CN216332710U - Automatic telescopic mechanism of girder of multi-rotor aircraft - Google Patents
Automatic telescopic mechanism of girder of multi-rotor aircraft Download PDFInfo
- Publication number
- CN216332710U CN216332710U CN202122679844.1U CN202122679844U CN216332710U CN 216332710 U CN216332710 U CN 216332710U CN 202122679844 U CN202122679844 U CN 202122679844U CN 216332710 U CN216332710 U CN 216332710U
- Authority
- CN
- China
- Prior art keywords
- motor
- lead screw
- screw nut
- aircraft
- telescopic
- 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
Images
Landscapes
- Transmission Devices (AREA)
Abstract
The utility model relates to an automatic telescopic mechanism of a crossbeam of a multi-rotor aircraft, which comprises a motor, a motor fixing seat, a coupler, a lead screw nut, a telescopic beam and a guide pipe, the motor is fixedly arranged on the motor fixing seat, the output end of the motor is connected with the coupling, the other end of the coupler is fixedly connected with the lead screw, the lead screw is provided with the lead screw nut, the outer side of the screw nut is fixedly connected with the end surface of the telescopic beam, the guide pipe is arranged on the outer side of the telescopic beam, the motor is adopted to drive the screw, the screw and the screw nut are engaged to move, thereby drive the flexible roof beam motion with screw nut fixed connection, through changing turning to of motor, realize the flexible function of automation of roof beam, the girder of many rotors shortens the back volume and than the volume when expanding twice, has solved many rotors aircraft because of the great inconvenient problem of transporting that leads to of volume.
Description
Technical Field
The utility model relates to the technical field of aircrafts, in particular to an automatic telescopic mechanism for a crossbeam of a multi-rotor aircraft.
Background
The multi-rotor aircraft is an unmanned flying machine applied to various industries, wherein in-flight displacement motion control enables the attitude angle of the multi-rotor aircraft to be changed through adjusting the rotating speed of each rotor of the multi-rotor aircraft and through the rotating speed difference between the rotors, when the attitude angle is not zero, the pulling force generated by the rotation of the rotors is orthogonally decomposed into a component parallel to a vertical plane and a component parallel to a horizontal plane, the former is used for offsetting the gravity of the multi-rotor aircraft, and the latter drives the multi-rotor aircraft to move horizontally.
At present, the vertical take-off and landing fixed wing aircrafts appearing at home and abroad are very many, wherein most of the vertical take-off and landing parts adopt electric multiple rotors, and in the actual use process, in order to pursue the efficiency of a complete machine, the multiple rotors are generally adopted for arrangement, so that the volume of the whole aircraft is larger, but the whole aircraft is difficult to transport after being unfolded.
An effective solution to the problems in the related art has not been proposed yet.
SUMMERY OF THE UTILITY MODEL
Aiming at the technical problems in the prior art, the utility model provides an automatic telescopic mechanism of a crossbeam of a multi-rotor aircraft, which can solve the problem that the multi-rotor aircraft is inconvenient to transport due to large volume.
In order to achieve the technical purpose, the technical scheme of the utility model is realized as follows:
the utility model provides an automatic telescopic machanism of many rotor crafts girder, includes motor, motor fixing base, shaft coupling, lead screw, screw nut, flexible roof beam and stand pipe, motor fixed mounting in the motor fixing base, the output of motor is connected with the shaft coupling, the other end of shaft coupling with lead screw fixed connection, the lead screw is provided with screw nut, screw nut's the outside with the terminal surface fixed connection of flexible roof beam, the flexible roof beam outside is provided with the stand pipe.
Further, the motor fixing seat is fixedly connected with the aircraft body structure.
Further, the lead screw is connected with the lead screw nut in a meshed mode.
Further, the inside hollow tubular structure that is of flexible roof beam, flexible roof beam outside is square structure, the inside quad slit structure that is of stand pipe, flexible roof beam with stand pipe clearance fit.
Furthermore, the guide pipe is fixedly connected with the aircraft body structure
The utility model has the beneficial effects that:
the motor is adopted to drive the lead screw, the telescopic beam fixedly connected with the lead screw nut is driven to move through the meshing motion of the lead screw and the lead screw nut, the automatic telescopic function of the telescopic beam is realized through changing the steering direction of the motor, the volume of the girder with the multiple rotors is twice smaller than that of the girder with the multiple rotors when the girder is extended after being shortened, and the problem that the transportation of the aircraft with the multiple rotors is inconvenient due to the fact that the size of the aircraft is larger is solved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
Fig. 1 is a schematic structural view of a boom automatic retraction mechanism for a multi-rotor aircraft according to the present invention.
In the figure: 1. the motor 2, the motor fixing seat 3, the coupler 4, the lead screw 5, the lead screw nut 6, the telescopic beam 7 and the guide pipe.
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. All other embodiments that can be derived by one of ordinary skill in the art from the embodiments given herein are intended to be within the scope of the present invention.
As shown in fig. 1, the utility model provides an automatic telescoping mechanism for a crossbeam of a multi-rotor aircraft, which comprises a motor 1, a motor fixing seat 2, a coupler 3, a screw rod 4, a screw nut 5, a telescopic beam 6 and a guide pipe 7, wherein the motor 1 is fixedly installed on the motor fixing seat 2, the output end of the motor 1 is connected with the coupler 3, the other end of the coupler 3 is fixedly connected with the screw rod 4, the screw rod 4 is provided with the screw nut 5, the outer side of the screw nut 5 is fixedly connected with the end face of the telescopic beam 6, and the guide pipe 7 is arranged on the outer side of the telescopic beam 6.
In one embodiment of the present invention, the motor fixing base 2 is fixedly connected with an aircraft body structure.
In one embodiment of the utility model, the spindle 4 is in a meshing connection with the spindle nut 5.
In a specific embodiment of the present invention, the inside of the telescopic beam 6 is a hollow tubular structure, the outside of the telescopic beam 6 is a square structure, the inside of the guide tube 7 is a square hole structure, and the telescopic beam 6 is in clearance fit with the guide tube 7.
In a particular embodiment of the utility model, the guide tube 7 is fixedly connected to the aircraft airframe structure.
For the convenience of understanding the above technical solution of the present invention, the following detailed description of the above technical solution of the present invention is made by specific use of:
when the multi-rotor aircraft girder automatic telescoping mechanism is used specifically, the motor 1 drives the lead screw 4 to move through the coupler 3, the lead screw 4 is meshed with the lead screw nut 5 to drive the telescopic girder 6 fixedly connected with the lead screw nut 5 to move, the telescopic girder 6 can only do axial linear motion under the limitation of the guide pipe 7, the automatic telescoping function of the telescopic girder 6 is realized by changing the steering direction of the motor 1, the volume of the multi-rotor aircraft girder after being shortened is twice that of the multi-rotor aircraft girder when being unfolded, and the problem that the multi-rotor aircraft is inconvenient to transport due to large volume is solved.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the utility model, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (5)
1. The utility model provides a many rotor crafts girder automatic telescoping mechanism which characterized in that: including motor (1), motor fixing base (2), shaft coupling (3), lead screw (4), screw nut (5), flexible roof beam (6) and stand pipe (7), motor (1) fixed mounting in motor fixing base (2), the output of motor (1) is connected with shaft coupling (3), the other end of shaft coupling (3) with lead screw (4) fixed connection, lead screw (4) are provided with screw nut (5), the outside of screw nut (5) with the terminal surface fixed connection of flexible roof beam (6), flexible roof beam (6) outside is provided with stand pipe (7).
2. The automated multi-rotor aircraft longeron telescoping mechanism of claim 1, wherein: the motor fixing seat (2) is fixedly connected with an aircraft body structure.
3. The automated multi-rotor aircraft longeron telescoping mechanism of claim 1, wherein: the screw rod (4) is meshed with the screw rod nut (5).
4. The automated multi-rotor aircraft longeron telescoping mechanism of claim 1, wherein: the telescopic beam is characterized in that the inside of the telescopic beam (6) is of a hollow tubular structure, the outside of the telescopic beam (6) is of a square structure, the inside of the guide pipe (7) is of a square hole structure, and the telescopic beam (6) is in clearance fit with the guide pipe (7).
5. A rotary-wing aircraft girder automatic retraction mechanism according to any of claims 2 to 4, wherein: the guide pipe (7) is fixedly connected with the aircraft body structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122679844.1U CN216332710U (en) | 2021-11-04 | 2021-11-04 | Automatic telescopic mechanism of girder of multi-rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122679844.1U CN216332710U (en) | 2021-11-04 | 2021-11-04 | Automatic telescopic mechanism of girder of multi-rotor aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216332710U true CN216332710U (en) | 2022-04-19 |
Family
ID=81134393
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122679844.1U Active CN216332710U (en) | 2021-11-04 | 2021-11-04 | Automatic telescopic mechanism of girder of multi-rotor aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216332710U (en) |
-
2021
- 2021-11-04 CN CN202122679844.1U patent/CN216332710U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205707297U (en) | Fixed-wing unmanned plane | |
| CN111301677A (en) | Eight-wing flapping wing aircraft capable of hovering and flight control method thereof | |
| CN103935511A (en) | Tilt-three-rotor craft | |
| CN104787327A (en) | Axle distance-variable multi-rotor aircraft | |
| CN105501439A (en) | Rotor wing decelerating and locking device for rotor wing and fixed wing combined type vertical take-off and landing air vehicle | |
| CN113232852A (en) | Transmission mechanism for wings of tilt rotor aircraft | |
| CN105775122A (en) | Tilt rotor type aircraft | |
| CN101177167A (en) | Power-driven system of aircraft | |
| CN212401527U (en) | Novel unmanned aerial vehicle undercarriage receive and releases device | |
| CN216332710U (en) | Automatic telescopic mechanism of girder of multi-rotor aircraft | |
| CN114987752B (en) | Wing for tiltrotor aircraft, tiltrotor aircraft and tilting method | |
| CN111762316A (en) | Tilting component of tilting rotor unmanned aerial vehicle, tilting rotor unmanned aerial vehicle and using method | |
| CN209972084U (en) | Foldable triphibian four-rotor aircraft | |
| CN107161330A (en) | A kind of variable abnormally-structured displacement multi-rotor unmanned aerial vehicle | |
| CN209064352U (en) | A kind of non-3 points of coaxial multirotor helicopters | |
| CN113184185A (en) | Streamlined coaxial many rotor unmanned aerial vehicle of adaptable adverse circumstances | |
| CN113148136A (en) | Unmanned aerial vehicle with fixed wing and many rotors switch function | |
| CN209617480U (en) | A kind of unmanned vehicle | |
| CN108454824B (en) | Multistage telescopic wing mechanism | |
| CN203652108U (en) | Transmission mechanism for extension and retraction of ceiling propeller of vertical takeoff and landing low-altitude civil rotorcraft | |
| CN206871352U (en) | Hybrid power unmanned plane with small rotor | |
| CN218229412U (en) | Cycloidal propeller duct power device and aircraft using same | |
| CN216660275U (en) | Automatic folding mechanism of many rotor crafts girder | |
| CN212448078U (en) | Tilting rotor unmanned aerial vehicle tilting component and tilting rotor unmanned aerial vehicle | |
| CN205440866U (en) | Rotorcraft aircraft verts |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230809 Address after: Room 202, No. 11 Dexing Lane, Chong'an District, Wuxi City, Jiangsu Province, 214000 Patentee after: Yang Haiyan Address before: 215143 Building 2, No. 18, Qianghua Road, Huayang village, Wangting Town, Xiangcheng District, Suzhou City, Jiangsu Province Patentee before: HELIPELLER GENERAL AIRCRAFT CO.,LTD. |