CN210027887U - Variable-pitch disc assembly for transferring torque of helicopter rotor shaft and helicopter - Google Patents
Variable-pitch disc assembly for transferring torque of helicopter rotor shaft and helicopter Download PDFInfo
- Publication number
- CN210027887U CN210027887U CN201822277026.7U CN201822277026U CN210027887U CN 210027887 U CN210027887 U CN 210027887U CN 201822277026 U CN201822277026 U CN 201822277026U CN 210027887 U CN210027887 U CN 210027887U
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- tail
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- 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 utility model discloses a helicopter rotor shaft is displacement dish assembly and helicopter for torque transmission, include to follow tail rotor shaft endwise slip and with tail rotor shaft transmission complex mode overcoat in the displacement dish of tail rotor shaft, overcoat be used for driving the gliding displacement sleeve of displacement dish and be used for driving the drive assembly of displacement sleeve along tail rotor shaft endwise slip in the displacement dish, be provided with the transfer line that is used for being connected with paddle subassembly on the displacement dish, the displacement dish passes through angular contact ball bearing and is connected with the rotation of displacement sleeve. The utility model discloses not only can realize the tail-rotor displacement through the displacement dish, accessible displacement dish realizes the moment of torsion transmission to the tail-rotor shaft moreover to realize the high-speed rotation of displacement dish, extension bearing life.
Description
Technical Field
The utility model relates to a helicopter field, in particular to helicopter rotor axle torque transmission is with displacement dish assembly.
Background
Helicopter tail rotors are components used to balance reactive torque and steer the helicopter in heading. The rotating tail rotor is equivalent to a vertical stabilizing plane and can stabilize the heading of the helicopter. Although the tail rotor functions differently than a rotor, they are both aerodynamic in rotation and operate in an asymmetric airflow during forward flight, and thus the tail rotor structure has many similarities to the rotor structure. At present, the tail rotor mainly has a seesaw type, a universal joint type, a hinged type, a bearingless type and a duct tail rotor type.
The conventional tail rotor generally comprises a tail blade, a tail rotor hub and a variable pitch mechanism, wherein the tail blade is connected to the tail rotor hub and is a rotating wing surface for generating aerodynamic force; the tail rotor hub is an intermediate component for connecting the tail rotor blades with a tail transmission system and a tail control system; the tail rotor pitch-changing mechanism mainly comprises a sliding cylinder, a three-fork driving lever, a pitch-changing pull rod and the like, and is used for changing the pitch angle of the tail rotor so as to change the size and the direction of the pull force of the tail rotor. In the prior art, most helicopter tail rotors are variable in pitch by adopting a multi-part transmission structure to transmit the operating force of a steering engine to a variable pitch pull rod and finally to the tail rotors. The direct consequence of such a design is that its structural weight increases and excessive transmission joints can lead to a reduction in the reliability of the transmission; meanwhile, in the prior art, the rotor shaft transmits torque through the variable-pitch pull rod, so that the service lives of the pull rod and the bearing are shortened.
SUMMERY OF THE UTILITY MODEL
In view of this, the utility model aims at providing a helicopter rotor shaft is displacement dish assembly and helicopter for torque transmission not only can realize the tail-rotor displacement through the displacement dish, and accessible displacement dish realizes the torque transmission to the tail-rotor shaft moreover to realize the high-speed rotation of displacement dish, extension bearing life.
The utility model discloses a helicopter rotor shaft is displacement disc assembly for torque transmission, include with can follow tail rotor shaft axial slip and with tail rotor shaft transmission complex mode the displacement disc of overcoat in tail rotor shaft, overcoat in displacement disc be used for driving the gliding displacement sleeve of displacement disc and be used for driving the gliding drive assembly of displacement sleeve along tail rotor shaft axial, be provided with the transfer line that is used for being connected with the paddle subassembly on the displacement disc, through displacement disc and tail rotor shaft transmission complex, make the displacement disc rotate along with tail rotor shaft, and tail rotor shaft drives tail rotor paddle subassembly and rotate, thereby make the displacement disc realize the torque transmission to tail rotor shaft, optimized the biography power route, prolonged the life of bearing and other spare parts; meanwhile, the driving assembly drives the pitch-variable sleeve to slide so as to drive the pitch-variable disc to slide, and the pitch-variable disc slides to drive the tail rotor blade assembly to rotate, so that the pitch variation of the tail rotor is realized; the variable-pitch disc is rotationally connected with the variable-pitch sleeve through the angular contact ball bearings, the two angular contact ball bearings are arranged at intervals along the axial direction, so that the high-speed rotation of the variable-pitch disc is realized, and the service life of the bearing can be prolonged.
Furthermore, the variable-pitch disc is in transmission fit with the tail rotor shaft through a sliding ring so as to realize axial sliding of the variable-pitch disc; and a self-lubricating annular thin-walled part for transmitting torque is arranged between the variable-pitch disc and the tail rotor wing shaft, and the self-lubricating annular thin-walled part adopts a self-lubricating gasket to realize torque transmission, optimize a force transmission path, avoid the pull rod from directly bearing the torque and prolong the service life of the pull rod.
Furthermore, the driving assembly comprises a steering engine, a pull rod and a variable-pitch rocker arm, the pull rod is located on the outer side of the variable-pitch sleeve and is connected with the steering engine in a transmission mode, the variable-pitch rocker arm is arranged between the pull rod and the variable-pitch sleeve, the steering engine is fixed on a tail rotor support, a tail rotor shaft is supported on the tail rotor support in a rotatable mode, the output end of the steering engine is located in the tail rotor support, one end of the pull rod extends into the tail rotor support and is hinged to the steering engine rocker arm arranged at the output end of the steering engine, the other end of the pull rod extends out of the tail rotor support and is hinged to one end of the variable-pitch rocker arm, the other end of the variable-pitch rocker arm is hinged to the variable-pitch sleeve, the pull rod is driven by the steering engine to move up and down, the variable-pitch rocker arm drives the variable-pitch sleeve to slide along the axial direction, and.
Furthermore, be provided with on the tail-rotor support with displacement rocking arm complex connecting rod, the connecting rod is located between pull rod and the displacement sleeve, and this connecting rod one end is articulated with the displacement rocking arm, and the other end is articulated with the linking arm that is equipped with on the tail-rotor support, improves transmission efficiency, guarantees transmission stability.
Further, the one end that the displacement dish is close to paddle subassembly is provided with first sealed lid, the one end that the displacement sleeve is close to paddle subassembly is provided with the sealed lid of second, the other end of displacement dish and displacement sleeve is provided with and is used for forming the sealed lid of common sealed third to displacement dish and displacement sleeve, first sealed lid compresses tightly the lid for the bearing, the sealed lid of second is the shield, the sealed end face of third is lock nut, lock nut's sealed end is equipped with seals and does not hinder the displacement dish along with tail rotor shaft 1 pivoted annular to the displacement sleeve.
Further, tail rotor blade subassembly includes the tail rotor shaft neck of being connected with tail rotor shaft, presss from both sides and is fixed in the tail rotor blade on the tail rotor clamp with tail rotor shaft neck normal running fit's tail rotor, the tail rotor presss from both sides the one end outer wall that is close to tail rotor shaft and is equipped with the first radial connecting portion that are used for being connected with the transfer line, first radial connecting portion are located the homonymy with the windward side of tail rotor blade, the displacement dish is close to the outer wall that tail rotor pressed from both sides one end and is equipped with the second radial connecting portion that are used for being connected with the transfer line, the transfer line both ends are articulated with first radial connecting portion and second radial connecting portion respectively, and the transfer line both ends adopt joint bearing to articulate with first radial connecting portion and second radial connecting portion respectively, make the displacement dish can drive tail rotor clamp along axial slip and rotate, realize the tail rotor displacement. One end of the tail rotor clamp is sleeved on the tail rotor shaft neck, and is in rotating fit with the tail rotor shaft neck through two sliding bearings which are arranged at intervals along the axial direction of the tail rotor shaft neck, so that stable variable pitch motion is realized; the tail rotor pull-twist strip penetrates through the tail rotor clamp and the tail rotor shaft neck, two ends of the tail rotor pull-twist strip are fixed to the tail rotor clamp and the tail rotor shaft neck through pins respectively, and the tail rotor pull-twist strip is arranged to bear centrifugal force so as to reduce stress of the sliding bearing (avoid axial bearing of the centrifugal force), and therefore the service life of the bearing is greatly prolonged; an O-shaped sealing ring is further arranged between the tail rotor clamp and the tail rotor shaft neck, so that the waterproof, dustproof and sand-proof effects are improved.
The utility model also discloses an use helicopter rotor axle for the moment of torsion transmission displacement dish assembly's helicopter, helicopter rotor axle for the moment of torsion transmission displacement dish assembly install in this helicopter, not only can realize the tail-rotor displacement through the displacement dish, and accessible displacement dish realizes the moment of torsion transmission to the tail-rotor axle moreover to realize the high-speed rotation of displacement dish, extension bearing life.
The utility model has the advantages that: the utility model discloses a helicopter rotor shaft is displacement dish assembly and helicopter for torque transmission not only can realize the tail-rotor displacement through the displacement dish, and accessible displacement dish realizes the torque transmission to the tail-rotor shaft moreover to realize the high-speed rotation of displacement dish, extension bearing life.
Drawings
The invention will be further described with reference to the following figures and examples:
fig. 1 is a schematic structural view of the present invention;
FIG. 2 is a cross-sectional view of the depulped blade of FIG. 1;
FIG. 3 is a partial cross-sectional left view of FIG. 2;
FIG. 4 is a top partial cross-sectional view of FIG. 2;
FIG. 5 is a schematic view of the tailed paddle blade assembly of FIG. 4;
fig. 6 is a perspective view of the present invention.
Detailed Description
As shown in fig. 1 to 6: the variable-pitch disk assembly for torque transmission of the helicopter rotor shaft comprises a variable-pitch disk 3 which can slide along the axial direction of the tail rotor shaft 1 and is sleeved on the tail rotor shaft 1 in a transmission matching mode with the tail rotor shaft 1, a variable-pitch sleeve 4 which is sleeved on the variable-pitch disk 3 and is used for driving the variable-pitch disk 3 to slide, and a driving assembly which is used for driving the variable-pitch sleeve 4 to slide along the axial direction of the tail rotor shaft 1, wherein the variable-pitch disk 3 is provided with a transmission rod 5 which is used for being connected with a blade assembly, and the variable-pitch disk 3 is in transmission matching with the tail rotor shaft 1, so that the variable-pitch disk 3 rotates along with the tail rotor shaft 1 and drives the tail rotor blade assembly to rotate, thereby the variable-pitch disk 3 realizes torque transmission to the tail rotor shaft 1, a force transmission path is optimized, and the service lives of a bearing and other parts are prolonged; meanwhile, the driving assembly drives the variable-pitch sleeve 4 to slide so as to drive the variable-pitch disc 3 to slide, and the variable-pitch disc 3 slides to drive the tail rotor blade assembly to rotate, so that the variable pitch of the tail rotor is realized; the variable-pitch disc 3 is rotationally connected with the variable-pitch sleeve 4 through the angular contact ball bearings 15, and the two angular contact ball bearings 15 are arranged at intervals along the axial direction in the embodiment, so that the high-speed rotation of the variable-pitch disc 3 is realized, and the service life of the bearing can be prolonged.
In this embodiment, the variable-pitch disc 3 is in transmission fit with the tail rotor shaft 1 through the sliding ring 13 to realize axial sliding of the variable-pitch disc 3, the sliding ring 13 in this embodiment is a piston ring, and two piston rings are arranged at intervals along the axial direction to improve the service life of the bearing; and a self-lubricating annular thin-walled part 14 for transmitting torque is arranged between the variable-pitch disc 3 and the tail rotor shaft 1, and the self-lubricating annular thin-walled part 14 of the embodiment adopts a self-lubricating gasket to realize torque transmission, optimize a force transmission path, prevent a pull rod from directly bearing the torque and prolong the service life of the pull rod. Still be provided with dust seal and O type sealing washer between the tail-rotor shaft 1 of this embodiment and displacement dish 3 to improve waterproof, dustproof, sand control stone effect.
In the embodiment, the driving assembly comprises a steering engine 6, a pull rod 7 located outside the variable-pitch sleeve 4 and in transmission connection with the steering engine 6, and a variable-pitch rocker arm 8 arranged between the pull rod 7 and the variable-pitch sleeve 4, the steering engine 6 is fixed on a tail rotor support 9, the tail rotor shaft 1 is rotatably supported on the tail rotor support 9, the output end of the steering engine 6 is located in the tail rotor support 9, one end of the pull rod 7 extends into the tail rotor support 9 and is hinged to a steering engine rocker arm 10 arranged at the output end of the steering engine 6, the other end of the pull rod 7 extends out of the tail rotor support 9 and is hinged to one end of the variable-pitch rocker arm 8, and the other end of the variable-pitch rocker arm 8 is hinged; the steering engine 6 drives the pull rod 7 to move up and down, the variable-pitch rocker arm 8 is further driven to move along with the pull rod 7, the variable-pitch rocker arm 8 drives the variable-pitch sleeve 4 to slide along the axial direction, the variable-pitch sleeve 4 drives the variable-pitch disc 3 to slide along the axial direction, and the variable-pitch disc 3 drives the tail rotor blade assembly to rotate, so that the tail rotor pitch variation is realized. The pull rod 7, the steering engine rocker arm 10, the variable pitch rocker arm 8 and the variable pitch sleeve 4 are hinged by joint bearings, and the steering engine rocker arm, the variable pitch rocker arm 8 and the variable pitch sleeve are characterized by high load capacity, impact resistance, corrosion resistance, wear resistance, self-aligning, good lubrication and the like; one end of the variable-pitch rocker arm 8, which is used for being connected with the variable-pitch sleeve 4, is of a semicircular structure, so that the assembly is convenient, and the connection is firm; the tail rotor shaft 1 is rotationally connected with a tail rotor support 9 through an angular contact ball bearing, a bearing seat for supporting the tail rotor shaft 1 and a dustproof plate are arranged on the tail rotor support 9 to improve the supporting and protecting effects, and a dustproof seal is arranged between the bearing seat and the tail rotor shaft 1 to improve the dustproof and sand prevention effects; an opening for testing the propeller pitch is formed in the side face of the tail rotor support 9, so that a special detection tool is externally connected to directly test the propeller pitch; and through setting up tail-rotor support 9, be convenient for assemble with the helicopter tail beam pole, promote support intensity and rigidity, anti-fatigue effect is good.
In this embodiment, the tail rotor support 9 is provided with a connecting rod 11 matched with the pitch-variable rocker arm 8, the connecting rod 11 is located between the pull rod 7 and the pitch-variable sleeve 4, one end of the connecting rod 11 is hinged with the pitch-variable rocker arm 8, and the other end of the connecting rod 11 is hinged with a connecting arm 12 arranged on the tail rotor support 9, so that the transmission efficiency is improved, and the transmission stability is ensured; the connecting rod 11, the pitch-variable rocker arm 8 and the connecting arm 12 are hinged by joint bearings, and the pitch-variable rocker arm has the characteristics of high load capacity, impact resistance, corrosion resistance, wear resistance, self-aligning, good lubrication and the like.
In this embodiment, the one end that the displacement dish 3 is close to paddle subassembly is provided with first sealed lid 16, the one end that the displacement sleeve 4 is close to paddle subassembly is provided with the sealed lid 17 of second, the other end of displacement dish 3 and displacement sleeve 4 is provided with and is used for forming the sealed lid 18 of third sealed jointly to displacement dish 3 and displacement sleeve 4, the first sealed lid 16 of this embodiment compresses tightly the lid for the bearing, the sealed lid 17 of second is the shield, the sealed end face of third is lock nut, lock nut's sealed end face is equipped with seals displacement sleeve 4 and does not hinder displacement dish 3 along with tail rotor shaft 1 pivoted annular.
In this embodiment, the tail rotor blade assembly includes a tail rotor shaft neck 19 connected to the tail rotor shaft 1, a tail rotor clip 20 rotationally fitted to the tail rotor shaft neck 19, and a tail rotor blade 21 fixed to the tail rotor clip 20, the outer wall of one end of the tail rotor clip 20 close to the tail rotor shaft 1 is provided with a first radial connecting portion 22 for connecting to the transmission rod 5, the first radial connecting portion 22 is located at the same side as the windward side of the tail rotor blade 21, the outer wall of one end of the variable-pitch disc 3 close to the tail rotor clip 20 is provided with a second radial connecting portion 23 for connecting to the transmission rod 5, two ends of the transmission rod 5 are respectively hinged to the first radial connecting portion 22 and the second radial connecting portion 23, two ends of the transmission rod 5 of this embodiment are respectively hinged to the first radial connecting portion 22 and the second radial connecting portion 23 by joint bearings, so that the variable-pitch disc 3 can drive the tail rotor clip 20 to rotate along axial sliding, and the variable pitch of the tail rotor is realized. One end of the tail rotor clamp 20 of the embodiment is externally sleeved on the tail rotor shaft neck 19 and is in running fit with the tail rotor shaft neck 19 through two sliding bearings which are arranged at intervals along the axial direction of the tail rotor shaft neck 19, so that stable variable pitch motion is realized; the tail rotor is characterized in that penetrating tail rotor pulling and twisting strips are arranged in the tail rotor clamp 20 and the tail rotor shaft neck 19, two ends of each tail rotor pulling and twisting strip are fixed to the tail rotor clamp 20 and the tail rotor shaft neck 19 through pins respectively, and the tail rotor pulling and twisting strips are arranged to bear centrifugal force so as to reduce stress of a sliding bearing (avoid axial bearing of the centrifugal force), so that the service life of the bearing is greatly prolonged; an O-shaped sealing ring is further arranged between the tail rotor clamp 20 and the tail rotor shaft neck 19 so as to improve the waterproof, dustproof and sand-proof effects.
In this embodiment, still including being used for driving tail-rotor shaft 1 pivoted tail-rotor motor 2, tail-rotor motor 2 is fixed in on the tail-rotor support 9, the axis of steering wheel 6 is mutually perpendicular with tail-rotor motor 2's axis, makes tail-rotor motor 2 and drive assembly parts such as pull rod 7, displacement rocking arm 8 separately arrange in tail-boom pole both sides, makes both sides weight keep unanimous basically to guarantee that the atress is more even, promote performance.
In this embodiment, the tail rotor shaft neck 19 is fixedly connected with the tail rotor shaft 1 through the flapping hinge 24, and because the windward sides of the first radial connecting portion 22 and the tail rotor blade 21 are located at the same side, flapping can be effectively inhibited; the axis of the flapping hinge 24 deviates from the axis of the first radial connecting part 22, so that a slight inclination angle (basically coaxial) is formed between the axis of the flapping hinge 24 and the axis of the first radial connecting part 22, thereby effectively inhibiting periodic variable pitch, reducing the coupling of the periodic variable pitch and the flapping, and prolonging the service life of the bearing.
In the embodiment, the tail rotor blade 21 is made of a high-strength carbon fiber-epoxy composite material, the edge of the windward side of the tail rotor blade 21 is coated with the nickel alloy iron-coated layer, so that the service life and the sand stone resistance can be prolonged, the forward movement of the center of gravity can be realized by arranging the nickel alloy iron-coated layer, the flutter stability of the tail rotor blade 21 is improved, and the hinge moment of the tail rotor blade 21 is reduced; the tail rotor shaft 1 is used for installing the dynamic balance weight plate 25 with the one end tip that the tail rotor paddle subassembly is connected, realizes good dynamic balance through adjusting the counter weight.
The utility model also discloses an use helicopter rotor axle for the moment of torsion transmission displacement dish assembly's helicopter, helicopter rotor axle for the moment of torsion transmission displacement dish assembly install in this helicopter, not only can realize the tail-rotor displacement through the displacement dish, and accessible displacement dish realizes the moment of torsion transmission to the tail-rotor axle moreover to realize the high-speed rotation of displacement dish, extension bearing life.
Finally, 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 the present invention can be modified or replaced by other means without departing from the spirit and scope of the present invention, which should be construed as limited only by the appended claims.
Claims (7)
1. The utility model provides a helicopter rotor shaft is displacement dish assembly for torque transmission which characterized in that: including with can follow tail-rotor shaft endwise slip and with tail-rotor shaft transmission complex mode overcoat in the displacement dish of tail-rotor shaft, overcoat in the displacement dish be used for driving the gliding displacement sleeve of displacement dish and be used for driving the displacement sleeve along tail-rotor shaft endwise slip's drive assembly, be provided with the transfer line that is used for being connected with the paddle subassembly on the displacement dish, the displacement dish passes through angular contact ball bearing and is connected with the rotation of displacement sleeve.
2. A helicopter rotor shaft torque transmitting pitch disc assembly according to claim 1 wherein: the variable-pitch disc is in transmission fit with the tail rotor wing shaft through a sliding ring, and a self-lubricating annular thin-walled part used for transmitting torque is arranged between the variable-pitch disc and the tail rotor wing shaft.
3. A helicopter rotor shaft torque transmitting pitch disc assembly according to claim 1 wherein: the drive assembly comprises a steering engine, a pull rod and a variable-pitch rocker arm, wherein the pull rod is located on the outer side of the variable-pitch sleeve and is connected with the steering engine in a transmission mode, the variable-pitch rocker arm is arranged between the pull rod and the variable-pitch sleeve, the steering engine is fixed on a tail rotor support, a tail rotor shaft is supported on the tail rotor support in a rotatable mode, the output end of the steering engine is located in the tail rotor support, one end of the pull rod stretches into the tail rotor support and is hinged to the steering engine rocker arm arranged at the output end of the steering engine, the other end of the pull rod stretches out of the tail rotor support and is hinged to one end of.
4. A helicopter rotor shaft torque transfer pitch disc assembly according to claim 3 wherein: the tail rotor support is provided with a connecting rod matched with the variable-pitch rocker arm, the connecting rod is located between the pull rod and the variable-pitch sleeve, one end of the connecting rod is hinged with the variable-pitch rocker arm, and the other end of the connecting rod is hinged with a connecting arm arranged on the tail rotor support.
5. A helicopter rotor shaft torque transmitting pitch disc assembly according to claim 1 wherein: the one end that the displacement dish is close to paddle subassembly is provided with first sealed lid, and the one end that the displacement sleeve is close to paddle subassembly is provided with the sealed lid of second, and the other end of displacement dish and displacement sleeve is provided with and is used for forming the sealed third sealed lid jointly to displacement dish and displacement sleeve.
6. A helicopter rotor shaft torque transmitting pitch disc assembly according to claim 5 wherein: paddle subassembly includes the tail-rotor axle journal of being connected with the tail-rotor axle, presss from both sides and is fixed in the tail-rotor paddle on the tail-rotor clamp with tail-rotor axle journal normal running fit's tail-rotor, the tail-rotor is pressed from both sides the one end outer wall that is close to the tail-rotor axle and is equipped with the first radial connecting portion that are used for being connected with the transfer line, first radial connecting portion are located the homonymy with the windward side of tail-rotor paddle, the displacement dish is close to the outer wall that the tail-rotor pressed from both sides one end and is equipped with the radial connecting portion of second that are used for being connected with the transfer line, the transfer line both ends are articulated with first radial connecting.
7. A helicopter to which the variable pitch disk assembly for helicopter rotor shaft torque transmission of any of claims 1 to 6 is applied, characterized in that: the variable-pitch disc assembly for transmitting the torque of the rotor shaft of the helicopter is arranged on the helicopter.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2018113150490 | 2018-11-06 | ||
| CN201811315049 | 2018-11-06 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210027887U true CN210027887U (en) | 2020-02-07 |
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Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811639384.6A Withdrawn CN109502010A (en) | 2018-11-06 | 2018-12-29 | Helicopter tail rotor displacement displacement disc assembly and helicopter |
| CN201822277026.7U Active CN210027887U (en) | 2018-11-06 | 2018-12-29 | Variable-pitch disc assembly for transferring torque of helicopter rotor shaft and helicopter |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811639384.6A Withdrawn CN109502010A (en) | 2018-11-06 | 2018-12-29 | Helicopter tail rotor displacement displacement disc assembly and helicopter |
Country Status (1)
| Country | Link |
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| CN (2) | CN109502010A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109502010A (en) * | 2018-11-06 | 2019-03-22 | 珠海隆华直升机科技有限公司 | Helicopter tail rotor displacement displacement disc assembly and helicopter |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115783243A (en) * | 2021-09-09 | 2023-03-14 | 中国科学院沈阳自动化研究所 | Rotor unmanned aerial vehicle hub system verts |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5071319A (en) * | 1987-09-30 | 1991-12-10 | The Boeing Company | Low maintenance, advanced technology swashplate |
| EP3216696B1 (en) * | 2014-08-08 | 2018-04-11 | LEONARDO S.p.A. | Helicopter |
| CN204527631U (en) * | 2015-03-19 | 2015-08-05 | 河南金原碟科技有限公司 | Multi-rotor aerocraft oar dish |
| CN105667786B (en) * | 2016-01-12 | 2017-11-10 | 深圳清华大学研究院 | The tail-rotor drive system and its control method of helicopter, helicopter |
| CN205707301U (en) * | 2016-04-20 | 2016-11-23 | 程靖 | A kind of pulp distance varying mechanism |
| CN106081102A (en) * | 2016-08-11 | 2016-11-09 | 深圳天鹰兄弟无人机创新有限公司 | A kind of unmanned plane and bar thick stick formula tail-rotor distance changing mechanism thereof |
| RU2656737C1 (en) * | 2016-12-13 | 2018-06-06 | федеральное государственное бюджетное образовательное учреждение высшего образования "Уфимский государственный авиационный технический университет" | Skew machine |
| CN207725606U (en) * | 2017-08-09 | 2018-08-14 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of rotor wing unmanned aerial vehicle tail-rotor distance changing mechanism |
| CN207875998U (en) * | 2018-02-08 | 2018-09-18 | 天津曙光天成科技有限公司 | A kind of tail-rotor structure and the unmanned plane with it |
| CN109502010A (en) * | 2018-11-06 | 2019-03-22 | 珠海隆华直升机科技有限公司 | Helicopter tail rotor displacement displacement disc assembly and helicopter |
-
2018
- 2018-12-29 CN CN201811639384.6A patent/CN109502010A/en not_active Withdrawn
- 2018-12-29 CN CN201822277026.7U patent/CN210027887U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109502010A (en) * | 2018-11-06 | 2019-03-22 | 珠海隆华直升机科技有限公司 | Helicopter tail rotor displacement displacement disc assembly and helicopter |
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| CN109502010A (en) | 2019-03-22 |
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