CN107472524B - Aircraft rotor tilting mechanism - Google Patents
Aircraft rotor tilting mechanism Download PDFInfo
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- CN107472524B CN107472524B CN201710830832.XA CN201710830832A CN107472524B CN 107472524 B CN107472524 B CN 107472524B CN 201710830832 A CN201710830832 A CN 201710830832A CN 107472524 B CN107472524 B CN 107472524B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/80—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement for differential adjustment of blade pitch between two or more lifting rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
- B64C27/59—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
- B64C27/605—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including swash plate, spider or cam mechanisms
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- 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
Abstract
The invention relates to an aircraft rotor tilting mechanism, which comprises a main vertical shaft, a main driving disk, a main fixed disk and a rotor wing arranged on the outer circumference of the main driving disk, wherein the main driving disk and the main fixed disk are both sleeved on the main vertical shaft, and the main driving disk can rotate and can turn over relative to a horizontal plane; the main fixed disc is arranged below the driving disc, a tiny gap is reserved between the main fixed disc and the driving disc, friction is not generated when the driving disc rotates relative to the main fixed disc, the main fixed disc can be overturned relative to a horizontal plane, and a pulling device is arranged at the lower end of the main fixed disc; simple structure and low production cost.
Description
Technical Field
The present invention relates to an aircraft rotor tilting mechanism.
Background
The helicopter is flexible and mobile due to the characteristics of vertical lifting, low-speed cruising and the like, and is military. Security patrol, geological exploration, hydropower construction, fish flood investigation, traffic management and other industries are widely applied.
The coaxial double-rotor helicopter is a helicopter with an upper rotor and a lower rotor which are opposite and have the same theoretical axis, and because the directions of the two rotors are opposite, the torques generated by the two rotors are balanced with each other in a flying state with the constant course, and unbalanced torques are generated by the total torque difference of the upper rotor and the lower rotor, so that the course control can be realized, and the coaxial double-rotor helicopter is a lifting surface and a control surface with the longitudinal and transverse directions and the course in the flying process of the helicopter.
The transmission and control structure of the existing coaxial double-wing helicopter has the advantages of relatively complex, high processing difficulty and high production cost, greatly restricts the use and development of the coaxial double-wing helicopter, and has the following specific defects:
(1) The transmission adopts a sleeve type structure, the dead axle, the forward rotating axle and the reverse rotating axle are sleeved together, the structure is complex, the processing difficulty is high, and the production cost is high;
(2) The adjustment of rotor adopts automatic tilter control, and the structure is complicated, processing and installation difficulty.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides the aircraft rotor wing tilting structure which is simple in structure and low in production cost.
The technical scheme for solving the technical problems is as follows: the main tilting mechanism comprises a main vertical shaft, a driving disc, a main fixed disc and a main rotor wing arranged on the outer circumference of the driving disc, wherein the driving disc is sleeved on the main vertical shaft through a turnover mechanism and can rotate and turn over relative to a horizontal plane;
the main fixed disk is sleeved on the main vertical shaft and is arranged at the lower part of the main fixed disk, the main fixed disk can drive the main fixed disk to turn over, the lower end of the main fixed disk is provided with two pulling devices, and the two pulling devices can be respectively arranged at two sides of the lower end of the main fixed disk.
The beneficial effects of the invention are as follows: can be used as a tilting mechanism of a single rotor, and has simple structure and low production cost.
Further, a plurality of balls are arranged on the upper end face of the main fixed disc, a small gap is reserved between each ball and the corresponding driving disc, and when the driving disc rotates relative to the main fixed disc, the balls and the driving disc are not contacted; when the main fixed disc pushes the driving disc to incline, the main fixed disc and the driving disc are in sliding contact through the balls.
The beneficial effect of adopting the further technical scheme is that: the movable disc rotates relative to the main fixed disc, and the movable disc and the main fixed disc are not contacted, so that friction is avoided between the movable disc and the main fixed disc; when the main fixed disc pushes the driving disc to incline, the main fixed disc and the driving disc are in sliding contact through the balls, so that friction between the main fixed disc and the driving disc is reduced.
Further, the pulling device comprises a pull rod and a connecting rod, one end of the connecting rod is fixed at the lower end of the main fixed disc, the other end of the connecting rod is hinged with one end of the pull rod, and the other end of the pull rod is a free end.
Further, the driving disc is hinged with the main vertical shaft through a turnover mechanism, and the turnover mechanism is sleeved on the main vertical shaft and is hinged with the main vertical shaft.
Further, the turnover mechanism comprises two symmetrically arranged first rotating shafts, a truss and two symmetrically arranged second rotating shafts, the second rotating shafts are perpendicular to the first rotating shafts, the first rotating shafts comprise first inner rotating ends and first outer rotating ends, and the first outer rotating ends are in rotating connection with the truss;
the second rotating shaft comprises a second inner rotating end and a second outer rotating end, and the second inner rotating end is connected with the truss in a rotating mode.
Further, the main fixed disk is sleeved at the lower part of the driving disk, the diameter of an inner hole of the main fixed disk is matched with the outer diameter of the lower part of the driving disk, the first inner rotating end is rotationally connected with the main vertical shaft, and the second outer rotating end is rotationally connected with the driving disk.
Further, the main fixed disk is sleeved at the lower part of the driving disk, a cylindrical boss is arranged at the lower end of the driving disk, the main fixed disk is sleeved on the boss, the first inner rotating end is rotationally connected with the main vertical shaft, and the second outer rotating end is rotationally connected with the driving disk.
Further, the main fixed disc is arranged below the driving disc, and is sleeved on the main vertical shaft through a universal bearing.
Further, the main fixed disk is connected to the main vertical shaft through the turnover mechanism and the bearing or through the turnover mechanism and the sleeve, a first rotating end of a first rotating shaft of the turnover mechanism is rotationally connected with an outer ring of the bearing or an outer wall of the sleeve, and a second outer rotating end of a second rotating shaft of the turnover mechanism is rotationally connected with the main fixed disk.
Further, the device also comprises a secondary tilting mechanism, wherein the secondary tilting mechanism is connected with the primary tilting mechanism through a connecting rod mechanism, the connecting mechanism comprises a first connecting rod, a second connecting rod and a third connecting rod, and the second connecting rod is hinged between the first connecting rod and the third connecting rod.
The beneficial effects of adopting the further technical scheme are as follows: the tilting mechanism can be used as a tilting mechanism of a double-rotor aircraft, has simple structure, lower production cost and easier installation.
Further, the auxiliary tilting mechanism comprises an auxiliary vertical shaft, an auxiliary movable disc and a first auxiliary fixed disc which are sleeved on the auxiliary vertical shaft, and an auxiliary rotor wing which is arranged on the auxiliary movable disc, wherein the auxiliary movable disc is sleeved on the auxiliary vertical shaft through the turnover mechanism, and the auxiliary movable disc can rotate and can turn over relative to a horizontal plane;
the first auxiliary fixed disc is arranged below the auxiliary movable disc, the first auxiliary fixed disc can turn over relative to the horizontal plane, the lower end of the first auxiliary fixed disc is fixedly connected with one end of the first connecting rod, and one end of the third connecting rod is fixedly connected with the driving disc.
Further, the auxiliary tilting mechanism comprises an auxiliary vertical shaft, an auxiliary movable disc sleeved on the auxiliary vertical shaft, an auxiliary rotor wing mounted on the auxiliary movable disc, and a second auxiliary fixed disc mounted on the main vertical shaft and positioned at the upper part of the main disc, wherein the auxiliary movable disc is sleeved on the auxiliary vertical shaft through the turnover mechanism, the auxiliary movable disc can rotate and can turn over relative to a horizontal plane, and the lower end of the auxiliary movable disc is fixedly connected with one end of the first connecting rod;
the second auxiliary fixed disc can turn over relative to the horizontal plane, and the upper end of the second auxiliary fixed disc is fixedly connected with one end of the third connecting rod.
Further, the auxiliary tilting mechanism comprises an auxiliary vertical shaft, an auxiliary movable disc and a first auxiliary fixed disc which are sleeved on the auxiliary vertical shaft, and an auxiliary rotor wing which is installed on the auxiliary movable disc, wherein the auxiliary movable disc is sleeved on the auxiliary vertical shaft through the turnover mechanism and can rotate and turn over relative to a horizontal plane, the first auxiliary fixed disc is arranged below the auxiliary movable disc and can turn over relative to the horizontal plane, and the lower end of the first auxiliary fixed disc is fixedly connected with one end of the first connecting rod;
the device further comprises a second auxiliary fixed disc sleeved on the main vertical shaft, the second auxiliary fixed disc can turn over relative to the horizontal plane, and the upper end of the second auxiliary fixed disc is fixedly connected with one end of the third connecting rod.
Drawings
FIG. 1 is a schematic structural diagram of embodiment 1 of the present invention;
FIG. 2 is a schematic structural diagram of embodiment 2 of the present invention;
FIG. 3 is a schematic structural view of embodiment 3 of the present invention;
FIG. 4 is a schematic structural view of embodiment 4 of the present invention;
FIG. 5 is a schematic diagram of the connection of the tilting mechanism to the main vertical shaft and the driving disk in the present invention;
FIG. 6 is a schematic diagram of the connection between the active disc and the main fixed disc according to the present invention;
in the drawings, the list of component names indicated by the respective reference numerals is as follows: 1. the main vertical shaft, 2, the driving disc, 2-1, the boss, 3, the main rotor, 4, the main fixed disc, 5, the pulling device, 5-1, the pull rod, 5-2, the connecting rod, 6, the link mechanism, 6-1, the first connecting rod, 6-2, the second connecting rod, 6-3, the third connecting rod, 7, the auxiliary vertical shaft, 8, the auxiliary moving disc, 9, the auxiliary rotor, 10, the first auxiliary fixed disc, 12, the second auxiliary fixed disc, 13, the first rotating shaft, 14, the truss, 15 and the second rotating shaft.
Detailed Description
The principles and features of the present invention are described below with reference to the drawings, the examples are illustrated for the purpose of illustrating the invention and are not to be construed as limiting the scope of the invention.
Example 1
As a tilting mechanism of a single-rotor aircraft, as shown in fig. 1, the tilting mechanism of the rotor of the aircraft comprises a main tilting mechanism, wherein the main tilting mechanism comprises a main vertical shaft 1, a driving disc 2, a main fixed disc 4 and a main rotor 3 arranged on the outer circumference of the driving disc 2, the driving disc 2 is sleeved on the main vertical shaft 1 through a tilting mechanism, and the driving disc 2 can rotate and can tilt relative to a horizontal plane;
the main fixed disk 4 is sleeved on the main vertical shaft 1 and is arranged at the lower part of the main fixed disk 2, a tiny gap is reserved between the upper end face of the main fixed disk 4 and the lower end face of the main fixed disk 2, friction cannot be generated when the main fixed disk 4 rotates, the main fixed disk 4 can be overturned, two pulling devices 5 are arranged at the lower end of the main fixed disk 4, and the pulling devices 5 are symmetrically arranged at the left side and the right side of the main fixed disk 4.
The pulling device 5 comprises a pull rod 5-1 and a connecting rod 5-2, one end of the connecting rod 5-2 is fixed at the lower end of the main fixed disc 4, the other end of the connecting rod is hinged with one end of the pull rod 5-1, and the other end of the pull rod 5-2 is a free end.
The driving disc 2 is hinged with the main vertical shaft 1 through a turnover mechanism, and the turnover mechanism is sleeved on the main vertical shaft 1 and is hinged with the main vertical shaft 1.
As shown in fig. 5, the turnover mechanism comprises two symmetrically arranged first rotation shafts 13, a truss 14 and two symmetrically arranged second rotation shafts 15, wherein the second rotation shafts 15 are perpendicular to the first rotation shafts 13, the first rotation shafts 13 comprise a first inner rotation end and a first outer rotation end, and the first outer rotation end is rotationally connected with the truss 14;
the second rotating shaft 15 comprises a second inner rotating end and a second outer rotating end, the second inner rotating end is rotationally connected with the truss 14, the first inner rotating end is rotationally connected with the main vertical shaft 1, and the second outer rotating end is rotationally connected with the driving disc 2.
The main fixed disk 4 is sleeved at the lower part of the driving disk 2, the diameter of an inner hole of the main fixed disk 2 is matched with the outer diameter of the lower part of the driving disk 2, the first inner rotating end is rotationally connected with the main vertical shaft 1, and the second outer rotating end is rotationally connected with the driving disk 2.
As shown in fig. 6, the main fixed disk 4 is sleeved at the lower part of the driving disk 2, a cylindrical boss 2-1 is arranged at the lower end of the driving disk 2, the main fixed disk 4 is sleeved on the boss 2-1, the first rotating end is rotationally connected with the main vertical shaft 1, the second outer rotating end is rotationally connected with the driving disk 2, and when the main fixed disk 4 is turned over, the driving disk 2 is driven to turn over around a first rotating shaft 13 or a second rotating shaft 15.
The main fixed disc 4 is arranged below the driving disc 2, the main fixed disc 4 is sleeved on the main vertical shaft 1 through a universal bearing, and when the main fixed disc 4 turns over, the driving disc 2 is driven to turn over around the first rotating shaft 13 or the second rotating shaft 15.
The invention relates to an aircraft rotor wing tilting mechanism, which is used as a single rotor wing and has the following working principle: pulling the pull rod 5-1, the pull rod 5-1 drives the connecting rod 5-2, the connecting rod 5-2 drives the main fixed disc 4 to turn over, the main fixed disc 4 drives the main fixed disc 4 to turn over, and the driving disc 2 is driven to turn over around the first rotating shaft 13 or the second rotating shaft 15, so that the main rotor 3 is inclined.
Example 2
As a tilt structure of a twin-rotor aircraft, as shown in fig. 2, the difference from embodiment 1 is that: the device further comprises a secondary tilting mechanism, the secondary tilting mechanism is connected with the primary tilting mechanism through a connecting rod mechanism 6, the connecting mechanism 6 comprises a first connecting rod 6-1, a second connecting rod 6-2 and a third connecting rod 6-3, and the second connecting rod 6-2 is hinged between the first connecting rod 6-1 and the third connecting rod 6-3.
The auxiliary tilting mechanism comprises an auxiliary vertical shaft 7, an auxiliary movable disc 8 and a first auxiliary fixed disc 10 which are sleeved on the auxiliary vertical shaft 7, and an auxiliary rotor 9 which is arranged on the auxiliary movable disc 8, wherein the auxiliary movable disc 8 is sleeved on the auxiliary vertical shaft 7 through a turnover mechanism, and the auxiliary movable disc 8 can rotate and can turn over relative to a horizontal plane;
the first auxiliary fixed disc 10 is arranged below the auxiliary movable disc 8, the first auxiliary fixed disc 10 can turn over relative to the horizontal plane, the lower end of the first auxiliary fixed disc 10 is fixedly connected with one end of the first connecting rod 6-1, and one end of the third connecting rod 6-3 is fixedly connected with the driving disc 2.
The working principle is as follows:
pulling the pull rod 5-1, wherein the pull rod 5-1 drives the connecting rod 5-2, the connecting rod 5-2 drives the main fixed disc 4 to turn over, and the main fixed disc 4 drives the driving disc 2 to turn over, so that the main rotor 3 is inclined; the driving disc 2 turns over to drive the link mechanism to act, so that the first auxiliary fixed disc 10 turns over, and the first auxiliary fixed disc 10 drives the auxiliary movable disc 8 to turn over around the first rotating shaft 13 or the second rotating shaft 15, so that the inclination of the auxiliary rotor 9 is realized.
Example 3
As a tilting structure of a twin-rotor aircraft, as shown in fig. 3, the difference from embodiment 2 is that the auxiliary tilting mechanism includes an auxiliary vertical shaft 7, an auxiliary movable disk 8 sleeved on the auxiliary vertical shaft 7, an auxiliary rotor 9 mounted on the auxiliary movable disk 8, and a second auxiliary fixed disk 12 mounted on the main vertical shaft 1 and located at the upper part of the main disk, the auxiliary movable disk 8 is sleeved on the auxiliary vertical shaft 7 through a tilting mechanism, the auxiliary movable disk 8 can rotate and can be turned relative to the horizontal plane, and the lower end of the auxiliary movable disk 8 is fixedly connected with one end of the first connecting rod 6-1;
the second auxiliary fixing plate 12 can be turned over relative to the horizontal plane, and the upper end of the second auxiliary fixing plate 12 is fixedly connected with one end of the third connecting rod 6-3.
The working principle is as follows: pulling the pull rod 5-1, wherein the pull rod 5-1 drives the connecting rod 5-2, the connecting rod 5-2 drives the main fixed disc 4 to turn over, and the main fixed disc 4 drives the driving disc 2 to turn over, so that the main rotor 3 is inclined; the driving disc 2 overturns to drive the second auxiliary fixed disc 12 to overturne, and the overturning of the second auxiliary fixed disc 12 drives the connecting rod mechanism to act, so that the first connecting rod 6-1 drives the auxiliary movable disc 8 to overturn around the first rotating shaft 13 or the second rotating shaft 15, and the inclination of the auxiliary rotor 9 is realized.
Example 4
As a tilting structure of a dual rotor aircraft, as shown in fig. 4, the difference from embodiment 2 is that the secondary tilting mechanism includes a secondary vertical shaft 7, a secondary movable disk 8 and a first secondary fixed disk 10 which are sleeved on the secondary vertical shaft 7, and a secondary rotor 9 which is mounted on the secondary movable disk 8, the secondary movable disk 8 is sleeved on the secondary vertical shaft 7 through a tilting mechanism, the secondary movable disk 8 can rotate and can be tilted with respect to a horizontal plane, the first secondary fixed disk 10 is disposed below the secondary movable disk 8, the first secondary fixed disk 10 can be tilted with respect to the horizontal plane, and the lower end of the first secondary fixed disk 10 is fixedly connected with one end of the first connecting rod 6-1;
the device further comprises a second auxiliary fixed disc 12 sleeved on the main vertical shaft 1, the second auxiliary fixed disc 12 can turn over relative to the horizontal plane, and the upper end of the second auxiliary fixed disc 12 is fixedly connected with one end of the third connecting rod 6-3.
The working principle is as follows:
pulling the pull rod 5-1, wherein the pull rod 5-1 drives the connecting rod 5-2, the connecting rod 5-2 drives the main fixed disc 4 to turn over, and the main fixed disc 4 drives the driving disc 2 to turn over, so that the main rotor 3 is inclined; the driving disc 2 turns over to drive the second auxiliary fixed disc 12 to turn over, the second auxiliary fixed disc 12 turns over to drive the connecting rod mechanism to act, the first connecting rod 6-1 drives the first auxiliary fixed disc 10 to turn over, and the first auxiliary fixed disc 10 drives the auxiliary movable disc 8 to turn over around the first rotating shaft 13 or the second rotating shaft 15, so that the inclination of the auxiliary rotor 9 is realized.
The foregoing description of the preferred embodiments of the invention is not intended to limit the invention to the precise form disclosed, and any such modifications, equivalents, and alternatives falling within the spirit and scope of the invention are intended to be included within the scope of the invention.
Claims (10)
1. The aircraft rotor tilting mechanism is characterized by comprising a main tilting mechanism, wherein the main tilting mechanism comprises a main vertical shaft (1), a driving disc (2), a main fixed disc (4) and a main rotor (3) arranged on the outer circumference of the driving disc (2), the driving disc is sleeved on the main vertical shaft (1) through a tilting mechanism, and the driving disc (2) can rotate and can tilt relative to a horizontal plane;
the main fixed disc (4) is sleeved on the main vertical shaft (1) and is arranged at the lower part of the driving disc (2), the main fixed disc (4) can drive the driving disc (2) to turn over, and a pulling device (5) is arranged at the lower end of the main fixed disc (4);
a plurality of balls are arranged on the upper end surface of the main fixed disc (4), a tiny gap is reserved between each ball and the corresponding driving disc (2), and when the driving disc (2) rotates relative to the main fixed disc (4), the balls are not contacted with the driving disc (2); when the main fixed disc (4) pushes the driving disc (2) to incline, the main fixed disc (4) and the driving disc (2) are in sliding contact through the balls.
2. Aircraft rotor tilting mechanism according to claim 1, characterized in that the pulling means (5) comprise a pull rod (5-1) and a connecting rod (5-2), one end of the connecting rod (5-2) being fixed at the lower end of the main stator (4), the other end being hinged to one end of the pull rod (5-1), the other end of the pull rod (5-2) being a free end.
3. Aircraft rotor tilting mechanism according to claim 2, characterized in that the tilting mechanism comprises two symmetrically arranged first rotational shafts (13), a truss (14) and two symmetrically arranged second rotational shafts (15), the second rotational shafts
(15) Perpendicular to the first rotation shaft (13), the first rotation shaft (13) comprises a first inner rotation end and a first outer rotation end, and the first outer rotation end is rotationally connected with the truss (14);
the second rotating shaft (15) comprises a second inner rotating end and a second outer rotating end, and the second inner rotating end is connected with the truss in a rotating way.
4. An aircraft rotor tilting mechanism according to claim 3, wherein the main stator (4) is sleeved on the lower part of the main rotor (2), the diameter of the inner hole of the main stator (2) is adapted to the outer diameter of the lower part of the main rotor (2), the first inner rotating end is rotationally connected with the main vertical shaft (1), and the second outer rotating end is rotationally connected with the main rotor (2).
5. An aircraft rotor tilting mechanism according to claim 3, wherein the main stator (4) is sleeved on the lower part of the driving disc (2), a cylindrical boss is arranged at the lower end of the driving disc (2), the main stator (4) is sleeved on the boss, the first inner rotating end is rotationally connected with the main vertical shaft (1), and the second outer rotating end is rotationally connected with the driving disc (2).
6. An aircraft rotor tilting mechanism according to claim 3, characterized in that the main stator (4) is arranged below the main rotor (2) and the main stator (4) is journalled on the main vertical shaft (1) by means of a universal bearing.
7. An aircraft rotor tilting mechanism according to any of claims 1-6, further comprising a secondary tilting mechanism connected to the primary tilting mechanism by means of a linkage mechanism (6), the connection mechanism (6) comprising a first link
(6-1), a second link (6-2) and a third link (6-3), the second link (6-2) being hinged between the first link (6-1) and the third link (6-3).
8. The aircraft rotor tilting mechanism according to claim 7, characterized in that it comprises a secondary vertical shaft (7), a secondary rotor (8) and a first secondary stator (10) which are sleeved on the secondary vertical shaft (7), and a secondary rotor mounted on the secondary rotor
(8) The auxiliary rotor wing (9) is sleeved on the auxiliary vertical shaft through the turnover mechanism, and the auxiliary rotor wing (8) can rotate and can turn over relative to a horizontal plane;
the first auxiliary fixed disc (10) is arranged below the auxiliary movable disc (8), the first auxiliary fixed disc (10) can drive the auxiliary movable disc (8) to turn over, the lower end of the first auxiliary fixed disc (10) is fixedly connected with one end of the first connecting rod (6-1), and one end of the third connecting rod (6-3) is fixedly connected with the driving disc (2).
9. The aircraft rotor tilting mechanism according to claim 7, characterized in that it comprises a secondary vertical shaft (7), a secondary rotor (9) mounted on said secondary rotor (8) and a secondary rotor (8) mounted on said primary vertical shaft (1) and located above said primary rotor, said secondary rotor being mounted on said secondary vertical shaft by means of said tilting mechanism, said secondary rotor (8) being rotatable and tiltable relative to the horizontal plane, said secondary rotor (8)
Is fixedly connected with one end of the first connecting rod (6-1);
the second auxiliary fixing disc (12) can be overturned, and the upper end of the second auxiliary fixing disc (12) is fixedly connected with one end of the third connecting rod (6-3).
10. The aircraft rotor tilting mechanism according to claim 7, characterized in that it comprises a secondary vertical shaft (7), a secondary rotor (8) and a first secondary stator (10) which are sleeved on the secondary vertical shaft (7), and a secondary rotor mounted on the secondary rotor
(8) The auxiliary rotor wing (9) is arranged on the main shaft, the auxiliary movable disc (8) is sleeved on the auxiliary vertical shaft through the turnover mechanism, and the auxiliary movable disc
(8) The first auxiliary fixed disc (10) is arranged below the auxiliary movable disc (8), the first auxiliary fixed disc (10) can be turned over, and the lower end of the first auxiliary fixed disc (10) is fixedly connected with one end of the first connecting rod (6-1);
the device further comprises a second auxiliary fixed disc (12) sleeved on the main vertical shaft (1), the second auxiliary fixed disc (12) can be turned over, and the upper end of the second auxiliary fixed disc (12) is fixedly connected with one end of the third connecting rod (6-3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710830832.XA CN107472524B (en) | 2017-09-15 | 2017-09-15 | Aircraft rotor tilting mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710830832.XA CN107472524B (en) | 2017-09-15 | 2017-09-15 | Aircraft rotor tilting mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107472524A CN107472524A (en) | 2017-12-15 |
| CN107472524B true CN107472524B (en) | 2023-07-04 |
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ID=60585104
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710830832.XA Active CN107472524B (en) | 2017-09-15 | 2017-09-15 | Aircraft rotor tilting mechanism |
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| CN (1) | CN107472524B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101480531A (en) * | 2008-11-14 | 2009-07-15 | 罗之洪 | Rotor mechanism of single-rotor toy helicopter |
| WO2013026963A1 (en) * | 2011-08-25 | 2013-02-28 | Kokkelink Rene Felix Charles | Helicopter rotor system, and helicopter including such a rotor system |
| CN106428543A (en) * | 2016-11-11 | 2017-02-22 | 杨超峰 | Rotor control mechanism and dual-rotor unmanned plane |
| CN107140198A (en) * | 2017-06-21 | 2017-09-08 | 中电科芜湖钻石飞机制造有限公司 | Double coaxial tilting rotor wing unmanned aerial vehicle nacelle structures |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6616095B2 (en) * | 2001-02-16 | 2003-09-09 | Bell Helicopter Textron Inc. | Coupled aircraft rotor system |
| GB2409845A (en) * | 2004-01-08 | 2005-07-13 | Robert Graham Burrage | Tilt-rotor aircraft changeable between vertical lift and forward flight modes |
-
2017
- 2017-09-15 CN CN201710830832.XA patent/CN107472524B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101480531A (en) * | 2008-11-14 | 2009-07-15 | 罗之洪 | Rotor mechanism of single-rotor toy helicopter |
| WO2013026963A1 (en) * | 2011-08-25 | 2013-02-28 | Kokkelink Rene Felix Charles | Helicopter rotor system, and helicopter including such a rotor system |
| CN106428543A (en) * | 2016-11-11 | 2017-02-22 | 杨超峰 | Rotor control mechanism and dual-rotor unmanned plane |
| CN107140198A (en) * | 2017-06-21 | 2017-09-08 | 中电科芜湖钻石飞机制造有限公司 | Double coaxial tilting rotor wing unmanned aerial vehicle nacelle structures |
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|---|---|
| CN107472524A (en) | 2017-12-15 |
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