<p>The method involves removing the damaged area of fiber composite component, and forming a splice (2) in the region of the removed damaged area. The Z-pins (5) formed as spring steel wires are inserted into the fiber composite component (1) in the region of the splice. A repair-fiber semi-finished material (6) is inserted to the splice such that the repair fiber semi-finished material is draped around the Z-pins and the fiber bundle of repair fiber semi-finished material is not damaged by the Z-pins. The repair fiber semi-finished material is cured.</p>
申请公布号
EP2602098(A1)
申请公布日期
2013.06.12
申请号
EP20120195841
申请日期
2012.12.06
申请人
DEUTSCHES ZENTRUM FUER LUFT- UND RAUMFAHRT E.V.
发明人
HOLZHUETER, DIRK;HUEHNE, CHRISTIAN;KOLESNIKOV, BORIS;STEFFEN, OLAF