Deutsches Zentrum Fur Luft-und Raumfahrt E.v.

Deutsche Forschungsanstalt Fur Luft-und Raumfahrt E.v.

Saertex Wagener Gmbh & Co. Kg

Airbus Deutschland Gmbh

Forschungszentrum Karlsruhe Gmbh

Deutsche Forschungsanstalt Fur Luft-und Ramfarht E.v.

Arno Erk Pabsch

Christof Sigle

Matthias Piening

Axel Siegfried Herrmann

Gert Wagener

Markus Kleineberg

Carsten Schoeppinger

Volker Krajenski

Jens Kleffmann

Axel S Herrmann

Lambert Feher

Wilm Felix Unckenbold

A thread or other element for bonding fibers in a fibrous reinforcement for use in a fiber composite is such that it is at least degraded in the course of the production of said fiber composite.

Fiber-reinforced composites and method for the production thereof

A forming jig includes a grid pattern of support walls arranged on a support base and having upper free ends located along an imaginary curved surface, and modular sectional profile members arranged on the walls to enclose a vacuum chamber within the jig. Grooves, channels and air passages between neighboring profile members communicate into the vacuum chamber. The outer surface of the profile members matches the intended inner surface of a structural component to be fabricated using the jig. In the fabrication process, a film is applied to the outer surface to pre-establish a vacuum, the film is removed while simultaneously a vacuum skin is applied, stringer members are set into the grooves, fiber skin layers are laid up, a sealant is applied around the perimeter, a structural shell is vacuumed onto the skin layers, and then this preformed component is removed from the jig, injected with resin unless the skin layers were pre-impregnated with resin, and cured.

Automated fabrication of an integral fiber reinforced composite structural component using a positioning and assembly support

A microwave device for de-icing and keeping areas of hollow body structures free from ice keeps atmospherically exposed leading edges and adjacent areas free of ice by means of a coolant circuit. The surface segments between the adjacent areas are kept free from ice as a result of the effects of a microwave device on the wall of the surface segments and the heating that occurs by the exposure to microwave radiation. A series of consecutive microwave-tight chambers is disposed behind the wall of the exposed area. A microwave source supplies microwaves to the chambers with the aid of a decoupling structure disposed therein, resulting in high/multimode excitation. The waste heat of the microwave sources is collected by means of a coolant circuit and transported to the r areas adjacent the leading edge for permanent heating in order to keep the surfaces free from ice. The microwave sources are cyclically operated.

Microwave device for de-icing, or keeping hollow bodies free from ice and method for the operation of the device

A method for producing sections in sandwich structures of fiber composites is provided, as well as the structures. The method involves shaping sectional cores around a cut-out, applying bands circumferentially along the perimeter of the cut-out, and covering the sectional cores and to circumferential bands, with layers. The sandwich structure is then impregnated with resin.

Method for producing sections in sandwich structures of fiber composites and sections produced accordingly

In a structural element of high unidirectional rigidity, in which unidirectional fiber strands are completely embedded in sheaths and said sheaths are connected to a shell skin and wherein part of the shell skin is in the form of stringers, there is provided an inner division of the cross-section of the shell skin thereby providing the strength of the fibers and the stiffness of the fibers in a direction perpendicular to the skin plane for every direction of loading.

Structural element of high unidirectional rigidity

In a process for producing large-surface structural elements from fiber-reinforced composite materials by resin transfer moulding, a mold (,) that can be evacuated has a dimensionally stable part (,) and an elastically deformable part (,). The mold (,) has connections for injecting a resin mixture and connections to a pressure sink. A fibrous fabric (,) is set into the mold (,). Elongated pipes having a large supporting surface (,) and a cavity (,) that extends in the longitudinal direction of the pipes above the supporting surface (,) are provided on the surface of the fibrous fabric (,) opposite to the dimensionally stable mold part (,) to inject the resin mixture and to ensure the connection with the pressure sink. The supporting surface (,) of the pipes has a narrow slit (,) which extends substantially over the whole length of the pipes and which is in communication over its whole length with the cavity (,). At least one end of the pipes extends outwards through the edges of the elastically deformable and dimensionally stable mold parts and is linked to the resin supply pipe or to the pressure sink. The mold (,) is evacuated down to an inner pressure of less than 50 hPa.

Apparatus for making components of large area by RTM

An aircraft with supporting wings including wing shells with good shear strength made of fibrous composite materials, particularly fiber-reinforced plastics, having members taking up tensile and compressive forces on the inside of the wing shells. The members have unidirectional fibers extending longitudinally of the wing, and fixing elements which can be joined detachably to fuselage attachments are provided on the members at the root end of the wing. Stringers are constructed on the inside of the wing shells and spaced longitudinally of the shells, their fiber component being formed by a fiber layer joined to the fiber layer of the wing shell. Fiber bundles are arranged between spaced stringers as unidirectional stiffening elements. The fiber bundles are embedded in the synthetic resin matrix of the plane load-bearing structure and extend longitudinally of the supporting wing. Groups of three fiber bundles extending adjacent each other are provided, of which the two outer bundles in each case form a loop at the root of the supporting wing to receive a bolt which has to be inserted in the loop perpendicular to the plane of the two fiber bundles. The inner bundle is turned down to form a second loop perpendicular to the first loop to receive a bolt which has to be inserted in and perpendicular to the plane of this loop. Both bolts act as connection members to attachment members on the fuselage.

Aircraft with supporting wings having members for taking up tensile and

In a structural member with large unidirectional rigidities unidirectional fiber bundles are completely embedded in shear resistant sheaths. The shear resistant sheaths are joined to a shear resistant torsion shell made up of skin layers by shear resistant vertical walls. A part of the vertical walls is shaped into stringers. Dividing layers (20) interrupting the passage of tension between adjacent unidirectional fiber bundles (30) are provided between the shear resistant sheaths (31) of the unidirectional fiber bundles (30).

Structural members with large unidirectional rigidities

In a wing with wing shells with good shear strength made of fibrous composite materials, particularly fiber-reinforced plastics, for aircraft, members taking up tensile and compressive forces are attached to the inside of the wing shells. These members have unidirectional fibers extending longitudinally of the wing. Stringers spaced longitudinally of the wing are provided on the inside of the wing shells, their fiber component being formed by a fiber ply joined to the fiber ply of the wing shell. Unidirectional fibre bundles are arranged between spaced stringers, the bundles being embedded with good shear strength in the synthetic resin matrix of the wing shells, extending longitudinally of the wing and having a substantially rectangular cross-section.

Aircraft wing

A rotor blade is made of fiber-reinforced synthetic resin and comprises a moulded core with central, front and rear elements and a foot end fastening element, a unidirectional fiber layer being wound longitudinally of the core, a first cross-binding lying over the fiber layer and a second cross-binding forming a covering for the entire assembly.

Rotor blade

A rotor blade is made of fibre-reinforced synthetic resin and comprises a moulded core with central, front and rear elements and a foot end fastening element, a unidirectional fibre layer being wound longitudinally of the core, a first cross-binding lying over the fibre layer and a second cross-binding forming a covering for the entire assembly.

Growing community of inventors

Braunschweig, Germany

Arno Erk Pabsch