CN109436299B - Star-shaped pitch-changing mechanism of helicopter tail rotor and helicopter - Google Patents
Star-shaped pitch-changing mechanism of helicopter tail rotor and helicopter Download PDFInfo
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- CN109436299B CN109436299B CN201811639432.1A CN201811639432A CN109436299B CN 109436299 B CN109436299 B CN 109436299B CN 201811639432 A CN201811639432 A CN 201811639432A CN 109436299 B CN109436299 B CN 109436299B
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- tail rotor
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- 230000007246 mechanism Effects 0.000 title claims abstract description 62
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 12
- 229910000990 Ni alloy Inorganic materials 0.000 claims description 6
- 229910052742 iron Inorganic materials 0.000 claims description 6
- 230000005540 biological transmission Effects 0.000 claims description 5
- 238000005323 electroforming Methods 0.000 claims description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 3
- 239000004593 Epoxy Substances 0.000 claims description 3
- 229910052799 carbon Inorganic materials 0.000 claims description 3
- 239000002131 composite material Substances 0.000 claims description 3
- 238000000034 method Methods 0.000 abstract description 10
- 230000008569 process Effects 0.000 abstract description 8
- 238000004519 manufacturing process Methods 0.000 abstract description 7
- 230000033001 locomotion Effects 0.000 description 7
- 238000013461 design Methods 0.000 description 5
- 230000008859 change Effects 0.000 description 4
- 238000006073 displacement reaction Methods 0.000 description 4
- 235000017166 Bambusa arundinacea Nutrition 0.000 description 3
- 235000017491 Bambusa tulda Nutrition 0.000 description 3
- 241001330002 Bambuseae Species 0.000 description 3
- 235000015334 Phyllostachys viridis Nutrition 0.000 description 3
- 239000011425 bamboo Substances 0.000 description 3
- 238000007789 sealing Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/30—Blade pitch-changing mechanisms
- B64C11/32—Blade pitch-changing mechanisms mechanical
Abstract
The invention discloses a helicopter tail rotor star-shaped pitch-changing mechanism and a helicopter, which comprise a pitch-changing assembly for driving tail rotor blade pitch-changing, wherein the pitch-changing assembly comprises a star-shaped pitch-changing connecting rod, a first knuckle bearing mechanism which is connected with the star-shaped pitch-changing connecting rod and moves along with the star-shaped pitch-changing connecting rod in the vertical direction, and a blade clamp which is connected with the first knuckle bearing mechanism, rotates along with the first knuckle bearing mechanism to adjust the blade pitch-changing and is arranged on a shell, and the problems of high manufacturing difficulty, huge volume, difficult blade pitch-changing, low control precision, complex overall structure, short service life and high manufacturing cost of the unmanned helicopter in the traditional process can be overcome.
Description
Technical Field
The invention relates to the field of helicopters, in particular to a helicopter tail rotor star-shaped pitch-changing mechanism and a helicopter.
Background
Helicopter tail rotor is a component used to balance reactive torque and to steer the helicopter in heading. The rotating tail rotor is equivalent to a vertical stabilizer, and can stabilize the heading of the helicopter. Although the rear rotor functions differently from the rotor, they are all aerodynamic due to rotation and operate in an asymmetric airflow when flying forward, so the tail rotor structure has many similarities with the rotor structure. The structural forms of the tail rotor are teeterboard, universal joint type, articulated type, bearingless type, ducted tail rotor type and the like.
Since the power of the tail rotor is typically from the main engine of the helicopter, the primary method of controlling the amount of force applied by the tail rotor is to vary the pitch, i.e. pitch, of the propeller. At present, the development of the aircraft is still in a primary development stage, the design of unmanned helicopter tail rotor pitch variation is also good and bad at home and abroad, and the unmanned helicopter tail rotor pitch variation generally adopts a multi-part transmission structure to transmit the steering force of a steering engine to a pitch-variable pull rod and finally transmits the steering force to a tail rotor. A direct consequence of such a design is that its structural mass increases and that too many drive joints can lead to a reduced reliability of the drive. In accident investigation of a helicopter, the accident caused by a tail rotor system reaches 32% in the failure of a helicopter body system, wherein the accident rate of a tail rotor transmission shaft is 18%, and the accident rate of the tail rotor is 14%. Therefore, a reliable tail rotor design is a key for guaranteeing the flight safety.
Therefore, a tail rotor mechanism which has the advantages of simple structure, high safety performance, easiness in processing and manufacturing, convenience in accurately controlling tail rotor pitch and convenience in safely steering of an unmanned helicopter is needed.
Disclosure of Invention
In view of the above, the invention aims to overcome the defects in the prior art, and provides a helicopter tail rotor star-shaped pitch-changing mechanism which can solve the problems of large manufacturing difficulty, huge volume, difficult blade pitch change, low control precision, complex overall structure, short service life and high manufacturing cost of an unmanned helicopter in the traditional process.
The star-shaped pitch-changing mechanism of the helicopter tail rotor comprises a pitch-changing assembly for driving the pitch of the tail rotor blade, wherein the pitch-changing assembly comprises a star-shaped pitch-changing connecting rod, a first knuckle bearing mechanism which is connected with the star-shaped pitch-changing connecting rod and moves along with the star-shaped pitch-changing connecting rod in the vertical direction, and a blade clamp which is connected with the first knuckle bearing mechanism, rotates along with the first knuckle bearing mechanism so as to adjust the pitch of the blade and is arranged on a shell; according to the tail rotor mechanism assembly in the technical scheme, the pitch-changing mechanism is pushed to move in the vertical direction (namely along the axial direction of the push rod) through the pitch-changing push rod, and then the blades are driven to deflect in the vertical direction, so that pitch changing of the blades is realized, and the blades are driven to move in the circumferential direction (the direction perpendicular to the axial direction of the push rod) through the shell fixedly arranged with the tail rotor power mechanism.
Further, the shell comprises a double-sleeve structure formed by combining an inner sleeve and an outer sleeve which are coaxially arranged, a paddle is fixedly connected with one end of a paddle clamp, the paddle clamp is arranged on the wall of the outer sleeve through a self-lubricating bushing, the other end of the paddle clamp is provided with a shaft neck structure for being arranged on the wall of the inner sleeve, the shaft neck of the paddle clamp is provided with a connecting block integrally formed with the paddle clamp, the star-shaped variable pitch connecting rod structure is in a hexagonal star shape, six corner ends are downwards bent to form a connecting part in transmission connection with the paddle clamp, a first knuckle bearing mechanism is rotatably connected with the connecting part and is rotatably matched with the connecting block; adopt six connecting rods to connect the structural mode of paddle, make the mechanism operate more steadily, compare traditional double-paddle mechanism, mechanism atress in this technical scheme is more even, confirms the length of connecting block through paddle pivoted angle scope, makes the arrangement between link mechanism more reasonable, and the structure is compacter, effectively reduces the noise that produces in the tail-rotor mechanism motion
Further, six connecting rod ends of the six-star-shaped deformation distance connecting rod are uniformly distributed along the circumferential direction, the six paddles are uniformly distributed along the circumferential direction of the shell, and elliptical holes for the first knuckle bearing mechanism to move in the vertical direction and drive the paddle clamp to rotate are formed in the connecting part; the first joint bearing drives the paddle clamp to rotate through being matched with the elliptical hole on the connecting part, so that the pitch of the paddle is changed, the long axis of the elliptical hole is perpendicular to the vertical direction, the structural design of the elliptical hole ensures that the moving structure cannot be blocked in the moving process, and meanwhile, the function of driving the paddle to rotate along the vertical direction can be directly realized.
Further, be provided with the second joint bearing that is used for supporting tail rotor blade pivoted between the connecting block of oar clamp and the outer sleeve section of thick bamboo wall of oar clamp installation, second joint bearing passes through shear bolt connection on the casing, and second joint bearing 8 provides the supporting point for the rotation of oar clamp blade, guarantees the stability in the rotation process.
Further, the blade is made of a high-strength carbon fiber-epoxy composite material, and the front edge of the blade is wrapped by nickel alloy electroforming iron clad; the front edge of the blade is wrapped on the front edge of the blade by adopting nickel alloy electroforming iron, and the nickel alloy iron is arranged at the windward front end part of the blade, so that the gravity center of the blade moves forward, the flutter stability of the blade is improved, and meanwhile, the hinge moment of the blade is reduced, so that the blade can run more stably.
A helicopter body is provided with the unmanned helicopter tail rotor star-shaped pitch-changing mechanism.
The beneficial effects of the invention are as follows: the invention discloses a helicopter tail rotor star-shaped pitch-changing mechanism, which can solve the problems of high manufacturing difficulty, huge volume, difficult blade pitch changing, low control precision, complex overall structure, short service life and high manufacturing cost of an unmanned helicopter in the traditional process.
Drawings
The invention is further described below with reference to the accompanying drawings and examples:
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a cross-sectional view of the present invention;
FIG. 3 is a schematic view of a first knuckle bearing connection structure in accordance with the present invention;
FIG. 4 is a schematic cross-sectional view of the present invention;
fig. 5 is a schematic view of a connecting portion structure in the present invention.
Reference numerals
A connecting block 1; the hexagram deformation distance connecting rod 2; a housing 3; a paddle clamp 4; a paddle clamp bolt 5; an outer cylinder self-lubricating bushing 6; an inner cylinder self-lubricating bushing 7; a second knuckle bearing 8; a paddle 9; a first knuckle bearing 10; a journal 12; an outer sleeve wall 13; an inner sleeve wall 14; a connection portion 15; a top cover 16; a tail rotor motor 17; a pitch-changing tail rotor bracket 18; a linear steering engine 19; angular contact ball bearings 20; a variable-pitch push rod 21; a pitch change push rod self-lubricating bushing 22; shear bolts 23; and a bushing 24.
Detailed Description
Fig. 1 is a schematic structural view of the present invention, fig. 2 is a schematic structural view of the present invention, fig. 3 is a schematic structural view of a first joint bearing connection structure of the present invention, fig. 4 is a schematic structural view of a cross section of the present invention, fig. 5 is a schematic structural view of a connection part of the present invention, and as shown in the drawing, a helicopter tail rotor star-shaped pitch-varying mechanism of the present invention includes a pitch-varying mechanism connected with a linear steering engine mechanism for driving a tail rotor blade 9 to vary a pitch, and a tail rotor power mechanism for driving the pitch-varying mechanism to rotate, wherein the pitch-varying mechanism includes a housing 3 for mounting the blade 9, a link mechanism disposed in the housing 3 for adjusting a pitch of the blade 9, and a pitch-varying push rod 21 connected between the link mechanism and the linear steering engine mechanism, and the housing 3 is in driving connection with the tail rotor power mechanism in a manner of rotating around the pitch-varying push rod 21. According to the technical scheme, the tail rotor mechanism assembly pushes the pitch-changing mechanism to move in the vertical direction (namely along the axial direction of the push rod 21) through the pitch-changing push rod 21, and then drives the blade 9 to deflect in the vertical direction so as to realize pitch changing of the blade 9, and the shell 3 fixedly arranged with the tail rotor power mechanism drives the blade 9 to move in the circumferential direction (the direction perpendicular to the axial direction of the push rod 21).
In this embodiment, the casing 3 contains the double sleeve structure that inner skleeve and the outer sleeve combination that coaxial setting formed, and paddle 9 and the one end fixed connection of oar press from both sides 4, oar press from both sides 4 through the self-lubricating bush and install on outer sleeve section of thick bamboo wall 13, the oar presss from both sides 4 other end and is provided with the axle journal 12 structure that is used for installing on inner sleeve section of thick bamboo wall 14, still be provided with on the oar presss from both sides the axle journal and be used for driving oar to press from both sides 4 along vertical direction pivoted connecting block 1, link mechanism includes the hexagram deformation apart from connecting rod 2 that is connected with the displacement push rod 21, and the angular point of hexagram deformation apart from connecting rod 2 is buckled downwards and is formed the connecting portion 15 that is connected with the transmission of oar clamp 4. The shell 3 comprises a double-sleeve structure formed by an inner sleeve and an outer sleeve, the bottom of the shell 3 is fixedly connected with the power output end of a tail vane motor 17 through bolts to provide power for circumferential rotation of the blades, as shown in figure 2, one end of a blade clamp 4 is fixedly connected with the blade clamp 4 through a blade clamp bolt 5, the blade clamp 4 penetrates through an outer sleeve wall 13 and is connected with an inner sleeve wall 14 through a shaft neck 12 arranged at the other end of the blade clamp 4, an inner sleeve self-lubricating bushing 7 and an outer sleeve self-lubricating bushing 6 are respectively arranged at the positions of the blade clamp 4, which are in rotary fit with the inner sleeve wall 14 and the outer sleeve wall 13, the rotary support is provided for the blades 9 through the two self-lubricating bushings, meanwhile, the double-sleeve connecting structure improves the stability of the blades 9 during movement, reduces the stress concentration phenomenon generated by receiving moment at the joint of the blades 9 and the blade clamp 4, prolongs the service life of the blades, the blade movement is smoother, the root parts of the connecting block 1 and the blade clamp 4 are fixedly connected together, the two are preferably connected in an integrally formed mode, the variable-pitch push rod 21 and the six-star-shaped variable-pitch connecting rod 2 are rotationally matched and connected, the corner end of the six-star-shaped variable-pitch connecting rod 2 (namely the end part of six corners of the six-star-shaped variable-pitch connecting rod) is vertically bent downwards to form a connecting part 15, the connecting part 15 is a circular structure with a mounting hole at the center, the six connecting rod ends of the six-star-shaped variable-pitch connecting rod 2 are uniformly distributed along the circumferential direction, the blades 9 are uniformly distributed in the circumferential direction of the shell 3, the six-connecting-rod-connected blade structural mode is adopted, so that the mechanism is more stable in operation, compared with the traditional double-blade mechanism, the mechanism stress in the technical scheme is more uniform, the length of the connecting block 1 is determined through the rotating angle range of the blades, the arrangement among the connecting rod mechanisms is more reasonable, the structure is more compact, and noise generated in the motion of the tail rotor mechanism is effectively reduced.
In this embodiment, the connecting portion 15 is provided with a first knuckle bearing 10, the first knuckle bearing 10 is rotationally connected with the connecting block 1, and the connecting portion 15 is provided with an elliptical hole for the first knuckle bearing 10 to move in a vertical direction and drive the paddle clamp 4 to rotate. The first joint bearing 10 drives the paddle clamp 4 to rotate through matching with the elliptical hole on the connecting part 15, so that the pitch change of the paddle 9 is realized, the long axis of the elliptical hole is vertical to the vertical direction, the design of the elliptical hole structure ensures that the moving structure can not be blocked in the moving process, and meanwhile, the function of driving the paddle 9 to rotate along the vertical direction can be directly realized, so that the structure is simple, the processing is easy, and the problem of complicated pitch change structure in the traditional process is solved.
In this embodiment, a second knuckle bearing 8 for supporting the rotation of the tail rotor blade 9 is disposed between the connection block 1 of the blade holder 4 and the outer sleeve wall 13 on which the blade holder 4 is mounted. The second knuckle bearing 8 is connected on the casing 3 through the shear bolt 23, and the second knuckle bearing 8 provides the supporting point for the rotation of oar clamp paddle, guarantees the stability of rotation in-process, and the centrifugal force that produces in the paddle motion process is transmitted to on the casing 3 through the second knuckle bearing 8, has improved the atress condition of two self-lubricating bush, has further promoted the life of each part, makes the mechanism operation more steady, has reduced the noise.
In this embodiment, the tail rotor power mechanism is mounted at the upper end of the pitch-changing tail rotor support 18, and the linear steering engine mechanism is mounted at the bottom end of the pitch-changing tail rotor support 18. The pitch-changing tail rotor bracket 18 comprises a plate in the vertical direction and two horizontal mounting plates perpendicular to the vertical direction, the tail rotor motor 17 is fixedly mounted on the horizontal mounting plate above, the linear steering engine 19 is fixedly connected with the horizontal mounting plate below, a plurality of reinforcing plate structures are arranged between the upper mounting plate and the lower mounting plate, and the overall structure is stable when the motion mechanism is ensured to operate.
In this embodiment, the distance-changing push rod structure is a stepped shaft type push rod structure, one end of the distance-changing push rod is connected with a linear steering engine mechanism for providing distance-changing power, and the distance-changing push rod 21 sequentially passes through the edge distance tail rotor bracket 18, the tail rotor power mechanism and the shell 3 from bottom to top in the vertical direction. The top cap 16 adopts the sealed setting of straight line steering wheel 19 with casing 3, reduces middle conversion link, improves whole response speed, adopts the mounting pattern that the displacement push rod runs through overall structure, makes each mounting structure compacter, practices thrift installation space, adopts sealing ring or other sealing means between displacement push rod and each junction point simultaneously, makes tail rotor mechanism inside be in good sealing state, improves the life of this mechanism.
In this embodiment, two angular contact ball bearings 20 are disposed between the pitch-changing push rod 21 and the hexagram pitch-changing connecting rod 2 along the axial direction of the push rod, a pitch-changing push rod self-lubricating bushing 22 is disposed between the pitch-changing push rod 12 and the housing 3, and a flanging bushing 24 is disposed between the tail rotor motor mechanism and the pitch-changing push rod 21. Through angular contact ball bearing 20, displacement push rod self-lubricating bush 22, turn-ups bush 24, ensure to have good axiality among each mechanism in the vertical direction, promote the steady performance of motion of mechanism, reduce the noise.
In this embodiment, the blade is made of a high-strength carbon fiber-epoxy composite material, the front edge of the blade is wrapped on the front edge of the blade by adopting nickel alloy electroforming iron clad, and the nickel alloy iron clad is arranged on the windward front end part of the blade 9, so that the gravity center of the blade is moved forward, the flutter stability of the blade 9 is improved, meanwhile, the hinge moment of the blade is reduced, and the blade is enabled to run more stably.
Finally, it is noted that the above embodiments are only for illustrating the technical solution of the present invention and not for limiting the same, and although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications and equivalents may be made thereto without departing from the spirit and scope of the technical solution of the present invention, which is intended to be covered by the scope of the claims of the present invention.
Claims (3)
1. A helicopter tail rotor star-shaped pitch-changing mechanism is characterized in that: the pitch-changing assembly comprises a star-shaped pitch-changing connecting rod, a first knuckle bearing mechanism and a paddle clamp, wherein the first knuckle bearing mechanism is connected with the star-shaped pitch-changing connecting rod and moves along the star-shaped pitch-changing connecting rod in the vertical direction; the shell comprises a double-sleeve structure formed by combining an inner sleeve and an outer sleeve which are coaxially arranged, a paddle is fixedly connected with one end of a paddle clamp, the paddle clamp is arranged on the wall of the outer sleeve through a self-lubricating bushing, the other end of the paddle clamp is provided with a shaft neck structure for being arranged on the wall of the inner sleeve, the shaft neck of the paddle clamp is provided with a connecting block integrally formed with the paddle clamp, the star-shaped variable-pitch connecting rod structure is in a hexagonal star shape, six corner ends are downwards bent to form a connecting part in transmission connection with the paddle clamp, a first joint bearing mechanism is rotationally connected with the connecting part and is rotationally matched with the connecting block; six connecting rod ends of the six connecting rod with the six hexagonal star-shaped deformation distances are uniformly distributed along the circumferential direction, the six paddles are uniformly distributed along the circumferential direction of the shell, and elliptical holes for the first joint bearing mechanism to move in the vertical direction and drive the paddle clamps to rotate are formed in the connecting part; a second joint bearing for supporting the rotation of the tail rotor blade is arranged between the connecting block of the blade clamp and the wall of the outer sleeve barrel of the blade clamp.
2. The helicopter tail rotor radial pitch mechanism of claim 1 wherein: the blade is made of a high-strength carbon fiber-epoxy composite material, and the front edge of the blade is wrapped by nickel alloy electroforming iron clad.
3. A helicopter, characterized in that: a helicopter body having mounted thereon a helicopter tail rotor radial pitch mechanism as claimed in any one of claims 1 to 2.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2018113155456 | 2018-11-06 | ||
| CN201811315545 | 2018-11-06 |
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| Publication Number | Publication Date |
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| CN109436299A CN109436299A (en) | 2019-03-08 |
| CN109436299B true CN109436299B (en) | 2023-11-07 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811639432.1A Active CN109436299B (en) | 2018-11-06 | 2018-12-29 | Star-shaped pitch-changing mechanism of helicopter tail rotor and helicopter |
| CN201822258401.3U Active CN209467316U (en) | 2018-11-06 | 2018-12-29 | Helicopter tail rotor regulating system and helicopter |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822258401.3U Active CN209467316U (en) | 2018-11-06 | 2018-12-29 | Helicopter tail rotor regulating system and helicopter |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109436299B (en) * | 2018-11-06 | 2023-11-07 | 珠海隆华直升机科技有限公司 | Star-shaped pitch-changing mechanism of helicopter tail rotor and helicopter |
| CN115571331A (en) * | 2022-12-08 | 2023-01-06 | 中国空气动力研究与发展中心低速空气动力研究所 | Combined type high-speed helicopter propeller pitch-changing device and control system |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5306119A (en) * | 1992-03-24 | 1994-04-26 | Kawasaki Jukogyo Kabushiki Kaisha | Ducted tail rotor for rotor craft |
| US5383767A (en) * | 1992-12-23 | 1995-01-24 | Eurocopter France | Blade-hub linkage device with a laminate attachment |
| CN105599898A (en) * | 2016-02-26 | 2016-05-25 | 天峋创新（北京）科技有限公司 | Three-rotor-wing tail rotor hub of unmanned helicopter |
| CN205707301U (en) * | 2016-04-20 | 2016-11-23 | 程靖 | A kind of pulp distance varying mechanism |
| CA3004224A1 (en) * | 2017-07-27 | 2018-07-11 | Airbus Helicopters Deutschland GmbH | A control transfer member for a pitch control device of a ducted rotorcraft tail rotor |
| CN209467316U (en) * | 2018-11-06 | 2019-10-08 | 珠海隆华直升机科技有限公司 | Helicopter tail rotor regulating system and helicopter |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3366584B1 (en) * | 2017-02-27 | 2019-04-17 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Pitch control device for a ducted tail rotor of a rotorcraft |
-
2018
- 2018-12-29 CN CN201811639432.1A patent/CN109436299B/en active Active
- 2018-12-29 CN CN201822258401.3U patent/CN209467316U/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5306119A (en) * | 1992-03-24 | 1994-04-26 | Kawasaki Jukogyo Kabushiki Kaisha | Ducted tail rotor for rotor craft |
| US5383767A (en) * | 1992-12-23 | 1995-01-24 | Eurocopter France | Blade-hub linkage device with a laminate attachment |
| CN105599898A (en) * | 2016-02-26 | 2016-05-25 | 天峋创新（北京）科技有限公司 | Three-rotor-wing tail rotor hub of unmanned helicopter |
| CN205707301U (en) * | 2016-04-20 | 2016-11-23 | 程靖 | A kind of pulp distance varying mechanism |
| CA3004224A1 (en) * | 2017-07-27 | 2018-07-11 | Airbus Helicopters Deutschland GmbH | A control transfer member for a pitch control device of a ducted rotorcraft tail rotor |
| CN209467316U (en) * | 2018-11-06 | 2019-10-08 | 珠海隆华直升机科技有限公司 | Helicopter tail rotor regulating system and helicopter |
Also Published As
| Publication number | Publication date |
|---|---|
| CN209467316U (en) | 2019-10-08 |
| CN109436299A (en) | 2019-03-08 |
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