CN215622684U - Single-server linkage mechanism - Google Patents
Single-server linkage mechanism Download PDFInfo
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- CN215622684U CN215622684U CN202121949892.1U CN202121949892U CN215622684U CN 215622684 U CN215622684 U CN 215622684U CN 202121949892 U CN202121949892 U CN 202121949892U CN 215622684 U CN215622684 U CN 215622684U
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Abstract
The utility model discloses a single-server linkage mechanism which comprises a rack, wherein one side of the rack is provided with a mounting seat in rotary connection, a first bearing is arranged in the rack, the bottom of the rack is provided with a server, the output end of the server is provided with a first connecting rod, the end part of the first connecting rod is provided with a first universal coupling, and the first universal coupling is connected with a second universal coupling through a fourth connecting rod; one side of the first connecting rod is provided with a second connecting rod, one end of the second connecting rod is hinged to the first connecting rod, a hinged point between the second connecting rod and the first connecting rod is located between the server and the first universal coupler, the other end of the second connecting rod is hinged to a third connecting rod, and a clamping piece is arranged at the end of the third connecting rod. The utility model has the advantages of improving the angular rate and the response speed of the unmanned aerial vehicle during steering and yaw, improving the load capacity of the unmanned aerial vehicle and reducing the cost of the unmanned aerial vehicle.
Description
Technical Field
The utility model belongs to the field of tilt-wing unmanned aerial vehicles, and particularly relates to a single-server linkage mechanism of a tilt-wing unmanned aerial vehicle.
Background
The structure of current wing unmanned aerial vehicle that verts (unmanned aerial vehicle for short), like application number 202011516772.2's a wing unmanned aerial vehicle that verts, including the fuselage, be equipped with wing actuating mechanism in the fuselage, the fuselage is improved level and is violently crossed the pivot of being connected with wing actuating mechanism, the both sides of fuselage all are equipped with the wing, the tip of pivot passes through rotary mechanism and connects the wing, be equipped with the screw on the rotary mechanism (including rotatable paddle with be used for driving the rotatory drive seat of paddle), rotary mechanism is used for driving the wing rotatory, but can not drive the screw rotatory.
The existing unmanned aerial vehicle enables the rotating shaft to rotate through the wing driving mechanism, the rotating shaft drives the propeller driving seat to rotate through the rotating mechanism, and the rotating mechanism simultaneously drives the wing to rotate around the rotating shaft. Because the equal synchronous follow pivot of the screw drive seat of unmanned aerial vehicle both sides is rotatory, the air current that two screws produced remains the parallel throughout, and the driving force direction that two screws produced is the same, can not directly provide the driving force for unmanned aerial vehicle's the driftage that turns to.
The existing unmanned aerial vehicle finishes steering yaw under the hovering state, the steering yaw is realized by adjusting the wings, the unmanned aerial vehicle is firstly switched to the hovering state, the included angle of the wings on the fuselage is changed through the rotating mechanism, the propeller airflow forms corresponding side washing airflow on the wings, the driving force of the unmanned aerial vehicle steering yaw is obtained by utilizing the side washing airflow, but the driving force generated by the side washing airflow is lower, so that the angular rate of the unmanned aerial vehicle steering yaw is lower, and the response speed is also lower.
Therefore, the existing unmanned aerial vehicle has the defects of small angular speed and low response speed in steering and yawing.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a single-servo linkage mechanism. The utility model has the advantages of improving the angular rate and the response speed of the unmanned aerial vehicle during steering and yaw, improving the load capacity of the unmanned aerial vehicle and reducing the cost of the unmanned aerial vehicle.
The technical scheme of the utility model is as follows: a single-server linkage mechanism comprises a rack, wherein a mounting seat in rotary connection is arranged on one side of the rack, a first bearing is arranged in the rack, a server is arranged at the bottom of the rack, a first connecting rod is arranged at the output end of the server, a first universal coupling is arranged at the end part of the first connecting rod, and the first universal coupling is connected with a second universal coupling through a fourth connecting rod; one side of the first connecting rod is provided with a second connecting rod, one end of the second connecting rod is hinged to the first connecting rod, a hinged point between the second connecting rod and the first connecting rod is located between the server and the first universal coupler, the other end of the second connecting rod is hinged to a third connecting rod, and a clamping piece is arranged at the end of the third connecting rod.
In the single-server linkage mechanism, the first connecting rod is connected with the first universal coupling through a first screw.
In the single-server linkage mechanism, the second connecting rod comprises a first pin shaft fixed with the first connecting rod, a second bearing is arranged on the first pin shaft, a first sleeve is arranged on the outer peripheral surface of the second bearing, the first sleeve is connected with a second sleeve through a screw rod, the screw threads at two ends of the screw rod are opposite in rotating direction, and the second sleeve is connected with a third connecting rod through a third bearing.
In the single-server linkage mechanism, one end of the third connecting rod is provided with a second pin shaft penetrating through the third bearing, and the other end of the third connecting rod is connected with the clamping piece through a second screw.
In the single-server linkage mechanism, the clamping piece comprises a C-shaped clamping ring, two ends of the clamping ring extend outwards to form a clamping plate, the clamping plate close to the third connecting rod is in threaded connection with the second screw, and the other third connecting rod is penetrated by the second screw.
In the single-server linkage mechanism, the mounting base is connected with the rack through a third pin shaft.
Compared with the prior art, the unmanned aerial vehicle yaw driving mechanism is equivalent to a rotating mechanism on the existing unmanned aerial vehicle, but can drive the propellers to rotate, so that the two propellers on the unmanned aerial vehicle can respectively and independently rotate relative to respective rotating shafts, the two propellers can generate driving forces in different directions, and the unmanned aerial vehicle can steer to yaw under the action of the driving forces in the two directions. Because the propeller can rotate under the driving of the unmanned aerial vehicle, and does not depend on the driving of the rotating shaft to rotate, the unmanned aerial vehicle does not need to be provided with a wing driving mechanism for driving the rotating shaft to rotate, the rotating shaft is directly fixed with the vehicle body, the weight of the unmanned aerial vehicle can be reduced, the load capacity of the unmanned aerial vehicle can be improved, and the cost of the unmanned aerial vehicle is obviously reduced after the wing driving mechanism is cancelled. Therefore, the unmanned aerial vehicle steering and yaw control system has the advantages of improving the angular rate and the response speed of the unmanned aerial vehicle during steering and yaw, improving the load capacity of the unmanned aerial vehicle and reducing the cost of the unmanned aerial vehicle.
Drawings
Fig. 1 is a schematic structural view of the present invention.
Fig. 2 is a schematic view of the present invention when installed in a drone.
Fig. 3 is a right side view of the left portion of fig. 2.
Fig. 4 is a left side view of the right side portion of fig. 2.
The labels in the figures are: 1-a frame, 2-a mounting seat, 20-a third pin shaft, 3-a first bearing, 4-a server, 5-a first connecting rod, 6-a first universal coupling, 7-a second connecting rod, 70-the first pin shaft, 71-a second bearing, 72-a first sleeve, 73-a screw, 74-a second sleeve, 75-a third bearing, 8-a second universal coupling, 9-a third connecting rod, 90-a second pin shaft, 91-a second screw, 10-a clamping piece, 100-a clamping ring, 101-a clamping plate, 11-a first screw and 12-a fourth connecting rod.
Detailed Description
The utility model is further illustrated by the following figures and examples, which are not to be construed as limiting the utility model.
Examples are given. A single-server linkage mechanism, as shown in fig. 1, includes a frame 1, a mounting base 2 rotatably connected to one side of the frame 1, a first bearing 3 disposed in the frame 1, a server 4 disposed at the bottom of the frame 1, a first connecting rod 5 disposed at an output end of the server 4, a first universal coupling 6 disposed at an end of the first connecting rod 5, a second universal coupling 8 connected to the first universal coupling 6 via a fourth connecting rod 12, and both the first universal coupling 6 and the second universal coupling 8 being cross-shaft type universal couplings; one side of the first connecting rod 5 is provided with a second connecting rod 7, one end of the second connecting rod 7 is hinged to the first connecting rod 5, a hinged point between the second connecting rod 7 and the first connecting rod 5 is located between the server 4 and the first universal coupler 6, the other end of the second connecting rod 7 is hinged to a third connecting rod 9, and the end of the third connecting rod 9 is provided with a clamping piece 10.
The first connecting rod 5 is connected with the first universal coupling 6 through a first screw 11.
The second connecting rod 7 comprises a first pin shaft 70 fixed with the first connecting rod 5, a second bearing 71 is arranged on the first pin shaft 70, a first sleeve 72 is arranged on the outer peripheral surface of the second bearing 71, the first sleeve 72 is connected with a second sleeve 74 through a screw 73, the thread directions of the two ends of the screw 73 are opposite, and the second sleeve 74 is connected with a third connecting rod 9 through a third bearing 75. The length of the second connecting rod 7 can be changed by rotating the screw rod 73, so that the adjustment during the assembly is convenient.
One end of the third connecting rod 9 is provided with a second pin 90 penetrating through the third bearing 75, and the other end of the third connecting rod 9 is connected with the clamping piece 10 through a second screw 91.
The clamping piece 10 comprises a C-shaped clamping ring 100, two ends of the clamping ring 100 extend outwards to form a clamping plate 101, the clamping plate 101 close to the third connecting rod 9 is in threaded connection with the second screw 91, and the other third connecting rod 9 is penetrated by the second screw 91.
The mounting seat 2 is connected with the frame 1 through a third pin shaft 20.
The servo 4 can adopt a steering engine or a stepping motor.
The assembly of the utility model on a drone, as shown in figure 2, is used to replace the rotating mechanism on existing drones for the interconnection between the wings 15, the propellers 14 and the shaft 13. During assembly, the end part of the rotating shaft 13 sequentially penetrates through the clamping piece 10 and the first bearing 3, the second screw 91 is screwed, the clamping piece 10 and the rotating shaft 13 are fixed, the mounting base 2 is fixed to the upper part of the wing through screws, the second universal coupling 8 is fixed to the lower part of the wing through screws, and the second universal coupling 8 is located on the rear side of the mounting base 2. And the server 4 is connected with a flight control system of the unmanned aerial vehicle.
The working principle is as follows: when the propeller 14 on any side of the unmanned aerial vehicle changes the direction of the driving force, the server 4 on the corresponding side drives the first connecting rod 5 to rotate, and the first connecting rod 5 drives the wings 15 to rotate around the third pin shaft 20 through the first screw 11, the first universal coupling 6, the fourth connecting rod 12 and the second universal coupling 8 in sequence; the first connecting rod 5 drives the lower end of the second connecting rod 7 to rotate around the second pin shaft 90, the included angle between the first connecting rod 5 and the second connecting rod 7 is changed, the third connecting rod 9 is fixed on the rotating shaft 13 through the clamping piece 10, the third connecting rod 9 sequentially passes through the second connecting rod 7 and the first connecting rod 5 to provide reaction force for the server 4, the server 4 is enabled to rotate around the rotating shaft 13, the server 4 drives the propeller 14 to rotate around the rotating shaft 13 through the rack 1, and the airflow direction of the propeller is changed. Under the action of the servo 4, the wing 15 and the propeller 14 rotate simultaneously.
The utility model has the advantages of improving the angular rate and the response speed of the unmanned aerial vehicle during steering and yaw, improving the load capacity of the unmanned aerial vehicle and reducing the cost of the unmanned aerial vehicle.
Claims (6)
1. Single server link gear, its characterized in that: the device comprises a rack (1), wherein a mounting seat (2) in rotary connection is arranged on one side of the rack (1), a first bearing (3) is arranged in the rack (1), a server (4) is arranged at the bottom of the rack (1), a first connecting rod (5) is arranged at the output end of the server (4), a first universal coupling (6) is arranged at the end part of the first connecting rod (5), and the first universal coupling (6) is connected with a second universal coupling (8) through a fourth connecting rod (12); one side of the first connecting rod (5) is provided with a second connecting rod (7), one end of the second connecting rod (7) is hinged to the first connecting rod (5), a hinged point between the second connecting rod (7) and the first connecting rod (5) is located between the server (4) and the first universal coupler (6), the other end of the second connecting rod (7) is hinged to a third connecting rod (9), and the end of the third connecting rod (9) is provided with a clamping piece (10).
2. The single-servo linkage of claim 1, wherein: the first connecting rod (5) is connected with the first universal coupling (6) through a first screw (11).
3. The single-servo linkage of claim 2, wherein: the second connecting rod (7) comprises a first pin shaft (70) fixed with the first connecting rod (5), a second bearing (71) is arranged on the first pin shaft (70), a first sleeve (72) is arranged on the outer peripheral surface of the second bearing (71), the first sleeve (72) is connected with a second sleeve (74) through a screw rod (73), the screw threads at two ends of the screw rod (73) are opposite in rotating direction, and the second sleeve (74) is connected with a third connecting rod (9) through a third bearing (75).
4. The single-servo linkage of claim 3, wherein: one end of the third connecting rod (9) is provided with a second pin shaft (90) penetrating through the third bearing (75), and the other end of the third connecting rod (9) is connected with the clamping piece (10) through a second screw (91).
5. The single-servo linkage of claim 1, wherein: the clamping piece (10) comprises a C-shaped clamping ring (100), two ends of the clamping ring (100) extend outwards to form a clamping plate (101), the clamping plate (101) close to the third connecting rod (9) is in threaded connection with the second screw (91), and the other third connecting rod (9) is penetrated by the second screw (91).
6. The single-servo linkage of claim 1, wherein: the mounting seat (2) is connected with the rack (1) through a third pin shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121949892.1U CN215622684U (en) | 2021-08-19 | 2021-08-19 | Single-server linkage mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121949892.1U CN215622684U (en) | 2021-08-19 | 2021-08-19 | Single-server linkage mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215622684U true CN215622684U (en) | 2022-01-25 |
Family
ID=79899495
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121949892.1U Active CN215622684U (en) | 2021-08-19 | 2021-08-19 | Single-server linkage mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215622684U (en) |
-
2021
- 2021-08-19 CN CN202121949892.1U patent/CN215622684U/en active Active
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20220926 Address after: 310006 Room 201, unit 1, building 13, Gen yuan, Xiacheng District, Hangzhou City, Zhejiang Province Patentee after: Chen Chao Address before: 310000 room 2412, building 3, no.300-11, No.10 Street (East), Qiantang New District, Hangzhou City, Zhejiang Province Patentee before: Hangzhou Juyong Technology Co.,Ltd. |