The method includes the step of positioning the sheets in an at least partially overlapping relationship. The method continues with the step of inserting a rivet that has a height through an overlapping area of the sheets. The method proceeds with the step of, with the rivet at a temperature in the range of 15-30° Celsius, collapsing the rivet between a pair of ramming surfaces to shorten the rivet and partially expand the rivet outwardly to lock the rivet with the sheets. The entire method results in a very strong connection between the sheets and with a great durability at a low cost.

The method includes the step of positioning the sheets in an at least partially overlapping relationship. The method continues with the step of inserting a rivet that has a height through an overlapping area of the sheets. The method proceeds with the step of, with the rivet at a temperature in the range of 15-30° Celsius, collapsing the rivet between a pair of ramming surfaces to shorten the rivet and partially expand the rivet outwardly to lock the rivet with the sheets. The entire method results in a very strong connection between the sheets and with a great durability at a low cost.

Apparatus and methods for installing composite rivets are disclosed. One disclosed method comprises: inserting a composite rivet blank comprising a composite material into a hole in a part; heating the composite rivet blank using Joule heating while the composite rivet blank is in the hole; and then finishing the composite rivet blank.

A tool configured to join at least two material layers, of which at least one material layer is in the form of a metal material layer, by a pin. The tool includes a driving-in device which drives the pin through the at least two material layers to be joined, and a welding device which, after the driving-in of the pin, welds at least one first section of the pin to the at least one metal material layer.

A tool configured to join at least two material layers, of which at least one material layer is in the form of a metal material layer, by a pin. The tool includes a driving-in device which drives the pin through the at least two material layers to be joined, and a welding device which, after the driving-in of the pin, welds at least one first section of the pin to the at least one metal material layer.

A method for joining together different components or different sections of a single component, wherein at least one of the components is a thermoplastic fiber composite component, by using a threaded fastener. Heat is used for softening the thermoplastic fiber composite component to be joined together with the threaded fastener. A joined-together fiber composite component of a vehicle, aircraft or spacecraft, can be obtained by the disclosed method.

A method for joining together different components or different sections of a single component, wherein at least one of the components is a thermoplastic fiber composite component, by using a threaded fastener. Heat is used for softening the thermoplastic fiber composite component to be joined together with the threaded fastener. A joined-together fiber composite component of a vehicle, aircraft or spacecraft, can be obtained by the disclosed method.

A coupling member head includes a holder configured to hold a coupling member at an end portion on a coupling target member side in an axial direction and configured to approach or separate from a coupling target member, a pair of electrodes, tips of the electrodes being positioned closer to the coupling target member side than a coupling member holding region of the holder, and a retraction mechanism configured to move the electrode to a radial outside of the holder when the holder approaches the coupling target member.

A coupling member head includes a holder configured to hold a coupling member at an end portion on a coupling target member side in an axial direction and configured to approach or separate from a coupling target member, a pair of electrodes, tips of the electrodes being positioned closer to the coupling target member side than a coupling member holding region of the holder, and a retraction mechanism configured to move the electrode to a radial outside of the holder when the holder approaches the coupling target member.

A method for connecting two aircraft components composed of thermoplastic composite material by a rivet. The two aircraft components are arranged, in sections, areally on one another, before bores in the two aircraft components are expanded by a mandrel element such that the bores, after the expansion, form one continuous bore for receiving the rivet. Here, the two aircraft components are locally warmed by the mandrel element such that, during the expansion of the bores, the components are thermoplastically deformed. The mandrel element is inserted through the first bore into the second bore. The rivet is introduced into the continuous bore. A system for carrying out the method is also disclosed.