CN216185991U - Multi-rotor unmanned aerial vehicle - Google Patents
Multi-rotor unmanned aerial vehicle Download PDFInfo
- Publication number
- CN216185991U CN216185991U CN202122667348.4U CN202122667348U CN216185991U CN 216185991 U CN216185991 U CN 216185991U CN 202122667348 U CN202122667348 U CN 202122667348U CN 216185991 U CN216185991 U CN 216185991U
- Authority
- CN
- China
- Prior art keywords
- fixedly connected
- motor
- reinforcing
- machine
- unmanned aerial
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 37
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 17
- 229910052782 aluminium Inorganic materials 0.000 claims description 17
- 238000005728 strengthening Methods 0.000 claims description 5
- 230000005611 electricity Effects 0.000 claims description 4
- 239000000178 monomer Substances 0.000 claims description 4
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
Images
Abstract
The utility model provides a multi-rotor unmanned aerial vehicle, comprising: a body; at least six arms fixedly connected with the machine body; the at least six machine arms are fixedly connected through an annular reinforcing middle frame; the tail end of each of the at least six machine arms is fixedly connected with a driving device. The scheme of the utility model has strong load-carrying capacity, stable machine body mechanism and low cost.
Description
Technical Field
The utility model relates to the technical field of high-load unmanned aerial vehicles, in particular to a multi-rotor unmanned aerial vehicle.
Background
Currently, multi-rotor drones have gained wide acceptance and use in the market. A multi-rotor unmanned aerial vehicle is an unmanned aerial vehicle which adopts a plurality of rotors as a power device and a control device, utilizes the pulling force generated by the rotors to enable the aircraft to take off by overcoming the gravity of the earth and change the posture and the position in the air.
The general size of current many rotor unmanned aerial vehicle is less, and the loading capacity is low and the range of application is narrow. There are also a few large-scale many rotor unmanned aerial vehicles, still are common fuselage-horn framework, are subject to material strength, have a series of problems such as the structure is complicated, transportation storage is used inconveniently, fuselage intensity is relatively poor, or the cost is expensive to realize.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a multi-rotor unmanned aerial vehicle, and solves the problems of low load, poor structural strength and high cost of the multi-rotor unmanned aerial vehicle.
In order to solve the technical problems, the technical scheme of the utility model is as follows:
a multi-rotor drone, comprising:
a body;
at least six arms fixedly connected with the machine body;
the at least six machine arms are fixedly connected through an annular reinforcing middle frame;
the tail end of each of the at least six machine arms is fixedly connected with a driving device.
Optionally, the driving device includes:
a motor mounting seat;
the motor is fixedly connected with the motor mounting seat and is positioned at the first end of the surface of the motor mounting seat;
and the electric controller is fixedly connected with the motor mounting seat and is positioned at the second end of the surface of the motor mounting seat.
Optionally, the motor mounting seat is fixedly connected to the tail end of the horn through a countersunk screw and a fixed pipe clamp.
Optionally, the driving device further includes:
a power supply cable;
the power supply cable is led into the inner part of the horn from the inner part of the machine body, led out from the tail end of the horn, connected to the electric regulator, penetrates through the motor mounting seat and is finally connected to the motor.
Optionally, the annular reinforcing middle frame includes: and adjacent two of the at least six machine arms are fixedly connected through one strengthening frame single body.
Optionally, the reinforcing frame unit includes:
an aluminum column;
the first reinforcing plate is fixedly connected with the aluminum column and is positioned at the first end of the aluminum column;
and the second reinforcing plate is fixedly connected with the aluminum column and is positioned at the second end of the aluminum column.
Optionally, the single reinforcing frame is further provided with a reinforcing connecting rod, and the other end of the reinforcing connecting rod is detachably connected with the machine head or the pedal of the machine body.
Optionally, the single reinforcing frame further has a screw hole site.
Optionally, the horn with the fuselage body is through two sets of pipe clamp group link, pipe clamp group includes:
fixing the pipe clamp;
the countersunk screw is fixedly connected with the fixed pipe clamp;
the long rod screw is fixedly connected with the fixed pipe clamp;
the machine arm is connected with the fixed pipe clamp through the countersunk head screw;
the machine body is connected with the fixed pipe clamp through the long rod screw.
Optionally, the middle part of the machine body is further provided with a quick-release plate, and the quick-release plate is installed on the machine body through a cover plate.
The scheme of the utility model at least comprises the following beneficial effects:
according to the scheme, the multi-rotor unmanned aerial vehicle comprises: a body; at least six arms fixedly connected with the machine body; the at least six machine arms are fixedly connected through an annular reinforcing middle frame; the tail end of each of the at least six machine arms is fixedly connected with a driving device. The loading capacity is improved, the machine body structure is strengthened, and the manufacturing and using cost is reduced.
Drawings
Figure 1 is a top view of a multi-rotor drone of the present invention;
figure 2 is an elevation view of a multi-rotor drone of the present invention;
fig. 3 is an enlarged schematic view of the arm tip structure of the multi-rotor drone of the present invention.
Description of reference numerals: 1. a body; 2. an annular reinforcing middle frame; 21. an aluminum column; 22. a first reinforcing plate; 31. a motor mounting seat; 32. a motor; 33. electrically adjusting; 4. a quick release plate; 5. and fixing the pipe clamp.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
As shown in fig. 1 and 2, an embodiment of the present invention proposes a multi-rotor drone, including:
a body 1;
at least six arms fixedly connected with the machine body 1;
the at least six machine arms are fixedly connected through an annular reinforcing middle frame 2;
the tail end of each of the at least six machine arms is fixedly connected with a driving device.
In this embodiment, through many rotor unmanned aerial vehicle, include: a body; at least six arms fixedly connected with the machine body; the at least six machine arms are fixedly connected through an annular reinforcing middle frame; the tail end of each of the at least six machine arms is fixedly connected with a driving device. The loading capacity is improved, the machine body structure is strengthened, and the manufacturing and using cost is reduced.
In an alternative embodiment of the present invention, the driving device includes:
a motor mount 31;
the motor 32 is fixedly connected with the motor mounting seat 31, and the motor 32 is positioned at a first end of the surface of the motor mounting seat 31;
with motor mount 31 fixed connection's electricity accent 33, electricity accent 33 is located the second end on motor mount 31 surface.
As shown in fig. 3, in this embodiment, the motor mounting seat 31 is a square box structure, and the motor 32 and the electronic scale 33 are both fixedly connected to the motor mounting seat 31 through screws, so that when a large load is loaded, the equipped high-power motor and electronic scale can enjoy better heat dissipation conditions, and the use load is reduced.
In another alternative embodiment of the present invention, the motor mounting seat 31 is fixedly connected to the end of the horn through a countersunk head screw and a fixed pipe clamp.
In this embodiment, the countersunk head screw may be formed with a 90-degree conical socket on the surface of the mounting hole of the motor mounting seat 31, and the head of the countersunk head screw is flush with the surface of the connecting member in the socket, so that the protrusion of the surface is reduced, and the upper and lower surfaces of the motor mounting seat 31 can be horizontally fixed.
In yet another alternative embodiment of the present invention, the driving device further includes:
a power supply cable;
the power supply cable is led into the inside of the horn from the inside of the body 1, led out from the tail end of the horn, connected to the electronic controller 33, passes through the motor mounting seat 31, and finally connected to the motor 32.
In this embodiment, the power supply cable further includes other cables, such as a control cable, but not limited to the above. The power supply cable is installed inside the horn and the motor mount, so that external interference can be reduced.
In a further alternative embodiment of the present invention, the annular reinforcing bezel 2 comprises: and adjacent two of the at least six machine arms are fixedly connected through one strengthening frame single body.
In this embodiment, center 2 is strengthened to the annular is stand alone type detachable design, matches detachable intensive frame monomer, and portability when both can realizing the unmanned aerial vehicle equipment like this can realize the reinforcement to unmanned aerial vehicle fuselage structure again, and the vibration and the bending of fuselage when having reduced big load flight provides fixed platform position for the expansion of unmanned aerial vehicle equipment afterwards again simultaneously.
In yet another alternative embodiment of the present invention, the reinforcing frame unit includes: an aluminum pillar 21; the first reinforcing plate 22 is fixedly connected with the aluminum column 21, and the first reinforcing plate 22 is positioned at a first end of the aluminum column 21; and the second reinforcing plate is fixedly connected with the aluminum column 21 and is positioned at the second end of the aluminum column 21.
In this embodiment, the reinforcing frame unit is installed between every two horn, and is formed by fixedly connecting the first reinforcing plate and the second reinforcing plate with the middle aluminum column through screws. Simultaneously the horn is can dismantle with strengthening the frame monomer and be connected, has adopted the design of the fixed pipe clamp that can relapse the dismouting, stock screw and mounting pad many times, makes like this many rotor unmanned aerial vehicle can realize the horn and strengthen the free dismouting of frame in the short time to the horn after disassembling can use the shipment of a normal size's SUV with strengthening the frame monomer, has outstanding portability.
In another optional embodiment of the present invention, a reinforcing link is further disposed on the reinforcing frame unit, and the other end of the reinforcing link is detachably connected to a machine head or a foot pedal of the machine body 1.
In the embodiment, the reinforcing connecting rods are further arranged on the reinforcing frame single bodies above the nose, the tail and the two landing gears, so that the strength of the machine body can be further improved.
In yet another alternative embodiment of the present invention, the single reinforcing frame further has screw hole sites.
In this embodiment, the screw hole sites may be reserved screw hole sites, which provides an expanded space and a fixed position for installing additional equipment in the future.
In a further alternative embodiment of the utility model, the horn is connected to the fuselage body 1 by two sets of pipe clamps, the sets of pipe clamps comprising: fixing the pipe clamp; the countersunk screw is fixedly connected with the fixed pipe clamp; the long rod screw is fixedly connected with the fixed pipe clamp; the machine arm is connected with the fixed pipe clamp through the countersunk head screw; the machine body 1 is connected with the fixed pipe clamp through the long rod screw.
In this embodiment, the countersunk screw of pipe clamp group inboard will fixed pipe clamp links firmly the innermost of horn, the through-hole in the pipe clamp group outside then passes the stock screw, will horn inner is fixed between the upper and lower board of fuselage body 1, has realized stable bearing capacity like this, and the dismouting ability also can be realized to the installation based on the screw simultaneously, further improvement unmanned aerial vehicle take the ability.
In yet another alternative embodiment of the present invention, a quick release plate 4 is further disposed in the middle of the fuselage body 1, and the quick release plate 4 is mounted on the fuselage body 1 through a cover plate.
In this embodiment, quick detach board 4 is used for maintaining fast and change flight control system, owing to itself does not undertake structure load effect, so need not set up the screw, can directly install on the fuselage through the form of apron, as the window of maintaining and upgrading unmanned aerial vehicle machine-mounted flight control system, can reduce unmanned aerial vehicle's maintenance pressure to a great extent like this, also be convenient for upgrade unmanned aerial vehicle flight control system in the future, also conveniently solve some problems that unmanned aerial vehicle met in the use.
According to the embodiment of the utility model, the load-carrying capacity is improved, the machine body structure is reinforced, and the manufacturing and using cost is reduced. Utilize high-power motor unit and outstanding fuselage design simultaneously, realized many rotor unmanned aerial vehicle's maximization, big load change.
While the foregoing is directed to the preferred embodiment of the present invention, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the utility model as defined in the appended claims.
Claims (10)
1. A multi-rotor unmanned aerial vehicle, comprising:
a body (1);
at least six arms fixedly connected with the machine body (1);
the at least six machine arms are fixedly connected through an annular reinforcing middle frame (2);
the tail end of each of the at least six machine arms is fixedly connected with a driving device (3).
2. A multi-rotor drone according to claim 1, characterized in that the drive means (3) comprise:
a motor mounting seat (31);
the motor (32) is fixedly connected with the motor mounting seat (31), and the motor (32) is positioned at the first end of the surface of the motor mounting seat (31);
with motor mount pad (31) fixed connection's electricity accent (33), electricity accent (33) are located the second end on motor mount pad (31) surface.
3. A multi-rotor drone according to claim 2, characterized in that the motor mount (31) is fixedly connected to the end of the horn by means of countersunk screws and fixed pipe clamps.
4. A multi-rotor drone according to claim 2, wherein the drive means (3) further comprise: a power supply cable; the power supply cable is led into the inner part of the horn from the inner part of the machine body (1), led out from the tail end of the horn, connected to the electric controller (33), penetrates through the motor mounting seat (31) and finally connected to the motor (32).
5. A multi-rotor drone according to claim 1, characterized in that the annular reinforcing middle frame (2) comprises: and adjacent two of the at least six machine arms are fixedly connected through one strengthening frame single body.
6. The multi-rotor drone of claim 5, wherein the reinforced frame unit includes:
an aluminum column (21);
the first reinforcing plate (22) is fixedly connected with the aluminum column (21), and the first reinforcing plate (22) is positioned at the first end of the aluminum column (21);
and the second reinforcing plate is fixedly connected with the aluminum column (21) and is positioned at the second end of the aluminum column (21).
7. The unmanned rotorcraft of claim 6, wherein the reinforcing frame is further provided with a reinforcing connecting rod, and the other end of the reinforcing connecting rod is detachably connected with a nose or a pedal of the fuselage body (1).
8. The multi-rotor drone of claim 6, wherein the stiffening frame monomers further have screw hole sites thereon.
9. A multi-rotor unmanned aerial vehicle according to claim 1, wherein the horn and the fuselage body (1) are connected by two sets of pipe clamps, the pipe clamps including:
a fixed pipe clamp (5);
the countersunk head screw is fixedly connected with the fixed pipe clamp (5);
a long rod screw fixedly connected with the fixed pipe clamp (5);
the machine arm is connected with the fixed pipe clamp (5) through the countersunk head screw;
the machine body (1) is connected with the fixed pipe clamp (5) through the long rod screw.
10. A multi-rotor unmanned aerial vehicle according to claim 1, wherein the fuselage body (1) is further provided at a middle portion thereof with a quick release plate (4), and the quick release plate (4) is mounted on the fuselage body (1) through a cover plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122667348.4U CN216185991U (en) | 2021-11-03 | 2021-11-03 | Multi-rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122667348.4U CN216185991U (en) | 2021-11-03 | 2021-11-03 | Multi-rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216185991U true CN216185991U (en) | 2022-04-05 |
Family
ID=80900008
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122667348.4U Active CN216185991U (en) | 2021-11-03 | 2021-11-03 | Multi-rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216185991U (en) |
-
2021
- 2021-11-03 CN CN202122667348.4U patent/CN216185991U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101443238B (en) | Device for attaching an aircraft engine | |
| CN206243488U (en) | Many power combinations change the unmanned plane for adapting to different landing mode different task load | |
| EP3594113A1 (en) | An apparatus for adjusting the center of gravity of a vertical take-off and landing aircraft | |
| CN105186767A (en) | Electric motor coach driving motor suspending system and installation method thereof | |
| CN102991727A (en) | Constraint system of airplane structure test | |
| CN113353270A (en) | Power system and flight device with same | |
| CN104576999A (en) | Electric car and power battery pack | |
| CN216185991U (en) | Multi-rotor unmanned aerial vehicle | |
| CN114104256A (en) | Multi-rotor unmanned aerial vehicle | |
| CN116039981B (en) | Adaptive multi-module assembled unmanned aerial vehicle | |
| CN204906085U (en) | [electric] motor coach driving motor suspension system | |
| CN207931974U (en) | A kind of device that unmanned plane horn quickly removes and installs | |
| CN212448021U (en) | Throwing type unmanned aerial vehicle fuselage | |
| CN110155312B (en) | Battery compartment of multi-rotor manned aircraft and manned aircraft comprising battery compartment | |
| CN211196626U (en) | Power supply system embedded unmanned aerial vehicle | |
| CN210338280U (en) | Many rotors manned vehicle | |
| CN202201166U (en) | Servo control integrated rapid assembling and dismantling airfoil system of unmanned aerial vehicle | |
| CN112478178A (en) | Mounting structure is placed to single rotor no aileron unmanned aerial vehicle engine | |
| CN206954485U (en) | Depopulated helicopter modular rack structure | |
| US11565823B2 (en) | Systems and methods of retrofitting an aircraft engine to an aircraft | |
| CN217049054U (en) | Helicopter equipment support | |
| CN218806678U (en) | Based on unmanned aerial vehicle seeker carry device | |
| CN207045653U (en) | Large aircraft organism safe is tethered at handle | |
| CN217515363U (en) | Water surface transportation system using airship platform | |
| CN208828094U (en) | Hybrid power unmanned plane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230906 Address after: 101200 Zhongguancun Science and Technology Park, Pinggu District, Beijing Pinggu District, Zone 1-231206 (cluster registration) Patentee after: Beijing Hangyou Zhixing Intelligent Technology Co.,Ltd. Address before: 101300 9-90, building 6, Ronghui garden, airport economic core area, Shunyi District, Beijing Patentee before: BEIJING LINGCHUANG ZHONGCHENG TECHNOLOGY CO.,LTD. |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20231102 Address after: No. 27, 20th Floor, Building B, No. 1 Yaojian Road, North of Gaoxin Avenue and West of Heying Road, Donghu New Technology Development Zone, Wuhan City, Hubei Province, 430000 Patentee after: Hubei Wuchuang Hangyou Intelligent Technology Co.,Ltd. Address before: 101200 Zhongguancun Science and Technology Park, Pinggu District, Beijing Pinggu District, Zone 1-231206 (cluster registration) Patentee before: Beijing Hangyou Zhixing Intelligent Technology Co.,Ltd. |
|
| TR01 | Transfer of patent right |