CN111114745A - Connecting piece and unmanned aerial vehicle thereof - Google Patents
Connecting piece and unmanned aerial vehicle thereof Download PDFInfo
- Publication number
- CN111114745A CN111114745A CN202010058670.4A CN202010058670A CN111114745A CN 111114745 A CN111114745 A CN 111114745A CN 202010058670 A CN202010058670 A CN 202010058670A CN 111114745 A CN111114745 A CN 111114745A
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- horn
- cavity
- connecting portion
- fuselage
- lining
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- 230000000903 blocking effect Effects 0.000 claims abstract description 6
- 238000010030 laminating Methods 0.000 claims description 3
- 230000003068 static effect Effects 0.000 claims description 3
- 238000005728 strengthening Methods 0.000 claims description 2
- 238000009434 installation Methods 0.000 abstract description 7
- 238000011900 installation process Methods 0.000 abstract description 3
- 238000010276 construction Methods 0.000 description 4
- 230000003014 reinforcing effect Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
- B64C1/069—Joining arrangements therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
Abstract
The invention discloses a connecting piece which comprises a machine arm connecting part, a hoop strip and a machine body connecting part; the horn connecting part is a cavity, one end of the cavity is provided with an opening allowing the horn to enter so as to form a horn inlet, and the other end of the cavity prevents the horn from extending out of the cavity so as to form a horn blocking opening; at least one hollow groove is arranged on the cavity wall along the circumferential direction of the cavity wall; the hoop strip presses the machine arm positioned in the cavity from the hollow groove to enable the machine arm to be tightly attached to the inner wall of the cavity; the fuselage connecting portion is outside the horn connecting portion, structure as an organic whole with the horn connecting portion, sets up the first screw hole that is used for being connected with the fuselage on the fuselage connecting portion. Because the prior art is inconvenient in use, the structure of the invention is improved, and the connecting part of the machine arm and the connecting part of the machine body are respectively arranged, thereby ensuring the coaxiality of installation, ensuring the assembly efficiency in the installation process and simultaneously reducing the quality of the connecting piece.
Description
Technical Field
The invention relates to a connecting piece, in particular to a connecting piece and an unmanned aerial vehicle thereof.
Background
An unmanned aerial vehicle, abbreviated as "unmanned aerial vehicle" ("UAV"), is an unmanned aerial vehicle that is operated using a radio remote control device and a self-contained program control device. Compared with manned aircraft, it has the advantages of small volume, low cost, convenient use, etc.
For the unmanned multi-rotor aircraft, a plurality of arms are required to be connected with the fuselage independently, and a connecting piece is required to be adopted for intermediate transition connection in connection. In order to reduce the overall quality of the inner wall of the existing known connecting piece, the inner wall of the existing known connecting piece is integrally manufactured into a hollow structure, but in the installation process of the hollow combination structure, a machine arm is often clamped in the connecting piece, so that the installation and connection are slow and difficult; and the coaxiality of the connection needs to be adjusted after the connection.
Disclosure of Invention
It is an object of the present invention to provide a connector which solves one or more of the above mentioned problems.
In order to achieve the purpose, the technical scheme provided by the invention is as follows:
the connecting piece comprises a machine arm connecting part, a hoop strip and a machine body connecting part; the horn connecting part is a cavity, one end of the cavity is provided with an opening allowing the horn to enter so as to form a horn inlet, and the other end of the cavity prevents the horn from extending out of the cavity so as to form a horn blocking opening; at least one hollow groove is arranged on the cavity wall along the circumferential direction of the cavity wall; the hoop strip presses the machine arm positioned in the cavity from the hollow groove to enable the machine arm to be tightly attached to the inner wall of the cavity; the fuselage connecting portion is outside the horn connecting portion, structure as an organic whole with the horn connecting portion, sets up the first screw hole that is used for being connected with the fuselage on the fuselage connecting portion.
According to the invention, the horn slides into the cavity along one side of the cavity, which is not grooved, then the horn is stopped by the horn blocking opening to continue to advance so as to show that the horn is installed in place, the horn is tightly attached to the inner wall of the cavity through the hollow groove on the other side of the cavity by the hoop strip, so that the large-area contact between the cavity and the horn is realized to enhance the friction force, and the horn is fixedly connected with the connecting piece.
The horn mouth can be a hole or a hole which can completely seal one end of the cavity, and the diameter of the hole is smaller than that of the horn.
The locking mode of the machine arm and the cavity by the hoop strip is various: firstly, the strap is independently used for winding the outer circumference of the horn and the cavity to play a role in binding the horn and the cavity, for example, through holes are arranged at two ends of the strap, so that the strap is wound around the outer circumference of the connecting part of the horn, two tail ends of the strap are gathered and locked by bolts or screws, and the binding is completed; secondly, two ends of the hoop strip are arranged to be a terminal structure of the cable tie, so that the hoop strip can achieve a hoop binding effect; and the other one is that a hoop strip connecting lug is arranged outside the cavity, a through hole or a threaded hole is formed in the connecting lug, through holes or threaded holes are formed in two ends of the hoop strip, and the hoop strip is fixed outside the cavity through bolts.
For the structures, the straps are required to have certain micro-deformation, so that the horn can be effectively pressed in the cavity. The number of the hoop strips corresponds to that of the hollow-out grooves, and the number of the hollow-out grooves is set according to actual needs, for example, only one hollow-out arm can be arranged when the short hollow-out arm is short, and two or more hollow-out arms can be arranged when the long hollow-out arm is long; the plurality of hollow-out grooves are preferably arranged at equal intervals, the equal intervals can be arranged at the same side at equal intervals, or can be arranged at equal intervals along a radial spiral at equal angles, and the machine arm can be fixed. In addition, the hoop strip itself can be also properly made with some hollowed-out structures to reduce the quality.
The machine body connecting part is of an integral structure with the machine arm connecting part, so that the machine body connecting part can be integrally formed during manufacturing, and later-period additional installation and connection are not needed.
The machine body connecting part can be arranged on one or more machine arm connecting parts, and one connecting part is optimally arranged in the middle or the whole machine arm connecting part is wrapped; two or more connecting parts may be disposed on the horn connecting part at equal intervals, which is not limited herein.
Further: the both ends of strake set up the through-hole, correspond this through-hole position on fuselage connecting portion and set up the second screw hole, and the bolt passes this through-hole and is connected so that the strake sees through the fretwork groove and closely laminates with the horn.
In order to further simplify the structure, the second threaded holes are formed in the two ends, corresponding to the hollow-out grooves, of the machine body connecting portion and used for connecting the hoop strips, and therefore the whole structure can be simplified.
Further: the machine body connecting part is square and is arranged at the position of the non-threaded hole of the machine body connecting part in a hollow mode. The square machine body connecting part is simple to manufacture and is simpler and more convenient to connect; the quality of the whole connecting piece can be effectively reduced by the hollow-out machine body connecting part.
Further: the fuselage connecting portion be two, set up respectively at the both ends of horn connecting portion, have the strengthening rib between two fuselage connecting portions. The reinforcing rib is outside the horn connecting portion, has both strengthened the intensity of fuselage connecting portion, also forms certain protection to the horn connecting portion simultaneously.
Further: the mechanical arm is characterized by further comprising a lining, a positioning block is arranged on one end face of the lining, a positioning groove is formed in a position of a stop of the mechanical arm, one end of the lining enters the mechanical arm from the end face of the mechanical arm, and the positioning block enters the positioning groove to enable the lining to be circumferentially static in the mechanical arm.
In some embodiments, a liner is provided, the liner primarily functioning to create friction inside the boom to further prevent the boom from rotating; the lining also plays a role in guiding, so that the machine arm can smoothly enter the cavity; in addition, when the hoop strip applies pressure to the horn, the strength of the horn can be enhanced at the thickness of the horn corresponding to the thickened part.
The length of the lining is not limited, and the length can be set according to the length of the cavity of the machine arm connecting part and can be the same as the length of the cavity or the length corresponding to the opening of the hollow groove.
The liner may also be a hollow structure of the cylinder or a solid body that is stronger than the hollow structure of the cylinder.
The number of the positioning blocks is not limited, if the positioning blocks are solid, the positioning blocks can be arranged at the middle position, and if the positioning blocks are hollow, one or more positioning blocks can be arranged at equal intervals along the circumferential direction.
Further: the terminal surface that the inside lining set up the locating piece sets up the retaining ring, the laminating of an terminal surface and horn terminal surface of retaining ring is in order to prevent the inside lining to fall into in the horn. In order to assemble more easily, also in order to prevent that when installing the horn after assembling the inside lining earlier, the horn originally blocks and influences the assemble duration, sets up the retaining ring on the inside lining, and during the assembly like this, the inside lining can assemble with the horn earlier, assembles with the connecting piece according to the position of locating piece and positioning groove again, and whole assembly effect is easier.
Further: the lining is provided with a hollow structure. In order to further reduce the mass, the inner liner is provided with a hollow structure, and the hollow form is not limited.
Further: the hoop strip presses the machine arm at the non-hollowed-out part of the inner lining through the machine arm. The machine arm is pressed at the non-hollow part, so that the strength of the machine arm can be ensured.
Including above arbitrary unmanned aerial vehicle of connecting piece, be connected through the connecting piece between horn and the fuselage.
The connecting piece is used for connecting the machine arm and the machine body, so that the assembly efficiency can be improved, and the assembly stability is better.
The invention has the technical effects that:
because the prior art is inconvenient in use, the structure of the invention is improved, and the connecting part of the machine arm and the connecting part of the machine body are respectively arranged, thereby ensuring the coaxiality of installation, ensuring the assembly efficiency in the installation process and simultaneously reducing the quality of the connecting piece.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention.
In the drawings:
FIG. 1 is a schematic structural view of an embodiment;
FIG. 2 is a schematic structural view of the second embodiment;
FIG. 3 is a schematic diagram of a third structure of the embodiment;
FIG. 4 is a schematic structural view of the fourth embodiment;
FIG. 5 is a schematic structural view of the fifth embodiment;
wherein the figures include the following reference numerals:
the device comprises a machine arm connecting part 1, a hollow groove 11, a machine arm blocking opening 12 and a positioning groove 13; the machine body connecting part comprises a hoop strip 2, a machine body connecting part 3, a first threaded hole 31, a hollow structure 32, a second threaded hole 33 and a reinforcing rib 34; the device comprises a machine arm 4, a lining 5, a positioning block 51, a retaining ring 52 and a lining hollow structure 53.
Detailed Description
The present invention will now be described in detail with reference to the drawings and specific embodiments, wherein the exemplary embodiments and descriptions are provided only for the purpose of illustrating the present invention and are not to be construed as unduly limiting the invention.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
Example one
As shown in figure 1, the connecting piece comprises a machine arm connecting part 1, a hoop strip 2 and a machine body connecting part 3. The horn connecting portion is a cavity having an opening at one end to allow entry of the horn into the cavity to become a horn entrance and an opening at the other end to prevent the horn from protruding out of the cavity to become a horn mouth where the horn mouth is completely blocked.
At least one hollow-out groove 11 is arranged on the cavity wall along the circumferential direction of the cavity wall; the hoop strip 2 compresses the machine arm 4 positioned in the cavity from the hollow groove 11 to enable the machine arm to be tightly attached to the inner wall of the cavity. The horn is internally tangent to the cavity.
The fuselage connecting portion is outside the horn connecting portion, with horn connecting portion structure as an organic whole, set up the first screw hole 31 that is used for being connected with the fuselage on the fuselage connecting portion.
The positions of the first threaded holes are indicated schematically in fig. 1, and the number and positions of the first threaded holes 31 are set and adjusted according to the actual connection requirements.
Fuselage connecting portion set up in the horn connecting portion (being the intermediate position of cavity) in this embodiment, and fuselage connecting portion are square, do not have first screw hole position fretwork setting, hollow out construction 32 at fuselage connecting portion 3.
The straps are open-ended rings, the ends of which are provided with through-holes through which bolts are passed to circumferentially clamp the straps outside the cavity. The straps are provided with cut-out structures.
In the embodiment, a hoop strip is pressed on one hollow-out groove, and the other hollow-out groove is used for displaying no hoop strip; the number of the hollow grooves can be adjusted.
In the use, the horn gets into in the cavity along the one end that does not have the fretwork groove, then is blockked at the cavity other end, and the strake is fixed horn and cavity together around cavity a week locking, and whole installation is used on the fuselage again. Simple structure, quick and convenient installation.
Example two
As shown in fig. 2, in this embodiment, a connecting block for connecting the hoop bar is provided on the arm connecting portion, a second threaded hole (a second through hole) is provided on the connecting block, the hoop bar is pressed on a hollow-out groove, and the other hollow-out groove is used for demonstrating that the hoop bar is not pressed.
In this embodiment, the length of the hoop strip is reduced, and the hoop strip can be connected by bolts in the using process and then is not locked, so that spare and accessory parts are not easy to lose.
EXAMPLE III
As shown in fig. 3, in the present embodiment, through holes are formed at two ends of the strap, a second threaded hole 33 is formed in the body connecting portion 3 corresponding to the through holes, and a bolt passes through the through holes and is connected to the second threaded hole 33, so that the strap is tightly attached to the arm through the hollow groove. In fig. 3 the straps are not installed.
The second threaded hole 33 is formed in the body connecting portion, the structure can be simplified, the connection between the hoop and the second threaded hole is hidden, and interference between the upper structure of the arm connecting portion and other structures of the unmanned aerial vehicle is effectively avoided.
Example four
As shown in fig. 4, in the present embodiment, the two body connecting portions are provided at both ends of the arm connecting portion, respectively, and a reinforcing rib 34 is provided between the two body connecting portions.
The reinforcing ribs 34 enable the outside of the machine arm connecting part to be wrapped by the machine body connecting part, so that the strength is increased; and the fuselage connecting portion is avoided being blocked in the installation, lets fuselage connecting portion outer frame do not have the structure of similar recess, and the assembly is easier, simple.
EXAMPLE five
As shown in fig. 5, the present embodiment differs from the above embodiments in that it includes a horn connecting portion 1, a bail 2, and a body connecting portion 3. The horn connecting portion is a cavity having an opening at one end to allow the horn to enter to become a horn entrance and an opening at the other end to prevent the horn from protruding out of the cavity to become a horn stopper, where the horn stopper is a hole having an opening diameter smaller than the horn diameter.
Two hollow grooves 11 are arranged on the cavity wall along the circumferential direction of the cavity wall; the hoop strip 2 compresses the machine arm 4 positioned in the cavity from the hollow groove 11 to enable the machine arm to be tightly attached to the inner wall of the cavity. The horn is inscribed in the cavity.
The fuselage connecting portion is outside the horn connecting portion, with horn connecting portion structure as an organic whole, set up the first screw hole 31 that is used for being connected with the fuselage on the fuselage connecting portion. The machine body is square, a hollow structure 32 is arranged on the machine body, and a second threaded hole 33 is formed in the machine body connecting part;
the mechanical arm is characterized by further comprising a lining, a positioning block is arranged on one end face of the lining, a positioning groove is formed in a position of a stop of the mechanical arm, one end of the lining enters the mechanical arm from the end face of the mechanical arm, and the positioning block enters the positioning groove to enable the lining to be circumferentially static in the mechanical arm. The inner liner is inscribed on the inner wall of the machine arm.
The terminal surface that the inside lining set up the locating piece sets up the retaining ring, the laminating of an terminal surface and horn terminal surface of retaining ring is in order to prevent the inside lining to fall into in the horn. The inner liner is provided with a hollow structure,
the assembly process in this embodiment is as follows: firstly, the lining 5 enters the horn from one end face of the horn 4, the check ring 52 prevents the lining from being immersed in the horn 4, then the horn enters the cavity along one side without a hollow groove in the cavity, the horn blocking opening 12 blocks the horn, the positioning block 51 enters the positioning groove 13, the hoop strip presses the horn through the hollow groove 11, two ends of the hoop strip are connected to a connecting part (a second threaded hole 33) of the machine body through bolts, connection of the horn and the connecting part of the horn is completed, and the whole connecting piece is connected to the machine body through the first threaded hole.
The inside lining is provided with hollow out construction 53 here, and the fuselage is connected and is roughly provided with hollow out construction, is provided with hollow out construction on the hoop strip to reduce whole quality.
EXAMPLE six
Including above arbitrary unmanned aerial vehicle of connecting piece, be connected through the connecting piece between horn and the fuselage.
The connecting piece is used for connecting the machine arm and the machine body, so that the assembly efficiency can be improved, and the assembly stability is better.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. The connecting piece, its characterized in that: comprises a machine arm connecting part, a hoop strip and a machine body connecting part;
the horn connecting part is a cavity, one end of the cavity is provided with an opening allowing the horn to enter so as to form a horn inlet, and the other end of the cavity prevents the horn from extending out of the cavity so as to form a horn blocking opening; at least one hollow groove is arranged on the cavity wall along the circumferential direction of the cavity wall;
the hoop strip presses the machine arm positioned in the cavity from the hollow groove to enable the machine arm to be tightly attached to the inner wall of the cavity;
the fuselage connecting portion is outside the horn connecting portion, structure as an organic whole with the horn connecting portion, sets up the first screw hole that is used for being connected with the fuselage on the fuselage connecting portion.
2. The connector of claim 1, wherein: the both ends of strake set up the through-hole, correspond this through-hole position on fuselage connecting portion and set up the second screw hole, and the bolt passes this through-hole and is connected so that the strake sees through the fretwork groove and closely laminates with the horn.
3. The connector of claim 1, wherein: the machine body connecting part is square and is arranged at the position of the non-threaded hole of the machine body connecting part in a hollow mode.
4. The connector of claim 1, wherein: the fuselage connecting portion be two, set up respectively at the both ends of horn connecting portion, have the strengthening rib between two fuselage connecting portions.
5. The connector of claim 1, wherein: the mechanical arm is characterized by further comprising a lining, a positioning block is arranged on one end face of the lining, a positioning groove is formed in a position of a stop of the mechanical arm, one end of the lining enters the mechanical arm from the end face of the mechanical arm, and the positioning block enters the positioning groove to enable the lining to be circumferentially static in the mechanical arm.
6. The connector of claim 5, wherein: the terminal surface that the inside lining set up the locating piece sets up the retaining ring, the laminating of an terminal surface and horn terminal surface of retaining ring is in order to prevent the inside lining to fall into in the horn.
7. The connector of claim 5, wherein: the lining is provided with a hollow structure.
8. The connector of claim 7, wherein: the hoop strip presses the machine arm at the non-hollowed-out part of the inner lining through the machine arm.
9. An unmanned aerial vehicle comprising a connector as claimed in any preceding claim, wherein: the horn is connected with the fuselage through the connecting piece.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010058670.4A CN111114745A (en) | 2020-01-18 | 2020-01-18 | Connecting piece and unmanned aerial vehicle thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010058670.4A CN111114745A (en) | 2020-01-18 | 2020-01-18 | Connecting piece and unmanned aerial vehicle thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111114745A true CN111114745A (en) | 2020-05-08 |
Family
ID=70489824
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010058670.4A Pending CN111114745A (en) | 2020-01-18 | 2020-01-18 | Connecting piece and unmanned aerial vehicle thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111114745A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105691605A (en) * | 2016-03-09 | 2016-06-22 | 深圳行天者创新技术有限公司 | Unmanned aerial vehicle with detachable vehicle arms |
| CN107344618A (en) * | 2017-07-25 | 2017-11-14 | 成都天麒科技有限公司 | A kind of more rotor plant protection unmanned planes |
| CN206914638U (en) * | 2017-06-19 | 2018-01-23 | 成都天麒科技有限公司 | A kind of unmanned plane horn component |
| CN208181394U (en) * | 2018-04-24 | 2018-12-04 | 杭州海康机器人技术有限公司 | A kind of plug-in unmanned plane folding arm mechanism of solar |
| CN211766238U (en) * | 2020-01-18 | 2020-10-27 | 杭州启飞智能科技有限公司 | Connecting piece and unmanned aerial vehicle thereof |
-
2020
- 2020-01-18 CN CN202010058670.4A patent/CN111114745A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105691605A (en) * | 2016-03-09 | 2016-06-22 | 深圳行天者创新技术有限公司 | Unmanned aerial vehicle with detachable vehicle arms |
| CN206914638U (en) * | 2017-06-19 | 2018-01-23 | 成都天麒科技有限公司 | A kind of unmanned plane horn component |
| CN107344618A (en) * | 2017-07-25 | 2017-11-14 | 成都天麒科技有限公司 | A kind of more rotor plant protection unmanned planes |
| CN208181394U (en) * | 2018-04-24 | 2018-12-04 | 杭州海康机器人技术有限公司 | A kind of plug-in unmanned plane folding arm mechanism of solar |
| CN211766238U (en) * | 2020-01-18 | 2020-10-27 | 杭州启飞智能科技有限公司 | Connecting piece and unmanned aerial vehicle thereof |
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