WO2011064520A1 - Procede pour realiser une jonction etanche entre des pieces d'aeronef - Google Patents
Procede pour realiser une jonction etanche entre des pieces d'aeronef Download PDFInfo
- Publication number
- WO2011064520A1 WO2011064520A1 PCT/FR2010/052578 FR2010052578W WO2011064520A1 WO 2011064520 A1 WO2011064520 A1 WO 2011064520A1 FR 2010052578 W FR2010052578 W FR 2010052578W WO 2011064520 A1 WO2011064520 A1 WO 2011064520A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- parts
- mold
- partition
- aircraft
- membrane
- Prior art date
Links
- 238000000034 method Methods 0.000 title claims abstract description 17
- 239000003566 sealing material Substances 0.000 claims abstract description 8
- 239000012528 membrane Substances 0.000 claims description 60
- 238000005192 partition Methods 0.000 claims description 57
- 239000000463 material Substances 0.000 claims description 15
- 238000002347 injection Methods 0.000 claims description 10
- 239000007924 injection Substances 0.000 claims description 10
- 102000000591 Tight Junction Proteins Human genes 0.000 claims description 3
- 108010002321 Tight Junction Proteins Proteins 0.000 claims description 3
- 210000001578 tight junction Anatomy 0.000 claims description 3
- 230000001413 cellular effect Effects 0.000 claims description 2
- 238000007373 indentation Methods 0.000 claims 1
- 238000007789 sealing Methods 0.000 description 14
- 229920001971 elastomer Polymers 0.000 description 8
- 239000000806 elastomer Substances 0.000 description 8
- 239000007788 liquid Substances 0.000 description 7
- 239000003381 stabilizer Substances 0.000 description 6
- 238000009434 installation Methods 0.000 description 5
- 238000006073 displacement reaction Methods 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 4
- 239000013536 elastomeric material Substances 0.000 description 3
- 229920001296 polysiloxane Polymers 0.000 description 3
- 239000011347 resin Substances 0.000 description 3
- 229920005989 resin Polymers 0.000 description 3
- 239000003351 stiffener Substances 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000011065 in-situ storage Methods 0.000 description 2
- 239000010410 layer Substances 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 238000006116 polymerization reaction Methods 0.000 description 2
- 229920001343 polytetrafluoroethylene Polymers 0.000 description 2
- 239000004810 polytetrafluoroethylene Substances 0.000 description 2
- 239000002356 single layer Substances 0.000 description 2
- 229920000271 Kevlar® Polymers 0.000 description 1
- 239000004952 Polyamide Substances 0.000 description 1
- 239000004959 Rilsan Substances 0.000 description 1
- 238000004873 anchoring Methods 0.000 description 1
- 239000004760 aramid Substances 0.000 description 1
- 229920003235 aromatic polyamide Polymers 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 210000004027 cell Anatomy 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000006260 foam Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 230000003601 intercostal effect Effects 0.000 description 1
- 239000004761 kevlar Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003071 parasitic effect Effects 0.000 description 1
- 235000011837 pasties Nutrition 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 229920002647 polyamide Polymers 0.000 description 1
- 229920000642 polymer Polymers 0.000 description 1
- -1 polytetrafluoroethylene Polymers 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 230000003252 repetitive effect Effects 0.000 description 1
- 239000000565 sealant Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
- 238000011179 visual inspection Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
- 230000004584 weight gain Effects 0.000 description 1
- 235000019786 weight gain Nutrition 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/84—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks by moulding material on preformed parts to be joined
- B29C70/845—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks by moulding material on preformed parts to be joined by moulding material on a relative small portion of the preformed parts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C45/00—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor
- B29C45/14—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
- B29C45/14467—Joining articles or parts of a single article
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
- B64C1/069—Joining arrangements therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/10—Bulkheads
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C7/00—Structures or fairings not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C45/00—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor
- B29C45/14—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
- B29C45/14467—Joining articles or parts of a single article
- B29C2045/1454—Joining articles or parts of a single article injecting between inserts not being in contact with each other
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2083/00—Use of polymers having silicon, with or without sulfur, nitrogen, oxygen, or carbon only, in the main chain, as moulding material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3082—Fuselages
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0081—Fuselage structures substantially made from particular materials from metallic materials
-
- 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 invention relates to the structural parts of aircraft such as fuselages.
- this partition raises different problems. As it is a structural partition, it must support the required efforts. It is known for this purpose to fix this partition to the primary structure by means of splices extending on both sides of the partition and involving at least two parts and several structural fasteners. Indeed, it is preferred to fix the fuselage without damaging the parts of the primary structure of the aircraft so as not to threaten the mechanical properties. But, when looking for a gain in mass, this arrangement is too heavy or critical fatigue. Thus, in some cases, the seal is achieved by putting in place a sealant sandwiched between the parts. But this solution requires adding a large amount of small and complex sheet metal parts to put in place.
- An object of the invention is to provide a tight junction between parts, including structural parts, for example during a second industrialization of the aircraft.
- the pieces are assembled on several parts of a mold.
- a sealing material is injected into the mold.
- sealing is effected by means of a sealed block molded in situ on the parts.
- This seal will, if necessary, be compatible with pressure differential prevailing on both sides of the block.
- the method can be implemented easily on an existing aircraft, for example an aircraft that requires conversion with major structural modifications. It is economical and light to perform. It does not require the addition of parts remaining permanently, or the establishment of fasteners out of those necessary for the temporary maintenance of the mold.
- the block produced is calibrated in volume.
- the method can be implemented in a repetitive manner while controlling the mass of the material thus installed. If necessary, the watertight junction can be removed and then carried out again if necessary, without any structural damage. This advantage is particularly important when a repair or inspection by visual inspection of the area is required in the aircraft.
- This method can be implemented using a sufficiently flexible sealing material that takes into account the movements of the structural parts during use of the aircraft.
- the invention is applicable to a structural part of an aircraft such as a fuselage, wing or empennage.
- the pieces form a frame and a rail of a fuselage.
- this arrangement is particularly useful for sealing a partition separating a front area and a rear area of an internal volume of the fuselage.
- At least one block of sealing material is installed in the mold, in particular opposite one face of one of the parts facing away from the other part.
- This arrangement facilitates the establishment of the sealing junction, especially when it is intended to represent a relatively large volume, or when certain areas may be difficult to fill with the sealing material initially in the liquid or pasty state.
- At least two of the mold parts have a recess for receiving one of the parts.
- At least two parts of the mold are clamped towards one another with clamping means such as self-locking fasteners, and after injection the clamping means are cut at one face of the material. sealing.
- clamping means such as self-locking fasteners
- At least one of the clamping means bears directly on one of the parts, between them.
- At least one of the parts of the mold is inserted into a housing, opposite a face of one of the parts facing away from the other room.
- the or each mold part inserted is made of cellular deformable material.
- sealing is effected by means of the same mold parts on other parts of the same aircraft having shapes and / or dimensions different from those of the parts.
- an aircraft which comprises elongated pieces and extending locally in main directions non-parallel to each other, and a molded block forming a tight junction between the pieces.
- the aircraft comprises a structural part, such as a fuselage, a wing or an empennage, comprising:
- a structural partition separating one from the other from the zones, for example front and rear, of the volume, the partition comprising a flexible membrane capable of deforming and supports supporting the membrane in a discontinuous manner,
- the block ensuring a tight connection between the wall and the rest of the structural part.
- the membrane makes it possible to adapt the dimensions of the partition to the actual dimensions of the structural part already made and to the deformations suffered by the latter during the use of the aircraft.
- the supports allow the partition to collect the necessary structural forces and transmit them to the structural part.
- the partition can be installed in an existing aircraft in a short period of time, without long immobilize the aircraft on the ground. This installation can take place in a particularly simple and inexpensive way. If the partition according to the invention is particularly useful in the second industrialization phase, that is to say for the establishment of this partition within an existing aircraft or at least in a completed structural part, the invention remains exploitable in first industrialization, that is to say to fix such a partition during the construction of the aircraft.
- FIG. 1 is a longitudinal vertical axial sectional view of an aircraft according to the invention showing the principle of the configuration of the partition;
- FIG. 2 is a rear view of the fuselage of Figure 1 showing the fixed elements supporting the partition;
- FIG. 3 is a view similar to Figure 2 showing the central portion of the partition to be fixed to the fixed elements of Figure 2;
- FIG. 4 is a view similar to FIG. 2 showing the principle of the arrangement of the supports of the membrane;
- Figure 5 is a detail view similar to Figure 4.
- FIG. 6 is a sectional view along the plane VI-VI of the partition of Figure 3;
- FIG. 7 is an enlarged view of detail D of Figure 1 illustrating the attachment of the partition in the upper part;
- Figure 8 is a view similar to Figure 7 showing the attachment of the sealing membrane in the upper part and its deformations;
- FIG. 9 is an enlarged view of the detail E of Figure 1 showing the attachment of the partition in the lower part;
- FIG. 10 is a sectional view along the X-X plane of the partition of Figure 5 showing its attachment in the side portion;
- Figures 11 and 12 are enlarged views of the details F and G of Figures 6 and 11 respectively;
- FIG. 13 is a perspective view of one of the sections of the membrane of FIG. 11;
- FIGS. 16, 17 and 18 are cross-sectional views showing the use of a mold for producing a sealing block for the partition of the preceding figures, according to plans XVI-XVI, XVII-XVII and XVIII-XVIII of Figures 17 and 16;
- Figures 19 and 20 are sectional views illustrating the sealing of the mold parts, the section of Figure 19 being taken along the plane XIX-XIX of Figure 17;
- Figure 21 is a sectional view along the XXI-XXI plane of the arrangement of Figure 17;
- FIG. 22 is a view similar to FIG. 11 showing the forces exerted by the membrane 60 on one of the beams of the partition when the partition is such that these forces are not balanced;
- FIG. 23 is a view similar to Figure 22 wherein the partition is such that the forces are balanced.
- FIG. 24 is another view on a larger scale of the detail G of FIG. 11.
- the aircraft illustrated in FIG. 1 is an aerodyne and in this case an airplane 2. It comprises a fuselage 4 having a generally elongated cylindrical shape whose main axis is the horizontal axis 6. At the front of the fuselage extends the cockpit 8. The aircraft is provided with unrepresented wings forming a wing, with landing gear of which part is visible in FIG. 1 and with engines 12.
- the orthogonal reference X, Y, Z is used in the following, in which the X and Y directions are horizontal and perpendicular to one another, the direction X being parallel to the axis 6, and the direction Z is vertical.
- the fuselage comprises frames 14 of circular shape each extending generally in a plane perpendicular to the axis 6 and carrying the skin 28 of the fuselage.
- the skin is reinforced by horizontal profiled rails 1 16 also attached to the frames.
- the frames are arranged in planes parallel to each other and succeeding each other along the axis 6. It is assumed here that the partition is installed to extend generally in a plane perpendicular to the axis 6, in the vicinity of the frame numbered 30 in the succession of frames starting at the nose of the device.
- the partition 20 a rigid subassembly 22, rigidly attached to the fuselage 4 and fixed permanently to the latter in this case. It extends in peripheral part of the partition. It comprises the left and right lateral sections of the frame 14, as well as the upper planar panels 24 and lower 26.
- the panels are fixed directly to the skin 28.
- the upper panel 24 extends continuously from the skin 28 of the fuselage to the height of a ceiling of a cabin of the plane.
- the lower panel 26 extends continuously from the skin 28 to the height of the floor of the cabin.
- These panels are attached to the structure main plane. They are each self-stiffened and provided in this case rectilinear vertical stiffeners 30, parallel and distant from each other.
- the upper and lower panels 24, 26 may have openings 110 for the passage of various systems such as air ducts and liquid, for example water, electrical and computer cables, etc.
- the partition 20 comprises a subassembly 32 attached to the subassembly 22 by means making it possible to dismount it easily and quickly.
- This subassembly comprises a non-rigid reinforcement comprising rigid portions 34 and deformable flexible zones 36.
- rigid portions 34 and deformable flexible zones 36 In the present example illustrated in detail in FIG. 5, there are five rigid portions 34 and five deformable flexible zones 36.
- the rigid parts and the flexible zones in this case, succeed one another alternately from one side to the other of the fuselage, starting here on the left by a rigid part 34, as illustrated with the letters "R" and " S "in Figure 4.
- Each part or each zone extends over the entire height of the subassembly 32.
- Those in the central zone of this subassembly have a generally rectangular shape. There are six of them in FIGS. 3, 4 and 5, and extend from the top panel 24 to the bottom panel 26 to which they are each fixed in their own right.
- Each of the rigid parts 34, or support comprises in this case two vertical rectilinear beams 40 extending at a distance from one another and for example spaced apart by 500 mm.
- the beams are located in line with the longitudinal rails of the floor of the aircraft.
- Each rigid portion comprises stabilizers in the form of intercostal crosspieces 42 rigidly connecting the two beams to one another.
- the stabilizers are attached to the beams away from the ends of the latter being regularly spaced along the height of the beams and forming with the latter a ladder configuration.
- the stabilizers 42 thus fixed to the beams rigidify each portion 34.
- each beam 40 is formed by a section whose section has a general shape of "H".
- the rear plate 44 of the profile has a flat shape while the front plate shown in detail in Figure 12 has a general shape in "V" reversed so that the two wings 48 of the plate are inclined rearwardly.
- Each wing thus has a flat vertical front face 50 inclined towards one side of the fuselage, for example by forming an angle of about 30 ° with the transverse direction Y.
- Each stabilizer 42 has a generally planar shape and extends in a horizontal plane. It may have recesses 52 to reduce the mass. Its edge The back is here rectilinear while its front edge 54 has a concave curved shape, for example in an arc, such that the median portion of this edge is closer to the rear edge than its end portions. Stabilizer 42 is attached to ribs 56 of associated beams 40. The edge 54 also extends back wings 48 and therefore the front faces 50 thereof.
- At least one of the rigid parts 34 can be arranged to accommodate a door 74 as shown in Figure 4 or a passage of another type allowing equipment or men to cross the partition.
- the door can be equipped with a "Z" shaped frame with a gasket.
- the door may include a self-stiffening skin, two horizontal fittings supporting hinges and door stops, an operating and locking mechanism and a visual security window.
- Each rigid portion 34 carries a section of deformable flexible membrane 60 fixed to the beams 40 so as to be able to move and to deform.
- This is in this case a layer of a non-metallic material such as an aramid resin in the form of fibers, for example a poly-para-phenylene terephthalamide marketed under the name of Kevlar.
- This resin is embedded in a silicone layer by means of an injection method so that the membrane 60 is armed and can withstand a cabin pressure differential of the type that can be experienced by a plane flying at a stratospheric altitude.
- the membrane 60 illustrated in particular in FIG. 13, has vertical rectilinear lateral edges 62 parallel to each other and by which it is fixed to the faces 50 of the two corresponding beams by being sandwiched between the fin 48 and a flange 64.
- flange is fixed to the fin for example by means of screws 66, washers and captive nuts 68 extending in the rear part of the fin.
- the membrane section 60 is fixed to the beams having a non-planar shape from one to the other of the latter, in this case a curved shape of cylindrical horizontal section.
- the membrane thus follows the front edge 54 of the stabilizer 42, remaining at a distance from the latter all along the latter.
- the radius of curvature of the membrane will for example be less than or equal to 800 mm.
- the membrane is mounted so as to be able to turn, that is to say, to invert its curvature so that its center of curvature extends not in front of the partition but behind it, as illustrated by the mixed line 60 '. This reversal can occur for example in case of depressurization of the cabin.
- the upper and lower end portions 70 of the membrane section have a curved configuration in two directions perpendicular to each other, in this case a spherical configuration.
- the upper and lower edges 72 of the membrane are rectilinear and horizontal in this case.
- the flexible zones 36 of the partition 20 are formed only by an armed membrane section 60. It is fixed to the fins 48 of the beams closest to the adjacent rigid parts 34 as illustrated in particular in FIG. 11. The shape and the attachment of the membrane section are the same as for the membrane section of each rigid part 34.
- the partition 20 is thus formed by the armature and the membrane sections 60 that it carries.
- FIG. 9 illustrates the attachment of one of the rigid parts 34 to the primary structure of the aircraft.
- the lower panel 26 extends under the floor 76 of the aircraft, in contact with the underside of the latter. This floor is started to provide an opening 78 to the right of each beam 40.
- a fitting 80 is fixed rigidly to the panel 26 behind the latter.
- a lower end of the beam 40 has an extension 82 connected to the fitting 80 by means of a traditional connection by axis and ball joints.
- this connection is adapted to resume efforts along the three directions X, Y and Z and to transmit displacements in the same directions.
- the connection to the fitting is able to transmit forces only in the X and Z directions.
- This seal 84 thus comprises a base portion 86 with a circular profile extending upwardly from its rear face by a sidewall 88.
- This seal is protected at the front and at the rear by two flanges 90. sandwich between the seal and the front face of the beam 40, while the front flange 90 has an "S" shape matching that of the front face of the seal.
- the seal 84 is thus protected against blunt objects that may be on the ground. To protect it during assembly and disassembly operations, it is advantageous for this seal to be preassembled with its two flanges before mounting.
- each beam 40 and the primary structure of the aircraft is performed in this case by means of a rod 90.
- Each of the rods 90 extends substantially in the direction Z.
- the connecting rod 90 is connected to the frame 14 in the front part and to the beam in the rear part, the two links being joints along axes of rotation 92 parallel to the Y direction in this example.
- the rods extending in the direction Z, they can transmit efforts and displacements in this direction.
- the beam 40 may have substantial displacements at least in the upper part relative to the primary structure of the aircraft.
- the rod 90 has a fixed length while the rod 90 associated with the other beam is adjustable in length.
- the seal between the partition 20 and the parts fixed to the fuselage, in the upper part and on the sides, is provided by a membrane 61 independent of the membrane 60 but made of the same material as the latter preferably.
- the membrane 61 itself can undergo significant displacements, for example more or less 20 mm in the general plane of the partition along the Y and Z directions, and more or less 10 mm in the X direction.
- FIG. 8 to reference 61 to the nominal configuration of the diaphragm, to reference 61 b to its position set back in direction X, to reference 61 c to its raised position in direction Z and finally to reference 61 to a configuration both raised and retreated.
- FIG. 8 to reference 61 to the nominal configuration of the diaphragm, to reference 61 b to its position set back in direction X, to reference 61 c to its raised position in direction Z and finally to reference 61 to a configuration both raised and retreated.
- FIG. 8 to reference 61 to the nominal configuration of the diaphragm, to
- the upper end edge of the membrane 61 is fixed rigidly to a locally horizontal panel 100, itself fixed on the side of its upper face to frames 14. taking the membrane 61 sandwiched between this panel and a flange 102. If the partition 20 is disassembled, the membrane 61 can remain in place and be deployed rearward in a cylindrical configuration of axis 6 to have a dressing function . It will then have the configuration 61 e illustrated in Figure 8.
- FIG. 14 illustrates the lower sealed fastening of the membrane 60 of a rigid portion 34.
- the lower ends of the beams 40 carry a cross-member 102 having a vertical flat bottom face 104 and a medial flat face 106 which is parallel to the Y direction and inclined relative to the X direction while being slightly turned upwards.
- the membrane 60 is sandwiched between this face and a flange 107 fixed rigidly to the cross member by appropriate means not shown.
- the lower end edge of the membrane extends away from the upper edge of the seal 84 to a musical note.
- the waterproof fastening of the membrane in the upper part is carried out analogously.
- the partition is installed using the following method.
- the rigid subassembly 22 intended to be fixed permanently, is installed during a conversion project where the aircraft is unloaded as is practiced for a major repair. While maintaining the integrity of the longitudinal stiffeners, then a seal is made between the fuselage and this subset as will be seen later. To this end, each of the smooth passages is sealed, as well as the passages for the various systems.
- the removable rigid parts 34 are installed.
- the membrane 60 is sealingly connected to the frame 14 by being sandwiched between a rear face of the frame and a flange 112 held rigidly in position on the frame by means of an assembly screw and nut prisoners.
- the frame is attached to the skin 28 by means of its foot 122, except where the frame straddles the beam 116 so that the foot 122 bypasses the latter.
- the frame and the rail are at this point locally perpendicular to each other. They are non-secant and non-coplanar locally.
- the tightness of the junction of this side of the frame between the frame 14 and the beam 116 is effected by means of a block 118 made of leakproof material molded in situ so as to seal the frame to the smooth and the skin over the smooth.
- the junction is performed on parts of the frame and the sill distant from their longitudinal ends.
- Block 118 is made in this case of an elastomer such as silicone.
- the molding is performed by means of a mold 124 in several parts 126 and 128.
- the two parts 126 are solid, rigid and form plates. They are generally symmetrical to each other and arranged on either side of the plane of the soul of the frame 14. They each have a notch 130 enabling them to span the smooth 116 and to be in contact by their foot 132 with the frame 14 and the skin 28. Each of these parts 124 makes a tight contact all along its contact surface with the frame, the skin and the external surface of the smooth.
- This seal is made for example with reference to Figure 19 by means of a flexible O-ring 134 housed in a groove 136 of the foot.
- the foot 132 is provided with a series of baffles 138 succeeding following the width of the foot, none of these baffles receiving a seal.
- the material of the portions 124 is chosen not to adhere to the injected elastomeric product. It will be for example PTFE (polytetrafluoroethylene) or polyamide1, 1 called rilsan, for example.
- Each of the parts 124 has a cavity 140 into which the elastomeric material will be injected and intended to accommodate in particular the foot 122 of the frame. Above this cavity, the parts 124 have a face 142 through which they come into surface contact with the respective face of the frame 14.
- the two parts 124 are clamped against each other by clamping means such as self-locking fasteners 144, 146 extending parallel to the stringer 116.
- One 146 of these clamping means may be provided to have a "V" configuration and pass between the frame 14 and the stringer 116, under the frame by being in direct contact with the latter. This clamping means bears against chamfered external faces 147 of parts 124.
- the stringer 116 has a relatively simple shape, it can be satisfied to perform the molding by means of the two parts 126.
- the stringer has an "S" shape open on one side. It is therefore preferable to use two other parts 128 for the mold. These parts are in this case strangulated bone-shaped plugs in the middle. These plugs are inserted into a housing formed by the bar, inside thereof, being held by means of a clamp 143 squeezing them perpendicular to the soul of the bar. Each of the plugs may protrude above the bar as shown in FIG. 21.
- the material of the plugs is chosen so as not to adhere with the injected elastomer product. It may be a closed cell polymer foam, for example.
- blocks or rigid cores 149 of elastomer polymerized before injection of the rest of the material and that is installed directly in the housing of the bar 116 between its face 150 facing the skin and the latter.
- two blocks 149 are used, one above the other, one bearing against the skin, the other bearing against this face of the arm. They are installed in line with the core of the frame 14 before closing the mold. These blocks improve the overall rigidity of the molded joint, after solidification.
- the injection is made from only one of the parts 126, by means of an injection hole 152 provided for this purpose, with a nozzle connected to the liquid elastomer reservoir.
- the two parts 126 are provided with vent holes to ensure complete filling of the cavity.
- the area to receive the elastomeric product is cleaned.
- the two parts 126 of the mold are put in place at the front and at the rear of the frame with their clamping means.
- the two plugs 128 are put in place by compressing them first manually, which is permitted by the section of the bar. They are then tightened with the clamp.
- the injection of the liquid elastomeric material is carried out.
- one or more of the baffles fill partially or completely with product.
- the liquid comes in particular in contact with the blocks 149 which are embedded in it.
- the two plugs 128 are removed, then the plates 126 by cutting the self-locking fasteners 144, 146. Once the parts 126 have been removed, the self-locking fasteners are again cut flush with the faces ( in particular the face 147) of the block 118 of solidified elastomer 118 from which they emerge. A section of these fasteners remains permanently inside the block.
- the sealed junction thus produced hides no structural attachment so that the connection between the frame and the skin, the connection between the heald and the skin, and so on remain accessible.
- FIG. 23 illustrates the diagram of the forces exerted on an intermediate beam 40 by the membrane sections 60 that it carries. We will see below how the partition is made so that these forces are balanced when the two closest beams 40 are not equidistant from this intermediate beam.
- Figure 22 illustrates a contrario the case in which these forces would not be balanced.
- the distance between the webs of the beams 40 supporting the membrane section located on the right is also designated by t 2 . It is assumed here that the distances l - and 1 2 are different from each other, the distance t 2 being for example here equal to approximately 1.5 times the distance
- the beam 40 undergoes in a current horizontal section a force F- ⁇ exerted by the membrane section situated to its left and a force F 2 exerted by the section of membrane located on its right. We assume here that these forces extend in a horizontal plane.
- the angle ⁇ designates the angle of the force F- ⁇ , which is exerted in the direction of the tangent to the membrane at the edge of the latter, with respect to the direction Y, and the angle ⁇ 2 the angle analogue relating to the force F 2 .
- the two angles ⁇ and ⁇ 2 are equal. This is because the front faces 50 of the wings 48 also form with the Y direction respective angles ⁇ and ⁇ 2 equal, the wings being symmetrical to each other with respect to the plane of the soul of the beam 40.
- the force F 2 has an intensity greater than the force Fi.
- the beam 40 is therefore not loaded in a balanced or symmetrical way by the two sections 60. This resultant has for its point of application the front end of the horizontal section of the beam. It generates a twisting moment around a center of inertia 63 of the section, located in the soul of the beam halfway from its front and rear edges.
- ⁇ 2 arctan (tan * ⁇ ⁇ l 2 )
- the faces 50 against which the membrane sections are in surface contact have the same inclination ⁇ and ⁇ 2 respectively with respect to the direction Y.
- the shape and / or the dimensions of each section are adapted to obtain this result. For example, it will be necessary to increase the radius of curvature of the right-hand section compared with the situation of FIG. 22. This results in a possible increase in mass and volume but which is insignificant and is negligible by compared to the total mass economy on the partition generated by this provision. There is no longer any parasitic result of torsion.
- each section of membrane takes into account the actual geometry of the anchoring of this section on the beams which itself takes into account the spacing between the beams. It is therefore minimized the efforts that the membrane sections 60 print to the primary structures.
- each membrane section is formed by a single layer of poly-para-phenylene terephthalamide impregnated with silicone.
- the membrane can be given a mass of 0.5 kg / m 2 .
- This choice of material makes it possible to minimize the mass of each membrane section and makes it equivalent in terms of resistance to an aluminum alloy membrane of 0.2 mm thickness. But such a product is not available, its installation is unlikely because of its fragility, and should be given at least a thickness of 1 mm for manufacturing reasons and robustness to the human factor.
- a weight gain of approximately 500% is therefore achieved with respect to an equivalent aluminum alloy membrane.
- the robustness of the membrane is assured despite its low mass. Its reversal in case of differential pressure reversal is not a problem.
- the membrane sections 60 not only withstand simple pressure and vacuum stresses but can also coexist with the original uses and possible degradations. human.
- the material of the membrane extends in double thickness at the place where the membrane is sandwiched between the flange 64 and the wing 48, knowing that this is an area where the membrane is particularly stressed.
- This doubling of the thickness can be achieved by simply folding the material forming the membrane and placing in the hollow of the fold a reinforcing member such as a ring 67 avoiding crushing of the latter.
- This ring 67 will for example have a diameter of between 2 and 3 mm. It is made in this case in a polyamide material. This ring extends away from the surface contact zone between the flange 64 and the wing 48 and is not sandwiched between them.
- the rod 67 may be arranged in the mold for impregnating the resin with the elastomeric material.
- the impregnated material forming a single layer, receives the rod and is folded on the latter before the polymerization of the elastomer.
- the flange 64 has, facing the membrane section 60, on the same side as the center of curvature of the latter, a face 69 of cylindrical shape extending opposite the membrane and whose own center of curvature is located on the side of the face 69 opposite the membrane. In case of reversal of the membrane, this face accommodates the membrane that can support it without the risk of tearing.
- the partition 20 described above has many advantages. It is possible to assemble and disassemble. Sealing is provided by means that take into account the structural deformations imposed by the use of the aircraft and the geometric imprecision of the various parts to be sealed, especially if the aircraft is already manufactured. The combination of fixed and rigid parts also allows such consideration. The number of fasteners to be installed and / or disassembled during assembly or dismounting in the fuselage is reduced.
- the dismantling time of the partition will for example be less than 24 hours.
- the mass of the entire partition will for example be about 800 kg.
- the partition preferably extends over most of the cross-sectional area of the internal volume of the fuselage.
- the partition 20 once in place separates a zone 109 located at the front of the partition and a zone 111 located at the rear.
- Zone 109 may be subjected to cabin pressure unlike zone 111.
- zone 111 may contain a liquid such as fuel unlike zone 109.
- the upper panel 24 is stabilized by means of several skin-connecting fittings 28, these fittings extending for example along four consecutive frames.
- the lower panel 26 is stabilized likewise.
- the rigid subassembly 22 may further comprise two special seal-holder profiles installed on the left and right sides of the frame.
- the method for producing the block 118 may be implemented on other parts than frames and smooth and out of a fuselage, for example on an aircraft wing rib.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Manufacturing & Machinery (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
- Injection Moulding Of Plastics Or The Like (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA2781778A CA2781778C (fr) | 2009-11-30 | 2010-11-30 | Procede pour realiser une jonction etanche entre des pieces d'aeronef |
US13/511,533 US9102106B2 (en) | 2009-11-30 | 2010-11-30 | Method of making a sealed junction between aircraft parts |
CN201080062446.7A CN102770263B (zh) | 2009-11-30 | 2010-11-30 | 在航空器部件之间形成密封接合的方法 |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0958507A FR2953158B1 (fr) | 2009-11-30 | 2009-11-30 | Procede pour realiser une jonction etanche entre des pieces d'aeronef |
FR0958507 | 2009-11-30 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2011064520A1 true WO2011064520A1 (fr) | 2011-06-03 |
Family
ID=42332487
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2010/052578 WO2011064520A1 (fr) | 2009-11-30 | 2010-11-30 | Procede pour realiser une jonction etanche entre des pieces d'aeronef |
Country Status (5)
Country | Link |
---|---|
US (1) | US9102106B2 (fr) |
CN (1) | CN102770263B (fr) |
CA (1) | CA2781778C (fr) |
FR (1) | FR2953158B1 (fr) |
WO (1) | WO2011064520A1 (fr) |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9889323B2 (en) * | 2013-03-13 | 2018-02-13 | The Boeing Company | Fire seal end cap and associated multi-member assembly and method |
JP6381191B2 (ja) | 2013-09-11 | 2018-08-29 | 三菱重工業株式会社 | 燃料タンク用ダム |
DE102013114391A1 (de) * | 2013-12-18 | 2015-06-18 | Airbus Operations Gmbh | Druckrumpf eines Flugzeuges, umfassend ein bewegbar relativ zur Rumpfstruktur befestigtes Druckschott |
GB201511402D0 (en) | 2015-06-30 | 2015-08-12 | Short Brothers Plc | Repair including a chamfered bracket and a chamfered bracket component for reinforcing a damaged structural element made from composite materials |
NL2015120B1 (en) * | 2015-07-09 | 2017-02-01 | Fokker Aerostructures Bv | Variable gap cover for an aircraft, mould assembly for forming such a cover and a method for manufacturing a variable gap cover. |
US10173765B2 (en) * | 2016-04-07 | 2019-01-08 | The Boeing Company | Pressure bulkhead apparatus |
US10926857B2 (en) * | 2016-06-17 | 2021-02-23 | The Boeing Company | Pressurized bulkhead |
DE102017125299A1 (de) | 2017-10-27 | 2019-05-02 | Airbus Operations Gmbh | Spaltabdeckung zwischen Kabinenmonumenten, insbesondere für eine Passagierkabine eines Flugzeuges |
FR3074143A1 (fr) * | 2017-11-29 | 2019-05-31 | Airbus Operations | Nervure de jonction voilure-caisson de voilure pour aeronef et procede de fabrication d'un aeronef au moyen d'une telle nervure |
US20190276157A1 (en) * | 2018-03-08 | 2019-09-12 | Bell Helicopter Textron Inc. | Flexible radial inlet plenum |
EP4035993A1 (fr) * | 2021-01-27 | 2022-08-03 | The Boeing Company | Connecteur pour connecter un caisson de voilure central à une cloison d'un aéronef |
CN114802698A (zh) | 2021-01-27 | 2022-07-29 | 波音公司 | 在飞机中用于连接中央翼盒和隔舱的接头 |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5242523A (en) * | 1992-05-14 | 1993-09-07 | The Boeing Company | Caul and method for bonding and curing intricate composite structures |
EP0793926A1 (fr) * | 1996-03-07 | 1997-09-10 | Nowiteck Establishment | Procédé de fabrication des brosses rotatives pour des stations de lavage pour voitures |
US6365086B1 (en) * | 1999-05-03 | 2002-04-02 | Christopher A. Schoonover | Method for connecting pieces of solid material |
WO2009037005A1 (fr) * | 2007-09-18 | 2009-03-26 | Airbus Operations Gmbh | Élément de structure et procédé pour rigidifier une enveloppe extérieure |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2840856A (en) * | 1952-10-18 | 1958-07-01 | Honeywell Regulator Co | Molding apparatus and procedure |
US4011819A (en) * | 1976-03-03 | 1977-03-15 | The United States Of America As Represented By The Secretary Of The Navy | Stress relieved molded cover assembly and method of making the same |
US4962904A (en) * | 1984-06-07 | 1990-10-16 | The Boeing Company | Transition fitting for high strength composite |
JPH0813622B2 (ja) * | 1990-04-12 | 1996-02-14 | 豊田合成株式会社 | ウエザストリップの型成形接続方法 |
GB2330793B (en) * | 1997-11-04 | 2002-08-28 | Draftex Ind Ltd | Assembly of extruded or moulded parts |
US6709614B1 (en) * | 1998-01-07 | 2004-03-23 | Henniges Elastomer- Und Kunststofftechnik Gmbh & Co. Kg | Method for producing a connection between a component and a structural element |
US6374570B1 (en) * | 2000-08-25 | 2002-04-23 | Lockheed Martin Corporation | Apparatus and method for joining dissimilar materials to form a structural support member |
US6419189B1 (en) * | 2000-11-01 | 2002-07-16 | The Boeing Company | Hot ruddervator apparatus and method for an aerospacecraft |
US6964723B2 (en) * | 2002-10-04 | 2005-11-15 | The Boeing Company | Method for applying pressure to composite laminate areas masked by secondary features |
US20050082716A1 (en) * | 2002-12-06 | 2005-04-21 | Barefield Kevin J. | Resin infusion potting |
US6877695B2 (en) * | 2002-12-13 | 2005-04-12 | The Boeing Company | Hinge cover integration into door seal edges |
US7530531B2 (en) * | 2004-10-04 | 2009-05-12 | The Boeing Company | Apparatus and methods for installing an aircraft window panel |
EP1647480B1 (fr) * | 2004-10-13 | 2010-12-08 | Airbus Operations GmbH | Couvre-joint pour aéronefs |
JP4758205B2 (ja) * | 2005-11-18 | 2011-08-24 | トヨタ自動車株式会社 | 成形体の製造方法 |
US8016237B2 (en) * | 2007-12-12 | 2011-09-13 | The Boeing Company | Methods and apparatus for an integrated aerodynamic panel |
EP2259965B1 (fr) * | 2008-03-31 | 2013-01-09 | Honda Patents & Technologies North America, LLC | Cloison de pressurisation pour avion |
-
2009
- 2009-11-30 FR FR0958507A patent/FR2953158B1/fr not_active Expired - Fee Related
-
2010
- 2010-11-30 US US13/511,533 patent/US9102106B2/en not_active Expired - Fee Related
- 2010-11-30 WO PCT/FR2010/052578 patent/WO2011064520A1/fr active Application Filing
- 2010-11-30 CN CN201080062446.7A patent/CN102770263B/zh not_active Expired - Fee Related
- 2010-11-30 CA CA2781778A patent/CA2781778C/fr not_active Expired - Fee Related
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5242523A (en) * | 1992-05-14 | 1993-09-07 | The Boeing Company | Caul and method for bonding and curing intricate composite structures |
EP0793926A1 (fr) * | 1996-03-07 | 1997-09-10 | Nowiteck Establishment | Procédé de fabrication des brosses rotatives pour des stations de lavage pour voitures |
US6365086B1 (en) * | 1999-05-03 | 2002-04-02 | Christopher A. Schoonover | Method for connecting pieces of solid material |
WO2009037005A1 (fr) * | 2007-09-18 | 2009-03-26 | Airbus Operations Gmbh | Élément de structure et procédé pour rigidifier une enveloppe extérieure |
Also Published As
Publication number | Publication date |
---|---|
CA2781778C (fr) | 2018-07-24 |
US20120280083A1 (en) | 2012-11-08 |
US9102106B2 (en) | 2015-08-11 |
FR2953158A1 (fr) | 2011-06-03 |
CN102770263B (zh) | 2016-05-18 |
CN102770263A (zh) | 2012-11-07 |
FR2953158B1 (fr) | 2012-01-20 |
CA2781778A1 (fr) | 2011-06-03 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CA2781778C (fr) | Procede pour realiser une jonction etanche entre des pieces d'aeronef | |
CA2781777C (fr) | Aeronef comportant une cloison interne | |
CA2742290C (fr) | Ensemble structurel d'aeronef et procede d'assemblage associe | |
CA2773532C (fr) | Radome et dispositif de fixation de ce radome a un aeronef | |
CA2702908C (fr) | Structure d'avion comportant des jonctions d'arrets de raidisseurs | |
FR2948099A1 (fr) | Procede de fabrication d'un aeronef a voilure fixe | |
EP2373531B1 (fr) | Plancher modulaire pour aéronef | |
EP2454473B1 (fr) | Dispositif d'assemblage de tronçons de pales d'eoliennes et procede de liaison de tronçons de pales d'eoliennes | |
EP2662280B1 (fr) | Poutre ventrale d'un aéronef | |
EP3802314B1 (fr) | Porte de cabine pressurisée d'aéronef à structure formée de poutres | |
WO2016135092A1 (fr) | Panneau composite muni d'une terminaison d'assemblage perfectionnée et structure comportant un tel panneau | |
EP3476740B1 (fr) | Structure primaire de mât de support d'un groupe propulseur d'aéronef en caisson formée par assemblage de deux demi-coquilles | |
CA2836525A1 (fr) | Verriere perfectionnee pour aeronef | |
EP3934978B1 (fr) | Porte de cabine pressurisée d'aéronef à armature intérieure de reprise d'efforts | |
FR3086269A1 (fr) | Systeme de fixation d'elements d'amenagement sur un plancher de vehicule comprenant des panneaux a parois laterales perforees | |
FR2953194A1 (fr) | Cloison d'aeronef comprenant des troncons de membrane | |
FR2969189A1 (fr) | Dispositif support d'element en couverture de toiture et en recouvrement de facade | |
EP3344524B1 (fr) | Procédé d'assemblage de panneaux d'une structure sandwich en matériaux composites, de durée réduite | |
FR3049928A1 (fr) | Troncon d'aeronef comprenant une cloison de pressurisation plane a poutres verticales | |
FR2960048A1 (fr) | Paroi formee d'une pluralite de panneaux solaires juxtaposes, comportant des moyens d'isolation thermique, et procede de fabrication d'une telle paroi | |
WO2016146800A1 (fr) | Assemblage a liaison souple et liaison souple pour un tel assemblage | |
FR2981680A1 (fr) | Huisserie metallique a caractere universel |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
WWE | Wipo information: entry into national phase |
Ref document number: 201080062446.7 Country of ref document: CN |
|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 10805795 Country of ref document: EP Kind code of ref document: A1 |
|
ENP | Entry into the national phase |
Ref document number: 2781778 Country of ref document: CA |
|
WWE | Wipo information: entry into national phase |
Ref document number: 13511533 Country of ref document: US |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
122 | Ep: pct application non-entry in european phase |
Ref document number: 10805795 Country of ref document: EP Kind code of ref document: A1 |