WO2007071398A1 - Protection device - Google Patents
Protection device Download PDFInfo
- Publication number
- WO2007071398A1 WO2007071398A1 PCT/EP2006/012317 EP2006012317W WO2007071398A1 WO 2007071398 A1 WO2007071398 A1 WO 2007071398A1 EP 2006012317 W EP2006012317 W EP 2006012317W WO 2007071398 A1 WO2007071398 A1 WO 2007071398A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- skin
- ribs
- aircraft structure
- glare
- aircraft
- Prior art date
Links
- 230000004313 glare Effects 0.000 claims abstract description 11
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 7
- 229910052782 aluminium Inorganic materials 0.000 claims description 7
- 239000004411 aluminium Substances 0.000 claims description 7
- 239000011800 void material Substances 0.000 description 7
- 239000000463 material Substances 0.000 description 5
- 239000003365 glass fiber Substances 0.000 description 4
- 230000008901 benefit Effects 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229920002430 Fibre-reinforced plastic Polymers 0.000 description 1
- 241000287828 Gallus gallus Species 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000006735 deficit Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/14—Layered products comprising a layer of metal next to a fibrous or filamentary layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
- B32B3/02—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by features of form at particular places, e.g. in edge regions
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/20—Layered products comprising a layer of metal comprising aluminium or copper
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
- B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
- B32B3/30—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by a layer formed with recesses or projections, e.g. hollows, grooves, protuberances, ribs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F7/00—Vibration-dampers; Shock-absorbers
- F16F7/12—Vibration-dampers; Shock-absorbers using plastic deformation of members
- F16F7/123—Deformation involving a bending action, e.g. strap moving through multiple rollers, folding of members
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/101—Glass fibres
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2305/00—Condition, form or state of the layers or laminate
- B32B2305/08—Reinforcements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2571/00—Protective equipment
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2605/00—Vehicles
- B32B2605/18—Aircraft
Definitions
- the present invention relates to a device for protecting a structure, in particular for protecting an aircraft structure against e.g. bird strike.
- the nose regions of the aircraft structure are critical regions, for which special measures have to be provided in order to pass the bird-strike text.
- these regions comprise structures made of aluminium sheeting, carbon fibre, glass fibre etc.
- Advantageous embodiments of the invention are provided in the dependent claims.
- the device comprises a skin made of GLARE, which skin can be affixed to a structure (aircraft structure) to be protected.
- the skin can for example be affixed or attached by riveting, screwing, bonding etc. to an aircraft structure such that a void or opening is created between the aircraft structure and the skin, into which void the skin deforms when a force acts on the skin, so as to absorb the force acting on the skin without damaging the aircraft structure.
- the material GLARE (GLAss-fibre REinforced aluminium) comprises a multitude of layers, each being only a few tenths of a millimetre in thickness. These layers are alternately made of aluminium and of a glass fibre laminate (glass-fibre reinforced plastic). These layers are bonded to each other under pressure.
- the material GLARE provides a very significant advantage in that it can absorb a lot of energy without tearing. In this process the energy is transformed leaving permanent deformation.
- the aircraft structure that is situated behind the impact location remains undamaged to a very large extent; i.e. a bird impacting on the skin made of GLARE does not penetrate right through to the aircraft structure.
- said device comprises a multitude of ribs that are located on that surface of the skin, which surface faces towards the aircraft structure.
- the ribs are used for stiffening the device if this is aerodynamically required.
- the ribs can be necessary for aerodynamic reasons in order to avoid a change in the profile contour of the aircraft structure because a deviation of the required profile contour leads to an impairment of the aerodynamics.
- the ribs comprise, for example, aluminium or GLARE or some other suitable material that causes stiffening of the device.
- the ribs are made of aluminium, which results in a weight reduction of up to 25%.
- the ribs can be connected to the skin, for example by bonding, riveting, bonding and riveting, screwing etc.
- Fig. 1 shows a perspective view of a device according to the exemplary embodiment.
- Fig. 2 shows a lateral top view of the device according to Fig. 1 in an installed state.
- Fig. 1 shows a perspective view of a device 1 for protecting an aircraft structure (not shown), for example in the region of the nose of an aircraft.
- the device 1 comprises a skin 2 made from the material GLARE.
- a multitude of ribs 4 are arranged in order to stiffen the device 1 if this is aerodynamically required.
- the ribs 4 can also be left out. the device 1 if this is aerodynamically required.
- the ribs 4 can also be left out.
- the ribs 4 are crescent shaped; however, they can have any desired shape.
- the ribs 4 are, for example, arranged so as to be equidistant from each other; however, they can also be arranged so as to be spaced apart from each other at different spacings according to aerodynamic requirements.
- the ribs are, for example, also made of GLARE or aluminium, and are, for example, bonded, glued, screwed, riveted or connected in some other way to the skin surface 3.
- Fig. 2 shows a somewhat perspective top view of the device 1 that is affixed to an aircraft structure 5 to be protected.
- the device 1 is, for example, in a region 6 screwed, bonded, glued, riveted etc. or otherwise firmly connected to the aircraft structure 5.
- a void or space 7 is formed between the skin 2 of the device 1 and the aircraft structure 5.
- This void 7 provides a buffer zone in order to absorb a force F that acts on an exterior surface 8 of the skin 2, in that the skin 2 deforms in the direction of the aircraft structure 5, i.e. into the void 7.
- the size of the void 7 matches the aerodynamic requirements, the profile contour of the aircraft structure, as well as the deformation characteristics of the GLARE material so as to prevent damage to the aircraft structure 5 from occurring .
- the skin 2 made of GLARE is sufficiently rigid to preferably maintain its shape (for example matched to a nose) by itself.
- the invention can be used not only in aircraft engineering but also in other areas, for example in automotive engineering, to protect a structure against the effect of a force.
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE602006015100T DE602006015100D1 (en) | 2005-12-20 | 2006-12-20 | PROTECTION DEVICE |
JP2008546251A JP2009520624A (en) | 2005-12-20 | 2006-12-20 | Protective material |
EP06841062A EP1963095B1 (en) | 2005-12-20 | 2006-12-20 | Protection device |
CA002629592A CA2629592A1 (en) | 2005-12-20 | 2006-12-20 | Protection device |
BRPI0620202-0A BRPI0620202A2 (en) | 2005-12-20 | 2006-12-20 | protection device |
US12/142,475 US20090127392A1 (en) | 2005-12-20 | 2008-06-19 | Protection device |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US75189805P | 2005-12-20 | 2005-12-20 | |
DE102005060958.9 | 2005-12-20 | ||
US60/751,898 | 2005-12-20 | ||
DE102005060958A DE102005060958A1 (en) | 2005-12-20 | 2005-12-20 | Aircraft structure protection, against damage from birds in flight, is an outer skin of glass fiber reinforced aluminum with a hollow zone to allow skin distortion through an impact |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/142,475 Continuation US20090127392A1 (en) | 2005-12-20 | 2008-06-19 | Protection device |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2007071398A1 true WO2007071398A1 (en) | 2007-06-28 |
WO2007071398B1 WO2007071398B1 (en) | 2007-08-23 |
Family
ID=38089512
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2006/012317 WO2007071398A1 (en) | 2005-12-20 | 2006-12-20 | Protection device |
Country Status (9)
Country | Link |
---|---|
US (1) | US20090127392A1 (en) |
EP (1) | EP1963095B1 (en) |
JP (1) | JP2009520624A (en) |
CN (1) | CN101389471A (en) |
BR (1) | BRPI0620202A2 (en) |
CA (1) | CA2629592A1 (en) |
DE (2) | DE102005060958A1 (en) |
RU (1) | RU2008129394A (en) |
WO (1) | WO2007071398A1 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN101786499A (en) * | 2008-12-15 | 2010-07-28 | 巴西航空有限公司 | Shock proof aircraft leading edge structure and aircraft with this structure |
EP2130762A3 (en) * | 2008-05-06 | 2013-01-23 | Alenia Aeronautica S.p.A. | Wing and empennage leading edge structure made of thermoplastic material with a stiffened double-shell configuration |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2918036A1 (en) * | 2007-06-26 | 2009-01-02 | Sogeclair Sa | Leading edge forming device for e.g. wing of aircraft, has rigid elements, external and internal walls forming metallic lattice, where rigid elements are extended between walls and connected directly/indirectly to walls |
CN102390520B (en) * | 2011-09-29 | 2014-06-18 | 西北工业大学 | Empennage capable of improving bird strike resistance of airplane |
GB201120707D0 (en) | 2011-12-01 | 2012-01-11 | Airbus Operations Ltd | Leading edge structure |
FR2989666B1 (en) | 2012-04-19 | 2014-12-05 | Eurocopter France | AIRCRAFT AERODYNAMIC SURFACE, AND AIRCRAFT PROVIDED WITH SAID AERODYNAMIC SURFACE |
FR2993857B1 (en) * | 2012-07-26 | 2015-03-27 | Airbus Operations Sas | DEVICE FOR PROTECTING A LONGERON STRUCTURE BEFORE A CENTRAL AIRCRAFT WING BOX AND AT LEAST ONE EQUIPMENT LOCATED IN THE SAME |
WO2014081356A1 (en) * | 2012-11-20 | 2014-05-30 | Saab Ab | An airframe leading edge |
JP6782533B2 (en) * | 2015-08-26 | 2020-11-11 | 三菱航空機株式会社 | Aircraft leading edge structure, aircraft wing and aircraft |
ES2744569T3 (en) * | 2016-05-24 | 2020-02-25 | Airbus Operations Sl | Armored leading edge and manufacturing procedure thereof |
CN106741822B (en) * | 2016-11-04 | 2019-07-26 | 清华大学 | Aircraft containing parallel institution deforms nose cone |
CN107651169B (en) * | 2017-08-31 | 2020-07-28 | 清华大学 | Bionic variant aircraft nose cone device based on hydropneumatic drive |
CN108910011B (en) * | 2018-05-08 | 2020-11-13 | 清华大学 | Space-expandable aircraft deformation nose cone with embedded segmented shell |
GB201821332D0 (en) * | 2018-12-31 | 2019-02-13 | Airbus Operations Gmbh | Aircraft flow body |
US11230365B2 (en) * | 2019-04-29 | 2022-01-25 | Airbus Operations Gmbh | Leading-edge component for an aircraft |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0529917A1 (en) * | 1991-08-23 | 1993-03-03 | British Aerospace Public Limited Company | Fusion bonded thermoplastic leading edge for aircraft aerodynamic surfaces |
WO2003000546A2 (en) * | 2001-06-20 | 2003-01-03 | Fairchild-Dornier Gmbh | Structural element for an aircraft |
EP1336469A1 (en) * | 2002-02-19 | 2003-08-20 | Alenia Aeronautica S.P.A. | Methods of manufacturing a stiffening element for an aircraft skin panel and a skin panel provided with the stiffening element |
WO2003068494A1 (en) * | 2002-02-13 | 2003-08-21 | Stork Fokker Aesp B.V. | Laminated panel with discontinuous internal layer |
WO2005087589A1 (en) * | 2004-03-16 | 2005-09-22 | Stork Fokker Aesp B.V. | Laminate with heating element |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2427065A (en) * | 1944-06-06 | 1947-09-09 | Universal Moulded Products Cor | Airfoil structure |
US4408742A (en) * | 1981-02-17 | 1983-10-11 | Korb George P | Hanger for rectangular-section downspouts |
ES2197727B1 (en) * | 2000-07-27 | 2005-04-01 | Construcciones Aeronauticas, S.A. | AIRCRAFT SUSTAINING SURFACE ATTACK EDGE. |
DE20220600U1 (en) * | 2002-09-09 | 2003-12-24 | Eurocopter Deutschland Gmbh | Aircraft used as rotary-wing aircraft, e.g. helicopter, comprises structural component at risk from impact/explosion which is made of lightweight composite material with rigid, strong support layer and fiber-reinforced elastomer layer |
FR2844742B1 (en) * | 2002-09-25 | 2005-04-29 | Pechiney Rhenalu | ALUMINUM-GLASS FIBER LAMINATED COMPOSITE SHEETS |
EP1495858B1 (en) * | 2003-07-08 | 2019-08-07 | Airbus Operations GmbH | Lightweight material structure made of metal composite material |
DE102004001078B8 (en) * | 2004-01-05 | 2013-06-13 | Airbus Operations Gmbh | fuselage |
RU2384462C2 (en) * | 2004-01-05 | 2010-03-20 | Эйрбас Дойчланд Гмбх | Hull |
BE1015867A3 (en) * | 2004-01-22 | 2005-10-04 | Sonaca Sa | Together leading edge of a wing element element wing aircraft and equipped at least such an assembly. |
DE102004018579A1 (en) * | 2004-04-16 | 2005-11-03 | Airbus Deutschland Gmbh | Panel for a structure of an aircraft |
-
2005
- 2005-12-20 DE DE102005060958A patent/DE102005060958A1/en not_active Ceased
-
2006
- 2006-12-20 DE DE602006015100T patent/DE602006015100D1/en active Active
- 2006-12-20 JP JP2008546251A patent/JP2009520624A/en active Pending
- 2006-12-20 CN CNA2006800464599A patent/CN101389471A/en active Pending
- 2006-12-20 WO PCT/EP2006/012317 patent/WO2007071398A1/en active Application Filing
- 2006-12-20 EP EP06841062A patent/EP1963095B1/en not_active Expired - Fee Related
- 2006-12-20 RU RU2008129394/02A patent/RU2008129394A/en not_active Application Discontinuation
- 2006-12-20 CA CA002629592A patent/CA2629592A1/en not_active Abandoned
- 2006-12-20 BR BRPI0620202-0A patent/BRPI0620202A2/en not_active Application Discontinuation
-
2008
- 2008-06-19 US US12/142,475 patent/US20090127392A1/en not_active Abandoned
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0529917A1 (en) * | 1991-08-23 | 1993-03-03 | British Aerospace Public Limited Company | Fusion bonded thermoplastic leading edge for aircraft aerodynamic surfaces |
WO2003000546A2 (en) * | 2001-06-20 | 2003-01-03 | Fairchild-Dornier Gmbh | Structural element for an aircraft |
WO2003068494A1 (en) * | 2002-02-13 | 2003-08-21 | Stork Fokker Aesp B.V. | Laminated panel with discontinuous internal layer |
EP1336469A1 (en) * | 2002-02-19 | 2003-08-20 | Alenia Aeronautica S.P.A. | Methods of manufacturing a stiffening element for an aircraft skin panel and a skin panel provided with the stiffening element |
WO2005087589A1 (en) * | 2004-03-16 | 2005-09-22 | Stork Fokker Aesp B.V. | Laminate with heating element |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2130762A3 (en) * | 2008-05-06 | 2013-01-23 | Alenia Aeronautica S.p.A. | Wing and empennage leading edge structure made of thermoplastic material with a stiffened double-shell configuration |
CN101786499A (en) * | 2008-12-15 | 2010-07-28 | 巴西航空有限公司 | Shock proof aircraft leading edge structure and aircraft with this structure |
US8123167B2 (en) | 2008-12-15 | 2012-02-28 | Embraer S.A. | Impact resistant aircraft leading edge structures and aircraft including the same |
EP2196391A3 (en) * | 2008-12-15 | 2012-03-28 | EMBRAER - Empresa Brasileira de Aeronáutica S.A. | Impact resistant aircraft leading edge structures and aircraft including the same |
Also Published As
Publication number | Publication date |
---|---|
EP1963095A1 (en) | 2008-09-03 |
JP2009520624A (en) | 2009-05-28 |
DE102005060958A1 (en) | 2007-06-21 |
US20090127392A1 (en) | 2009-05-21 |
WO2007071398B1 (en) | 2007-08-23 |
RU2008129394A (en) | 2010-01-27 |
DE602006015100D1 (en) | 2010-08-05 |
BRPI0620202A2 (en) | 2011-11-01 |
EP1963095B1 (en) | 2010-06-23 |
CA2629592A1 (en) | 2007-06-28 |
CN101389471A (en) | 2009-03-18 |
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