CN216660275U - Automatic folding mechanism of many rotor crafts girder - Google Patents
Automatic folding mechanism of many rotor crafts girder Download PDFInfo
- Publication number
- CN216660275U CN216660275U CN202122679728.XU CN202122679728U CN216660275U CN 216660275 U CN216660275 U CN 216660275U CN 202122679728 U CN202122679728 U CN 202122679728U CN 216660275 U CN216660275 U CN 216660275U
- Authority
- CN
- China
- Prior art keywords
- push rod
- connecting rod
- foldable
- folding mechanism
- double
- 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
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Tents Or Canopies (AREA)
Abstract
The utility model relates to an automatic folding mechanism for a crossbeam of a multi-rotor aircraft, which comprises a foldable half-beam, a connecting rod, a telescopic push rod, a push rod mounting seat, a fixed half-beam and a rotating shaft, wherein one end of the telescopic push rod is fixedly connected with the push rod mounting seat, the push rod mounting seat is fixedly connected with the fixed half-beam, the other end of the telescopic push rod is hinged with the connecting rod, the connecting rod is fixedly connected with the foldable half-beam, and the foldable half-beam is hinged with the fixed half-beam through the rotating shaft. Adopt flexible push rod to drive the connecting rod motion, through the connecting rod with can fold the fixed connection of half roof beam and can fold half roof beam and fixed half roof beam's hinged joint, thereby it is rotary motion around the pivot to drive can fold half roof beam, flexible through changing flexible push rod, thereby realize that many rotor crafts can fold the expansion and folding of half roof beam, the volume is twice less than the volume when expanding after the girder of many rotors is folding, solved many rotor crafts 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 folding 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 folding mechanism for 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 automatic folding mechanism comprises a foldable half beam, a connecting rod, a telescopic push rod, a push rod mounting seat, a fixed half beam and a rotating shaft, wherein one end of the telescopic push rod is fixedly connected with the push rod mounting seat, the push rod mounting seat is fixedly connected with the fixed half beam, the other end of the telescopic push rod is hinged with the connecting rod, the connecting rod is fixedly connected with the foldable half beam, and the foldable half beam is hinged with the fixed half beam through the rotating shaft.
Furthermore, the fixed half beam is of a square tubular structure, and the inner end of the fixed half beam is fixedly connected with the main body structure of the machine body.
Furthermore, fixed half roof beam outer end is provided with first pair of otic placode, first pair of otic placode is provided with the bearing, the pivot passes through the bearing with fixed half roof beam is connected.
Furthermore, the foldable half beam is provided with a second double-lug plate, and the connecting rod is fixedly arranged in the second double-lug plate.
Further, the first double-ear plate is larger than the second double-ear plate, and the first double-ear plate is connected with the second double-ear plate through the rotating shaft.
The utility model has the beneficial effects that:
the folding multi-rotor aircraft adopts the telescopic push rod to drive the connecting rod to move, the foldable half beam is driven to rotate around the rotating shaft through the fixed connection of the connecting rod and the foldable half beam and the hinged connection of the foldable half beam and the fixed half beam, the folding multi-rotor aircraft can be unfolded and folded by changing the telescopic push rod to stretch, the folded volume of the girder of the multi-rotor aircraft is one time smaller than that of the girder of the multi-rotor aircraft during unfolding, and the problem that the multi-rotor aircraft is inconvenient to transport due to larger volume 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.
Figure 1 is a schematic structural view of a multi-rotor aircraft longeron automatic folding mechanism according to the present invention;
figure 2 is an enlarged view of a longeron automatic folding mechanism ear plate of a multi-rotor aircraft according to the present invention.
In the figure: 1. the foldable half beam comprises a foldable half beam body, 2 connecting rods, 3 telescopic push rods, 4 push rod mounting seats, 5 fixed half beam bodies, 6 rotating shafts, 7 first double-lug plates, 8 second double-lug plates.
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. 1-2, the utility model provides an automatic folding mechanism for a crossbeam of a multi-rotor aircraft, which comprises a foldable half-beam 1, a connecting rod 2, a telescopic push rod 3, a push rod mounting seat 4, a fixed half-beam 5 and a rotating shaft 6, wherein one end of the telescopic push rod 3 is fixedly connected with the push rod mounting seat 4, the push rod mounting seat 4 is fixedly connected with the fixed half-beam 5, the other end of the telescopic push rod 3 is hinged with the connecting rod 2, the connecting rod 2 is fixedly connected with the foldable half-beam 1, and the foldable half-beam 1 is hinged with the fixed half-beam 5 through the rotating shaft 6.
In one embodiment of the present invention, the fixed half-beam 5 is a square tubular structure, and the inner end of the fixed half-beam 5 is fixedly connected with the main body structure of the machine body.
In an embodiment of the present invention, the outer end of the fixed half-beam 5 is provided with a first double-lug plate 7, the first double-lug plate 7 is provided with a bearing, and the rotating shaft 6 is connected with the fixed half-beam 5 through the bearing.
In one embodiment of the utility model, the foldable half-beam 1 is provided with a second double ear plate 8, the connecting rod 2 being fixedly mounted in the second double ear plate 8.
In an embodiment of the present invention, the first double ear plate 7 is larger than the second double ear plate 8, and the first double ear plate 7 is connected to the second double ear plate 8 through the rotating shaft 6
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 automatic folding mechanism is used specifically, according to the automatic folding mechanism for the girder of the multi-rotor aircraft, the telescopic push rod 3 drives the connecting rod 2 to move when being stretched, the connecting rod 2 is fixedly connected with the foldable half-beam 1, so that the foldable half-beam 1 is driven to move, the foldable half-beam 1 is hinged with the fixed half-beam 5, the moving direction of the foldable half-beam 1 is limited, the foldable half-beam 1 can only rotate around the rotating shaft 6, when the push rod 3 is shortened, the foldable half-beam 1 is unfolded around the rotating shaft 6, and when the push rod 3 is shortened to the shortest, the foldable half-beam 1 is just completely unfolded; when the push rod 3 extends, the foldable half beam 1 is folded around the rotating shaft 6, when the push rod 3 extends to the longest length, the foldable half beam 1 is just completely folded, the folded volume of the girder of the multi-rotor wing is one time smaller than that of the unfolded volume, and the problem that the multi-rotor wing aircraft is inconvenient to transport due to the 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 an automatic folding mechanism of many rotor crafts girder which characterized in that: the foldable half beam structure is characterized by comprising a foldable half beam (1), a connecting rod (2), a telescopic push rod (3), a push rod mounting seat (4), a fixed half beam (5) and a rotating shaft (6), wherein one end of the telescopic push rod (3) is fixedly connected with the push rod mounting seat (4), the push rod mounting seat (4) is fixedly connected with the fixed half beam (5), the other end of the telescopic push rod (3) is hinged with the connecting rod (2), the connecting rod (2) is fixedly connected with the foldable half beam (1), and the foldable half beam (1) is hinged with the fixed half beam (5) through the rotating shaft (6).
2. The automated folding mechanism for a longeron of a multi-rotor aircraft of claim 1, wherein: the fixed half beam (5) is of a square tubular structure, and the inner end of the fixed half beam (5) is fixedly connected with the main body structure of the machine body.
3. The automated folding mechanism for a longeron of a multi-rotor aircraft of claim 1, wherein: fixed half roof beam (5) outer end is provided with first pair otic placode (7), first pair of otic placode (7) are provided with the bearing, pivot (6) are passed through the bearing with fixed half roof beam (5) are connected.
4. The automated folding mechanism for a longeron of a multi-rotor aircraft of claim 3, wherein: the foldable half beam (1) is provided with a second double-lug plate (8), and the connecting rod (2) is fixedly arranged in the second double-lug plate (8).
5. The automated folding mechanism for a longeron of a multi-rotor aircraft of claim 4, wherein: the first double-ear plate (7) is larger than the second double-ear plate (8), and the first double-ear plate (7) is connected with the second double-ear plate (8) through the rotating shaft (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122679728.XU CN216660275U (en) | 2021-11-04 | 2021-11-04 | Automatic folding mechanism of many rotor crafts girder |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122679728.XU CN216660275U (en) | 2021-11-04 | 2021-11-04 | Automatic folding mechanism of many rotor crafts girder |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216660275U true CN216660275U (en) | 2022-06-03 |
Family
ID=81783001
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122679728.XU Active CN216660275U (en) | 2021-11-04 | 2021-11-04 | Automatic folding mechanism of many rotor crafts girder |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216660275U (en) |
-
2021
- 2021-11-04 CN CN202122679728.XU patent/CN216660275U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109703741A (en) | Folding morphing wing and aircraft based on Sarrus structure drive | |
| CN109592031B (en) | Bionic flapping wing aircraft with single side and single node | |
| CN106741912B (en) | Foldable long-endurance multi-rotor unmanned aerial vehicle | |
| CN111645848B (en) | Skeleton structure of telescopic wing | |
| CN109911195B (en) | Connecting rod type foldable flapping wing micro flying robot | |
| CN208412131U (en) | Vertical take-off and landing drone | |
| CN216660275U (en) | Automatic folding mechanism of many rotor crafts girder | |
| CN104787328B (en) | A kind of rotor folding and unfolding mechanism being applicable to composite aircraft | |
| CN112896487B (en) | Unmanned aerial vehicle synchronous unfolding and folding system, method and application | |
| CN108891591A (en) | A kind of aircraft | |
| CN118124847A (en) | Aerodynamic force-assisted plane-variable folding and unfolding mechanism for sweepback wings | |
| CN113148136A (en) | Unmanned aerial vehicle with fixed wing and many rotors switch function | |
| CN115675852B (en) | Tilting wing aircraft and flight control method thereof | |
| CN114435590B (en) | Variable-incidence-angle ornithopter with wing rotation function | |
| CN216611596U (en) | Unmanned aerial vehicle | |
| CN215436979U (en) | Paddle folding device and unmanned aerial vehicle automatic hangar | |
| CN107054637B (en) | Folding system of multi-rotor helicopter | |
| CN217170961U (en) | Novel unmanned aerial vehicle | |
| WO2018224033A1 (en) | Aircraft with imitation beetle elytron wings | |
| CN206068153U (en) | For the unmanned plane of geography information exploration | |
| CN210011875U (en) | Foldable six-shaft multi-rotor flight body | |
| CN106542088A (en) | Unmanned plane rotor folding and unfolding controlling organization and unmanned plane rotor extension and retraction system | |
| CN216332710U (en) | Automatic telescopic mechanism of girder of multi-rotor aircraft | |
| CN109911196B (en) | Drag-reduction foldable flapping-wing micro air vehicle | |
| CN217864742U (en) | Multi-degree-of-freedom flapping-wing flying robot transmission mechanism |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230811 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. |
|
| TR01 | Transfer of patent right |