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

Definitions

• the present invention relates to an aircraft floor panel and an installation for fastening fitting elements comprising such panels.
• the invention relates to an installation for fixing cabin layout elements (seats, offices, ...) in an aircraft.
• Such facilities are known in passenger aircraft, for example, which include at least two spaced-apart seat mounting rails extending longitudinally in a forward / reverse direction of the aircraft. Chassis each having two or more seats to form a span of chairs, can be attached to these mounting rails. Other cabin layout elements such as offices (“galleys”), toilets, ... are fixed on these same rails or on appropriate structural elements if necessary.
• FIG. 1 shows schematically a partial sectional view of a cabin floor of the prior art with a mounting rail 1 of seats.
• Each rail 1 comprises a lower rail element generally having an I-shaped profile, which consists of a lower sole 2, a vertical core 3 and an upper sole 4.
• Stretching upwards from of this upper flange 4 is an upper rail element having a C-shaped section 5 so as to form a slide for fixing the fitting elements and seats in particular.
• the upper sole 4 also comprises flat lateral flanges 6, 7 on which floor panels 8 are mounted.
• the conventional cabin floor covering is composed of composite sandwich floor panels (honeycomb structure). These floor panels 8 which are thin, typically of the order of 10 mm, are fixed by means of bolts on the side flanges 6, 7 of the seat mounting rails.
• a floor covering M for example a carpet, is installed. This floor covering M serves to protect the floor panels from aggression related to travel or any other aggression related to the occupancy of the cabin of the transport vehicle.
• the mounting rails 1 of seats have satisfactory mechanical characteristics to support the efforts corresponding to the elements of arrangement, and seats in particular. However, these mechanical characteristics alone are not sufficient because, as shown in Figure 1, a mounting rail 1 is particularly exposed to corrosion in an aircraft.
• the floor of an aircraft cabin is, in fact, subject to the influence of various corrosive elements such as spilled liquids, condensed moisture or other. We can then observe a rapid degradation of the mechanical characteristics of these rails. Frequent repairs or replacements by qualified operators are then required on aircraft in service.
• the objective of the present invention is therefore to provide a floor panel for a passenger transport vehicle such as an aircraft, simple in design and in its operating mode, economical, presenting a very high mechanical resistance, a high resistance to corrosion while having a minimum mass.
• Another object of the present invention is to have an installation for the attachment of a set of layout elements allowing a great flexibility in the interior design of a passenger transport vehicle.
• the invention relates to a floor panel for a passenger transport vehicle such as an aircraft.
• this panel comprises at least one mounting rail having a longitudinal axis, inserted in the thickness of the panel.
• this floor panel comprises an upper face comprising an elongated opening disposed along the longitudinal axis of the mounting rail to allow the installation of furniture elements and seats in particular, on said rail,
• the panel comprises a core sandwich structure comprising at least two walls respectively disposed on opposite external faces of a honeycomb core, these walls being composite reinforcements, the mounting rail having an I-shaped section; and being inserted into the honeycomb core.
• this mounting rail is made of a material meeting the criteria of mechanical strength and corrosion resistance related to applications in the aeronautical field. This is, for example, titanium or an aluminum alloy.
• the invention also relates to an installation for fixing a set of interior fittings and seats, in particular, in a passenger transport vehicle comprising only a set of substantially parallel transverse beams.
• this installation comprises floor panels as described above, which are assembled to the transverse beams by fastening means of the bolt type.
• the invention relates to an aircraft comprising such an installation for fixing a set of management elements.
• FIG. 1 shows schematically a partial sectional view of a cabin floor of the prior art
• FIG. 2 is a schematic representation of a floor panel for passenger transport vehicle according to one embodiment of the invention, the floor panel being shown in plan view ( Figure 2a)) and in section according to the AA axis of the floor panel ((Fig. 2b));
• FIG. 3 shows schematically a partial sectional view of an installation for fixing development elements in an aircraft according to one embodiment of the invention
• FIG. 2 shows a floor panel for a passenger vehicle according to one embodiment of the invention.
• the floor panel 9 comprises a core sandwich structure comprising at least two walls 10, 11 respectively disposed on opposite outer faces of a honeycomb core 12.
• These walls 10, 11 are composite reinforcements.
• the composites may be chosen from the group, given as a non-limiting example, comprising carbon composites, graphite composites, glass composites, silica composites, silicon carbide composites or any other composite providing the necessary rigidity. while responding to the constraint of low mass related to the aeronautical field.
• the honeycomb core 12 is, for example, made from aramid.
• Aramid fibers have a low flammability, a high tensile strength and a high modulus of elasticity.
• a floor covering 13 for example a carpet, can be installed on the floorboard 9.
• This covering 13 then serves as protection for the floorboards.
• the floor panel 9 comprises a seat mounting rail 14 having a longitudinal axis 15, inserted into the thickness of the panel 9.
• the same panel 9 may, however, comprise two or more rails 14 placed at different positions to allow arrangements accommodations according to the needs of the user.
• the mounting rail 14 comprises a bottom rail section having an inverted T-shape and having a lower flange 16 and a vertical core 17. It also has an upper rail section comprising a pair of flanges 18, 19. These flanges are spaced apart laterally along the longitudinal axis 15 of the mounting rail and each comprise a lip 20, 21. These lips 20, 21 are oriented towards each other to form a slide disposed along the longitudinal axis 15 of the mounting rail. This slide is intended for fixing the elements of arrangement and seat rails, in particular.
• the mounting rail 14 is not limited to this embodiment only for illustrative purposes and may include, for example, a lower rail section 16, 17 having a Q-shaped section.
• the upper face 22 of the floor panel has an elongate opening disposed along the longitudinal axis 15 of the mounting rail to allow attachment of the fitting elements.
• the rail 14 is inserted into the floor panel 9 before assembly of an assembly comprising the core 12 and at least the two walls 10, 11.
• it is made in the thickness of the core 12 a recess adapted to receive at least the lower rail section, then covers the mounting rail 14 on at least a portion of its outer surface of a film of unpolymerized glue.
• the recess has a shape suitable for receiving the portion of the mounting rail 14 for insertion into the thickness of the floor panel 9.
• the upper rail section also comprises two lateral flanges 24, 25 each having at least one hole for the passage of a fastening means 26 of the panel on a crossbar.
• This fastening means 26 is, for example, a bolt made of steel or titanium.
• the panel 9 thus comprises inserts 27 for interfacing the fastening means 26 and the sandwich structure and thus distribute the bonding forces that are local on a larger volume of the sandwich structure.
• Each of these inserts 27 comprises a hollow cylindrical body for the passage of a fastening means 26 of the bolt type. It further comprises a flange or wide head resting on the outer surface of the lower face of the floor panel 9 to distribute the forces on a larger area of the underside of the panel.
• An adhesive layer is advantageously disposed between the flange and the outer surface of the bottom wall of the floor panel 9 so as to ensure the tightness of the sandwich structure.
• the insert 27 is assembled to the sandwich structure so that the main axis of the hollow cylindrical body is centered on a corresponding hole of the lateral flanges 24, 25.
• This insert 27 is metallic and preferably made from an alloy. aluminum, titanium or Invar.
• Figure 3 shows a partial sectional view of an installation for fixing of elements of arrangement in a particular embodiment of the invention. This installation aims to allow the interior of an aircraft cabin.
• This installation comprises a set of transverse beams 28 of substantially parallel constant height and floor panels 9 as previously described assembled to these transverse beams 28 by fastening means 26 of the bolt type. These fixing means 26 are advantageously placed at each corner of the panel (FIG 2A). In addition, to ensure greater rigidity of the mounting rail 14, fastening means 26 are preferably provided at the side flanges 24, 25 of the fastening rail.
• a seal 29 is preferably placed between these panels and the upper sole 30 of the transverse beam 28.
• a seal 29 is advantageously placed between these floor panels 9 and the upper flanges of two transverse beams 28 successive ( Figure 3).
• This seal 29 may be metallic, composite or possibly rubber.
• Each of these transverse beams 28 is fixed to the fuselage of the aircraft.
• These transverse beams 28 are made, for example, of carbon fiber-reinforced organic matrix composite (CFRP).
• CFRP carbon fiber-reinforced organic matrix composite
• a space is provided in the lower part of the aircraft, generally used as baggage hold with or without the use of containers.
• the creation of this space requires a separation with the floor structure which is obtained by cladding panels 32.
• These cladding panels 32 are fixed on profiles 33 connected to the lower part of the transverse beams 28.
• each of the transverse beams 28 supports a set of profiles 33 to create this space for the passage of the systems 31.
• These trim panels 32 form the ceiling of the compartment compartment.
• the systems 31 are arranged between the covering panels 32 and the lower portions of the transverse beams 28.
• These profiles 33 may be made of light alloy. They are for example aluminum.

Landscapes

• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• Aviation & Aerospace Engineering (AREA)
• Body Structure For Vehicles (AREA)
• Laminated Bodies (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=36691792

Family Applications (1)

Country Status (9)

Families Citing this family (26)

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• 2005
  • 2005-09-28 FR FR0552918A patent/FR2891239B1/fr not_active Expired - Fee Related
• 2006
  • 2006-09-25 JP JP2008532755A patent/JP5246943B2/ja active Active
  • 2006-09-25 US US12/088,335 patent/US8544794B2/en not_active Expired - Fee Related
  • 2006-09-25 CN CN2006800357563A patent/CN101272948B/zh not_active Expired - Fee Related
  • 2006-09-25 WO PCT/EP2006/066711 patent/WO2007036508A1/fr active Application Filing
  • 2006-09-25 EP EP06793817A patent/EP1937551A1/fr not_active Withdrawn
  • 2006-09-25 CA CA2620759A patent/CA2620759C/fr not_active Expired - Fee Related
  • 2006-09-25 RU RU2008116627/11A patent/RU2413652C2/ru not_active IP Right Cessation
  • 2006-09-25 BR BRPI0616719-5A patent/BRPI0616719A2/pt not_active IP Right Cessation

Non-Patent Citations (2)

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