Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
  • B64D27/02—Aircraft characterised by the type or position of power plants
  • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
  • B64D27/18—Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings

Definitions

• the present invention relates to the embodiment of the primary structures of aircraft engine masts perfected in that the number of parts constituting them is reduced and in that the mass of said parts itself is reduced by the use of composite materials.
• the aircraft engine masts are the link between the engines and the wing of the aircraft.
• the masts further comprise a secondary structure complementary to the primary structure but not resuming efforts.
• This secondary structure provides the function of aerodynamic fairing between the engine leading edges and the wing, provides protection and segregation of systems such as hydraulic, electrical, fuel, air conditioning or other systems passing through the mast and supports engine covers and nacelles.
• the primary structure generally consists of a box consisting of a front upper spar, a rear upper spar, a lower spar, ribs and two side panels.
• the structural links are generally made on the one hand with the wing by three fasteners, a front attachment, a rear attachment and a fastener upper called spigot and on the other hand with the motor by two fasteners, a front attachment disposed at the tip of a pyramid and a rear attachment.
• the pyramid allows the engine to advance relative to the wing.
• the fasteners are constituted by fittings which are separate parts of the side members and panels.
• These panels are further provided with stiffeners in the longitudinal and transverse direction.
• the present invention aims to make this construction less complex and less cumbersome and to do so concerns mainly a primary structure of aircraft engine mast, characterized in that it comprises monobloc composite panels in replacement of metal spars and metal panels said composite panels comprising a draping of the fibers orienting the latter in crossed directions so as to integrate in the thickness of the skin of the composite panels a mesh replacing longitudinal and transverse stiffeners of the longitudinal members and metal panels.
• FIG. 1 an exploded view of a primary mast structure of the prior art
• Figure 2 an exploded view of a structure according to the invention
• Figure 3 a side view of a side panel of the structure of Figure 2
• FIGS. 4A, 4B, 4C details of FIG. 3
• Figure 5 a schematic view of an assembly of panels according to the invention
• Figure 6 a general view of a motor attached to an aircraft wing.
• FIG. 6 The fixing of the engines under the wings of aircraft make use of a supporting mast.
• a fixation is shown schematically in FIG. 6 where it is represented on engine 9, the fairing 19 of the engine fan, the wing 10, the fairing 11 of the engine support mast and the primary structure 20 of the mast.
• the primary structure 20, blackened in the figure, comprises the fasteners of the engine to the wing and has the role of supporting the engine, to pass the traction forces of the engine and to avoid the transmission of vibrations.
• This structure has attachment points of the engine and attachment points to the wing.
• FIG. 1 A primary structure of the prior art is shown in FIG. 1
• Figure 1 The primary structure of Figure 1 consists of upper longitudinal beams 2 and 4 lower metal and side panels 1, 3 metal. Inside the box reinforcement frames ensure the rigidity of the structure.
• the metal longitudinal members are provided with longitudinal stiffeners 13 and transverse 14.
• the parts made are complex machined metal parts and the mass of the assembly remains important.
• the primary aircraft engine mast structure 9 comprises one-piece composite panels 1a, 2a, 3a, 4a instead of metal longitudinal members 1, 2 and metal panels 3, 4 of the primary structure of the prior art.
• the composite panels according to the invention are made according to a lay-up 12 of the fibers orienting the latter in crossed directions so as to integrate in the thickness of the skin of the panels a mesh replacing the longitudinal stiffeners 13 and transverse 14 of the metal side members.
• FIG. 3 more particularly shows the composite side panels 1a, 3a of the structure in relation to the forces which are applied in particular at the inspection holes 8a, 8b, 8c, the draping of the composite side panels comprising reinforcement zones around it. visit holes.
• the draping of these composite panels is a quasi-isotropic draping (25/25/25/25) to ensure a recovery of homogeneous efforts in the material of the panels.
• the primary structure of the aircraft engine mast comprises attachment fittings for the engine to the mast and for attaching the mast to the wing 10 of the aircraft.
• These fittings 6, 7, 71, 61 are in the prior art made of inserts on the primary structure.
• fittings 7a which are mast attachments on the wing 10 are integrated with the composite side panels 1a, 3a.
• This embodiment provides greater cohesion to the box constituting the primary structure, the forces of the fasteners applying directly to the panels.
• at least one upper spar 2a is provided with flanges 16, 17 for connection with the side panels 1a, 3a.
• flanges 16, 17 are directed towards the outside of the structure so that the fixing of the upper and lateral panels is easily done by the outside of the box. In addition, this method of attachment increases the rigidity of the assembly.
• the upper spar 2a is a composite spar made by a strongly oriented type of draping (50/20/20/10) offering a high longitudinal rigidity.
• the draping of said upper spar 2a is reinforced in zones 18 of introduction of forces, in particular in areas adjacent to the fittings made in the side panels.
• the front fixing of the engine is carried out by a fitting located at the end of a pyramid 5a, support of the front attachment 6 of the mast to the engine 9.
• At least the beams of the pyramid are made of composite materials.
• the invention is not limited to the examples shown and in particular the rear attachment fitting 71 between the primary mast structure and the wing can also be integrated with the side panels.

Landscapes

• Engineering & Computer Science (AREA)
• Aviation & Aerospace Engineering (AREA)
• Connection Of Plates (AREA)
• Moulding By Coating Moulds (AREA)
• Laminated Bodies (AREA)
• Body Structure For Vehicles (AREA)

Priority Applications (5)

Applications Claiming Priority (2)

Publications (1)

Family

ID=36177705

Family Applications (1)

Country Status (9)

Families Citing this family (11)

Citations (3)

Family Cites Families (16)

• 2005
  • 2005-08-05 FR FR0552439A patent/FR2889505B1/fr not_active Expired - Lifetime
• 2006
  • 2006-07-13 CN CNA2006800280805A patent/CN101233047A/zh active Pending
  • 2006-07-13 WO PCT/EP2006/064240 patent/WO2007017339A1/fr not_active Ceased
  • 2006-07-13 RU RU2008108513/11A patent/RU2008108513A/ru not_active Application Discontinuation
  • 2006-07-13 EP EP06777772A patent/EP1910166A1/fr not_active Ceased
  • 2006-07-13 US US11/997,834 patent/US20090294579A1/en not_active Abandoned
  • 2006-07-13 JP JP2008524468A patent/JP2009502642A/ja active Pending
  • 2006-07-13 BR BRPI0614230-3A patent/BRPI0614230A2/pt not_active IP Right Cessation
  • 2006-07-13 CA CA002616068A patent/CA2616068A1/fr not_active Abandoned

Patent Citations (3)

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