, the six-axis multi-rotor flight vehicle has a non-coplanar rotor rotation plane, and can adjust the flight attitude while keeping a relatively static state or the original flight speed in the air, so that it is popular among people in the fields of photography and photography. However, the existing six-axis multi-rotor flight body cantilever has overlong length and overlarge cross-sectional area occupied by the rotor, and is easy to break, and the like, so that a large storage space is needed in the storage and transportation process. Therefore, the technical problem to be solved urgently in the industry is to provide a foldable six-shaft multi-rotor flying body.
SUMMERY OF THE UTILITY MODEL
Utility model purpose: the utility model provides a many rotors of folding six flight bodies to the cantilever length of solving the many rotors of current six is too big, needs great storage space, is difficult for depositing and the problem of transportation.
The technical scheme is as follows: a foldable six-axis multi-rotor flying body comprising: the folding power assembly comprises a base assembly, a folding assembly and a power assembly.
The basic assembly comprises a machine body, a plurality of lifting supports arranged at the bottom of the machine body, and a contraction fixing rod fixedly connected to the top of the machine body.
The folding assembly comprises a sliding sleeve ring sleeved on the contraction fixing rod, a plurality of first cantilever rods hinged to the top of the contraction fixing rod, a second cantilever rod hinged to the other end of the first cantilever rod through a pin shaft, a third cantilever rod hinged to the other end of the second cantilever rod through a pin shaft, a first connecting rod connected with the hinged position of the sliding sleeve ring and the first cantilever rod and the hinged position of the second cantilever rod, and a second connecting rod connected with the hinged position of the first cantilever rod and the hinged position of the second cantilever rod and the hinged position of the third cantilever rod.
And the power assembly comprises a motor supporting seat fixedly connected with the third cantilever rod, a micro motor arranged on the motor supporting seat, and a rotor connected with an output shaft of the micro motor.
In a further embodiment, the mobile power supply, the control assembly and the Beidou positioning system are arranged on the body and are electrically connected with each other.
In a further embodiment, a plurality of annular clamping grooves are formed in the shrinkage fixing rod, a plurality of hollow channels are formed in the sliding sleeve ring, annular fixing pieces are arranged in the hollow channels and penetrate through the inner side walls of the hollow channels to the annular clamping grooves, a plurality of springs are arranged between the hollow portions of the annular fixing pieces and the inner side walls of the hollow channels, and at least two adjusting nuts are arranged on the outer sides of the hollow channels.
In a further embodiment, the first cantilever rod, the second cantilever rod and the third cantilever rod are hollow cylinders made of aluminum materials, and wires are arranged inside the hollow cylinders and used for connecting the mobile power supply, the control assembly and the micro motor in the machine body.
In a further embodiment, the lifting support is connected with the machine body through a pin shaft.
In a further embodiment, the sum of the lengths of the first, second and third boom rods is greater than the sum of the lengths of both sides of the rotor.
In a further embodiment, a camera fixing seat is arranged at the middle position of the bottom of the machine body.
Has the advantages that: the utility model relates to a foldable six-axis multi-rotor flight body, which drives a first connecting rod and a second connecting rod to move downwards by moving a sliding lantern ring downwards and fixing the lantern ring, pulls the first cantilever rod, the second cantilever rod and a third cantilever rod to coincide with each other and folds in the vertical direction; the rotor wing of the flying body is disassembled by loosening the nut; the landing bracket is rotated to the bottom of the aircraft body through the pin shaft, so that the occupied area of the aircraft body is smaller. The problem of current six many rotor crafts's cantilever length too big, need great storage space, be difficult for depositing and transporting is solved.
Drawings
Fig. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a schematic structural view of the hollow channel of the present invention.
Fig. 3 is a schematic structural view of the folded folding assembly of the present invention.
The reference signs are: the structure comprises a machine body 1, a contraction fixing rod 2, a sliding lantern ring 3, a first cantilever rod 4, a second cantilever rod 5, a third cantilever rod 6, a first connecting rod 7, a second connecting rod 8, a motor supporting seat 9, a micro motor 10, a rotor wing 11, a lifting support 12, an annular clamping groove 201, a hollow channel 301, an annular fixing piece 302, a spring 303 and an adjusting nut 304.
Detailed Description
In the following description, numerous specific details are set forth in order to provide a more thorough understanding of the present invention. It will be apparent, however, to one skilled in the art, that the present invention may be practiced without one or more of these specific details. In other instances, well-known features have not been described in order to avoid obscuring the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
As shown in fig. 1, a foldable six-shaft multi-rotor 11 flight vehicle comprises: a foldable six-axis multi-rotor 11 flight mass comprising: the folding power assembly comprises a base assembly, a folding assembly and a power assembly.
The base assembly includes: a fuselage 1, a retractable fixing rod 2 and a lifting bracket 12. The mobile power supply, the control assembly and the Beidou positioning system are arranged in the machine body 1 and are electrically connected; the lifting supports 12 are connected with the machine body 1 through pin shafts and can rotate along the pin shafts to the bottom of the machine body 1; the shrinkage fixing rod 2 is welded on the top of the machine body 1.
Preferably, a camera fixing seat is arranged at a middle position of the bottom of the body 1. The camera fixing device is used for fixing the camera and conveniently completing various shooting tasks.
The folding assembly includes: a slip collar 3, a first boom lever 4, a second boom lever 5, a third boom lever 6, a first connecting rod 7 and a second connecting rod 8. The retractable fixing rod 2 is sleeved with a sliding collar 3, which can move up and down along the retractable fixing rod 2, as shown in fig. 2, a plurality of annular clamping grooves 201 are arranged on the retractable fixing rod 2, a plurality of hollow channels 301 are arranged in the sliding collar 3, an annular fixing member 302 is arranged in each hollow channel 301, and penetrates through the inner side wall of each hollow channel 301 to the inside of each annular clamping groove 201, a plurality of springs 303 are arranged between the hollow part of each annular fixing member 302 and the inner side wall of each hollow channel 301, and at least two adjusting nuts 304 are arranged on the outer side of each hollow channel 301. When the adjusting nut 304 is loosened, the spring 303 is in a natural extension state, the annular fixing piece 302 is completely positioned in the hollow channel 301, and the sliding lantern ring 3 can move up and down along the contraction fixing rod 2; when moving to the ring slot 201, the adjusting nut 304 is tightened, the spring 303 is compressed, and the ring fastener 302 extends out of the hollow channel 301 into the ring slot 201, so that the sliding collar 3 is fixed. The top of the contraction fixing rod 2 is hinged with a plurality of first cantilever rods 4, the second cantilever rod 5 is hinged at the other end of the first cantilever rod 4 through a pin shaft, the third cantilever rod 6 is hinged at the other end of the second cantilever rod 5 through a pin shaft, the first connecting rod 7 is connected with the hinged part of the sliding sleeve ring 3 and the first cantilever rod 4 as well as the hinged part of the sliding sleeve ring 5 and the second cantilever rod 5, and the second connecting rod 8 is connected with the hinged part of the first cantilever rod 4 and the hinged part of the second cantilever rod 5 as well as the hinged part of the third cantilever rod 6. When the flying body is unfolded, the annular fixing piece 302 is positioned in the annular clamping groove 201 at the top of the retractable fixing rod 2, the positions of the first connecting rod 7 and the second connecting rod 8 are fixed, and the first cantilever rod 4, the second cantilever rod 5 and the third cantilever rod 6 are also positioned horizontally. As shown in fig. 3, when the flying object is folded, the sliding collar 3 moves downward, the annular fixing member 302 is located in the annular clamping groove 201 at the bottom of the retractable fixing rod 2, the first connecting rod 7 pulls the first cantilever rod 4 to move downward along the hinged position of the first cantilever rod 4 and the top of the retractable fixing rod 2, and the second connecting rod 8 pushes the second cantilever rod 5 to move upward along the hinged position of the first cantilever rod 4 and the second cantilever rod 5, so that the folding is completed. After folding, the radius of the outermost circle of the cantilever rod is equal to or smaller than that of the aircraft body 1, so that the volume of the aircraft body is greatly reduced.
The power assembly comprises a motor supporting seat 9, a micro motor 10 and a rotor wing 11. The motor supporting seat 9 is fixedly connected with the other end of the third cantilever rod 6, the micro motor 10 is arranged on the motor supporting seat 9, and the rotor 11 is connected with and fixed to an output shaft of the micro motor 10 through a nut. The sum of the lengths of the two sides of the rotor wings 11 is smaller than the sum of the lengths of the first cantilever rod 4, the second cantilever rod 5 and the third cantilever rod 6, so that independent movement among the rotor wings 11 is ensured and the rotor wings are not influenced by each other. And the first cantilever rod 4, the second cantilever rod 5 and the third cantilever rod 6 are hollow cylinders made of aluminum materials, and electric wires are arranged inside the hollow cylinders and used for connecting a mobile power supply, a control assembly and a micro motor 10 in the machine body 1. The wiring in the barrel can avoid the mutual winding of the electric wires in the repeated folding and unfolding processes.
In order to facilitate understanding of the technical scheme of the foldable six-shaft multi-rotor 11 flight body, the working principle of the flight body is briefly explained: after the flying body is used, when the flying body is folded, the nut at the top of the rotor wing 11 is loosened, and the rotor wing 11 is taken down; then the lifting support 12 is pushed to rotate along the pin shaft to the bottom of the machine body 1; and finally, the sliding collar 3 is pulled to move downwards, the annular fixing piece 302 is positioned in the annular clamping groove 201 at the bottom of the contraction fixing rod 2, the first connecting rod 7 pulls the first cantilever rod 4 to move downwards along the hinged position of the first cantilever rod 4 and the top of the contraction fixing rod 2, and meanwhile, the second connecting rod 8 pushes the second cantilever rod 5 to move upwards along the hinged position of the first cantilever rod 4 and the second cantilever rod 5, so that the folding is completed. After folding, the radius of the outermost circle of the cantilever rod is equal to or smaller than that of the aircraft body 1, so that the volume of the aircraft body is greatly reduced.
It should be noted that the various features described in the above embodiments may be combined in any suitable manner without departing from the scope of the invention. In order to avoid unnecessary repetition, the present invention does not separately describe various possible combinations.
Claims (7)
1. A foldable six-axis multi-rotor flight body, comprising:
the basic assembly comprises a machine body, a plurality of lifting supports arranged at the bottom of the machine body and a contraction fixing rod fixedly connected to the top of the machine body;
the folding assembly comprises a sliding sleeve ring sleeved on the contraction fixing rod, a plurality of first cantilever rods hinged to the top of the contraction fixing rod, a second cantilever rod hinged to the other end of the first cantilever rod through a pin shaft, a third cantilever rod hinged to the other end of the second cantilever rod through a pin shaft, a first connecting rod connecting the hinged positions of the sliding sleeve ring and the first cantilever rod and the hinged positions of the sliding sleeve ring and the second cantilever rod, and a second connecting rod connecting the hinged positions of the first cantilever rod and the second cantilever rod and the hinged positions of the sliding sleeve ring and the second cantilever rod and the third cantilever rod;
and the power assembly comprises a motor supporting seat fixedly connected with the third cantilever rod, a micro motor arranged on the motor supporting seat, and a rotor connected with an output shaft of the micro motor.
2. The foldable six-axis multi-rotor flying body according to claim 1, wherein the body is provided with a mobile power source, a control assembly and a Beidou positioning system, which are electrically connected.
3. The collapsible six-axis multi-rotor flying object of claim 1 wherein a plurality of annular snap grooves are provided on the retraction securing lever, a plurality of hollow channels are provided in the sliding collar, an annular fixture is provided within the hollow channels and passes through inner side walls of the hollow channels into the annular snap grooves, a plurality of springs are provided between the hollow portion of the annular fixture and the inner side walls of the hollow channels, and at least two adjusting nuts are provided outside the hollow channels.
4. The foldable six-axis multi-rotor flight vehicle according to claim 1, wherein the first cantilever bar, the second cantilever bar and the third cantilever bar are hollow cylinders made of aluminum, and wires are arranged inside the hollow cylinders and used for connecting a mobile power supply, a control assembly and a micro motor in the vehicle body.
5. The foldable six-axis multi-rotor flying object according to claim 1, wherein the landing gear is connected to the fuselage by a pin.
6. The foldable six-axis multi-rotor flying body of claim 1, wherein the sum of the lengths of the first, second and third boom rods is greater than the sum of the lengths of the two sides of the rotor.
7. The foldable six-axis multi-rotor flying object according to claim 1, wherein a camera mount is provided at a middle position of the bottom of the fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920420302.2U CN210011875U (en) | 2019-03-29 | 2019-03-29 | Foldable six-shaft multi-rotor flight body |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920420302.2U CN210011875U (en) | 2019-03-29 | 2019-03-29 | Foldable six-shaft multi-rotor flight body |
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| Publication Number | Publication Date |
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| CN210011875U true CN210011875U (en) | 2020-02-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201920420302.2U Active CN210011875U (en) | 2019-03-29 | 2019-03-29 | Foldable six-shaft multi-rotor flight body |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114619433A (en) * | 2022-03-18 | 2022-06-14 | 唐山因泰智能科技发展有限公司 | Telescopic operating mechanism |
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2019
- 2019-03-29 CN CN201920420302.2U patent/CN210011875U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114619433A (en) * | 2022-03-18 | 2022-06-14 | 唐山因泰智能科技发展有限公司 | Telescopic operating mechanism |
| CN114619433B (en) * | 2022-03-18 | 2023-08-15 | 唐山因泰智能科技发展有限公司 | Telescopic operating mechanism |
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