CN216140166U - Rotor wing retracting mechanism for vertical take-off and landing oil-driven unmanned aerial vehicle - Google Patents
Rotor wing retracting mechanism for vertical take-off and landing oil-driven unmanned aerial vehicle Download PDFInfo
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- CN216140166U CN216140166U CN202121439473.3U CN202121439473U CN216140166U CN 216140166 U CN216140166 U CN 216140166U CN 202121439473 U CN202121439473 U CN 202121439473U CN 216140166 U CN216140166 U CN 216140166U
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Abstract
The utility model provides a rotor wing retracting mechanism for a vertical lifting oil-driven unmanned aerial vehicle, which comprises a rotor wing assembly and a retracting device, wherein the rotor wing assembly comprises a rotor wing and a rotating shaft; the winding and unwinding device comprises a fixed assembly fixedly installed inside the unmanned aerial vehicle body, a driving motor fixedly installed on the fixed assembly and a connecting assembly fixedly installed at the output end of the driving motor, wherein one end of the rotor wing assembly is fixedly connected with a rotating frame, and the rotating frame is respectively connected with the fixed assembly and the connecting assembly in a rotating mode, so that winding and unwinding driving of the rotor wing assembly is realized. According to the utility model, the retraction driving of the rotor wing assembly is realized by arranging the retraction device, the retraction control of the rotor wing assembly is realized, and the energy conversion efficiency of the unmanned aerial vehicle in the flight process is further increased; the fixing assembly is rotatably connected with the rotor assembly through the connecting assembly, so that the rotor assembly is matched with the rotor assembly in a folding and unfolding mode under the driving of the driving motor, the rotor assembly is controlled to be stored in one side of the unmanned aerial vehicle body, and the rotor assembly of the unmanned aerial vehicle is more convenient to store.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicles, in particular to a rotor wing retraction mechanism for a vertical take-off and landing oil-driven unmanned aerial vehicle.
Background
The rotor of unmanned aerial vehicle among the prior art is general fixed mounting in the fuselage outside for unmanned aerial vehicle's rotor part can cause air resistance for unmanned aerial vehicle's flight in-process, leads to the flight in-process to cause energy loss.
SUMMERY OF THE UTILITY MODEL
In view of the above, the present invention provides a rotor retraction mechanism for a vertical lift unmanned aerial vehicle, which facilitates retraction of a rotor.
In order to solve the technical problems, the utility model adopts the technical scheme that: a rotor wing retracting mechanism for a vertical lifting oil-driven unmanned aerial vehicle comprises a rotor wing assembly and a retracting device;
the winding and unwinding devices include fixed subassembly, the driving motor of fixed mounting on fixed subassembly and the coupling assembling of fixed mounting in driving motor's output of fixed mounting in unmanned aerial vehicle fuselage inside, the one end fixedly connected with rotating turret of rotor subassembly, the rotating turret rotates with fixed subassembly and coupling assembling respectively and is connected, realizes the drive of receiving and unwinding to the rotor subassembly.
The fixed subassembly is including fixed inserting the fixed grudging post and the fixed crossbearer of fixed mounting in the unmanned aerial vehicle fuselage outside of locating the unmanned aerial vehicle fuselage inside, be provided with in the fixed crossbearer with coupling assembling assorted first connect the through-hole.
The fixed vertical frame is fixedly connected with the fixed transverse frame, and one end of the fixed vertical frame is rotatably connected with one end of the rotating frame and used for rotating the rotor wing assembly.
The fixed grudging post one side is fixed to be provided with the spacing frame of drive, the spacing frame of drive is including the fixed roof-rack of drive and the spacing chassis of drive, driving motor fixed mounting is on the spacing chassis of drive, driving motor fixed insertion locates the fixed roof-rack middle part of drive, still be provided with second connect the via hole on the spacing chassis of drive.
Coupling assembling includes fixed mounting in the first link of driving motor output and fixed mounting the connecting rod on first link, the one end of first link is installed inside fixed crossbearer.
The coupling assembling still locates the connecting rod including fixed cover and connects the lantern ring, connect lantern ring one side and rotate the first connecting piece of connection, the other end of first connecting piece rotates and is connected with the second connecting piece.
A rotating shaft is arranged in the fixed transverse frame, and the other end of the second connecting piece is sleeved on the rotating shaft.
The connecting assembly further comprises a third connecting piece which is rotatably connected with the other end of the first connecting piece, and the other end of the third connecting piece is rotatably connected with the rotating frame.
The top of fixed crossbearer is provided with the first recess of bracing piece assorted with the rotor subassembly, unmanned aerial vehicle fuselage side be provided with the rotor part assorted second recess of rotor subassembly, realize accomodating of rotor subassembly.
The second connecting through hole is matched with the connecting rod, so that the moving position of the connecting rod is limited.
Preferably, the rotor assembly is a rotor assembly in the prior art, and the details are not repeated herein.
The utility model has the advantages and positive effects that:
(1) according to the utility model, the retraction driving of the rotor wing assembly is realized by arranging the retraction device, the retraction control of the rotor wing assembly is realized, and the energy conversion efficiency of the unmanned aerial vehicle in the flight process is further increased.
(2) The fixing assembly is rotatably connected with the rotor assembly through the connecting assembly, so that the rotor assembly is driven by the driving motor to be matched with the rotor assembly in a retracting mode, the rotor assembly rotates along the fixing vertical frame due to transmission of the connecting assembly, and the rotor assembly is controlled to be stored on one side of the unmanned aerial vehicle body.
(3) According to the unmanned aerial vehicle, the rotor wing assembly is stored at one side of the unmanned aerial vehicle body by arranging the first groove and the second groove which are matched with the rotor wing assembly, so that the rotor wing assembly of the unmanned aerial vehicle is more convenient to store.
Drawings
The accompanying drawings, which are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this specification, illustrate embodiments of the utility model and together with the description serve to explain the principles of the utility model and not to limit the utility model. In the drawings:
fig. 1 is an overall structural view of a rotor wing retracting mechanism for a vertical take-off and landing oil-driven unmanned aerial vehicle according to the present invention;
fig. 2 is a cross-sectional view of a rotor retraction mechanism for a vertical take-off and landing hydro-drone in accordance with the present invention;
fig. 3 is a schematic diagram of the internal structure of a rotor retraction mechanism for a vertical take-off and landing unmanned aerial vehicle according to the present invention;
fig. 4 is a schematic partial structural view of a fuselage of a vertical take-off and landing oil-driven unmanned aerial vehicle for a rotor wing retraction mechanism of the unmanned aerial vehicle;
FIG. 5 is an enlarged view of a portion of FIG. 1;
in the figure:
1. a rotor assembly; 11. a rotating frame; 12. a support bar; 13. a rotor section; 2. a retracting device; 3. a fixing assembly; 31. fixing a vertical frame; 32. fixing the transverse frame; 33. a first connecting through hole; 34. driving the limiting frame; 341. driving the fixed top frame; 342. driving the limiting underframe; 343. a second connecting through hole; 35. A rotating shaft; 36. a first groove; 4. a drive motor; 5. a connecting assembly; 51. a first connecting frame; 52. A connecting rod; 53. a connecting lantern ring; 54. a first connecting member; 55. a second connecting member; 56. a third connecting member; 6. a second groove.
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, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When a component is referred to as being "connected" to another component, it can be directly connected to the other component or intervening components may also be present. When a component is referred to as being "disposed on" another component, it can be directly on the other component or intervening components may also be present. The terms "vertical," "horizontal," "left," "right," and the like as used herein are for illustrative purposes only.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the utility model herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the utility model. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.
As shown in fig. 1 and 5, the present invention provides a rotor wing retracting mechanism for a vertical lifting/lowering unmanned aerial vehicle, which includes a rotor wing assembly 1 and a retracting device 2;
winding and unwinding devices 2 include fixed mounting in the inside fixed subassembly 3 of unmanned aerial vehicle fuselage, fixed mounting drive motor 4 and the coupling assembling 5 of fixed mounting in the output of drive motor 4 on fixed subassembly 3, rotor subassembly 1's one end fixedly connected with rotating turret 11, rotating turret 11 rotates with fixed subassembly 3 and coupling assembling 5 respectively and is connected, realizes the drive that receive and releases rotor subassembly 1.
The fixed component 3 comprises a fixed vertical frame 31 fixedly inserted inside the unmanned aerial vehicle body and a fixed cross frame 32 fixedly installed on the outer side of the unmanned aerial vehicle body, and a first connecting through hole 33 matched with the connecting component 5 is formed in the fixed cross frame 32.
Fixed grudging post 31 and fixed crossbearer 32 fixed connection, the one end of fixed grudging post 31 still rotates the one end that is connected with rotating turret 11 for realize with rotor subassembly 1's rotation.
As shown in fig. 1 and 2, a driving limiting frame 34 is fixedly arranged on one side of the fixed vertical frame 31, the driving limiting frame 34 includes a driving fixed top frame 341 and a driving limiting bottom frame 342, the driving motor 4 is fixedly mounted on the driving limiting bottom frame 342, the driving motor 4 is fixedly inserted in the middle of the driving fixed top frame 341, and a second connecting through hole 343 is further arranged on the driving limiting bottom frame 342.
As shown in fig. 1, 2 and 3, the connecting assembly 5 includes a first connecting frame 51 fixedly mounted at the output end of the driving motor 4, and a connecting rod 52 fixedly mounted on the first connecting frame 51, and one end of the first connecting frame 51 is mounted inside the fixed cross frame 32.
The connecting assembly 5 further comprises a connecting sleeve ring 53 fixedly sleeved on the connecting rod 52, a first connecting piece 54 is rotatably connected to one side of the connecting sleeve ring 53, and a second connecting piece 55 is rotatably connected to the other end of the first connecting piece 54.
In an embodiment, the connection collar 53 is matched with the connection rod 52, and fixing hoops are arranged on two sides of the connection collar 53 to fix the position of the connection collar 53.
A rotating shaft 35 is arranged in the fixed transverse frame 32, and the other end of the second connecting member 55 is sleeved on the rotating shaft 35.
The connecting assembly 5 further comprises a third connecting member 56 rotatably connected to the other end of the first connecting member 54, and the other end of the third connecting member 56 is rotatably connected to the rotating frame 11.
As shown in fig. 1, 2, 3 and 4, the top of fixed crossbearer 32 is provided with the first recess 36 of bracing piece 12 assorted with rotor subassembly 1, the unmanned aerial vehicle fuselage side is provided with the second recess 6 of 13 assorted with rotor subassembly 1's rotor portion, realizes accomodating rotor subassembly 1.
As shown in fig. 2, the second connecting through hole 343 is matched with the connecting rod 52, so as to limit the moving position of the connecting rod 52.
In the embodiment, the rotor assembly 1 is a rotor assembly 1 in the prior art, and the description is omitted here.
The working principle and the working process of the utility model are as follows:
when rotor assembly 1 needs to be accomodate:
the output end of the driving motor 4 extends out, the output end of the driving motor 4 drives the first connecting frame 51 to move towards the inside of the unmanned aerial vehicle, the first connecting frame 51 drives the connecting rod 52 to move towards the inside of the unmanned aerial vehicle, the connecting rod 52 drives the connecting sleeve ring 53 to move towards the inside of the unmanned aerial vehicle, the connecting sleeve ring 53 drives the first connecting piece 54 to move towards the inside of the unmanned aerial vehicle, the first connecting piece 54 drives the third connecting piece 56 to move towards the inside of the unmanned aerial vehicle, at the same time, the first connecting member 54 also drives the second connecting member 55 to rotate along the rotating shaft 35, further, the third link 56 rotates the rotary frame 11 along the position where the rotary frame 11 is connected to the stationary stand 31, and when the second link 55 reaches the lowest position, when the support rod 12 of the rotor assembly 1 is received in the first groove 36 and the rotor part 13 of the rotor assembly 1 is received in the second groove 6, the rotor assembly 1 is received;
when the rotor assembly 1 needs to be deployed:
the output of driving motor 4 is withdrawed, driving motor 4's output drives first link 51 and removes to the outside direction of unmanned aerial vehicle, first link 51 drives connecting rod 52 and removes to the outside direction of unmanned aerial vehicle, connecting rod 52 drives and connects lantern ring 53 and remove to the outside direction of unmanned aerial vehicle, it drives first connecting piece 54 and removes to the outside direction of unmanned aerial vehicle to connect lantern ring 53, first connecting piece 54 drives third connecting piece 56 and removes to the outside direction of unmanned aerial vehicle, meanwhile, first connecting piece 54 still drives second connecting piece 55 and rotates along axis of rotation 35, and then, third connecting piece 56 drives rotating turret 11 and rotates along rotating turret 11 and fixed grudging post 31 hookup location, when second connecting piece 55 reachs the highest position, when bracing piece 12 and the fixed pole setting of rotor subassembly 1 are in same straight line promptly, realize the expansion to rotor subassembly 1.
The utility model is characterized in that: by arranging the retraction device 2, retraction driving of the rotor wing assembly 1 is realized, retraction control of the rotor wing assembly 1 is realized, and further energy conversion efficiency of the unmanned aerial vehicle in the flight process is improved; the fixing component 3 is rotationally connected with the rotor wing component 1 through the connecting component 5, so that the rotor wing component 1 is driven by the driving motor 4 to be matched in a retractable manner, the rotor wing component 1 rotates along the fixing vertical frame 31 due to the transmission of the connecting component 5, and the rotor wing component 1 is controlled to be stored on one side of the unmanned aerial vehicle body; through setting up with rotor subassembly 1 assorted first recess 36 and second recess 6, realize accomodating rotor subassembly 1 in unmanned aerial vehicle fuselage one side for unmanned aerial vehicle's rotor subassembly 1 accomodate more conveniently.
The embodiments of the present invention have been described in detail, but the description is only for the preferred embodiments of the present invention and should not be construed as limiting the scope of the present invention. All equivalent changes and modifications made within the scope of the present invention should be covered by the present patent.
Claims (10)
1. A rotor wing retracting mechanism for a vertical lifting oil-driven unmanned aerial vehicle is characterized by comprising a rotor wing assembly (1) and a retracting device (2);
winding and unwinding devices (2) including fixed mounting in inside fixed subassembly (3), fixed mounting in driving motor (4) and the coupling assembling (5) of fixed mounting in the output of driving motor (4) on fixed subassembly (3) of unmanned aerial vehicle fuselage, the one end fixedly connected with rotating turret (11) of rotor subassembly (1), rotating turret (11) rotate with fixed subassembly (3) and coupling assembling (5) respectively and are connected, realize the drive that receive and releases rotor subassembly (1).
2. The rotor wing retracting mechanism for the vertical lifting oil-driven unmanned aerial vehicle is characterized in that the fixing component (3) comprises a fixing vertical frame (31) fixedly inserted in the unmanned aerial vehicle body and a fixing cross frame (32) fixedly installed on the outer side of the unmanned aerial vehicle body, and a first connecting through hole (33) matched with the connecting component (5) is formed in the fixing cross frame (32).
3. A rotor wing retracting mechanism for a vertical take-off and landing oil-driven unmanned aerial vehicle according to claim 2, wherein the fixed vertical frame (31) is fixedly connected with the fixed transverse frame (32), and one end of the fixed vertical frame (31) is rotatably connected with one end of the rotating frame (11) for realizing rotation with the rotor wing assembly (1).
4. The rotor wing retracting mechanism for the vertical lifting oil-driven unmanned aerial vehicle is characterized in that one side of the fixed vertical frame (31) is fixedly provided with a driving limiting frame (34), the driving limiting frame (34) comprises a driving fixed top frame (341) and a driving limiting underframe (342), the driving motor (4) is fixedly installed on the driving limiting underframe (342), the driving motor (4) is fixedly inserted in the middle of the driving fixed top frame (341), and a second connecting through hole (343) is further arranged on the driving limiting underframe (342).
5. A rotor wing retracting mechanism for a vertical take-off and landing oil-driven unmanned aerial vehicle according to claim 2, wherein the connecting assembly (5) comprises a first connecting frame (51) fixedly mounted at the output end of the driving motor (4) and a connecting rod (52) fixedly mounted on the first connecting frame (51), and one end of the first connecting frame (51) is mounted inside the fixed cross frame (32).
6. A rotor wing retracting mechanism for a vertical take-off and landing oil-driven unmanned aerial vehicle according to claim 5, wherein the connecting assembly (5) further comprises a connecting ring (53) fixedly sleeved on the connecting rod (52), one side of the connecting ring (53) is rotatably connected with a first connecting piece (54), and the other end of the first connecting piece (54) is rotatably connected with a second connecting piece (55).
7. The rotor wing retracting mechanism for the VTOL Unmanned Aerial Vehicle (UAV) according to claim 6, wherein a rotating shaft (35) is arranged in the fixed cross frame (32), and the other end of the second connecting piece (55) is sleeved on the rotating shaft (35).
8. A rotor wing retraction mechanism for a VTOL unmanned aerial vehicle according to claim 1, wherein the connection assembly (5) further comprises a third connection member (56) rotatably connected to the other end of the first connection member (54), the other end of the third connection member (56) being rotatably connected to the turret (11).
9. A rotor wing retracting mechanism for a vertical lifting oil-driven unmanned aerial vehicle according to claim 4, wherein a first groove (36) matched with the support rod (12) of the rotor wing assembly (1) is arranged at the top of the fixed cross frame (32), a second groove (6) matched with the rotor wing part (13) of the rotor wing assembly (1) is arranged on the side surface of the unmanned aerial vehicle body, and the rotor wing assembly (1) is accommodated.
10. A rotor wing retracting mechanism for a vertical lifting oil-driven unmanned aerial vehicle according to claim 4, wherein the second connecting through hole (343) is matched with the connecting rod (52) to limit the moving position of the connecting rod (52).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121439473.3U CN216140166U (en) | 2021-06-25 | 2021-06-25 | Rotor wing retracting mechanism for vertical take-off and landing oil-driven unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121439473.3U CN216140166U (en) | 2021-06-25 | 2021-06-25 | Rotor wing retracting mechanism for vertical take-off and landing oil-driven unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN216140166U true CN216140166U (en) | 2022-03-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202121439473.3U Active CN216140166U (en) | 2021-06-25 | 2021-06-25 | Rotor wing retracting mechanism for vertical take-off and landing oil-driven unmanned aerial vehicle |
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|---|---|
| CN (1) | CN216140166U (en) |
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2021
- 2021-06-25 CN CN202121439473.3U patent/CN216140166U/en active Active
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