Method for manufacturing a fibre composite component, fibre composite component, and structural component for an aircraft or spacecraft

Patent metadata

Field	Value
Publication number	US-2016101576-A1
Application number	US-201414485143-A
Country	US
Kind code	A1
Filing date	Sep 12, 2014
Priority date	Sep 16, 2013
Publication date	Apr 14, 2016
Grant date	—

Abstract

A method for manufacturing a fibre composite component is disclosed. A single-piece foam body or the parts of a multi-part foam body having at least one recess which is open towards a first side of the foam body are prepared and positioned. A rigidifying element for the backing structure or a preform or first semi-finished product for forming the rigidifying element is arranged in the recess at least in portions. A skin portion or a second semi-finished product for forming the skin portion is provided, and brought into contact, in regions, with the foam body on the first side thereof and with the rigidifying element. The skin portion or second semi-finished product and the rigidifying element or preform or first semi-finished product in contact therewith are processed further in such a way that a fibre composite component is obtained in which the skin portion and the rigidifying element are interconnected.

First claim

1 . A method for manufacturing a fibre composite component, which comprises a skin portion and a backing structure for rigidifying the skin portion, the method comprising:
preparing and positioning a single-piece foam body or the parts of a multi-part foam body, which comprises at least one recess which is open towards a first side of the foam body; prior to, during or after the positioning of the foam body or the parts thereof, arranging a rigidifying element for the backing structure or a preform or first semi-finished product for forming the rigidifying element in the recess at least in portions, such that the rigidifying element or preform or first semi-finished product is placed against the foam body at least in portions; providing the skin portion or a second semi-finished product for forming the skin portion; bringing the skin portion or second semi-finished product into contact, in regions, with the foam body on the first side thereof and with the rigidifying element or preform or first semi-finished product, causing the skin portion or second semi-finished product to be placed against the foam body at least in portions and the rigidifying element or preform or first semi-finished product to be positioned relative to the skin portion or second semi-finished product; and further processing the skin portion or second semi-finished product and the rigidifying element or preform or first semi-finished product in contact therewith such that a fibre composite component is obtained in which the skin portion and the rigidifying element are interconnected.

2 . The method according to claim 1 , wherein at least one surface portion of the foam body on the first side thereof is shaped in a manner corresponding to a shape, predetermined for the finished fibre composite component, of a region of the skin portion.

3 . The method according to claim 1 , wherein the rigidifying element is arranged in the recess as a composite component which comprises strengthening fibres, which are embedded in a solidified matrix material.

4 . The method according to claim 1 , wherein:
one or more layers of a fibre formation pre-impregnated with a matrix material with is not cured or not completely cured is arranged in the recess at least in portions as a first semi-finished product; or wherein the preform is formed using a fibre formation pre-impregnated with a matrix material which is not cured or not completely cured, and is arranged in the recess at least in portions; or wherein one or more layers of a dry fibre formation are arranged in the recess at least in portions as a first semi-finished product, and the first semi-finished product is soaked with a curable matrix material by injection during further processing; or wherein the preform is formed using a dry fibre formation, the preform is arranged in the recess of the foam body at least in portions in a dry state, and the preform is soaked with a curable matrix material by injection during further processing.

5 . The method according to claim 1 , wherein:
a fibre formation pre-impregnated with a matrix material which is not cured or not completely cured is brought into contact in regions with the first side of the foam body and with the rigidifying element or preform or first semi-finished product as a second semi-finished product; or wherein a dry fibre formation is brought into contact in regions with the first side of the foam body and with the rigidifying element or preform or first semi-finished product as a second semi-finished product, and the second semi-finished product is soaked with a curable material by injection during further processing.

6 . The method according to claim 4 , wherein the further processing comprises curing the matrix material of the first semi-finished product or preform and/or curing the matrix material of the second semi-finished product, the matrix material in particular being cured under the effect of increased pressure and/or increased temperature.

7 . The method according to claim 1 , wherein at least part of the foam body is connected to the skin portion and/or rigidifying component during further processing.

8 . The method according to claim 1 , wherein the foam body or part thereof is provided with a separating film in regions on the surface thereof, to prevent the foam body or the part thereof from connecting to the skin portion and/or the rigidifying element, in particular being glued to the skin portion and/or the rigidifying element.

9 . The method according to claim 1 , wherein after the further processing, material-removing machining is carried out on the foam body on a side of the foam body remote from the skin portion.

10 . The method according to claim 9 , wherein the foam body is removed in regions during the material-removing machining in such a way that a recess is formed which reaches as far as the skin portion, and in that a further rigidifying element is subsequently arranged in the recess and connected to the skin portion by additional connection elements.

11 . The method according to claim 1 , wherein the foam body is removed in regions during the material-removing machining in such a way that regions of the foam body which are in contact with the skin portion and/or the rigidifying element are left as additional mechanically supporting components of the fibre composite component and/or for acoustically and/or thermally insulating the fibre composite component.

12 . The method according to claim 9 , wherein during the material-removing machining the foam body is provided with at least one recess or at least one groove for receiving non-structural system components of an aircraft or spacecraft, in particular components and/or lines for electrical power supply or data processing or data transfer or lines and/or components of a hydraulic system or an air-conditioning or ventilation system or a fuel system or a water/wastewater system.

13 . The method according to claim 9 , wherein the foam body is provided, by way of the material-removing machining, with at least one access recess, which makes access possible to the rigidifying element from the side of the foam body remote from the skin portion.

14 . The method according to claim 1 , wherein after the further processing, and if material-removing machining is subsequently carried out on the foam body preferably after this machining, an internal lining for an internal region, in particular for a passenger cabin, of an aircraft or spacecraft is attached, in particular glued flat, to the foam body or to a foam component formed by regions left behind of the foam body.

15 . The method according to claim 1 , wherein a material for forming a structurally supporting cover layer is applied to surface regions of the foam body on a side of the foam body remote from the skin portion, in particular a fibre formation impregnated with matrix material which is not cured or not completely cured, which is subsequently cured, preferably under the effect of increased pressure and/or increased temperature, to form the structurally supporting cover layer.

16 . A fibre composite component manufactured by a method comprising:
preparing and positioning a single-piece foam body or the parts of a multi-part foam body, which comprises at least one recess which is open towards a first side of the foam body; prior to, during or after the positioning of the foam body or the parts thereof, arranging a rigidifying element for the backing structure or a preform or first semi-finished product for forming the rigidifying element in the recess at least in portions, in such a way that th

Assignees

• Airbus Operations Gmbh

Inventors

• Joern Paul

Classifications

• B64C1/12

  Construction or attachment of skin panels · CPC title

• B32B5/18

  characterised by features of a layer {of} foamed material · CPC title

• B29C70/30 Primary

  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 · CPC title

• B29C70/68 Primary

  by incorporating or moulding on preformed parts, e.g. inserts or layers {, e.g. foam blocks (mould constructions therefor B29C33/12; joining preformed parts by moulding B29C65/70)} · CPC title

• B29C70/84

  by moulding material on preformed parts to be joined {(joining plastic parts by moulding B29C65/70)} · CPC title