Method for bonding two fiber composite components with each other to form a fiber composite structure

A method for bonding two thermoset fiber composite components with each other to form a fiber composite structure of an aircraft, comprising:

• integrating conductive fibers underneath a bonding surface of at least one of the two thermoset fiber composite components, each conductive fiber comprising a carbon fiber coated with an electrically insulating coating, the conductive fibers running along the bonding surface and protruding at least at conductive fiber ends from a respective thermoset fiber composite component;
• arranging the two thermoset fiber composite components against each other at respective bonding surfaces of the two fiber thermoset composite components;
• passing an electric current through the conductive fibers by electrically contacting the conductive fibers at the protruding conductive fiber ends so that the respective thermoset fiber composite component is heated at the bonding surface to a curing temperature of the thermoset fiber composite component;
• and
• joining the two thermoset fiber composite components with each other at the respective bonding surfaces via secondary bonding, co-bonding and/or co-curing at the curing temperature, thereby forming the fiber composite structure,
• wherein the two thermoset fiber composite components are formed with a matrix material at least at one of the respective bonding surfaces curable under application of the curing temperature.