CN109436299A - Helicopter tail rotor star pitch-changing mechanism and helicopter - Google Patents
Helicopter tail rotor star pitch-changing mechanism and helicopter Download PDFInfo
- Publication number
- CN109436299A CN109436299A CN201811639432.1A CN201811639432A CN109436299A CN 109436299 A CN109436299 A CN 109436299A CN 201811639432 A CN201811639432 A CN 201811639432A CN 109436299 A CN109436299 A CN 109436299A
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- helicopter
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- 230000007246 mechanism Effects 0.000 title claims abstract description 69
- 238000006073 displacement reaction Methods 0.000 claims abstract description 66
- 238000004519 manufacturing process Methods 0.000 claims abstract description 12
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 12
- 238000009434 installation Methods 0.000 claims description 6
- 229910052742 iron Inorganic materials 0.000 claims description 6
- 229910000990 Ni alloy Inorganic materials 0.000 claims description 5
- 230000005540 biological transmission Effects 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
- 230000005611 electricity Effects 0.000 claims description 3
- 230000033001 locomotion Effects 0.000 description 11
- 238000010586 diagram Methods 0.000 description 8
- 238000000034 method Methods 0.000 description 8
- 238000013461 design Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 5
- 230000008859 change Effects 0.000 description 3
- 238000007789 sealing Methods 0.000 description 3
- 238000010008 shearing Methods 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 239000011148 porous material Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005323 electroforming Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of helicopter tail rotor star pitch-changing mechanism and helicopters, displacement component including driving tail-rotor blade displacement, displacement component includes star displacement connecting rod, the the first oscillating bearing mechanism for being arranged and moving with star displacement connecting rod in vertical direction is connect with star displacement connecting rod, setting is connect with the first oscillating bearing mechanism as the first oscillating bearing mechanism rotates and then adjusts blade displacement and is installed on the folder of the paddle on shell, unmanned helicopter manufacture difficulty in traditional handicraft can be overcome big, it is bulky, blade displacement is difficult, it is low to control precision, complicated integral structure, service life is short, the high problem of manufacturing cost.
Description
Technical field
The present invention relates to helicopter fields, and in particular to a kind of helicopter tail rotor star pitch-changing mechanism 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.
Summary of the invention
In view of this, providing helicopter tail rotor star displacement machine the purpose of the present invention is overcoming defect in the prior art
Structure can overcome unmanned helicopter manufacture difficulty in traditional handicraft big, bulky, and blade displacement is difficult, and control precision is low, whole
Structure is complicated for body, and service life is short, the high problem of manufacturing cost.
A kind of helicopter tail rotor star pitch-changing mechanism, the displacement component including driving tail-rotor blade displacement, displacement component packet
Star displacement connecting rod is included, setting is connect with star displacement connecting rod and as star displacement connecting rod is in the first pass that vertical direction moves
Bearings mechanism connect setting with the first oscillating bearing mechanism as the first oscillating bearing mechanism rotates and then adjusts blade displacement
And it is installed on the folder of the paddle on shell；Tail-rotor mechanism assembly in the technical program pushes pitch-changing mechanism perpendicular by displacement push rod
Histogram drives blade to deflect in vertical direction to (i.e. along the axial direction of push rod) movement, to realize that blade becomes
Away from by the shell being fixedly installed with tail-rotor power mechanism, circumferential (the axially vertical direction with push rod) occurs for drive blade
Movement.
Further, the shell includes that the inner sleeve of coaxial arrangement combines the double-sleeve structure to be formed, blade with outer sleeve
It is fixedly connected with one end of paddle folder, the paddle folder is installed on outer sleeve barrel by self-lubricating bushing, and the paddle presss from both sides the other end
It is provided with the journal structure for being mounted on inner sleeve barrel, is provided on the paddle folder axle journal and presss from both sides integrally formed company with paddle
Block is connect, the star displacement link mechanism is hexagram, and six angles end bends downward the connection to be formed with paddle folder transmission connection
Peace that portion, the first oscillating bearing mechanism and the interconnecting piece are rotatablely connected and the first oscillating bearing mechanism and link block are rotatably assorted
Dress；Using the tactic pattern of six connecting rod connection blades, keep mechanism operation more steady, compared with traditional double blades mechanism, originally
Mechanism in technical solution is more uniformly stressed, and the length of link block is determined by the angular range that blade rotates, makes connecting rod machine
Arrangement between structure is more reasonable, and structure is more compact, effectively reduces the noise generated in tail-rotor mechanism kinematic
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, it is provided on the interconnecting piece and is moved for the first oscillating bearing mechanism in vertical direction
And drive the elliptical aperture of paddle folder rotation；First oscillating bearing is real by driving paddle folder to rotate with the elliptical aperture cooperation on interconnecting piece
Existing blade displacement, elliptical aperture long axis is vertical with vertical direction, the design of oval pore structure, guarantees motion structure in moving process
It will not be stuck, while the function that driving blade rotates along the vertical direction can be directly realized by again, structure is simple, handling ease, together
When overcome the cumbersome problem of distance changing mechanism in traditional handicraft.
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 are connected on shell by shearing bolt, and second joint bearing 8 is paddle folder
The rotation of blade provides supporting point, guarantees the stability in rotation process.
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 star pitch-changing mechanism on helicopter body.
The beneficial effects of the present invention are: a kind of helicopter tail rotor star pitch-changing mechanism disclosed by the invention, can overcome biography
Unmanned helicopter manufacture difficulty is big in technique of uniting, bulky, and blade displacement is difficult, and control precision is low, and complicated integral structure makes
It is short with the service life, the high problem of manufacturing cost.
Detailed description of the invention
The invention will be further described with reference to the accompanying drawings and examples:
Fig. 1 is the structural diagram of the present invention；
Fig. 2 is cross-sectional view of the invention；
Fig. 3 is the first oscillating bearing attachment structure schematic diagram in the present invention；
Fig. 4 is midship section structure schematic diagram of the present invention；
Fig. 5 is interconnecting piece structural schematic diagram in the present invention.
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 diagram of the present invention, and Fig. 2 is cross-sectional view of the invention, and Fig. 3 is the first oscillating bearing in the present invention
Attachment structure schematic diagram, Fig. 4 are midship section structure schematic diagram of the present invention, and Fig. 5 is interconnecting piece structural schematic diagram in the present invention, are such as schemed
Shown, of the invention helicopter tail rotor star pitch-changing mechanism, including connect with straight line steering engine mechanism for driving tail-rotor blade 9 to become
Away from pitch-changing mechanism and drive pitch-changing mechanism rotation tail-rotor power mechanism, the pitch-changing mechanism includes for installing blade 9
Shell 3, be set in shell 3 for adjusting the link mechanism of 9 displacement of blade, being connected to link mechanism and straight line steering engine mechanism
Between displacement push rod 21, the shell 3 by around displacement push rod 21 rotate in a manner of with tail-rotor power mechanism be sequentially connected.This skill
Tail-rotor mechanism assembly in art scheme pushes pitch-changing mechanism in vertical direction (i.e. along the axis of push rod 21 by displacement push rod 21
To direction) movement, and then drive blade 9 deflect in vertical direction, to realize 9 displacement of blade, by with tail-rotor engine
The shell 3 of structure fixed setting drives blade 9 that circumferential (the axially vertical direction with push rod 21) movement occurs, passes through this technology
Unmanned helicopter tail-rotor star pitch-changing mechanism in scheme, can overcome unmanned helicopter manufacture difficulty in traditional handicraft big, body
Product is huge, and blade displacement is difficult, and control precision is low, and complicated integral structure, service life 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, the displacement pusher structure is the pusher structure of ladder shaft type, displacement push rod one end and offer change
Away from power straight line steering engine mechanism connection and displacement push rod 21 sequentially pass through from bottom to top along the vertical direction back gauge tail-rotor bracket 18,
Tail-rotor power mechanism, shell 3.Top cover 16 and 3 sealed set of shell reduce intermediate conversion links using straight line steering engine 19, improve
Whole Response speed runs through integrally-built Installation Modes using displacement push rod, keeps each mounting structure more compact, saves peace
Space is filled, while using sealing ring or other sealing means between displacement push rod and each connecting portion, keeps tail-rotor in-house
In good sealing state, the service life of the mechanism is improved.
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 the above examples are only used to illustrate the technical scheme of the present invention and are not limiting, although referring to compared with
Good embodiment describes the invention in detail, those skilled in the art should understand that, it can be to skill of the invention
Art scheme is modified or replaced equivalently, and without departing from the objective and range of technical solution of the present invention, should all be covered at this
In the scope of the claims of invention.
Claims (6)
1. a kind of helicopter tail rotor star pitch-changing mechanism, it is characterised in that: the displacement component including driving tail-rotor blade displacement becomes
Include star displacement connecting rod away from component, connect with star displacement connecting rod setting and as star displacement connecting rod is moved in vertical direction
The first oscillating bearing mechanism, connect with the first oscillating bearing mechanism setting as the first oscillating bearing mechanism rotates and then adjusts
Blade displacement is simultaneously installed on the folder of the paddle on shell.
2. helicopter tail rotor star pitch-changing mechanism according to claim 1, it is characterised in that: the shell includes coaxially to set
The inner sleeve set 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, and the paddle folder passes through
Self-lubricating bushing is installed on outer sleeve barrel, and the paddle folder other end is provided with the axle journal for being mounted on inner sleeve barrel
Structure, the paddle, which presss from both sides to be provided on axle journal, presss from both sides integrally formed link block with paddle, and the star displacement link mechanism is Magen David
Shape, six angles end bend downward the interconnecting piece to be formed with paddle folder transmission connection, and the first oscillating bearing mechanism and the interconnecting piece turn
Dynamic connection and the first oscillating bearing mechanism and link block are rotatably assorted installation.
3. helicopter tail rotor star pitch-changing mechanism according to claim 2, 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, the connection
It is provided in portion and is moved for the first oscillating bearing mechanism in vertical direction and drive the elliptical aperture of paddle folder rotation.
4. helicopter tail rotor star pitch-changing mechanism according to claim 2, 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.
5. helicopter tail rotor star pitch-changing mechanism 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.
6. a kind of helicopter, it is characterised in that: be equipped with according to any one of claims 1 to 5 go straight up on helicopter body
Tail paddle star pitch-changing mechanism.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811315545 | 2018-11-06 | ||
| CN2018113155456 | 2018-11-06 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109436299A true CN109436299A (en) | 2019-03-08 |
| CN109436299B CN109436299B (en) | 2023-11-07 |
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Family Applications (2)
| 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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| CN (2) | CN109436299B (en) |
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 (7)
| 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 |
| US20180244368A1 (en) * | 2017-02-27 | 2018-08-30 | Airbus Helicopters Deutschland GmbH | Pitch control device for a ducted tail rotor of a rotorcraft |
| 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 |
-
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 (7)
| 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 |
| US20180244368A1 (en) * | 2017-02-27 | 2018-08-30 | Airbus Helicopters Deutschland GmbH | Pitch control device for a ducted tail rotor of a rotorcraft |
| 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 |
| CN109436299B (en) | 2023-11-07 |
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