WO2008081098A1 - Avion a empennages arrieres annulaires - Google Patents
Avion a empennages arrieres annulaires Download PDFInfo
- Publication number
- WO2008081098A1 WO2008081098A1 PCT/FR2007/001959 FR2007001959W WO2008081098A1 WO 2008081098 A1 WO2008081098 A1 WO 2008081098A1 FR 2007001959 W FR2007001959 W FR 2007001959W WO 2008081098 A1 WO2008081098 A1 WO 2008081098A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- aircraft
- fuselage
- aerodynamic
- vertical
- empennages
- Prior art date
Links
- 238000012423 maintenance Methods 0.000 claims description 15
- 239000003381 stabilizer Substances 0.000 claims description 13
- 238000010790 dilution Methods 0.000 description 2
- 239000012895 dilution Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 1
- DMYHGDXADUDKCQ-UHFFFAOYSA-N fenazaquin Chemical compound C1=CC(C(C)(C)C)=CC=C1CCOC1=NC=NC2=CC=CC=C12 DMYHGDXADUDKCQ-UHFFFAOYSA-N 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 210000001835 viscera Anatomy 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/16—Aircraft characterised by the type or position of power plants of jet type
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/10—All-wing aircraft
- B64C2039/105—All-wing aircraft of blended wing body type
-
- 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
Definitions
- the present invention belongs to the field of aircraft comprising a rear propulsion and rear tail.
- the invention proposes an architecture comprising a set of aircraft tail fins forming an annular structure closed on itself, associated with one or more propulsion engines also located in the rear part of the aircraft.
- the rear stabilizers most often comprise a so-called basic form of the surfaces.
- This basic form of basic empennage is widely used on many civil transport aircraft such as Airbus A320 aircraft.
- the horizontal tail is fixed to the vertical empennage either at the top of the latter, form of T-shaped empennages, for example on the airplane Bael46, or in an intermediate position in height, form of so-called tail cross, for example on the aircraft Aerospatiale SE210 Caravelle.
- the vertical tail comprises two vertical aerodynamic surfaces attached to the ends of the empennage horizontal, form of empennage called in H, as for example on the plane Nord2500 Noratlas.
- rear stabilizers consists of two surfaces inclined between the vertical and the horizontal forming a V and whose combination ensures both the functions of the vertical and horizontal aerodynamic surfaces. This type of empennage said butterfly is used in particular on the plane
- the choice of a form of empennage for an aircraft generally depends on aerodynamic considerations, structural considerations and is influenced by the position and type of propulsion engines that generate constraints also of aerodynamic and structural order but also safety dependency to the extent that failures of an engine such as a burst turbine must not cause such consequences on empennages that the aircraft can no longer be controlled.
- the tail shapes different from the basic shape and for which the aerodynamic surfaces of the empennages are not individually attached to the fuselage correspond to airplane architectures with tail tail, but the known forms, T , in cross, in H or in V remain very close in their design of the basic form without overall aerodynamic and structural optimization of all empennages with the engines of propulsion.
- the present invention proposes a rear tailplane architecture of an aircraft compatible with the installation of turbojets, in particular modern generation turbojet engines with a high dilution ratio, or propellers with untarred propellers at the rear of an aircraft. and which optimizes empennages by a combination of the aerodynamic surfaces of said empennages forming a closed surface called single or double annular surface.
- a set of rear stabilizers according to the invention is suitable for an aircraft, comprising a fuselage, a wing and at least one propulsion motor attached. in a rear part of the fuselage, that is to say a part of the fuselage located behind the wing along a longitudinal axis X of the aircraft.
- the set of empennages comprises aerodynamic surfaces fixed in the rear part of the fuselage, and consists essentially of substantially horizontal aerodynamic surfaces and substantially vertical aerodynamic surfaces arranged to form an annular structure comprising at least one ring fixed to the fuselage in which ring is maintained at least one rear engine.
- the structure of the tail tail assembly comprises:
- the lower, vertical and upper aerody ⁇ amic surfaces attached to the fuselage by the aerodynamic surfaces form a ring.
- the lower, upper and vertical aerodynamic surfaces are provided with mobile elements forming aerodynamic control surfaces which make it possible to control the aircraft.
- the aerodynamic surfaces of the set of empennages are fixed together by connecting elements and assembly curves.
- a center fin is attached to the fuselage in its lower portion and attached to the upper aerodynamic surface in an upper portion of said central fin so that the tail assembly determines a two-ring structure of resistance and stability. reinforced rigidity.
- each structure of a ring advantageously comprises:
- the invention also relates to an aircraft comprising such a set of rear stabilizers without central drift and a propulsion motor attached to the upper aerodynamic surface and under said upper aerodynamic surface by a support mast.
- a substantially vertical maintenance well crosses the fuselage usefully, size and location maintenance wells such that the engine can be lowered and mounted substantially vertically through the well from or to its position fixed to the upper aerodynamic surface.
- Hatches ensure the closure of the lower and upper openings of the well, in normal operation of the aircraft, to ensure the continuity of the aerodynamic forms of the fuselage.
- the invention also relates to an aircraft comprising such a set of rear stabilizers and propulsion engines arranged substantially in the ring or rings formed by empennages, the engines being each fixed to the fuselage by a support mast.
- the invention also relates to an aircraft comprising such a set of rear stabilizers with a central fin and propulsion engines arranged substantially in the rings formed by the rear tail assembly, the engines being each fixed to the central fin by a support mast.
- FIG. 1 illustration of a twin-engine aircraft attached to the rear having a tail according to one embodiment
- FIG. 2a detail of the rear area of the aircraft of Figure 1 empennages in the functional position
- FIG. 3 illustration of a rear jet aircraft having a tail according to one embodiment
- FIG. 4 illustration of a tri-jet aircraft with a rear engine and having empennages according to another embodiment.
- FIG. 1 shows an aircraft comprising an exemplary architecture of a set of rear stabilizers 1 according to the invention.
- the aircraft comprises a reference trihedron defined by the longitudinal axis X, a vertical axis Z oriented positively downwardly of the aircraft when the aircraft is in a horizontal position and by a Y axis perpendicular to the X and Z axes and positive to the right of the aircraft in the direction of flight.
- the X and Z axes determine a vertical plane of symmetry of the aircraft and the X and Y axes determine a horizontal reference plane of the aircraft.
- the set of empennages comprises first lower aerodynamic surfaces 41a, 41b that are substantially horizontal and fixed to the fuselage 3 by roots of said lower aerodynamic surfaces. .
- the said lower aerodynamic surfaces are arranged substantially symmetrically with respect to the vertical plane XZ of symmetry of the aircraft and form a lower horizontal stabilizer.
- the lower aerodynamic surfaces 41a, 41b are not necessarily strictly parallel to the horizontal reference plane XY and form, if appropriate, a dihedral as is most often practiced for reasons of behavior. aerodynamics in general.
- Second substantially vertical aerodynamic surfaces 42a, 42b said vertical aerodynamic surfaces, two in number, are arranged at opposite ends to the roots of the lower aerodynamic surfaces 41a, 41b so that said two vertical surfaces extend over the lower aerodynamic surfaces, ie towards the Z negative.
- a third aerodynamic surface, said upper, 43, substantially horizontal is also arranged above the lower aerodynamic surfaces and maintained by the wingspan ends of said upper aerodynamic surface attached to upper ends of the vertical surfaces 42a, 42b.
- the lower aerodynamic surfaces 41a, 41b, the vertical aerodynamic surfaces 42a, 42b and the upper aerodynamic surface 43 form an annular structure, defining an aerodynamic channel, fixed to the fuselage 3 at the roots.
- lower aerodynamic surfaces, the fuselage effecting the closure of the annular structure.
- the aerodynamic surfaces 41a, 41b, 42a, 42b, 43 are substantially planar airfoil type bearing surfaces and are interconnected by curved aerodynamic shapes 412a, 412b, 423a, 423b providing a progressive aerodynamic and structural connection .
- all or part of the aerodynamic surfaces of the set of empennages (1) are provided in trailing edge areas of said aerodynamic surfaces of aerodynamic control surfaces, that is to say moving elements used for the control of the plane.
- the vertical aerodynamic surfaces 42a, 42b are advantageously provided with control surfaces, called yaw control, substantially vertical 421a, 421b for the control of the aircraft around the vertical axis Z and the lower aerodynamic surfaces 41a, 41b and or higher 43 are provided with control surfaces, called pitch control, substantially horizontal 431a, 431b for the control of the aircraft around the Y axis.
- the elevators are only present on the lower aerodynamic surfaces or, as in the examples illustrated in the figures, only on the upper aerodynamic surface.
- a fourth vertical aerodynamic surface 44 is arranged substantially in the vertical plane of symmetry XZ of the aircraft, fixed at one of its ends, said root, to the fuselage 3 and at its other end, said upper end, to the upper aerodynamic surface 43.
- the annular tail unit comprises a double-ring structure defining two aerodynamic channels separated by said central fin.
- the central fin 44 makes it possible to increase the structural strength and the rigidity of the set of empennages 1 and comprises, where appropriate, one or more rudders.
- one or motors 5, 5a, 5b are arranged in the aerodynamic channel or the aerodynamic channels of the annular tail unit.
- the engines are for example reactors, such as modern reactors with high dilution ratio, or non-ducted propeller engines such as turbine engines whose propellers are designed for the propulsion of fast subsonic aircraft.
- the central fin 44 when it is used, is advantageously reinforced to provide protection for one engine against debris thrown by the other engine in the case of a burst.
- Each engine is maintained by a carrier structure 51a, 51b, 52a, 52b, 53 such as a hanging mat which is fixed to the fuselage 3 (as illustrated in FIG. 1) or to an aerodynamic surface of the annular stabilizer, in particular at the upper aerodynamic surface 43 (as illustrated in FIG. 4) or the central drift 44 (as illustrated in FIG. 3).
- a carrier structure 51a, 51b, 52a, 52b, 53 such as a hanging mat which is fixed to the fuselage 3 (as illustrated in FIG. 1) or to an aerodynamic surface of the annular stabilizer, in particular at the upper aerodynamic surface 43 (as illustrated in FIG. 4) or the central drift 44 (as illustrated in FIG. 3).
- the engines 5, 5a, 5b are placed in the direction of the longitudinal axis X so that the noise radiated by said engines, noise radiated by unpaved propellers and or air inlets and or nozzles of said propulsion engines, are masked, at least in part, by the different empennage surfaces.
- the engine attachment mats 5a, 5b are attached to the fuselage 3 or to the central drift 44.
- the set of empennages 1 determines two rings, a first ring being formed by a lower aerodynamic surface 41a, a vertical aerodynamic surface 42a, a portion 43a of the upper aerodynamic surface 43 located on the side of the lower aerodynamic surface considered relative to the plane of vertical symmetry XZ of the aircraft and the central centreboard 44, and a second ring formed by the other lower aerodynamic surface 41b, the other vertical aerodynamic surface 42b, a portion 43b of the upper aerodynamic surface located from the side of the lower aerodynamic surface considered with respect to the vertical plane of symmetry XZ of the aircraft and the central drift 44.
- Each ring for maintenance purposes, in particular for operations of maintenance, mounting or removal of motors, can be opened and for that it comprises as illustrated in FIG. 2b for one of the two rings:
- the hinge area 432 is arranged to allow upward rotation of an articulated subassembly of the set of empennages 1 about an axis substantially parallel to the longitudinal axis X of the aircraft.
- the opening zone 411 is located near the fuselage 3 or at the boundary between the fuselage 3 and the lower aerodynamic surface 41a. In the "unlocked" condition, which corresponds to a period of aircraft maintenance operations, the opening zone 411 releases the articulated subassembly of the ring which can be tilted upwardly of the aircraft around the aircraft. the hinge area 432.
- the articulation zone 432 is arranged near the upper end of the central fin 44, which makes it possible to produce the articulated part of the ring by means of a single structural assembly capable of presenting a significant rigidity.
- the engine 5 is hooked in axial position under the upper aerodynamic surface. In this case it is not used of central drift.
- a maintenance shaft is arranged in the fuselage vertically to the engine.
- the maintenance well is closed off by traps under normal operating conditions of the aircraft, and its dimensions are such that the engine can be lowered or mounted substantially. vertically through the fuselage when the well hatches are open.
- the proposed invention makes it possible to produce a set of empennages for an aircraft comprising one or more engines located in the rear part of the airplane which has continuous shapes on the aerodynamic and structural planes and which ensures a favorable engine integration on the aerodynamic and acoustic plans without penalizing the necessary maintenance operations on the engines.
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Tires In General (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Toys (AREA)
Abstract
Description
Claims
Priority Applications (8)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP07870354A EP2089273B1 (fr) | 2006-11-30 | 2007-11-29 | Avion a empennages arrieres annulaires |
US12/516,594 US8573530B2 (en) | 2006-11-30 | 2007-11-29 | Aircraft with rear annular tail |
CA2670649A CA2670649C (fr) | 2006-11-30 | 2007-11-29 | Avion a empennages arrieres annulaires |
BRPI0719551-6A BRPI0719551A2 (pt) | 2006-11-30 | 2007-11-29 | Avião com empenagens traseiras anulares |
RU2009124912/11A RU2471673C2 (ru) | 2006-11-30 | 2007-11-29 | Самолет с кольцевым хвостовым оперением |
AT07870354T ATE512049T1 (de) | 2006-11-30 | 2007-11-29 | Flugzeug mit ringförmigem heck |
JP2009538745A JP5237958B2 (ja) | 2006-11-30 | 2007-11-29 | アニュラー型尾翼式航空機 |
CN2007800501291A CN101646600B (zh) | 2006-11-30 | 2007-11-29 | 带有环形后尾翼的飞机 |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0655199A FR2909359B1 (fr) | 2006-11-30 | 2006-11-30 | Avion a reacteurs disposes a l'arriere |
FR0655199 | 2006-11-30 |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2008081098A1 true WO2008081098A1 (fr) | 2008-07-10 |
WO2008081098A8 WO2008081098A8 (fr) | 2009-10-08 |
Family
ID=38042772
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2007/001959 WO2008081098A1 (fr) | 2006-11-30 | 2007-11-29 | Avion a empennages arrieres annulaires |
Country Status (10)
Country | Link |
---|---|
US (2) | US8128023B2 (fr) |
EP (1) | EP2089273B1 (fr) |
JP (1) | JP5237958B2 (fr) |
CN (1) | CN101646600B (fr) |
AT (1) | ATE512049T1 (fr) |
BR (1) | BRPI0719551A2 (fr) |
CA (1) | CA2670649C (fr) |
FR (1) | FR2909359B1 (fr) |
RU (1) | RU2471673C2 (fr) |
WO (1) | WO2008081098A1 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2011023396A2 (fr) | 2009-08-28 | 2011-03-03 | Benjamin Parzy | Aéronef ayant au moins deux groupes de propulsion électriques montés au niveau d'un empennage de celui-ci |
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FR2909359B1 (fr) * | 2006-11-30 | 2009-09-25 | Airbus France Sas | Avion a reacteurs disposes a l'arriere |
FR2929591B1 (fr) * | 2008-04-02 | 2010-12-24 | Airbus France | Avion a controle en tangage et en lacet par un ensemble propulsif. |
US9302766B2 (en) | 2008-06-20 | 2016-04-05 | Aviation Partners, Inc. | Split blended winglet |
CA2728765C (fr) | 2008-06-20 | 2017-06-13 | Aviation Partners, Inc. | Pointe d'aile incurvee |
US8720815B2 (en) * | 2010-04-27 | 2014-05-13 | Rolls-Royce Corporation | Aircraft propulsion system |
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WO2012107650A1 (fr) * | 2011-02-11 | 2012-08-16 | Airbus Operations (S.A.S) | Avion à système propulsif arrière |
ES2856270T3 (es) | 2011-06-09 | 2021-09-27 | Aviation Partners Inc | El winglet integrado doble |
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US9845159B2 (en) * | 2013-03-07 | 2017-12-19 | United Technologies Corporation | Conjoined reverse core flow engine arrangement |
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EP2878536B1 (fr) * | 2013-11-29 | 2017-05-24 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Stabilisateur de pas avancé |
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CN104229143A (zh) * | 2014-09-29 | 2014-12-24 | 张天昊 | 一种推进器 |
FR3032179B1 (fr) * | 2015-01-30 | 2018-04-06 | Moncef Kaabi | Gouvernes et moteur de secours pour avion |
CN108190006B (zh) * | 2015-08-14 | 2023-07-07 | 上海高博航空制造有限公司 | 喷气式襟翼增升连接翼系统及其飞行器 |
US9815560B2 (en) | 2015-09-21 | 2017-11-14 | General Electric Company | AFT engine nacelle shape for an aircraft |
US10442541B2 (en) | 2015-10-26 | 2019-10-15 | General Electric Company | Method and system for cross engine debris avoidance |
FR3043984B1 (fr) * | 2015-11-25 | 2017-12-22 | Snecma | Avion propulse par une turbomachine muni d'un ecran acoustique |
EP3187420B1 (fr) * | 2015-12-31 | 2018-05-23 | Airbus Operations S.L. | Aéronef avec moteurs montés à l'arrière |
EP3269635A1 (fr) * | 2016-07-12 | 2018-01-17 | The Aircraft Performance Company UG | Aile d'avion |
EP3321186A1 (fr) * | 2016-11-14 | 2018-05-16 | Airbus Operations GmbH | Avion |
FR3061143B1 (fr) * | 2016-12-23 | 2022-07-01 | Xsun | Drone volant solaire comprenant deux ailes portantes en tandem sur lesquelles sont couplees des cellules photovoltaiques |
FR3068002B1 (fr) * | 2017-06-23 | 2019-07-19 | Airbus Operations (S.A.S.) | Fond etanche arriere presentant une membrane integrale a geometrie composee |
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CN107804469B (zh) * | 2017-09-25 | 2024-04-19 | 中国商用飞机有限责任公司 | 飞机 |
DE102017128164B4 (de) * | 2017-11-28 | 2021-01-07 | Bernhard Hauber | Flugzeug |
EP3511243B1 (fr) * | 2018-01-15 | 2021-12-29 | The Aircraft Performance Company GmbH | Aile d'avion |
CN108423171A (zh) * | 2018-03-30 | 2018-08-21 | 天长航空技术有限公司 | 无舵面垂直起降固定翼无人机 |
EP3670323B1 (fr) * | 2018-12-19 | 2021-02-17 | LEONARDO S.p.A. | Aeronef et procede de fabrication associe |
US11498674B2 (en) * | 2019-12-04 | 2022-11-15 | Textron Aviation Inc. | Aircraft floats |
US11267577B2 (en) | 2019-12-06 | 2022-03-08 | General Electric Company | Aircraft having an engine wing assembly |
US11639671B2 (en) | 2021-07-06 | 2023-05-02 | General Electric Company | Unducted fan turbine engine with a cowl door |
FR3135708A1 (fr) * | 2022-05-19 | 2023-11-24 | Safran | Aeronef a trainee reduite par la reduction d’intensite des tourbillons marginaux |
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-
2006
- 2006-11-30 FR FR0655199A patent/FR2909359B1/fr active Active
-
2007
- 2007-11-28 US US11/946,579 patent/US8128023B2/en active Active
- 2007-11-29 RU RU2009124912/11A patent/RU2471673C2/ru not_active IP Right Cessation
- 2007-11-29 BR BRPI0719551-6A patent/BRPI0719551A2/pt not_active IP Right Cessation
- 2007-11-29 JP JP2009538745A patent/JP5237958B2/ja not_active Expired - Fee Related
- 2007-11-29 EP EP07870354A patent/EP2089273B1/fr not_active Not-in-force
- 2007-11-29 US US12/516,594 patent/US8573530B2/en not_active Expired - Fee Related
- 2007-11-29 AT AT07870354T patent/ATE512049T1/de not_active IP Right Cessation
- 2007-11-29 WO PCT/FR2007/001959 patent/WO2008081098A1/fr active Application Filing
- 2007-11-29 CA CA2670649A patent/CA2670649C/fr not_active Expired - Fee Related
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FR2411128A1 (fr) * | 1977-12-09 | 1979-07-06 | Moraly Paul | Aeronef et, en particulier, avion a helice carenee par les gouvernes de direction et de profondeur |
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Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2011023396A2 (fr) | 2009-08-28 | 2011-03-03 | Benjamin Parzy | Aéronef ayant au moins deux groupes de propulsion électriques montés au niveau d'un empennage de celui-ci |
Also Published As
Publication number | Publication date |
---|---|
US8573530B2 (en) | 2013-11-05 |
RU2471673C2 (ru) | 2013-01-10 |
ATE512049T1 (de) | 2011-06-15 |
US20090065632A1 (en) | 2009-03-12 |
EP2089273A1 (fr) | 2009-08-19 |
US8128023B2 (en) | 2012-03-06 |
BRPI0719551A2 (pt) | 2013-12-10 |
WO2008081098A8 (fr) | 2009-10-08 |
FR2909359A1 (fr) | 2008-06-06 |
CN101646600B (zh) | 2013-04-24 |
RU2009124912A (ru) | 2011-01-10 |
CN101646600A (zh) | 2010-02-10 |
JP5237958B2 (ja) | 2013-07-17 |
EP2089273B1 (fr) | 2011-06-08 |
CA2670649C (fr) | 2015-09-08 |
FR2909359B1 (fr) | 2009-09-25 |
CA2670649A1 (fr) | 2008-07-10 |
JP2010510933A (ja) | 2010-04-08 |
US20120325958A1 (en) | 2012-12-27 |
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