EP3055124A1 - Structure de construction légère et procédé de fabrication d'une structure de construction légère - Google Patents

Structure de construction légère et procédé de fabrication d'une structure de construction légère

Info

Publication number
EP3055124A1
EP3055124A1 EP14786643.8A EP14786643A EP3055124A1 EP 3055124 A1 EP3055124 A1 EP 3055124A1 EP 14786643 A EP14786643 A EP 14786643A EP 3055124 A1 EP3055124 A1 EP 3055124A1
Authority
EP
European Patent Office
Prior art keywords
wall
fiber
fiber composite
lightweight
face
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP14786643.8A
Other languages
German (de)
English (en)
Inventor
Johann SCHWÖLLER
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Scalewings Ip GmbH
Original Assignee
Schwoller Johann
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Schwoller Johann filed Critical Schwoller Johann
Publication of EP3055124A1 publication Critical patent/EP3055124A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
    • B29D99/0014—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings provided with ridges or ribs, e.g. joined ribs
    • B29D99/0017—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings provided with ridges or ribs, e.g. joined ribs with filled hollow ridges
    • 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
    • B29C63/00—Lining or sheathing, i.e. applying preformed layers or sheathings of plastics; Apparatus therefor
    • B29C63/0026—Lining or sheathing, i.e. applying preformed layers or sheathings of plastics; Apparatus therefor an edge face with strip material, e.g. a panel edge
    • 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
    • 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
    • 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
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
    • B29D99/0021—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings provided with plain or filled structures, e.g. cores, placed between two or more plates or sheets, e.g. in a matrix
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B64C3/182—Stringers, longerons
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B64C3/185—Spars
    • 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
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
    • B29D99/0014—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings provided with ridges or ribs, e.g. joined ribs
    • 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
    • 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 lightweight structure and a method for producing a lightweight structure, in particular for aircraft.
  • the sandwich inner layers such shell elements or shell structures are usually made very thin and can not usually take over the pressure, tensile or shear loads due to the narrow web width of the reinforcing element. Therefore, in this area in the shell usually no core material can be inserted to allow a direct bond with the outer layer.
  • additional layers of fiber composite material must be introduced, which increases the weight. This recess of the sandwich material in this area as well as the incorporation of the reinforcing material require a significant overhead in production.
  • US 2008/0295334 A1 discloses a method in which two structural elements, such as, for example, a frame element and a skin of an aircraft wing, are connected to one another.
  • a U-shaped rail is placed on the frame member in the region of the end face, which extends laterally a piece over the side surfaces of the frame member addition.
  • This rail thus forms a wide surface, which is used for connection to the second structural elements, the connection being made by gluing.
  • WO 2012/091695 A1 discloses a similar connecting device which has tabs projecting laterally on a structural component in order to provide the largest possible connecting surface to a further structural component.
  • US 2004/0051005 A1 describes a fastening device for fastening metal parts to the surface of a composite panel.
  • the connector has L- and U-shaped fiber reinforced layers which are nested and bonded together and to the composite panel to provide a receptacle for the metal part.
  • US 2005/0064134 A1 discloses an apparatus, a system and a method for connecting components with a serrated tension connection.
  • This train connection comprises a base element and a serrated element.
  • the train connection is screwed to a plate-shaped component and / or glued and connected to a drawstring. Tensile forces are absorbed by the plate-shaped component via the tension connection and introduced into the tension band.
  • a lightweight structure In aircraft construction of small to medium-sized aircraft, however, a lightweight structure has prevailed, are used in which Strukturwandungen consisting of a first fiber outer layer, an intermediate layer and a second outer fiber layer, wherein in the region of the end faces of the Strukturwandungen elongated slivers between the opposite Fiber outer layers are used.
  • the elongated fiber slivers serve to absorb tensile forces along the longitudinal direction of the structure walls.
  • the invention has for its object a lightweight structure and a method for producing a lightweight structure, in particular for aircraft to create, with which a very stable, lightweight lightweight structure can be efficiently produced.
  • the lightweight construction structure has at least one substantially plate-shaped structural transformation and an enveloping element.
  • the structure wall and the cladding element are each formed from a fiber composite material.
  • the structure wall is formed from a first outer fiber layer, an intermediate layer and a second outer fiber layer.
  • a U-shaped connection profile or reinforcing profile is arranged, which has a base wall and two side walls.
  • the base wall is at the end face of the structure wall and the side walls of the U-shaped connection profile are disposed adjacent the outer surfaces of the first and second outer fiber layers and bonded to the fiber outer layers.
  • the sheath element has a fiber composite reinforcement band.
  • the sheath element and the structure walls are connected to one another, wherein the structure wall bears with its end face against the fiber composite reinforcement band.
  • the lightweight structure according to the invention can be produced much more simply and quickly, since the fiber composite reinforcement band can be laminated on the covering element in a planar manner , This is much easier than arranging and bonding elongated fibers between the outer fiber layers of the structure wall.
  • the fiber-reinforced band can basically be arbitrarily wide and arbitrarily strong in order to absorb corresponding tensile forces.
  • the structure wall itself does not have to absorb tensile forces, but merely to keep the enveloping element in its position and preferably two opposing enveloping elements at a distance.
  • the U-shaped connection profile serves to establish a firm connection between the enveloping element and the structure wall. Since only forces in the plane of the structure wall are introduced into the structure wall and the proportion of forces in the longitudinal direction of the structure wall is low, since the tensile forces are absorbed by the fiber composite reinforcement strip in the longitudinal direction of the structure wall, the surface of the base wall of the structural wall is sufficient to connect the structure walls to the cover element U-shaped connection profile. There are no additional on the outer surfaces of the structure wall projecting connecting portions necessary. It is also sufficient that one or more U-shaped connection profiles are provided only in sections on the end face of the structure wall.
  • the structure wall can initially be produced almost completely with an automatic process.
  • the joining of the structure wall to the enveloping element takes place by bringing the not yet cured fiber composite reinforcing strip under pressure into contact with the structure wall.
  • the fiber composite reinforcement tape consists of reinforcing fibers embedded in a matrix material.
  • the not yet cured matrix material connects to the end face of the structure wall and in particular to the or the U-shaped connection profile.
  • additional adhesive This is particularly expedient if the structure wall is not at right angles to the enveloping element, so that a wedge-shaped gap between the end face of the structure wall and the enveloping element is filled.
  • the U-shaped connection profile is preferably formed from a fiber composite material.
  • the fiber direction of this element preferably runs diagonally to the longitudinal extent of the U-shaped connection profile, so that the remaining tensile / compressive forces can be optimally introduced into the structural components from the longitudinal reinforcement band.
  • the fiber composite reinforcement band preferably extends parallel to the structure wall over the entire length (or even only a part of the length of the structural component) or width of the enveloping element.
  • the U-shaped connection profile can also be formed from two L-shaped connection profiles, overlapping the region of the end face of the structure wall, each with a leg for forming the base.
  • U-shaped connection profiles may be arranged in sections on the end face of the structure wall.
  • the U-shaped connection profiles may be arranged at a distance from each other on the end face of the structure wall.
  • the U-shaped connection profile can be slotted in the region of the side wall, so that it is flexible in the region of the base. As a result, any spatial shapes and in particular curves can be formed with the end faces of the structure walls. Since the fiber composite reinforcement tape is flexible prior to bonding to the cover member, the fiber composite reinforcement tape may generally be formed into any shape before it is cured. The lightweight structure according to the invention thus allows any shape.
  • the structure walls are made by laminating and curing the interlayer with the two outer fiber layers and then cut into a desired shape. It is thus possible to produce large sheets of fiber composite materials from which a plurality of structural walls are cut.
  • the cutting of the structural walls is preferably fully automatic with appropriate cutting or milling machines.
  • the structure walls can be made so easily with any contour or shape.
  • the structural wall is preferably made by using as interleaf a filling material, such as foam, wherein at least one hole is cut into the filling material into which a reinforcing body of a material having a higher strength than the filling material is inserted. and then the filler together with the reinforcing body with the two outer fiber layers is laminated and cured.
  • a filling material such as foam
  • This aspect of the present invention can also be used for other lightweight structures in which the structural wall is not connected to a U-shaped connection profile according to the invention with an enveloping element.
  • the insertion of reinforcing body into the filling material prior to lamination of the fiber outer layers thus constitutes an independent idea of the invention.
  • the filling material may be made of a foam, honeycomb or tubular material or another material which transmits the transverse forces from one outer fiber layer to the other fiber material. Can transfer outer layer and thus reliably keeps the fiber outer layer at a distance.
  • a reinforcing body a wood body, a metal body, in particular an aluminum body, and / or a fiber composite body may be used.
  • the fiber composite body in turn, consists of a filling material, which is coated with fiber outer layer. The thickness of such a fiber composite body corresponds to the thickness of the filling material so that it can be introduced flush with the surface.
  • a plurality of structural walls are assembled into a skeleton.
  • the framework is then connected to the sheath element and at least one fiber composite reinforcement band is substantially parallel to a structural transformation.
  • the individual structural walls need not be firmly connected to each other. It suffices a plug connection or a temporary adhesive connection.
  • the corners of the connectors can be glued after fixing with prefabricated angle profiles.
  • the strength of the entire lightweight structure is achieved by the connection at several points of the Hüllettis with one and preferably the plurality of structural walls.
  • the present invention is concerned with the displacement of the tensile and compressive forces from a component subjected to bending stress, e.g. a wing spar, a reinforcing rib or e.g. a rib in the wrapping element.
  • a component subjected to bending stress e.g. a wing spar, a reinforcing rib or e.g. a rib in the wrapping element.
  • a component subjected to bending stress e.g. a wing spar, a reinforcing rib or e.g. a rib in the wrapping element.
  • the most important point of the present invention is the displacement of the tensile and compressive forces from the spar edge region or from the structure wall into the shell or the enveloping element.
  • the structure wall can be milled out of a sandwich panel material with a CNC milling machine to save time and money.
  • the structure wall essentially only transfers the shear forces from top to bottom and absorbs low shear forces. In contrast to the prior art, however, the structure wall absorbs almost no tensile and compressive forces of the bending load.
  • the tensile and compressive forces are absorbed by the fiber composite reinforcement tape which is laminated to the inner layer of the airfoil or wrapper.
  • Width of the webbing is a direct force on the wrapping possible.
  • the enveloping element can therefore pass through without interruption.
  • a fiber composite reinforcement band in the region between the end face of the structure wall and in particular between the end face and the base wall of the connection profile.
  • the spar or the rib can be milled from a sandwich plate material.
  • the tensile and compressive forces are absorbed by a train-pressure band, but this is within the U-profile.
  • This tape can be introduced when gluing the U-profile on the milled component.
  • a variant is also that are cut from a plate with longitudinal fibers strips, which are glued when gluing the U-profile between the U-profile and the plate edge.
  • Such a structure wall can be arranged at locations in a lightweight structure, on which no fiber composite reinforcement tape is provided on the enveloping element or in which the structure wall is not applied to an enveloping element.
  • This method also offers the possibility that even curved edges can be executed in this way.
  • the tension-pressure band is here relatively thin or executed in several thinner layers, the U-profile is cut straight or V-shaped at the side edges. As a result, the U-profile can be set to radii. Due to the thin design of the prefabricated tension-compression band, this will be placed around the radii. With smaller radii, the tape can also be inserted as a wet laminate.
  • FIGS. show in: 1 is a fragmentary side sectional view of a lightweight structure according to the invention:
  • FIG. 2 shows an enveloping element of the lightweight structure
  • Figure 3 is a fragmentary side sectional view of another embodiment of a lightweight structure according to the invention.
  • FIG. 4 shows a central wing section of an aircraft in a perspective view
  • Figure 5 is a side wing portion of an aircraft in a perspective view
  • FIG. 6 shows an embodiment of a plate-shaped structure wall of a lightweight structure in a perspective view
  • FIG. 7 shows the side wing section from FIG. 5 with a fiber reinforcement band in a perspective view
  • Figure 8 is a detail view of Figure 7 at a transition from one structure wall to another structure wall with offset;
  • Figure 9 shows a detail of Figure 7 with fiber composite reinforcing tape on the upper side and underside applied to the lightweight structure
  • FIG. 10 shows a further detail view from FIG. 7.
  • This lightweight structure 8 comprises at least one reinforcing component or a plate-shaped structural wall 4 and at least one envelope element 1 (FIGS. 1 and 2).
  • the plate-shaped structure wall 4 is formed from a first outer fiber layer 4b, an intermediate layer 4a and a second outer fiber layer 4c. At an end face 6 of the plate-shaped structure wall 4, a U-shaped reinforcing or connecting profile 5 is arranged.
  • the U-shaped connection profile 5 has a base wall 9, and two side walls 10.
  • the U-shaped connecting profile 5 is formed such that the two side walls relative to the base wall 9 are inclined at a predetermined angle of approximately 2 ° or 5 ° or 10 ° to each other.
  • the U-shaped connection profile 5 has a certain bias by means of which the connection profile 5 holds itself after the application of its own position on the structure wall 4.
  • the power flow extends from the sheath element 1 via the base wall 9 and via the side walls 10 into the fiber outer layers 4b, 4c.
  • the U-shaped connecting profile 5 has reinforcing fibers extending diagonally to its longitudinal extension. These lead to an optimal force transmission of shear forces on the structure wall.
  • the connecting profile 5 is arranged in a partial region of the end face 6 of the structure wall 4 such that the base wall 9 and the side walls 10 abut respectively on the end face 6 and on the intermediate layer 4a, the first outer fiber layer 4b and the second outer fiber layer 4c and be fixed to these by means of an adhesive connection.
  • the sheath element or sheath element 1 is likewise formed from a first outer fiber layer 1b, an intermediate layer 1a and a second outer fiber layer 1c.
  • a reinforcing strip or a fiber composite reinforcing strip 2 is arranged.
  • the fiber composite reinforcement band 2 is preferably formed from a carbon fiber composite.
  • the structure wall or the U-shaped connection profile 5 arranged thereon is connected to the fiber composite reinforcement band 2.
  • the fiber composite reinforcing tape 2 is twice or three or four, or five or six times wider than the base wall 9 of the U-shaped connecting profile. 5
  • a fiber belt 7 whose construction is similar to the fiber composite reinforcement strip 2 can additionally be provided in the region between the end face 6 of the structure wall 4 and the base wall 9 of the connection profile 5 (FIG. 3).
  • a structure wall 4 with such a fiber belt 7 can be provided in areas of the lightweight structure 8, in which no fiber reinforcement band is arranged and still provide a certain draft stability.
  • the wing sections 1 1, 12 comprise a skeleton 13, which is formed from interconnected structure walls 4.
  • the frame 13 of the central wing section 11 is formed of four transversal beams 14 extending transversely to the direction of flight and which are connected to one another via a plurality of longitudinal struts 15 extending in the longitudinal direction of the aircraft (FIG. 4).
  • the longitudinal beams 15 are formed such that at their ends to be connected to the transverse bars 14 reinforcing body made of wood are used.
  • the reinforcing bodies 16 are formed with pin-shaped connecting elements 17.
  • reinforcing bodies 16 made of wood are also used in the transverse struts 14, which have corresponding recesses 18 for receiving the connecting elements 17 of the longitudinal struts.
  • angle profiles 21 are arranged in the recesses 18 for fixing the connecting elements 17 (FIG. 6).
  • walls 4 and / or the reinforcing body 16 further functional and / or reinforcing body, such as metal bushings can be used.
  • metal body may be embedded in aluminum as reinforcing body 16 in the cross members 14 and the longitudinal beams.
  • the skeleton 13 of the lateral wing section 12 is formed of two transversely extending to the flight direction transverse beams 14, which are connected to each other via a plurality of longitudinal longitudinal direction extending in the longitudinal direction of the aircraft 15 ( Figure 5).
  • the longitudinal beams 15 are formed such that at their ends to be connected to the transverse bars 14 reinforcing body made of wood are used.
  • the reinforcing bodies 16 are designed as pin-shaped connecting elements 17.
  • reinforcing bodies 16 made of wood are also used in the transverse struts 14, which have corresponding recesses 18 for receiving the connecting elements 17 of the longitudinal struts.
  • a structural wall 4 of the central and the lateral wing section 1 1, 12 is described by way of example (FIG. 6), on the end face 6 of which connecting profiles 5 are applied in sections.
  • receiving recesses 22 are formed in the end faces 6 of the structure wall.
  • the angle profiles 21 for connecting the structure wall 4 to a further structure wall 4 are shown on an end face 6 of the structure wall.
  • the angle profiles 21 are glued to the respective adjacent structure walls 4.
  • the angle profiles are preferably formed from a fiber-reinforced composite material.
  • connection region of the lateral wing section 12 will be described in more detail (FIG. 5).
  • landing flap 19 and an aileron 23, and a corresponding actuating mechanism 20 are integrated.
  • the cross members 14 corresponding reinforcing body 16 made of wood, plastic or metal.
  • the aileron 23 is attached to other cross members 14 in the same manner, these further transverse members 14 are arranged with offset to the above-described cross member 14 on which the landing flap 19 is hinged.
  • an end portion of this cross member 14 is provided with a reinforcing body 16 made of metal.
  • the fiber composite reinforcing tapes 2 are arranged on the longitudinal and transverse spars, in particular on the U-shaped connecting profiles 5 arranged thereon (FIGS. 7 to 10).
  • the fiber composite reinforcing tapes 2 are arranged along all transverse struts 14 (FIGS. 7 and 8 show, by way of example only, one fiber composite reinforcing strip) and along the longitudinal struts 15, fiber composite reinforcing tapes 2 are provided in the longitudinal struts 15 arranged at the edge and in severely loaded structural walls 4.
  • These fiber composite reinforcing tapes 2 are arranged on a lower half-shell of the enveloping element 1 and are correspondingly connected via an adhesive bond with the upper and lower end faces 6 of the transverse struts 14 and the connecting profiles 4 arranged thereon.
  • the connection between the bonding profiles and the fiber composite reinforcing tapes can also be made by the resin of a fiber composite reinforcement tape with which the bonding profiles are brought into contact as long as the fiber composite extension tape has not yet cured. If the laminate of the fiber composite tape is already hardened when it is glued to the structural element, this must be pretreated accordingly for the bond with the structural element.
  • the fiber composite reinforcing tape 2 is first laminated to the inside of the Hüllelements 1, which is why this can not only be straight but also bent ( Figures 7 and 8).
  • the fiber composite reinforcement band 2 does not have to be arranged exactly parallel to the structural wall 4, since the bonding preferably takes place only via the reinforcement profile 4.
  • the fiber reinforcement band can pass through several structure walls without interruption
  • the fiber composite reinforcement band 2 can extend over smaller regions outside the structure walls 4 (FIGS. 8 to 10).
  • the fiber composite reinforcement band 2 can protrude beyond the end of the structural walls 4 (FIGS. 9 and 10).
  • the fiber composite reinforcement band 2 can follow the curved contour of the enveloping element 1 (FIG. 7).
  • the structure wall 4 of the lightweight construction structure 8 according to the invention is produced almost completely by an automatic process. It is provided that initially as a spacer 4a, a filler, such. As foam is used. This liner 1 a is initially in plate-like shape.
  • the structure wall 4 is to have reinforcing bodies 16 later, at least one hole or recess is cut, drilled or milled into the filling material 4a. Subsequently, in the hole, a reinforcing body 16 made of wood, such as. B. birch plywood or poplar plywood used. In addition, it can be provided that in the intermediate layer 4a or in the or the reinforcing body 16 more body, such. As a metal bushing made of aluminum, to be used. For this purpose, a recess is already made in the production of the reinforcing body, e.g.
  • the intermediate layer 4a is laminated with the first outer fiber layer 4b and the second outer fiber layer 4c and cured.
  • intermediate layer, reinforcing element intermediate products
  • structural wall intermediate products
  • the enveloping element 1 or a lower wall of the enveloping element 1 are formed from a fiber composite. To form this fiber composite, a first shape is provided. In the finished state of the lightweight construction structure it is provided that the fibers in the enveloping element 1 preferably extend diagonally to the end face 6 of the structure walls 4.
  • the fiber composite reinforcing tape 2 is made of reinforcing fibers embedded in a matrix material.
  • the joining of the structure wall 4 with the enveloping element 1 takes place by applying the structure wall to the not yet cured fiber composite reinforcing strip under pressure.
  • the not yet cured matrix material connects to the end face of the structure wall and in particular to the U-shaped reinforcement profiles or the U-shaped reinforcement profile.
  • an upper wall of the enveloping element 1 is placed on the lower wall and the structure wall (s) with the reinforcing strip arranged thereon and together with its shape.
  • a plurality of structural walls are assembled to form a skeleton, in which case the skeleton is then connected to a lower half shell of the enveloping element. Subsequently, an upper half-shell of the enveloping element is placed and the entire lightweight structure 8 hardens. This is preferably done in two superimposed forms.
  • the advantage of the method is that the structure walls can be cut from sheet material.
  • the connection profiles are then glued to the structure walls.
  • the fiber composite reinforcing tape is laminated.
  • the structure walls are then glued to the end face of the connection profile, preferably on the not yet cured reinforcing tape ( Figure 1). It can also be provided that adhered to the front side of the structure wall of the fiber belt 7 and then the connection profile is glued over or it is first glued the fiber belt 7 in the connection profile and this glued together with the connection profile on the front side of the structure wall.
  • This structure wall which is closed off in such a manner on the end face and then tensioned, can then be bonded to a further structural wall or to the enveloping element 7.
  • a structural wall 4 with fiber belt 7 is preferably provided at exposed positions which are not covered by a fiber reinforcing strip can be completely covered by the U-shaped connection profile 5 or only in certain regions and in particular at the end regions of the fiber belt 7.
  • the attachment of such fiber belts is very simple and can be carried out quickly Fiber straps are fixed during assembly and it ensures a good force transmission into the body of the structure wall.
  • an aircraft assembly (assembly for aerial sports equipment, aircraft and other aircraft), ie a component for an aircraft, air sports equipment, and other aircraft, such as a helicopter, in particular a fuselage, a wing, a side, elevators, ailerons, to produce a landing flap or a tail unit made of a lightweight structure according to the invention by means of the method according to the invention.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Architecture (AREA)
  • Civil Engineering (AREA)
  • Structural Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Manufacturing & Machinery (AREA)
  • Laminated Bodies (AREA)

Abstract

L'invention concerne une structure de construction légère (8) qui comporte au moins une paroi de structure (4) sensiblement en forme de panneau et un élément d'enveloppe (1). La paroi de structure et l'élément d'enveloppe sont formés chacun à partir d'un matériau composite à base de fibres. La paroi de structure (4) est constituée d'une première couche fibreuse extérieure (1b) et d'une deuxième couche fibreuse extérieure (1c). Dans au moins une zone partielle de la face frontale (6) de la paroi de structure (4) est disposé un profilé d'assemblage en U (5) qui comporte une paroi de fond (9) et deux parois latérales (10). La paroi de fond (9) est disposée en appui sur la face frontale (6) de la paroi de structure (4) et les parois latérales (10) du profilé d'assemblage en U (5) sont disposées en appui sur les faces extérieures de la première et de la deuxième couche fibreuse extérieure (1b, 1c) et reliées auxdites couches fibreuses extérieures (1b, 1c).
EP14786643.8A 2013-10-08 2014-10-08 Structure de construction légère et procédé de fabrication d'une structure de construction légère Withdrawn EP3055124A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
AT506472013 2013-10-08
PCT/EP2014/071575 WO2015052257A1 (fr) 2013-10-08 2014-10-08 Structure de construction légère et procédé de fabrication d'une structure de construction légère

Publications (1)

Publication Number Publication Date
EP3055124A1 true EP3055124A1 (fr) 2016-08-17

Family

ID=51753199

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Application Number Title Priority Date Filing Date
EP14786643.8A Withdrawn EP3055124A1 (fr) 2013-10-08 2014-10-08 Structure de construction légère et procédé de fabrication d'une structure de construction légère

Country Status (3)

Country Link
US (1) US20160311188A1 (fr)
EP (1) EP3055124A1 (fr)
WO (1) WO2015052257A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113398411B (zh) 2014-09-16 2024-04-19 费雪派克医疗保健有限公司 头帽组件和具有头帽的接口组件
US10589837B2 (en) * 2016-02-08 2020-03-17 Bell Helicopter Textron Inc. Spar for a composite wing structure

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT398064B (de) * 1992-07-01 1994-09-26 Hoac Austria Flugzeugwerk Wr N Kunststoff-verbundprofil, insbesondere flügelholm für den flugzeugbau
US6520706B1 (en) * 2000-08-25 2003-02-18 Lockheed Martin Corporation Composite material support structures with sinusoidal webs and method of fabricating same
US6863767B2 (en) 2001-08-23 2005-03-08 Lockheed Martin Corporation Paste-bond clevis joint
US7238409B1 (en) * 2002-05-23 2007-07-03 Rohr, Inc. Structural element with rib-receiving member
US6749155B2 (en) 2002-09-13 2004-06-15 The Boeing Company Composite assembly with integrated composite joints
US7244487B2 (en) 2003-04-24 2007-07-17 Lockheed Martin Corporation Apparatus, system, and method of joining structural components with a tapered tension bond joint
DE102005034621B3 (de) 2005-07-19 2007-01-11 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verbundstruktur und Verfahren zur Herstellung einer Verbundstruktur
DE102006041654A1 (de) * 2006-08-24 2008-03-20 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verfahren und Vorrichtung zur Herstellung eines Faserverbundwerkstoff-Bauteils
US8082667B2 (en) 2007-05-31 2011-12-27 The Boeing Company Apparatus and methods for securing a first structural member and a second structural member to one another
WO2012091695A1 (fr) 2010-12-28 2012-07-05 Bell Helicopter Textron Inc. Système d'assemblage à charge multidirectionnelle

Non-Patent Citations (2)

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None *
See also references of WO2015052257A1 *

Also Published As

Publication number Publication date
WO2015052257A1 (fr) 2015-04-16
US20160311188A1 (en) 2016-10-27

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