Classifications

• • 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
  • B64C1/18—Floors
• • 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
  • B64C1/12—Construction or attachment of skin panels
• • 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
  • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
  • F16B5/00—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them
  • F16B5/01—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of fastening elements specially adapted for honeycomb panels
• • 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
  • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
• • 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 present invention relates to a device for fixing a light panel such as a sandwich structure panel on a support.
• Another object of the present invention is a passenger transport vehicle such as an aircraft, comprising such fastening devices.
• Sandwich structures of composite material have properties, especially mechanical, exceptional for a minimum mass. These structures are therefore widely used in the aerospace industry (hatches, floors, leading edges, fins, interior partitions, etc.).
• Figure 1 schematically shows a partial sectional view of a cabin floor of the prior art.
• the floor is made of floorboards 1 with a sandwich structure.
• Each panel 1 comprises at least two walls 2, 3 disposed respectively on opposite outer faces of a honeycomb core 4.
• These floor panels 1 which are thin, typically of the order of 10 mm, are secured by bolts on the side flanges 5, 6 of seat mounting rails.
• the panel 1 also comprises local reinforcements 7 for interfacing the bolts and the sandwich structure. To achieve such reinforcement, it is possible to use a local filling of the panel or to install an insert. To place such an insert in the panel, a recess is typically formed using a cutting tool in one of the walls 2, 3 and over a large part of the thickness of the core 4. A metal insert 7 comprising a body 8 and a flange 9, or wide head, is placed in this recess so that the flange 9 covers the outer surface of the wall 2 having the orifice. An adhesive layer may be disposed between the flange 9 and the outer surface of the wall 3 to seal the sandwich structure 1. This wide head 9 advantageously allows to distribute a local stress such as that generated by a bolt on a zone relatively wide wall 2, 3.
• the recess may be opening, an orifice being made in each of the walls 2, 3 so that the body of the insert 7 passes through the entire thickness of the core 4.
• the object of the present invention is therefore to provide a device for fixing a light panel, simple in its design and in its operating mode, economic, with a high resistance to corrosion while having a minimum mass and allowing perform the assembly of a light panel on a support without damaging this panel or the fastener.
• the invention relates to a device for fixing a light panel such as a sandwich structure panel on a support, compatible with manufacturing tolerances and ensuring possible interchangeability while allowing a transfer of large loads in the plane of the panel between this panel and the support.
• This device comprises an insert comprising a hollow main body and at least one flange intended to come at least partially in abutment against one face of the panel, the insert being intended to receive a fixing member.
• the flange has an outer surface comprising toothing elements and the device comprises a piece of ductile material having an opening for the passage of the fastener. This piece is intended to be placed between the outer surface of the flange and the support on which the panel must be fixed.
• the toothing elements are intended to cooperate, when fixing said panel on the support, with the piece of ductile material to achieve this fixation without causing deformation of the panel.
• ductile material here means a soft material capable of plastically deforming, irreversibly under the effect of a force. The toothing thus deforms the piece of ductile material by transmitting the fixing forces of the panel to this piece so as not to cause deformation of the panel.
• this piece of ductile material can advantageously be replaced very easily by the operator for a minimal cost.
• the lightweight panel is typically a sandwich structure panel having a foam or honeycomb core.
• the flange at least is made of hard metal material
• the insert is a one-piece piece made of hard metal material
• the hard metal material is selected from the group consisting of steel, titanium, invar, an aluminum alloy.
• the invention also relates to a passenger transport vehicle such as an aircraft comprising panels secured to supports.
• this vehicle comprises devices for fastening a panel as described above, making the assembly of at least one of said panels on at least one of said supports.
• FIG. 1 shows schematically a partial sectional view of a cabin floor of the prior art
• - Figure 2 is a schematic representation of a partial sectional view of a floor panel for passenger transport vehicle comprising a device for fixing this panel according to one embodiment of the invention
• - Figure 3 shows schematically an enlarged sectional view of the connection of the floor panel with its support shown in Figure 2;
• FIG. 2 shows a floor panel for a passenger vehicle according to one embodiment of the invention.
• the floorboard 10 comprises a core sandwich structure comprising at least two walls 11, 12 respectively disposed on opposite outer faces of a honeycomb core 13.
• the walls 11, 12 are reinforcements of fibers.
• the fibers may be chosen from the group, given as a non-limiting example, comprising carbon fibers, graphite fibers, glass fibers, silica fibers, silicon carbide fibers or any other fiber providing the necessary rigidity. while responding to the constraint of low mass related to the aeronautical field.
• the honeycomb core 13 is, for example, made from aramid.
• Aramid fibers have a low flammability, a high tensile strength and a high modulus of elasticity.
• This covering 14 serves as protection for the floor panels 10 for the prevention of aggression related to the movements or any other aggression related to the occupation of the floor. the cab of the transport vehicle.
• This floor panel 10 comprises at least one mounting rail of furniture elements and seats 15 in particular, having a longitudinal axis, this mounting rail 15 being inserted at least partially in the thickness of the panel.
• the same panel 10 may, however, have two or more rails 15 placed at different positions to allow arranging arrangements according to the needs of the user.
• the mounting rail 15 has a lower rail section having an inverted T-shaped or Q-shaped cross-section.
• upper rail having a C-shaped section for receiving means for coupling and fixing the fitting elements, and in particular seat rails.
• the upper face of the floor panel 10 has an elongated opening disposed along the longitudinal axis of the mounting rail 15 to allow the fixing of the landscaping elements.
• the floor panel 10 is fixed by means of a fastener 16 on a support which is in this case a floor support rail 17.
• the fastener 16 is a bolt made of steel or titanium.
• One or more layers such as a seal 27 may be placed between the floorboard and the support 17. This seal 27 may be metallic, composite or optionally rubber.
• the panel 10 comprises inserts 18 for interfacing the fixing member 16 of the bolt type and the sandwich structure.
• Each of these inserts 18 comprises a hollow main body 19 for the passage of a fastener 16 and at least one flange 20 bearing on the face 12 of the floor panel intended to be in contact with the support.
• An adhesive layer may advantageously be disposed between the flange and the outer surface of the wall 12 of the floor panel so as to ensure the tightness of the sandwich structure.
• the insert 18 is assembled to the sandwich structure so that the main axis of the hollow cylindrical body 19 is centered on a corresponding hole of the side flanges 21, 22 of the seat mounting rail.
• This insert 18 is a one-piece piece made of hard metal material. Preferably, it is made of titanium, steel, Invar or from an aluminum alloy.
• the insert is not made of a single piece but comprises at least one flange 20 of hard metal material attached to a hollow main body 19 of composite material or plastic material reinforced with fiber. carbon.
• the assembly of the flange (s) 20 on this hollow main body (19) may optionally be produced by means of an adhesive layer, of the epoxy type, for example.
• This flange has an external surface comprising toothing elements 23.
• the toothing is preferably made annularly on the outer face the flange 20 so as to cooperate with a washer 24 made of a ductile material such as aluminum for example.
• This washer 24 has an opening for the passage of the fixing member 16 and is placed between the outer surface of the flange 20 and the panel support 17.
• Figure 3 shows an enlarged sectional view of the fixation of the light panel of Figure 2 on its support.
• the elements of Figure 3 bearing the same references as the elements described in Figure 2 represent the same objects.
• a piece of ductile material 24 is placed in a housing 25 made in the panel support 26.
• This panel support 26 is for example a cross member.
• this piece of ductile material 24 is associated with the hollow main body 19 by deformation of the face of this ductile material in contact with the hollow main body 19.
• the hollow main body 19 may have a cylindrical outer surface having raised elements. These raised elements provide additional surfaces for the transmission of forces to the core of the sandwich structure. They include as an example a spiral. Alternatively, it may be an alternation of recesses and projections, these projections having a section of square, rectangular or any other suitable form.
• the fixing device of the invention advantageously allows, once the connection is made, a transfer of forces exerted in the plane of the panel in the support structure without biasing the fastener.
• This transfer of forces makes it possible to drill holes in the support structure with diameters much greater than the diameters of the fasteners, so as to be compatible with manufacturing tolerances and possibly to allow the interchangeability of light panels.

Landscapes

• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• Aviation & Aerospace Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Connection Of Plates (AREA)
• Body Structure For Vehicles (AREA)
• Electrochromic Elements, Electrophoresis, Or Variable Reflection Or Absorption Elements (AREA)
• Fastening Of Light Sources Or Lamp Holders (AREA)
• Led Device Packages (AREA)
• Floor Finish (AREA)

Priority Applications (8)

Applications Claiming Priority (2)

Publications (1)

Family

ID=36263746

Family Applications (1)

Country Status (11)

Cited By (3)

Families Citing this family (38)

Citations (3)

Family Cites Families (19)

• 2005
  • 2005-09-28 FR FR0552927A patent/FR2891325B1/fr not_active Expired - Fee Related
• 2006
  • 2006-09-27 AT AT06831233T patent/ATE441034T1/de not_active IP Right Cessation
  • 2006-09-27 US US12/088,369 patent/US8220222B2/en active Active
  • 2006-09-27 WO PCT/FR2006/050946 patent/WO2007036673A1/fr not_active Ceased
  • 2006-09-27 EP EP06831233A patent/EP1929159B1/fr not_active Not-in-force
  • 2006-09-27 JP JP2008532840A patent/JP5067890B2/ja not_active Expired - Fee Related
  • 2006-09-27 CN CN2006800357845A patent/CN101273207B/zh not_active Expired - Fee Related
  • 2006-09-27 BR BRPI0616725-0A patent/BRPI0616725A2/pt not_active IP Right Cessation
  • 2006-09-27 CA CA2623240A patent/CA2623240C/fr not_active Expired - Fee Related
  • 2006-09-27 DE DE602006008809T patent/DE602006008809D1/de active Active
  • 2006-09-27 RU RU2008116617/11A patent/RU2401949C2/ru not_active IP Right Cessation

Patent Citations (3)

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