CN103708030A - Planar flexible beam unit - Google Patents
Planar flexible beam unit Download PDFInfo
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- CN103708030A CN103708030A CN201210517344.0A CN201210517344A CN103708030A CN 103708030 A CN103708030 A CN 103708030A CN 201210517344 A CN201210517344 A CN 201210517344A CN 103708030 A CN103708030 A CN 103708030A
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Abstract
A planar flexible beam unit (1, 40) used for the multi-blade main rotor of a helicopter is an interface between a rotor shaft (2) and the multi-blade main rotor. The planar flexible beam unit (1, 40) comprises a plurality of roughly-planar torque arms (3-7, 41-46), each of the torque arms (3-7, 41-46) has a roughly-concave arc-shaped surface (8) along its radial extension portion, and forms an integral body with its adjacent torque arm (3-7, 41-46). Each of the torque arms (3-7, 41-46) comprises two roughly-straight unidirectional fiber bundles (10-14) obtained through the agglomeration of hard synthetic resin and arranged along the roughly-concave arc-shaped surface (8) of its radial extension portion. Each of the fiber bundles penetrates into two roughly-opposite torque arms (3-7, 41-46), and has no substantial direction change.
Description
Technical field
The present invention relates to have the planar flexible beam element of feature described in claim 1.
Background technology
Lifting airscrew system is fixed helicopter blade and support to engine output shaft, and comprises that (being not limited only to this) is arranged on propeller hub on output shaft and blade is attached to one group of axle or the yoke on propeller hub.Rotor system must bear that huge centnifugal force that blade when rotation apply allows that they are waved simultaneously, pitching and lagging motion.For a plurality of different system of this task, be the modification of Basic Design, be called radial type and without bearing-type or hingeless formula.Articulated system is used the rigidity axle that is equipped with hinge and bearing so that the motion of aforesaid blade.Without bearing arrangement, comprise special composite material axle, be called as flexible beam, thus its have enough flexible can distortion so that blade under the state that there is no bearing and additional mechanism providing additional operation, move.For hingeless rotor, the function of discrete hinge is by a little less than the counter-bending ability in some region but can transmit all loads, such as the structure of shearing force, centnifugal force etc., realizes.For these hingeless rotors, defined the compensation that is equal to of flapping hinge.
For flexible beam, need a certain minimum cross-section support centrifugal blade load and the sagging load of static blade, simultaneously above-mentioned blade motion needs flexibility to dye to have sizable torsional flexibility.Flexible beam, at the tangential and wing to can not be too soft on flexible, because the significant wing particularly in low rotative speed situation is out of shape to blade, or longitudinal bending, will occur under normal operation.Thereby will be at centrifugal load intensity, strength at repeated alternation, torsional flexibility, the tangential and wing to balance between flexible.Existing design limitation is reducing flapping hinge skew, and can not realize automatically and manufacturing at present.The minimum cross-section that flexible beam needs as around structure, has the closed cuff of flexible beam in conjunction with the cuff for pitch control subsystem in, has increased aerodynamic drag.
Document US5284420A has recorded a kind of many blades rotor for the anti-spiral propeller that is coupled of helicopter afterbody, there is propeller hub main body, on it, be connected with coilable band, each band by two bundle flattened cross-sectionals, around the fiber of hub radial arrangement, form, every bundle forms at least two half-unit of different blades and reverses and crooked in the passage area that is approaching propeller hub main center, thus along propeller hub body cross-section more large scale form the tangent line of propeller hub main center circumference.The blade quantity of described many blades rotor can be odd number or even number.The central area of described many blades rotor forms has the propeller hub that volume reduces, and blade keeps strong and can be arranged in propeller hub by torsion element, thus between the work fiber of described blade holding element dispense pressure best.When forming the bundle of at least two half-unit of different blades, in the region of vicinity propeller hub main center, reverse and bending, described bundle has high torsion and crooked rotor inertia, causes correspondingly high flapping hinge skew.The manufacture of described torsion and crooked bundle is more complicated.
Document US5091029A has recorded a kind of manufacture for the method for many legs flexible beam of hingeless flexible beam lifting airscrew, wherein flexible beam is integral structure and only by composite material, is made, and comprise the full-length flaggy of high strength fibre in the same way, from the first leg, extend and divide when passing the propeller hub part of flexible beam, and extend to two relative legs on diameter haply, and cross and one-way slab interlayer are located between full-length flaggy, realize required gradient and the shape of propeller hub and the leg of flexible beam, wherein last flaggy coating is to make on the rotatable lay-up tool of dodecahedral shape.
Summary of the invention
Therefore the object of this invention is to provide planar flexible beam element as the interface between rotor shaft and many blades rotor, in particular for thering is many blades main rotor of the helicopter of low flapping hinge skew.A further object of the present invention is to provide the planar flexible beam element that is applicable to automated manufacturing.
Scheme provided by the invention has the planar flexible beam element of feature described in claim 1 usings as rotor shaft and many blades rotor, in particular for the interface between many blades main rotor of helicopter.The preferred embodiments of the present invention propose with dependent claims.
According to the present invention, planar flexible beam element is as rotor shaft and many blades rotor, especially as the interface between many blades main rotor of the helicopter with low flapping hinge skew, described planar flexible beam element is made by Composite condensation material, being preferably the torque arm having more than the plane haply of 4 forms, each torque arm has along its extension concave arc surface haply on each side radially, and the torque arm being adjacent at described torque arm root area is in aggregates, root at described torque arm has the larger width of relatively described torque arm thickness, thereby the preferred proportion of thickness/width is for being less than 1: 3, torque arm described in each comprise that two bundles are condensed by hard resin and along its radially extension along roughly straight unidirectional fibre that roughly concave arc surface is arranged, described in each, fibrous bundle penetrates two roughly relative torque arms and do not have significant direction to change, i.e. described direction variation is less than 35 °.
According to basic characteristics of invention flexible beam unit, act on a force and moment on the arm of force, such as centnifugal force, dancing in the air the shimmy moment of deflection of lead-lag is directly offset by the fibrous bundle that roughly unidirectional fibre forms by described by two relative torque arms, because main rotor shaft is transported element and is passed two roughly relative torque arms, and number of components is reduced.Flexible beam of the present invention unit allows root area to have large width, thereby causes the flapping hinge skew of each torque arm lower, and described low flapping hinge skew is equal to the low rigidity of waving in flexible beam unit inside.The torque arm rigidity reducing of the shimmy and/or pitching moment of opposing is provided along the concave arc surface in each side of extension radially.
Due to the central concentrated load of having eliminated at flexible beam unit center of the present invention, flexible beam of the present invention unit allows the design of simple and lightweight.And another advantage is, flexible beam of the present invention unit can be automatically and low cost fabrication.
According to the preferred embodiment of the present invention, the center of planar flexible beam element have circular opening using reduce rigidity and as a selection for surrounding other configuration between rotor shaft and many blades rotor, such as propeller hub and damping arrangement.。
According to another preferred embodiment of the present invention, each torque arm is general triangular shape at its root area, adjacent its contiguous torque arm place.This triangle has large width at root area, and when being transmitted by rotor shaft, is applicable to especially carry-over moment at the concave arc surface of each torque arm radial direction.
Another preferred embodiment according to the present invention, root area thickness in the direction perpendicular to general plane torque arm reduces.The root area that flexible beam of the present invention unit allows to close on rotor shaft has little thickness and large width and makes the flapping hinge skew of each torque arm lower, and described low flapping hinge skew is equal to the low rigidity of waving in flexible beam unit inside.The little thickness of torque arm makes the comfort level that aerodynamic drag is low and improve relative fitful wind susceptibility.
According to present invention further optimization embodiment, root area has at least one hole to be improved stiffness characteristics and reduces weight for further through the torque arm of general planar.The damping additional equipment that this hole is suitable for holding for rotor hub and blade motion also can hold the equipment that allows whole rotor hub to tilt.
According to a further advantageous embodiment of the invention, 5 torque arms can be set so that straight unidirectional fibre bundle intersects at root area, and change in the intrafascicular slight direction being produced by the intrafascicular arc of other decussating fibers of bearing of decussating fibers the load causing.
According to another preferred embodiment of the present invention, can arrange 4 or 6,7,8..... torque arm, so that straight unidirectional fibre bundle intersects at root area, and changes in the intrafascicular slight direction being produced by the intrafascicular arc of other decussating fibers of bearing of decussating fibers the load causing.
According to another preferred embodiment of the present invention, there is power transmitting elements for power is delivered to described many blades rotor from described rotor shaft, described power transmits the component has deflection degree around any axis vertical with rotor shaft, for further reducing the rigidity of waving between 0 to 100%.Described power transmits the component can be avoided directly fixing to rotor shaft, and clamping is reduced and the deflection degree that improves planar flexible beam element of the present invention to allow whole rotor hub to tilt.
According to a further advantageous embodiment of the invention, described power transmission unit has bar, and described bar is hinged with the circumference of first end and described rotor shaft respectively, and hinged with the second end and the excircle between two described torque arms of described many blades rotor.
According to a further advantageous embodiment of the invention, described power transmission unit has bar, described bar is hinged with the circumference of first end and described rotor shaft respectively, and with the second end with between described torque arm or the center of the planar flexible beam element of aiming at described torque arm hinged.
According to a further advantageous embodiment of the invention, described bar is arranged to that described circumference with described rotor shaft is radially or tangentially.
According to a further advantageous embodiment of the invention, the integrated connection arrangement that this center has the rotor shaft of being integrated into is usingd as power transmits the component.
According to a further advantageous embodiment of the invention, power transmission comprises the shimmy damping arrangement that centers and arrange.
Accompanying drawing explanation
The preferred embodiments of the present invention are explained with reference to following description and accompanying drawing.
Fig. 1 shows the block diagram of the rotor shaft with planar flexible beam element of the present invention,
Fig. 2 shows the birds-eye view of planar flexible beam element of the present invention,
Fig. 3 shows the birds-eye view of the planar flexible beam element preferred embodiment according to the present invention,
Fig. 4 a shows the birds-eye view that rotor shaft is connected to planar flexible beam element of the present invention,
Fig. 4 b shows the birds-eye view that another rotor shaft is connected to planar flexible beam element of the present invention,
Fig. 5 shows the block diagram of the rotor shaft with planar flexible beam element of the present invention preferred embodiment,
Fig. 6 shows the part sectional view of the rotor shaft connection that runs through Fig. 5, and
Fig. 7 illustrates the birds-eye view of another preferred embodiment of planar flexible beam element of the present invention.
The specific embodiment
According to Fig. 1, planar flexible beam element 1 is to using as centered by the rotor shaft 2 of many blades main rotor (not shown) of helicopter.Planar flexible beam element 1 comprises 5 torque arm 3-7 of concentric propeller hub (not shown) and general plane, and this torque arm Cong Gai center extends radially out and has a circular opening.These 5 torque arm 3-7 are that equal angles separates.Planar flexible beam element 1 is made by complex chemical compound.
Each torque arm 3-7 radially has roughly intrados 8 in every one side of extension at it, the torque arm 3-7 being adjacent at the root area 9 of described torque arm 3-7 is in aggregates, and there is relatively large width, thereby make the ratio of thickness/width for being less than 1:3.This thickness be restricted to and this width vertical with planar flexible beam element 1 corresponding to torque arm 3-7 the extension separately at their chord line.
As shown in Figure 2, individual features represents by the same reference numerals of Fig. 1.Described in each, torque arm 3-7 comprises roughly straight unidirectional fibre 10-14 of two bundles, by hard resin, condense and arrange diametrically along concave arc surface roughly 8, described in each, fibrous bundle 10-14 penetrates two roughly relative torque arm 3-7 and curvature is constant and do not have significant direction to change, along the whole length of any described fibrous bundle 10-14, described direction variation is less than 35 °.Fibrous bundle 10-14 is arranged to any load bearing in any fibrous bundle 10-14 through the approaching center of root area 9 separately, and this load is produced by the slight variation in any fibrous bundle 10-14 direction.
As shown in Figure 3, individual features is by Fig. 1, and identical Reference numeral represents in 2.Each torque arm 3-7 of described planar flexible beam element 1 comprises hole 15, be and extend through the roughly dihedral of root area 9 separately and adapt to roughly concave arc surface 8, thereby for torque arm 3, corresponding fibrous bundle 10,14 passes to bottom between concave arc surface 8 and from the top of triangle 15 being horizontally through in the radial direction roughly, fibrous bundle 11 enters two adjacent torque arms 4,7 along described triangle 15 bottoms through center.At two infalls 16,17 of fibrous bundle 11 and fibrous bundle 10,14, by any direction of fibrous bundle 10,11,14, changing the power causing can transmit between described fibrous bundle 10,11,14.Identical principle is for the relevant straight unidirectional fibre bundle 10-14 of other torque arm 4-7.
As shown in Fig. 4 a, corresponding feature identical Reference numeral in Fig. 1-3 represents.Planar flexible unit 1 provides power transmission 20 for power is transferred to described many blades rotor from described rotorshaft 2.This power transmission 20 is positioned at the inside of the polygonal-shaped openings of planar flexible unit 1.Interior ring 19 use bar 21-25 are fixed to rotor shaft 2 coaxially, and the part with first end as the interior ring 19 in described rotor shaft 2, is respectively fixed to the planar flexible beam center between the torque arm 3-7 described in two with the second end.Described in each, the second end of bar 21-25 is with being bolted to center.The length of the diameter of interior ring 19 and/or each bar 21-25 changes to allow bar 21-25 in internally encircling mutually 19 any position radially and between tangential.
As shown in Figure 4 b, corresponding feature identical Reference numeral in Fig. 1-4a represents.Planar flexible beam element 1 provides power transmission 20 for power is transferred to described many blades rotor from described rotorshaft 2.Interior ring 19 use bar 21-25 are fixed to rotor shaft 2 coaxially, and the first end of bar 21-25 is the part in described rotor shaft 2 as interior ring 19, and the second end is respectively fixed to the center between the root area 9 of described torque arm 3-7.The length of the diameter of interior ring 19 and/or each bar 21-25 changes and allows bar 21-25 in internally encircling mutually 19 any position radially and between tangential.
As shown in Figure 5, corresponding for feature in Fig. 1-4 identical Reference numeral represent.Planar flexible beam element 1 is provided with the coaxial rotor hub with integrated connection arrangement 18 and usings as coaxial power transmission 20, for power is transferred to described many blades rotor from described rotor shaft 2.Described integrated connection arrangement 18 is around the circular aperture distribution in planar flexible beam element 1 center, for coupling device (not shown) is installed to rotor shaft 2.
As shown in Figure 6, corresponding feature identical Reference numeral in Fig. 1-5 represents.For the power transmission 20 that power is transferred to planar flexible beam element 1 from described rotor shaft 2, provide the interior ring 19 being coaxially fixed to rotor shaft 2.Interior ring 19 comprises that upper flange 26 and lower flange 27 are to be mounted to any bar 21-25 on interior ring 19.Any bar 21-25 is comprised of two upper bend plates 28 and two lower knuckle plates 29, and all described snyed plates 28,29 are roughly parallel to each other.Any bar 21-25 is fixed to upper flange 26 and lower flange 27 with each inner bolt 30,31, hinged at described rotor shaft 2 places and first end internally to encircle mutually respectively 19.The root area 9 of planar flexible beam element 1 is arranged as between two upper bend plates 28 and two lower knuckle plates 29 parallel.Outer bolt 32 is connected two upper bend plates 28 with fixing respectively with two lower knuckle plates 29, the vertical center through the planar flexible beam element 1 between two described torque arm 3-7.Any bar 21-25 allows the amount of deflection of pointing to described excircle from interior ring 19 to increase.
As Fig. 7, for feature, in Fig. 1-6, identical Reference numeral represents accordingly.Planar flexible beam element 40 comprises 6 torque arm 41-46, each torque arm comprises hole 15, hole 15 is the general triangular of adjacent each root area 9 and adapts to roughly concave arc surface 8, thereby for torque arm 44, each fibrous bundle 10,14 is horizontally through and passes to bottom from triangle 15 tops between the roughly concave arc surface 8 in radial direction, and fibrous bundle 13 enters the torque arm 43,45 of two adjacency along described triangular base through center.At two infalls 16,17 of fibrous bundle 13 and fibrous bundle 10,14, by any direction of fibrous bundle 10,13,14, changing the power causing can transmit between described fibrous bundle 10,13,14.Identical principle is for the relevant straight unidirectional fibre bundle 10-14 of other torque arm 41,42 and 46.
Reference numerals list
Planar flexible beam element Isosorbide-5-Nitrae 0
Planar torque arm 3-7,41-46
Straight unidirectional fibre bundle 10-14
Hole 15
Intersect 16,17
Bar 21-25
Claims (9)
1. the planar flexible beam element (1 of the main rotor of the many blades for helicopter, 40), as the interface between rotor shaft (2) and many blades rotor, torque arm (the 3-7 that comprises 4 or more general plane, 41-46), torque arm (3-7 described in each, 41-46) have along its radially concave arc surface of extension (8) the torque arm (3-7 that is adjacent, 41-46) in aggregates, torque arm (3-7 described in each, 41-46) comprise that two bundles are condensed by hard resin and roughly its radially extension along roughly straight unidirectional fibre bundle (10-14) that roughly concave arc surface (8) is arranged, described in each fibrous bundle with roughly fixedly curvature generally about a described torque arm (3-7, corresponding longitudinal axis 41-46) is symmetrically from described respective torque arm (3-7, 41-46) stretch into two roughly relative described torque arm (3-7, 41-46), it is characterized in that, comprise that power transmits the component (20) is for transferring to described many blades rotor by power from described rotor shaft (2), described power transmits the component (20) is deflection around axis any and that described rotor shaft (2) is vertical, and described power transmits the component (20) has bar (21-25), described bar (21-25) is respectively with first end and hinged in the interior ring (19) of described rotor shaft (2), with the second end and two described torque arm (3-7 in described many blades rotor, excircle 41-46) hinged or with the second end be positioned at described torque arm (3-7, 41-46) or with described torque arm (3-7, the center of 41-46) aiming at is hinged.
2. planar flexible beam element according to claim 1 (Isosorbide-5-Nitrae 0), is characterized in that, its center has the opening of circular.
3. planar flexible beam element according to claim 1 (Isosorbide-5-Nitrae 0), is characterized in that, each torque arm (3-7,41-46) is general triangular at its root area in abutting connection with torque arm (3-7,41-46) (9).
4. planar flexible beam element according to claim 3 (Isosorbide-5-Nitrae 0), is characterized in that, on perpendicular to described general plane torque arm (3-7,41-46) direction, described root area (9) has thickness/width ratio and is less than 1: 3.
5. planar flexible beam element according to claim 3 (Isosorbide-5-Nitrae 0), is characterized in that, described root area (9) has at least one hole (15) through described general plane torque arm (3-7,41-46).
6. planar flexible beam element according to claim 3 (Isosorbide-5-Nitrae 0), is characterized in that, adjacent described general plane torque arm (3-7,41-46), and described root area (9) comprises shear rigidity or accurate isotropic laminar texture.
7. planar flexible beam element according to claim 1 (Isosorbide-5-Nitrae 0), is characterized in that having 5 or 6 torque arms (3-7,41-46).
8. planar flexible beam element according to claim 2 (Isosorbide-5-Nitrae 0), is characterized in that, its center has the integrated connection arrangement (18) that is integrated into described rotor shaft (2).
9. planar flexible beam element according to claim 1 (Isosorbide-5-Nitrae 0), is characterized in that, described bar (21-25) radially or is tangentially arranged into respectively on the described ring (19) that is positioned at described rotor shaft (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210517344.0A CN103708030A (en) | 2012-10-08 | 2012-10-08 | Planar flexible beam unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210517344.0A CN103708030A (en) | 2012-10-08 | 2012-10-08 | Planar flexible beam unit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103708030A true CN103708030A (en) | 2014-04-09 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210517344.0A Pending CN103708030A (en) | 2012-10-08 | 2012-10-08 | Planar flexible beam unit |
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| Country | Link |
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| CN (1) | CN103708030A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173092A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Helicopter rotor vibration adjusting system |
| CN112550669A (en) * | 2020-12-11 | 2021-03-26 | 中国直升机设计研究所 | Seesaw formula does not have bearing tail propeller hub and helicopter tail-rotor |
| CN113955095A (en) * | 2021-10-09 | 2022-01-21 | 中国直升机设计研究所 | Multi-base-body composite flexible beam for bearingless rotor wing |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4676720A (en) * | 1984-07-10 | 1987-06-30 | Kawasaki Jukogyo Kabushiki Kaisha | Bearingless hub structure for rotary-wing aircrafts |
| US5091029A (en) * | 1991-01-15 | 1992-02-25 | United Technologies Corporation | Method of manufacturing a unitary, multi-legged helicopter rotor flexbeam made solely of composite materials |
| US5284420A (en) * | 1991-10-16 | 1994-02-08 | Aerospatiale Nationale Insustrielle | Plastics multi-blade variable-pitch rotor |
| CN1774366A (en) * | 2003-04-08 | 2006-05-17 | 欧洲直升机德国有限责任公司 | Rotor and gyrocopter with said rotor |
| US20060216150A1 (en) * | 2003-04-08 | 2006-09-28 | Eurocopter Deutschland Gmbh | Hinged rotor provided with plate-shaped rotor head element and a rotorcraft provided with said rotor |
| KR20130117687A (en) * | 2012-04-18 | 2013-10-28 | 유로캅터 도이칠란트 게엠베하 | Aerodynamic blade attachment for a bearingless rotor of a helicopter |
-
2012
- 2012-10-08 CN CN201210517344.0A patent/CN103708030A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4676720A (en) * | 1984-07-10 | 1987-06-30 | Kawasaki Jukogyo Kabushiki Kaisha | Bearingless hub structure for rotary-wing aircrafts |
| US5091029A (en) * | 1991-01-15 | 1992-02-25 | United Technologies Corporation | Method of manufacturing a unitary, multi-legged helicopter rotor flexbeam made solely of composite materials |
| US5284420A (en) * | 1991-10-16 | 1994-02-08 | Aerospatiale Nationale Insustrielle | Plastics multi-blade variable-pitch rotor |
| CN1774366A (en) * | 2003-04-08 | 2006-05-17 | 欧洲直升机德国有限责任公司 | Rotor and gyrocopter with said rotor |
| US20060216150A1 (en) * | 2003-04-08 | 2006-09-28 | Eurocopter Deutschland Gmbh | Hinged rotor provided with plate-shaped rotor head element and a rotorcraft provided with said rotor |
| KR20130117687A (en) * | 2012-04-18 | 2013-10-28 | 유로캅터 도이칠란트 게엠베하 | Aerodynamic blade attachment for a bearingless rotor of a helicopter |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173092A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Helicopter rotor vibration adjusting system |
| CN112173092B (en) * | 2020-09-25 | 2023-06-06 | 中国直升机设计研究所 | Helicopter rotor vibration adjusting system |
| CN112550669A (en) * | 2020-12-11 | 2021-03-26 | 中国直升机设计研究所 | Seesaw formula does not have bearing tail propeller hub and helicopter tail-rotor |
| CN112550669B (en) * | 2020-12-11 | 2023-06-27 | 中国直升机设计研究所 | Teeterboard type bearingless tail rotor hub and helicopter tail rotor |
| CN113955095A (en) * | 2021-10-09 | 2022-01-21 | 中国直升机设计研究所 | Multi-base-body composite flexible beam for bearingless rotor wing |
| CN113955095B (en) * | 2021-10-09 | 2023-09-05 | 中国直升机设计研究所 | Multi-matrix composite flexible beam for bearingless rotor wing |
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| C53 | Correction of patent of invention or patent application | ||
| CB02 | Change of applicant information |
Address after: Germany Danube Voight Applicant after: Air Passenger helicopter Germany Co., Ltd Address before: Germany Danube Voight Applicant before: Eurocopter Deutschland |
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Free format text: CORRECT: APPLICANT; FROM: EUROCOPTER DEUTSCHLAND TO: KONGKE HELICOPTER GERMANY GMBH |
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Application publication date: 20140409 |