CN209467315U - Helicopter tail rotor displacement regulating system and helicopter - Google Patents
Helicopter tail rotor displacement regulating system and helicopter Download PDFInfo
- Publication number
- CN209467315U CN209467315U CN201822254374.2U CN201822254374U CN209467315U CN 209467315 U CN209467315 U CN 209467315U CN 201822254374 U CN201822254374 U CN 201822254374U CN 209467315 U CN209467315 U CN 209467315U
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- displacement
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- helicopter
- push rod
- regulating system
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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
-
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Sliding-Contact Bearings (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Toys (AREA)
Abstract
The utility model discloses a kind of helicopter tail rotor displacement regulating systems, including connecting the pitch-changing mechanism for driving tail-rotor blade displacement with straight line steering engine mechanism, the pitch-changing mechanism includes for installing the shell of blade, being set in shell for adjusting the link mechanism of blade displacement, the displacement push rod connecting with link mechanism；The link mechanism includes the hexagram displacement connecting rod connecting with displacement push rod and for driving blade in vertical direction to deflect and realize the first oscillating bearing mechanism of displacement；The technical program can overcome unmanned helicopter tail rotor pitch control manufacture difficulty in traditional handicraft big, bulky, and blade displacement is difficult, and control precision is low, and complicated integral structure, service life is short, the high problem of manufacturing cost.
Description
Technical field
The utility model relates to helicopter fields, and in particular to a kind of helicopter tail rotor displacement regulating system and helicopter.
Background technique
Helicopter tail rotor is for balancing reaction torque and carrying out the component of directional control to helicopter.The tail-rotor phase being rotating
When stabilization can be played to helicopter course in a fixed fin.Although the function of rear paddle is different from rotor, they
It is all the state that generates air force, work in asymmetric flow when preceding winged by rotation, therefore tail-rotor structure and rotation
Wing structure has many similarities.The structure type of tail-rotor has seesaw type, Universal connector hair style, radial type, bearing-free formula, " contains
Road tail-rotor " formula etc..
Since the power of tail-rotor is generally from the sustainer of helicopter, the main side of tail-rotor amount of force is controlled
Method is exactly to change the screw pitch of propeller, i.e. displacement.The development of current such aircraft is right both at home and abroad also in primary developing stage
It is also very different in the design of unmanned helicopter tail-rotor displacement, is using more parts mostly general unmanned helicopter tail-rotor displacement
The steering force of steering engine is transmitted on pitch-change-link by drive mechanism, finally passes to tail-rotor again.Caused by such design directly
Consequence is exactly that its architecture quality increases, and excessive drive joint will lead to the reliability reduction of transmission.In helicopter
In accident investigation, the accident as caused by tail-rotor system has reached 32% in the helicopter fuselage system failure, and wherein tail-rotor passes
The accident rate 18% of moving axis, tail-rotor accident rate are 14%.It can be seen that a set of reliable tail-rotor design is to ensure flight peace
Full key.
Need a kind of structure simple thus, security performance is high, and processing and manufacturing is easy, while convenient accurate control tail-rotor displacement
It is convenient to the tail-rotor mechanism that unmanned helicopter turns to safely.
Utility model content
In view of this, providing helicopter tail rotor displacement tune the purpose of the utility model is to overcome defect in the prior art
Section system can overcome unmanned helicopter manufacture difficulty in traditional handicraft big, bulky, and blade displacement is difficult, control precision
Low, complicated integral structure, service life is short, the high problem of manufacturing cost.
A kind of helicopter tail rotor displacement regulating system of the utility model, including connect with straight line steering engine mechanism for driving
The pitch-changing mechanism of tail-rotor blade displacement, the pitch-changing mechanism include for installing the shell of blade, being set in shell for adjusting
The link mechanism for saving blade displacement, the displacement push rod being connect with link mechanism；The link mechanism includes connecting with displacement push rod
Hexagram displacement connecting rod and for driving blade in vertical direction to deflect and realize the first oscillating bearing of displacement
Mechanism；Six angles end of the hexagram displacement connecting rod bends downward to form interconnecting piece, is provided with ellipse on the interconnecting piece
Hole, elliptical aperture long axis is vertical with vertical direction, and first oscillating bearing is coupled by elliptical aperture in interconnecting piece；The shell
Body includes that the inner sleeve of coaxial arrangement combines the double-sleeve structure to be formed with outer sleeve, and blade is fixedly connected with one end that paddle presss from both sides,
The paddle folder is installed on outer sleeve barrel by self-lubricating bushing, and the paddle folder other end is provided with for being mounted on inner sleeve
Journal structure on barrel, the paddle press from both sides the link block being additionally provided on axle journal for connecting with the first oscillating bearing；Pass through change
It pushes pitch-changing mechanism to move vertical direction (i.e. along the axial direction of push rod) away from push rod, and then drives blade in vertical direction
Deflect, to realize blade displacement, by the shell being fixedly installed with tail-rotor power mechanism, drive blade occur it is circumferential (with
The axially vertical direction of push rod) movement.
Further, six connecting-rod heads of the hexagram displacement connecting rod are distributed uniformly and circumferentially, and blade is six
And it is uniformly distributed in shell circumferencial direction；Using the tactic pattern of six connecting rod connection blades, keep mechanism operation more steady, than
Traditional double blades mechanism is played, the mechanism in the technical program is more uniformly stressed, and is determined by the angular range that blade rotates
The length of link block keeps the arrangement between link mechanism more reasonable, and structure is more compact, effectively reduces and produces in tail-rotor mechanism kinematic
Raw noise.
Further, it is provided between the link block of the paddle folder and the outer sleeve barrel of paddle folder installation and is used to support tail-rotor paddle
The second joint bearing of leaf rotation；Second joint bearing is connected on shell by shearing bolt, and second joint bearing is paddle folder
The rotation of blade provides supporting point, guarantees the stability in rotation process, and the centrifugal force generated in blade motion process passes through the
Two oscillating bearings are transmitted on shell, are improved the stress condition of double self-lubricating bushings, are further improved the use of each component
Service life.
Further, the displacement pusher structure is the pusher structure of ladder shaft type；Displacement push rod one end and offer displacement are dynamic
The straight line steering engine mechanism of power connects and displacement push rod sequentially passes through back gauge tail-rotor bracket, tail-rotor power from bottom to top along the vertical direction
Mechanism, shell are convenient to install different parts, are limited the axial runout of each part using the structure of ladder shaft type.
Further, between the displacement push rod and hexagram displacement connecting rod along displacement push rod axial direction setting there are two
Angular contact ball bearing is provided with self-lubricating bushing between the displacement push rod and shell；Pass through angular contact ball bearing, displacement push rod
Self-lubricating bushing, flange bushing ensure on vertical direction it is each it is inter-agency there is good concentricity, the movement of hoisting mechanism is flat
Stability energy reduces noise.
Further, sealing ring, displacement push rod and displacement are provided between the displacement push rod and hexagram displacement connecting rod
Sealing ring or other sealing means are used between connecting rod, displacement connecting rod and remaining position, keep tail-rotor in-house in good
Sealing state improves the service life of the mechanism.
Further, the blade is closed using high-strength carbon fiber-epoxy composite material manufacture, the blade leading edge using nickel
Golden electroforming iron clad package；The blade leading edge is wrapped in blade leading edge using nickel alloy electricity cast packet iron, is set using nickel alloy iron clad
It is placed in the front end position windward of blade, its center of gravity is made to move forward, improves blade flutter stability, while reducing blade hinge moment,
Keep blade operation more steady.
A kind of helicopter is equipped with the unmanned helicopter tail-rotor displacement regulating system on helicopter body.
The beneficial effects of the utility model are: a kind of helicopter tail rotor displacement regulating system disclosed by the utility model, energy
Enough overcome unmanned helicopter manufacture difficulty in traditional handicraft big, bulky, blade displacement is difficult, and control precision is low, whole to tie
Structure is complicated, and service life is short, the high problem of manufacturing cost.
Detailed description of the invention
The utility model is further described with reference to the accompanying drawings and examples:
Fig. 1 is the structural schematic diagram of the utility model；
Fig. 2 is the cross-sectional view of the utility model；
Fig. 3 is the first oscillating bearing attachment structure schematic diagram in the utility model；
Fig. 4 is the utility model midship section structure schematic diagram；
Fig. 5 is interconnecting piece structural schematic diagram in the utility model.
Appended drawing reference
Link block 1；Hexagram displacement connecting rod 2；Shell 3；Paddle folder 4；Paddle presss from both sides bolt 5；Outer cylinder self-lubricating bushing 6；Inner cylinder
Self-lubricating bushing 7；Second joint bearing 8；Blade 9；First oscillating bearing 10；Axle journal 12；Outer sleeve barrel 13；Inner sleeve barrel
14；Interconnecting piece 15；Top cover 16；Tail-rotor motor 17；Displacement tail-rotor bracket 18；Straight line steering engine 19；Angular contact ball bearing 20；Displacement pushes away
Bar 21；Displacement push rod self-lubricating bushing 22；Shearing bolt 23；Flange bushing 24.
Specific embodiment
Fig. 1 is the structural schematic diagram of the utility model, and Fig. 2 is the cross-sectional view of the utility model, and Fig. 3 is in the utility model
First oscillating bearing attachment structure schematic diagram, Fig. 4 are the utility model midship section structure schematic diagram, and Fig. 5 is in the utility model
Interconnecting piece structural schematic diagram, as shown, the helicopter tail rotor displacement regulating system of the utility model, including with straight line steering engine machine
Structure connection is described for driving the pitch-changing mechanism of 9 displacement of tail-rotor blade and driving the tail-rotor power mechanism of pitch-changing mechanism rotation
Pitch-changing mechanism includes for installing the shell 3 of blade 9, being set in shell 3 for adjusting the link mechanism of 9 displacement of blade, connecting
The displacement push rod 21 between link mechanism and straight line steering engine mechanism is connect, the shell 3 around displacement push rod 21 in a manner of rotating
It is sequentially connected with tail-rotor power mechanism.Tail-rotor mechanism assembly in the technical program pushes pitch-changing mechanism by displacement push rod 21
It is moved vertical direction (i.e. along the axial direction of push rod 21), and then blade 9 is driven to deflect in vertical direction, to realize
9 displacement of blade drives blade 9 that the circumferential (axial direction with push rod 21 occurs by the shell 3 being fixedly installed with tail-rotor power mechanism
Vertical direction) movement, by the unmanned helicopter tail-rotor displacement regulating system in the technical program, traditional handicraft can be overcome
Middle unmanned helicopter manufacture difficulty is big, bulky, and blade displacement is difficult, and control precision is low, complicated integral structure, service life
It is short, the high problem of manufacturing cost.
In the present embodiment, the shell 3 includes that the inner sleeve of coaxial arrangement combines the double-sleeve structure to be formed with outer sleeve,
Blade 9 is fixedly connected with one end of paddle folder 4, and the paddle folder 4 is installed on outer sleeve barrel 13 by self-lubricating bushing, the paddle
It presss from both sides 4 other ends and is provided with 12 structure of axle journal for being mounted on inner sleeve barrel 14, be additionally provided with use on the paddle folder axle journal
In the link block 1 that driving paddle folder 4 rotates along the vertical direction, link mechanism includes the hexagram displacement connecting with displacement push rod 21
Connecting rod 2, the angle end of hexagram displacement connecting rod 2 bend downward the interconnecting piece 15 to be formed with 4 transmission connection of paddle folder.Shell 3 includes
The double-sleeve structure that inside and outside sleeve is formed, 3 bottom of shell are fixedly connected by bolt with the power output end of tail-rotor motor 17, are
Blade circumferentially rotates offer power, and as described in Figure 2, one end of paddle folder 4 presss from both sides bolt 5 for 4 company of fixation of blade 9 and paddle folder by paddle
It connects, paddle folder 4 passes through outer sleeve barrel 13 and connect by the axle journal 12 that paddle presss from both sides the setting of 4 the other end with inner sleeve barrel 14, paddle
Be respectively arranged at the position that folder 4 is rotatably assorted with inner sleeve barrel 14 and outer sleeve barrel 13 inner cylinder self-lubricating bushing 7 and
Outer cylinder self-lubricating bushing 6 provides rotation support by two self-lubricating bushings for 9 displacement of blade, meanwhile, double sleeve connection knots
Structure improves the stability when movement of blade 9, mitigates the stress that blade 9 receives torque and generate with 4 junctions of paddle folder and concentrates now
As, blade life is promoted, keeps blade movement more steady, link block 1 presss from both sides 4 roots with paddle and is fixed together, and preferred two
Person uses integrally formed mode, and displacement push rod 21 is matched and connect with the rotation of hexagram displacement connecting rod 2, and hexagram displacement connects
The angle end (i.e. the end at six angles of Magen David) of bar 2 is bent to form interconnecting piece 15 straight down, offers centered on interconnecting piece 15
Six connecting-rod heads of the circular configuration of mounting hole, the hexagram displacement connecting rod 2 are distributed uniformly and circumferentially, the blade
9 are uniformly distributed in 3 circumferencial direction of shell, using the tactic pattern of six connecting rod connection blades, keep mechanism operation more steady, than
Traditional double blades mechanism is played, the mechanism in the technical program is more uniformly stressed, and is determined by the angular range that blade rotates
The length of link block 1 keeps the arrangement between link mechanism more reasonable, and structure is more compact, effectively reduces in tail-rotor mechanism kinematic
The noise of generation.
In the present embodiment, the first oscillating bearing 10, the first oscillating bearing 10 and the company are provided on the interconnecting piece 15
The rotation connection of block 1 is connect, is provided on the interconnecting piece 15 and is moved for the first oscillating bearing 10 in vertical direction and paddle is driven to press from both sides 4
The elliptical aperture of rotation.First oscillating bearing 10 realizes blade by driving 4 rotation of paddle folder with the elliptical aperture cooperation on interconnecting piece 15
9 displacements, elliptical aperture long axis is vertical with vertical direction, the design of oval pore structure, guarantees that motion structure will not in moving process
It being stuck, while the function that driving blade 9 rotates along the vertical direction can be directly realized by again, structure is simple, handling ease, while gram
The cumbersome problem of distance changing mechanism in traditional handicraft is taken.
In the present embodiment, it is provided with and is used between the outer sleeve barrel 13 of 4 installation of link block 1 and paddle folder of the paddle folder 4
The second joint bearing 8 for supporting tail-rotor blade 9 to rotate.Second joint bearing 8 is connected on shell 3 by shearing bolt 23, the
Two oscillating bearings 8 provide supporting point for the rotation that paddle presss from both sides blade, guarantee the stability in rotation process, produce in blade motion process
Raw centrifugal force is transmitted on shell 3 by second joint bearing 8, improves the stress condition of double self-lubricating bushings, further
The service life of each component is improved, keeps mechanism operation more steady, reduces noise.
In the present embodiment, tail-rotor power mechanism is installed on 18 upper end of displacement tail-rotor bracket, and straight line steering engine mechanism is installed on change
Away from 18 bottom end of tail-rotor bracket.Displacement tail-rotor bracket 18 includes the plate and two pieces vertical with vertical direction horizontal peaces of vertical direction
Horizontal mounting plate above is fixedly mounted in loading board, tail-rotor motor 17, and straight line steering engine 19 is fixedly connected on being horizontally mounted for lower section
Plate is provided with muti-piece stiffening plate structure between upper lower installation board, and when guaranteeing movement mechanism operation, overall structure is more steady.
In the present embodiment, 21 structure of displacement push rod is the pusher structure of ladder shaft type, displacement push rod one end and offer
The straight line steering engine mechanism of displacement power connects and displacement push rod 21 sequentially passes through back gauge tail-rotor bracket from bottom to top along the vertical direction
18, tail-rotor power mechanism, shell 3 are convenient to install different components, are limited all parts using the structure of ladder shaft type
Axial runout, top cover 16 and 3 sealed set of shell reduce intermediate conversion links using straight line steering engine 19, improve Whole Response speed
Degree runs through integrally-built Installation Modes using displacement push rod, keeps each mounting structure more compact, saves installation space, together
When displacement push rod and each connecting portion between use sealing ring or other sealing means, keep tail-rotor in-house in good
Sealing state improves the service life of the mechanism.
In the present embodiment, it is provided between the displacement push rod 21 and hexagram displacement connecting rod 2 along push rod axial direction
Two angular contact ball bearings 20 are provided with displacement push rod self-lubricating bushing 22, the tail between the displacement push rod 12 and shell 3
Flange bushing 24 is provided between paddle motor mechanism and displacement push rod 21.Pass through angular contact ball bearing 20, displacement push rod self-lubricating
Bushing 22, flange bushing 24 ensure on vertical direction it is each it is inter-agency there is good concentricity, the movement of hoisting mechanism is steady
Performance reduces noise.
In the present embodiment, the blade is used using high-strength carbon fiber-epoxy composite material manufacture, the blade leading edge
Nickel alloy electricity cast packet iron is wrapped in blade leading edge, and the front end position windward of blade 9 is set to using nickel alloy iron clad, makes its center of gravity
Forward improves 9 flutter stability of blade, while reducing blade hinge moment, keeps blade operation more steady.
Finally, it is stated that above embodiments are merely intended for describing the technical solutions of the present application, but not for limiting the present application, although ginseng
The utility model is described in detail according to preferred embodiment, those skilled in the art should understand that, it can be to this
The technical solution of utility model is modified or replaced equivalently, without departing from the objective and model of technical solutions of the utility model
It encloses, should all cover in the scope of the claims of the utility model.
Claims (8)
1. a kind of helicopter tail rotor displacement regulating system, it is characterised in that: including connecting with straight line steering engine mechanism for driving tail
The pitch-changing mechanism of paddle blade displacement, the pitch-changing mechanism include for installing the shell of blade, being set in shell for adjusting
The link mechanism of blade displacement, the displacement push rod being connect with link mechanism；The link mechanism includes connecting with displacement push rod
Hexagram displacement connecting rod and for driving blade in vertical direction to deflect and realize the first oscillating bearing machine of displacement
Structure；Six angles end of the hexagram displacement connecting rod bends downward to form interconnecting piece, is provided with elliptical aperture on the interconnecting piece,
Elliptical aperture long axis is vertical with vertical direction, and first oscillating bearing is coupled by the elliptical aperture on interconnecting piece in connection
Portion；The shell structure is that the inner sleeve of coaxial arrangement combines the double-sleeve structure to be formed, blade and the one of paddle folder with outer sleeve
End is fixedly connected, and the paddle folder is installed on outer sleeve barrel by self-lubricating bushing, and the paddle folder other end, which is provided with, to be used for
The journal structure being mounted on inner sleeve barrel, the paddle press from both sides the company being additionally provided on axle journal for connecting with the first oscillating bearing
Connect block.
2. helicopter tail rotor displacement regulating system according to claim 1, it is characterised in that: the hexagram displacement connects
Six connecting-rod heads of bar are distributed uniformly and circumferentially, and blade is six and is uniformly distributed in shell circumferencial direction.
3. helicopter tail rotor displacement regulating system according to claim 1, it is characterised in that: the link block of paddle folder with
The second joint bearing for being used to support the rotation of tail-rotor blade is provided between the outer sleeve barrel of paddle folder installation.
4. helicopter tail rotor displacement regulating system according to claim 1, it is characterised in that: the displacement pusher structure is
The pusher structure of ladder shaft type.
5. helicopter tail rotor displacement regulating system according to claim 1, it is characterised in that: the displacement push rod and hexagonal
Along the setting of displacement push rod axial direction there are two angular contact ball bearing between star displacement connecting rod, the displacement push rod and shell it
Between be provided with self-lubricating bushing.
6. helicopter tail rotor displacement regulating system according to claim 1, it is characterised in that: the displacement push rod and hexagonal
Sealing ring is provided between star displacement connecting rod.
7. helicopter tail rotor displacement regulating system according to claim 1, it is characterised in that: the blade is using high-intensitive
The manufacture of carbon fiber-epoxy composite material, the blade leading edge are wrapped up using nickel alloy electricity cast packet iron.
8. a kind of helicopter, it is characterised in that: installation is gone straight up to just like of any of claims 1-7 on helicopter body
Tail paddle displacement regulating system.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2018113155422 | 2018-11-06 | ||
| CN201811315542 | 2018-11-06 |
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| Publication Number | Publication Date |
|---|---|
| CN209467315U true CN209467315U (en) | 2019-10-08 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811639621.9A Active CN109466749B (en) | 2018-11-06 | 2018-12-29 | Helicopter variable-pitch drive assembly and helicopter |
| CN201822254374.2U Active CN209467315U (en) | 2018-11-06 | 2018-12-29 | Helicopter tail rotor displacement regulating system and helicopter |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811639621.9A Active CN109466749B (en) | 2018-11-06 | 2018-12-29 | Helicopter variable-pitch drive assembly and helicopter |
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| CN (2) | CN109466749B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109466749A (en) * | 2018-11-06 | 2019-03-15 | 珠海隆华直升机科技有限公司 | Helicopter displacement drive assembly and helicopter |
| CN111547252A (en) * | 2020-04-21 | 2020-08-18 | 中国航发湖南动力机械研究所 | Tail rotor pitch control shaft device and preparation method thereof |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5868351A (en) * | 1996-05-23 | 1999-02-09 | Bell Helicopter Textron Inc. | Rotor blade stowing system |
| FR2926786B1 (en) * | 2008-01-30 | 2010-02-19 | Eurocopter France | METHOD OF OPTIMIZING A MINIMUM ACOUSTIC ACOUSTIC GENE CARENE ANTI-COUPLE ROTOR FOR A GIRAVION, IN PARTICULAR A HELICOPTER, AND CARENE ANTI-TORQUE ROTOR SO OBTAINED |
| CN201613027U (en) * | 2010-02-21 | 2010-10-27 | 张伟 | Model helicopter tail torque conversion device and model helicopter utilizing the same |
| ITRM20110563A1 (en) * | 2011-10-27 | 2013-04-28 | K4A S R L | "HOMOCINETIC CARDANIC JOINT FOR HELICOPTER ROTORS" |
| CN106741926A (en) * | 2015-11-24 | 2017-05-31 | 中国直升机设计研究所 | A kind of helicopter ball flexible hub damper arrangement form |
| CN205499338U (en) * | 2016-03-21 | 2016-08-24 | 深圳市龙云创新航空科技有限公司 | Self -adaptation variable -pitch propeller oar and aircraft |
| CN109466749B (en) * | 2018-11-06 | 2023-07-04 | 珠海隆华直升机科技有限公司 | Helicopter variable-pitch drive assembly and helicopter |
-
2018
- 2018-12-29 CN CN201811639621.9A patent/CN109466749B/en active Active
- 2018-12-29 CN CN201822254374.2U patent/CN209467315U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109466749A (en) * | 2018-11-06 | 2019-03-15 | 珠海隆华直升机科技有限公司 | Helicopter displacement drive assembly and helicopter |
| CN111547252A (en) * | 2020-04-21 | 2020-08-18 | 中国航发湖南动力机械研究所 | Tail rotor pitch control shaft device and preparation method thereof |
| CN111547252B (en) * | 2020-04-21 | 2021-12-24 | 中国航发湖南动力机械研究所 | Tail rotor pitch control shaft device and preparation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109466749B (en) | 2023-07-04 |
| CN109466749A (en) | 2019-03-15 |
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