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
  • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
  • B29C70/06—Fibrous reinforcements only
  • B29C70/08—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers
  • B29C70/086—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers and with one or more layers of pure plastics material, e.g. foam layers
• • 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
  • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
  • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
• • 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
  • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
  • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
  • B29C65/4805—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the type of adhesives
  • B29C65/483—Reactive adhesives, e.g. chemically curing adhesives
• • 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
  • B29C66/00—General aspects of processes or apparatus for joining preformed parts
  • B29C66/40—General aspects of joining substantially flat articles, e.g. plates, sheets or web-like materials; Making flat seams in tubular or hollow articles; Joining single elements to substantially flat surfaces
  • B29C66/41—Joining substantially flat articles ; Making flat seams in tubular or hollow articles
  • B29C66/45—Joining of substantially the whole surface of the articles
• • 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
  • B29C66/00—General aspects of processes or apparatus for joining preformed parts
  • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
  • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
  • B29C66/721—Fibre-reinforced materials
• • 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
  • B29C66/00—General aspects of processes or apparatus for joining preformed parts
  • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
  • B29C66/73—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset
  • B29C66/735—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the extensive physical properties of the parts to be joined
  • B29C66/7352—Thickness, e.g. very thin
• • 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
  • B29K2011/00—Use of rubber derived from chloroprene as moulding material
• • 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
  • B29K2063/00—Use of EP, i.e. epoxy resins or derivatives thereof, as moulding material
• • 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
  • B29K2307/00—Use of elements other than metals as reinforcement
• • 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
  • B29K2995/00—Properties of moulding materials, reinforcements, fillers, preformed parts or moulds
  • B29K2995/0037—Other properties
  • B29K2995/0089—Impact strength or toughness
• • 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
  • B29L2009/00—Layered products
• • 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
  • B29L2031/3091—Bicycles
• • 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
  • B29L2031/721—Vibration dampening equipment, e.g. shock absorbers
• • 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
• • 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
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
  • Y10T156/10—Methods of surface bonding and/or assembly therefor
• • 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
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T428/00—Stock material or miscellaneous articles
  • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
  • Y10T428/24942—Structurally defined web or sheet [e.g., overall dimension, etc.] including components having same physical characteristic in differing degree
  • Y10T428/2495—Thickness [relative or absolute]

Definitions

• the present invention relates to structural panels of laminated composite material used for the construction of aircraft fuselages. More particularly, the invention relates to an aircraft structural panel subjected to high energy impacts and whose particular structure avoids the intrusion of projectiles impacting beyond a defined distance inside the fuselage. It is known that the use of composite materials makes it possible, for equal mechanical performance, to form lighter structures. This is particularly advantageous in the case of aeronautical structures. In many cases, the composite structures of low or medium thickness such as the skin of an aircraft fuselage, the nacelle panels, the gear box panels, do not contain projectiles having a speed and / or high incident energy.
• wrinkling can lead to delamination (detachment of folds) that is harmful under impact and special features can appear during dimensioning under static loads and fatigue.
• shielding protection solutions (combination of several absorbent or resistant materials within a laminate) as a secondary structure, as disclosed in international application WO 2006/070014 are disadvantageous from several points of view:
• US patent application 2007/095982 discloses an aircraft structural panel made of a composite material with fiber reinforcement and capable of withstanding impacts such as collisions with birds.
• the skin is made of a composite material specially optimized in its composition to resist shocks and not to break during these impacts but to deform and deflect the trajectory of the impacting body.
• This solution is effective in the event of impact with a projectile such as a bird that behaves like a viscous fluid and whose impact energy is distributed over a large panel area.
• the solution is not effective against shocks with debris that generally impact a small area.
• the invention proposes a structural panel made of a laminated composite material and comprising a face exposed to impacts, further comprising a layer made of a hyper-elastic material reported by collage on his other face.
• a debris impinging the exposed face of this composite panel will see a part of its energy dissipated by the local rupture of the composite skin, the remaining energy being absorbed by the deformation of the layer of material hyper- elastic that holds the debris and pushes it outward. Thanks to the layer of hyper- elastic, the dissipative power of the composite material can be exploited to sound. maximum.
• the structural panel comprises a fiber reinforced composite skin in the form of continuous carbon fibers in an epoxy matrix.
• This type of material has optimum structural resistance characteristics with respect to service demands such as static mechanical stresses or fatigue and thus allows significant gains in mass on the primary structure of the aircraft, in comparison with a primary structure. metallic.
• this material has no significant plastic deformation capacity capable of dissipating the energy of an impact and prevent the penetration of a projectile by its own deformation.
• the addition of a layer of hyper-elastic material makes it possible to dimension such a panel with respect to service requirements only, the layer of hyper-elastic material ensuring the absence of penetration of the projectile into the fuselage where it would be likely to degrade systems.
• the structural panels implemented according to this embodiment are particularly suitable for constituting fuselage structures in areas of the aircraft where protection of the systems by the composite primary structure is necessary and where an analysis of the damage tolerance of said primary structure makes it possible to demonstrate the feasibility of aircraft return after damage. Indeed, a structural panel according to the invention dissipates part of the impact by the damage and the fractures of the composite folds.
• the primary structure panels concerned have a thickness of between 2 mm and 4 mm of carbon composite - epoxy resin for a continuous fiber volume ratio greater than or equal to 50%.
• the density of such a panel is of the order of 1500 kg / m 3 .
• the thickness of the layer of hyper-elastic material is equal to or less than the skin thickness of composite material.
• the typical density of the hyper-elastic materials with rubber behavior is of the order of 1000 Kg / m 3 . So that the protection according to the invention of the internal systems of the aircraft with respect to the penetration into the fuselage of a projectile is obtained for a mass of material used less than the solution of the prior art of dimension the thickness of the composite material so that the impact can not cause it to break.
• the structural panel is a panel stiffened by profiles reported on said panel by any means known to those skilled in the art such as co-firing, gluing or riveting, the layer of hyper-elastic material is simply reported between the stiffeners.
• the layer of hyper-elastic material consists of a polychloropene elastomer such as NEOPRENE® distributed by the company Dupont Chemicals.
• This material has hyperelastic elongation capacities of the order of 500% and is able to withstand the operating conditions which involve, in the zones considered, temperature variations between -55 0 C and +70 0 C in a humid atmosphere, depending on the phases of the flight, but also chemical attacks such as products such as hydraulic oils or fuel.
• the layer of hyper-elastic material is preferably reported by gluing. Although the direct vulcanization on the relevant face of the structural composite material panel is possible this solution involves modifying the embodiment of the panels and handling heavier panels during assembly, itself made more complex because of the presence of the layer of hyper-elastic material. It is therefore preferable to report the layer of hyper-elastic material after assembly. Said bonding must be strong so that the penetration of the projectile or debris mainly causes a local hyper-elastic deformation of the layer of rubber material and not a "peeling" of this layer by breaking the adhesive along the surface. composite skin interface - layer of hyper-elastic material. The bonding must also withstand the same environmental conditions as the layer of hyper-elastic material.
• the structural element exposed to the impacts of an aircraft fuselage is manufactured according to the steps of: fabricating skin panels of composite material assembling said panels to constitute the fuselage element to report the layer of hyper-elastic material on the inner faces of the panels exposed to impacts after assembly.
• a composite structural panel according to the invention makes it possible to exploit damage by rupture of the skin made of stratified composite material which is a major source of dissipation of energy.
• a laminated composite skin would be dimensioned so as not to break under the effect of the impact because ensuring only the non penetration of the projectile.
• a landing gear box roof of carbon-epoxy resin composite material which, according to the prior art, would require a thickness of 6.5 mm in order to withstand the impact of a tire debris
• a thickness of 3.25 mm corresponding to the thickness necessary for the resumption of operating stress, associated with a layer of hyper-elastic material of chloropolymer type of 3 mm , a gain in mass of the order of 20%.
• Figure 1 shows schematically the different phases (Figures IA, IB, IC) of the impact of a projectile on the outer face of a structural panel 1 according to the invention.
• Figure 2 shows schematically the structural features of a panel according to the invention comprising stiffeners.
• FIG. IA a projectile (1) impacting the composite panel according to the invention (2) on the side of the composite material skin (3).
• This type of projectile (1) may consist of: debris such as debris of tires whose behavior is flexible, that is to say that the projectile is likely to deform elastically under the effect of the impact , and arrives on the structure with an incident energy of the order of 4000 joules.
• This type of debris generates a so-called local loading of the structure, the surface of the impact being approximately equal to the largest area of undistorted debris
• Figure 1B when the projectile (1) encounters the composite skin (3), a large part of the incident energy is dissipated by the mechanisms of damage and rupture of the material on a zone affected by the impact (5). These modes of damage (delamination, fiber breakage, vaporization of the resin and others) dissipate a good part of the incident energy and slow down the projectile.
• Figure IC the projectile passes through the composite skin and meets the layer of hyper-elastic material (4) which thanks to its hyper-elastic deformation capacity absorbs the remaining kinetic energy of the projectile without breaking and then pushes it outside .
• the thickness of the layer of hyper-elastic material is chosen so that for a projectile of characteristics given the penetration distance of the projectile remains below a threshold (s) thus ensuring the absence of damage to the systems located behind the structural panel.
• a threshold s
• the structural panels have stiffeners (6) attached to the inner face of the skin.
• the layer of hyper-elastic material (4) is simply reported by gluing (7) between said stiffeners after assembly of the structural panels.

Landscapes

• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• Chemical & Material Sciences (AREA)
• Composite Materials (AREA)
• Laminated Bodies (AREA)
• Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

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Family Applications (1)

Country Status (4)

Families Citing this family (7)

Family Cites Families (12)

• 2008
  • 2008-03-28 FR FR0801686A patent/FR2929169A1/fr not_active Withdrawn
• 2009
  • 2009-03-26 WO PCT/FR2009/000333 patent/WO2009133257A2/fr active Application Filing
  • 2009-03-26 US US12/934,755 patent/US8906493B2/en not_active Expired - Fee Related
  • 2009-03-26 EP EP09738291A patent/EP2280817A2/de not_active Withdrawn

Non-Patent Citations (2)

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