A system for the state monitoring of a fiber composite structure, in particular of an aircraft or spacecraft, include a fiber composite structure; a multiplicity of state sensors which, on and/or in the fiber composite structure, are configured to detect state data of the fiber composite structure an energy store configured to store electrical energy for the supply of the state sensors in a rechargeable manner; an energy generating layer configured, on the fiber composite structure, to generate the electrical energy for the supply of the state sensors; and a data processing unit configured for wireless data communication with the state sensors for the further processing of the detected state data.

A method for forming a geomembrane liner testable for leaks by securing adjacent panels together with the conductivity of the lower surface of an overlying panel broken along a line adjacent the panel overlapping edge, and the overlapping edges sealed along the line. A heat welder has slots for the overlapping panel edges, with a heated wedge between the slots and having a projection to break the conductivity of the overlying panel bottom surface as it passes the wedge. The slots merge to press the liner edges together to heat weld them along the line of broken conductivity as the welder is moved along the panel edges.

A method for forming a geomembrane liner testable for leaks by securing adjacent panels together with the conductivity of the lower surface of an overlying panel broken along a line adjacent the panel overlapping edge, and the overlapping edges sealed along the line. A heat welder has slots for the overlapping panel edges, with a heated wedge between the slots and having a projection to break the conductivity of the overlying panel bottom surface as it passes the wedge. The slots merge to press the liner edges together to heat weld them along the line of broken conductivity as the welder is moved along the panel edges.

Embodiments of the invention relate to a sealing element for thermally connecting thermoplastic materials along a bent or curved contour, including a plurality of flat support substrates with a front face and a rear face, the substrates having at least one heating element on the front face, and including a contoured element which has a front face in the shape of the contour to be sealed, wherein the rear face of the support substrates is secured to the front face of the contoured element and/or the front face of the support substrates is secured to the rear face of the contoured element.

Systems, methods, and apparatus for using aircraft bondline embedded current sensors to determine a lightning damage index are disclosed. A method of predicting lightning strike damage to at least one type of aircraft involves sensing, with at least one current sensor node embedded in at least one type of aircraft, induced current. The method further involves generating, with at least one current sensor node, at least one current signal representative of the induced current. Also, the method involves determining, electromagnetic density data associated with at least one region of at least one type of aircraft by using at least one current signal. Further, the method involves creating an index that provides a numeric representation for predicted lightning strike damage to at least one type of aircraft based on the electromagnetic density data, dimensions of at least one type of aircraft, and design features of at least one type of aircraft.

Embodiments of the invention relate to a sealing element for thermally joining thermoplastic materials along a bent or cambered contour, including a plurality of heating elements which each has a flat carrier substrate with a front and a rear side, at least one heating circuit being disposed on the front side, and at least one contour element which has a bent or cambered contour, the heating elements being disposed on the contour element.