CN220315289U - Rotor wing balance mechanism and aircraft - Google Patents
Rotor wing balance mechanism and aircraft Download PDFInfo
- Publication number
- CN220315289U CN220315289U CN202321784525.XU CN202321784525U CN220315289U CN 220315289 U CN220315289 U CN 220315289U CN 202321784525 U CN202321784525 U CN 202321784525U CN 220315289 U CN220315289 U CN 220315289U
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- sleeve
- rotor
- pushing
- balancing mechanism
- connecting piece
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- 238000006243 chemical reaction Methods 0.000 claims abstract description 25
- 230000000087 stabilizing effect Effects 0.000 claims description 4
- 238000001125 extrusion Methods 0.000 description 6
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
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Abstract
The utility model discloses a rotor wing balancing mechanism and an aircraft, wherein the rotor wing balancing mechanism comprises a pushing device and a stable sleeve sleeved on a rotor wing rotating shaft, the pushing device comprises a conversion assembly, a driver and a connecting piece matched with the stable sleeve, the driver drives the connecting piece to move up and down through the conversion assembly to push the stable sleeve to slide along the rotor wing rotating shaft, so that the upper end part of the stable sleeve can be wedged into a hinge gap between a blade and the rotor wing rotating shaft, the rotor wing is stably arranged on the rotor wing rotating shaft, jolt of the aircraft on the ground is effectively avoided, and the rotor wing of the aircraft is more stable in the ground running.
Description
Technical Field
The utility model relates to the field of aero-automobiles, in particular to a rotor wing balancing mechanism and an aero-vehicle.
Background
The traditional helicopter adopts a double-oar (2-piece rotor), three-oar (3-piece rotor) or four-oar (4-piece rotor) design, and the required number of the paddles is different for helicopters with different carrying capacities. The existing aircraft generally uses a teeterboard rotor, wherein the teeterboard rotor is hinged between the blades and the rotor shaft, so that periodic waving can occur during flight, most bending moment can be unloaded, and fatigue and vibration of the blades and the hub can be reduced, thereby being applicable to the aircraft. However, when the existing teeterboard type rotor runs on the rough or uneven ground, the problem that the rotor jolts up and down easily occurs, so that potential safety hazards in the aspect of ground driving of a flying automobile are caused.
Disclosure of Invention
Aiming at the defects of the prior art, the utility model aims to provide a rotor wing balancing mechanism for an aircraft, and the rotor wing can be stably arranged on a rotor wing rotating shaft when the aircraft runs on the ground, so that the problem that the rotor wing of the aircraft runs on the ground is effectively avoided.
In order to achieve the above purpose, the present utility model provides the following technical solutions:
the utility model provides a rotor balance mechanism, includes thrust unit and overlaps at the epaxial steady cover of rotor, thrust unit includes conversion component, driver and with steady cover matched with connecting piece, the driver drives the connecting piece through conversion component and reciprocates, promotes steady cover and slides along the rotor pivot for the upper end of this steady cover can wedge between paddle and the rotor pivot and have the hinge clearance.
The utility model further provides that: the conversion assembly comprises a conversion frame, a pushing rod and a linkage rod, wherein the driver is arranged on the conversion frame, an output shaft of the driver is hinged with one end part of the linkage rod, and the linkage rod is connected with the connecting piece through the pushing rod to push the connecting piece to drive the stable sleeve to move up and down.
The utility model further provides that: the linkage rod is provided with a limiting cross rod, the conversion frame is provided with a limiting groove which is inclined upwards towards the direction of the stable sleeve, and the end part of the limiting cross rod is arranged in the limiting groove and used for guiding the movement of the linkage rod.
The utility model further provides that: the connecting piece is provided with one or more guide posts, and the conversion frame is provided with guide holes matched with the guide posts.
The utility model further provides that: the pushing rod comprises a pushing sleeve hinged with the connecting piece and a pushing rod core hinged with the linkage rod, the pushing rod core is inserted into the pushing sleeve, and a spring propped against the pushing rod core is arranged in the pushing sleeve.
The utility model further provides that: the outer circular contour surface of the stable sleeve is provided with an inwards concave annular groove, the connecting piece is provided with an arc-shaped arm, and the arc-shaped arm is arranged in the annular groove to push the stable sleeve to move.
The utility model further provides that: the upper end of the stable sleeve is a conical surface.
The utility model further provides that: the rotor wing positioning device also comprises a positioning sleeve which is fixed on the rotor wing rotating shaft and is arranged below the stable sleeve, magnets are arranged on opposite surfaces of the positioning sleeve and the stabilizing sleeve, and the positioning sleeve can attract the stabilizing sleeve through magnetic force of the magnets.
The utility model further provides that: the rotary wing driving device is characterized by further comprising a fixed support, and the pushing device is arranged on one side of the rotary wing rotating shaft through the fixed support.
The utility model also provides an aircraft, which comprises an aircraft body and a rotor wing rotating shaft arranged on the aircraft body, wherein the rotor wing balancing mechanism is arranged on the rotor wing rotating shaft.
The utility model has the beneficial effects that: according to the rotor balancing mechanism, the pushing device pushes the stable sleeve to move on the rotor rotating shaft to control the relative position of the stable sleeve on the rotor rotating shaft, when the aircraft is in a flying state, the pushing device pushes the stable sleeve to be away from the rotor, the stable sleeve can not influence the normal rotation of the rotor at the moment, when the aircraft is in a ground running state, the pushing device pushes the stable sleeve to be close to the rotor, so that a hinge gap exists between the wedged blades and the rotor rotating shaft at the upper end of the stable sleeve, the rotor is stably arranged on the rotor rotating shaft, jolt of the aircraft running on the ground is effectively avoided, and the aircraft runs on the ground more stably.
Drawings
FIG. 1 is a schematic view of a rotor balancing mechanism;
FIG. 2 is a schematic view of the pushing device with the conversion frame removed;
FIG. 3 is a schematic structural view of a conversion frame;
FIG. 4 is an exploded view of the push rod;
FIG. 5 is a schematic structural view of the stationary sleeve;
fig. 6 is a schematic view of the rotor balancing mechanism mounted on the rotor shaft.
Reference numerals illustrate: 1. a pushing device; 11. a conversion assembly; 111. a conversion frame; 112. a push rod; 1121. pushing the sleeve; 1122. pushing the rod core; 1123. a spring; 113. a linkage rod; 114. a limiting cross bar; 115. a limit groove; 12. a driver; 13. a connecting piece; 131. an arc arm; 2. a rotor shaft; 3. a smooth sleeve; 31. a conical surface; 32. an annular groove; 4. a fixed bracket; 5. and (5) positioning the sleeve.
Detailed Description
A rotor balancing mechanism and an aircraft according to the present utility model will be described in further detail with reference to figures 1 to 6.
As can be seen from fig. 1 and 6, a rotor balancing mechanism comprises a pushing device 1 and a stationary sleeve 3 sleeved on a rotor shaft 2, wherein the diameter of an inner hole of the stationary sleeve 3 is larger than that of the rotor shaft 2 in order to enable the stationary sleeve 3 to slide on the rotor shaft 2 more smoothly. The outer diameter of the stationary sleeve 3 is matched with the hinge gap between the blade and the rotor shaft 2, and the upper end of the stationary sleeve 3 can be designed into a conical surface 31, so that the upper end of the stationary sleeve 3 can be wedged into the hinge gap between the blade and the rotor shaft 2.
As can be seen from fig. 2, the pushing device 1 includes a conversion assembly 11, a driver 12, and a connecting piece 13 matched with the stationary sleeve 3, the driver 12 may be some power sources such as an air cylinder, and the driver 12 is connected with the connecting piece 13 through the conversion assembly 11.
As can be seen from fig. 5, the outer circumferential surface of the stationary sleeve 3 is provided with an annular groove 32 recessed inwards, the connecting piece 13 is provided with an arc arm 131, the arc arm 131 is placed in the annular groove 32 to push the stationary sleeve 3 to move, so that the connecting piece 13 is matched with the stationary sleeve 3, the groove width of the annular groove 32 is larger than the thickness of the arc arm 131, so that the arc arm 131 has a certain movable space, and the mutual collision caused by vibration of an aircraft is avoided.
As can be seen from fig. 2 and 3, the switch assembly 11 includes a switch frame 111, a push rod 112 and a link rod 113, wherein the switch frame 111 is provided with a fixing bracket 4 below the switch frame, the switch frame 111 is mounted on one side of the rotor shaft 2 through the fixing bracket 4, and wherein the driver 12 is provided on the switch frame 111, so that the push device 1 is mounted on one side of the rotor shaft 2 through the fixing bracket 4.
The output shaft of the driver 12 is hinged to one end of the linkage rod 113, the other end of the linkage rod 113 is hinged to one end of the pushing rod 112, and the other end of the pushing rod 112 is hinged to the connecting piece 13, so that the linkage rod 113 is connected with the connecting piece 13 through the pushing rod 112 to push the connecting piece 13 to drive the stable sleeve 3 to move up and down.
In order to limit the movement track of the linkage rod 113, the linkage rod 113 is provided with a limiting cross rod 114, the conversion frame 111 is provided with a limiting groove 115 which is inclined upwards towards the direction of the stable sleeve 3, and the end part of the limiting cross rod 114 is arranged in the limiting groove 115 and used for guiding the movement of the linkage rod 113, so that the end part of the linkage rod 113 hinged with the pushing rod 112 is required to move along the setting direction of the limiting groove 115 to drive the pushing rod 112 to move, and the pushing rod 112 can push the connecting piece 13 to move up and down to avoid the deviation. At the same time, in order to guide the connecting piece 13 to move up and down and avoid deflection, the connecting piece 13 is provided with one or more guide posts 116, and the conversion frame 111 is provided with guide holes matched with the guide posts 116.
Therefore, the driver 12 drives the connecting piece 13 to move up and down through the conversion assembly 11 to push the stable sleeve 3 to slide along the rotor shaft 2 to control the relative position of the stable sleeve 3 on the rotor shaft 2, when the aircraft is in a flying state, the pushing device 1 pushes the stable sleeve 3 to be away from the rotor, at this time, the stable sleeve 3 can not influence the rotor to rotate normally on the rotor shaft 2, when the aircraft is in a ground driving state, the pushing device 1 pushes the stable sleeve 3 to be close to the rotor, so that the upper end part of the stable sleeve 3 can be wedged into a hinge gap between the blade and the rotor shaft 2, the rotor is stably mounted on the rotor shaft 2, jolt of the aircraft on the ground driving rotor is effectively avoided, and the aircraft is enabled to run more stably on the ground.
When the aircraft is in a flying state, the pushing device 1 can push the stable sleeve 3 to be located at a position far away from the rotor, but a certain movable clearance still exists between the stable sleeve 3 and the connecting piece 13 of the pushing device 1, so that the stable sleeve 3 moves up and down to collide and sound, a positioning sleeve 5 is arranged below the stable sleeve 3, the positioning sleeve 5 is fixed on the rotor rotating shaft 2, magnets are arranged on opposite faces of the positioning sleeve 5 and the stable sleeve 3, and the positioning sleeve 5 can attract the stable sleeve 3 through magnetic force of the magnets.
When the aircraft goes on uneven road surface and jolts, steady cover 3 can receive the extrusion of rotor different degree, and if the wedge position of steady cover 3 is fixed, will lead to the rotor to take place the damage easily, consequently need the catch bar 112 can be according to extrusion dynamics difference automatic adjustment steady cover 3 wedge position, and specific structure is as shown in fig. 4: the push rod 112 comprises a push sleeve 1121 hinged with the connecting piece 13 and a push rod core 1122 hinged with the linkage rod 113, the push rod core 1122 is inserted in the push sleeve 1121 pipe, a spring 1123 which is propped against the push rod core 1122 is arranged in the push sleeve 1121 pipe, the spring 1123 is in a precompression state, when the rotor wing extrudes the stable sleeve 3, the extrusion force born by the stable sleeve 3 can be conducted to the push sleeve 1121, the push sleeve 1121 counteracts the extrusion force born by the compression spring 1123, and the extrusion forces formed by the extrusion of different degrees are counteracted by different compression amounts of the spring 1123, so that the stable sleeve 3 can automatically adjust the wedging position, and the rotor wing is effectively prevented from being damaged.
As can be seen from fig. 6, the present utility model further provides an aircraft, which includes an aircraft body and a rotor shaft 2 disposed on the aircraft body, wherein the rotor balancing mechanism is disposed on the rotor shaft 2.
The foregoing is only a preferred embodiment of the present utility model. The protection scope of the present utility model is not limited to the above embodiments, and all technical solutions belonging to the concept of the present utility model belong to the protection scope of the present utility model. It should be noted that modifications and adaptations to the present utility model may occur to one skilled in the art without departing from the principles of the present utility model and are intended to be within the scope of the present utility model.
Claims (10)
1. A rotor balancing mechanism is characterized in that: comprises a pushing device and a stable sleeve sleeved on a rotor shaft,
the pushing device comprises a conversion assembly, a driver and a connecting piece matched with the stable sleeve, wherein the driver drives the connecting piece to move up and down through the conversion assembly to push the stable sleeve to slide along the rotor shaft, so that the upper end part of the stable sleeve can be wedged into a hinge gap between a blade and the rotor shaft.
2. The rotor balancing mechanism of claim 1, wherein: the conversion assembly comprises a conversion frame, a pushing rod and a linkage rod, wherein the driver is arranged on the conversion frame, an output shaft of the driver is hinged with one end part of the linkage rod, and the linkage rod is connected with the connecting piece through the pushing rod to push the connecting piece to drive the stable sleeve to move up and down.
3. A rotor balancing mechanism according to claim 2, wherein: the utility model discloses a gear box, including the gear box, the gear box is provided with the gear box, the gangbar is provided with a spacing horizontal pole, the conversion frame has seted up the upwards spacing groove of orientation steady cover direction slope, the spacing inslot is arranged in to the tip of spacing horizontal pole for guide gangbar removal.
4. A rotor balancing mechanism according to claim 3, wherein: the connecting piece is provided with one or more guide posts, and the conversion frame is provided with guide holes matched with the guide posts.
5. A rotor balancing mechanism according to claim 2, 3 or 4, wherein: the pushing rod comprises a pushing sleeve hinged with the connecting piece and a pushing rod core hinged with the linkage rod, the pushing rod core is inserted into the pushing sleeve, and a spring propped against the pushing rod core is arranged in the pushing sleeve.
6. The rotor balancing mechanism of claim 1, wherein: the outer circular contour surface of the stable sleeve is provided with an inwards concave annular groove, the connecting piece is provided with an arc-shaped arm, and the arc-shaped arm is arranged in the annular groove to push the stable sleeve to move.
7. The rotor balancing mechanism of claim 1, wherein: the upper end of the stable sleeve is a conical surface.
8. The rotor balancing mechanism of claim 1, wherein: the rotor wing positioning device also comprises a positioning sleeve which is fixed on the rotor wing rotating shaft and is arranged below the stable sleeve, magnets are arranged on opposite surfaces of the positioning sleeve and the stabilizing sleeve, and the positioning sleeve can attract the stabilizing sleeve through magnetic force of the magnets.
9. The rotor balancing mechanism of claim 1, wherein: the rotary wing driving device is characterized by further comprising a fixed support, and the pushing device is arranged on one side of the rotary wing rotating shaft through the fixed support.
10. An aircraft, includes the aircraft body and sets up the rotor pivot on the aircraft body, characterized by: a rotor balancing mechanism according to any one of claims 1 to 8, provided on a rotor shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321784525.XU CN220315289U (en) | 2023-07-07 | 2023-07-07 | Rotor wing balance mechanism and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321784525.XU CN220315289U (en) | 2023-07-07 | 2023-07-07 | Rotor wing balance mechanism and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220315289U true CN220315289U (en) | 2024-01-09 |
Family
ID=89409126
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321784525.XU Active CN220315289U (en) | 2023-07-07 | 2023-07-07 | Rotor wing balance mechanism and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220315289U (en) |
-
2023
- 2023-07-07 CN CN202321784525.XU patent/CN220315289U/en active Active
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