Eurocopter Deutschland Gmbh

Airbus Helicopters Deutschland Gmbh

Steffen Kunze

Wolfgang Buchs

Rainer Suchy

Thomas Unterhauser

Tom Kretschmer

Christian Wellhausen

Gabriele Dreher

Umberto Girard

Thomas Thiess

Andreas Wiers

Matthias Steer

Hermann Spanner

Barbara Hermann

Thessa Gierer

The present invention relates to a method of fabricating a mold core () for making hollow parts () based on a composite material including fibers, fabrics, or textiles together with a resin, the method consisting in mixing a filler material () and a binder material () in order to obtain a uniform mixture of materials, and in solidifying, compacting, and shaping the resulting mixture in order to constitute said core, the method being characterized in that it further consists in introducing into the mixture at least one complementary material () that is expandable under the effect of heat or by applying another physical or chemical principle, and in mixing said materials () in order to obtain a uniform distribution of the complementary material () in the mixture.

Method of fabricating an improved mold core and a mold core obtained by said method

A method of fabricating components () based on fiber-reinforced plastics material, in particular with the help of a wrapped mold core (), includes the following steps: a) fabricating the mold core (); b) wrapping the mold core () with a wrapper () that withstands resin; c) applying fiber semi-finished products () and introducing resin to create the plastics component (); and d) hardening the plastics component () under the effect of temperature; which method is improved by the fact that, under all circumstances, and during hardening in step d), substantial pressure equilibrium is established across the fiber semi-finished product () between ambient pressure (p) and the pressure (p) inside the core. A device is also described.

Fiber-reinforced component fabrication with mold cores

A fuselage structure, particularly an aircraft door () of composite material comprising at least one panel () and at least one beam () mounted to each other and the panel () with the panel () being formed of at least one group of composite layers (). The at least one beam () is provided at least at one of its respective ends () with a flange () suitable for adhesive engagement with the at least one panel (). The at least one group of composite layers () of the panel () is in form locking engagement with this flange () of the beam ().

Fuselage structure made of composite material

An aircraft door arrangement, especially for an airplane, comprising a door; a door frame; a support arm with a pivoting axis on the door side, on which the door is mounted so as to swivel, and a pivoting axis on the frame side, on which the support arm is mounted so as to swivel on the door frame, whereby at least the pivoting axis on the door side is defined by two articulated joints positioned at a distance from each other in the vertical direction of the support arm, of which articulated joints at least one articulated joint has two bearings positioned at a distance from each other in the vertical direction; a pivoting drive that is arranged in the area of the support arm on the door side and that serves to swivel the door; and a driven element that is coupled to the pivoting drive and to the door and that transmits an actuating movement of the pivoting drive to the door. The aircraft door arrangement is characterized in that one of the two bearings of at least one of the articulated joints on the frame side is configured as a pivoting drive mounting to which the pivoting drive is attached.

Aircraft door arrangement

Growing community of inventors

Vagen, Germany

Steffen Kunze