Abstract: Fluid conduit segments are provided that include, but are not limited to integrated heating systems for protection against freezing. To this effect PTC-fabric heating elements are provided that are integrated in the fluid conduit segments and that in the negative temperature range include, but are not limited to a PTC-temperature-dependent resistance. The heating system thus provides a higher output in the negative temperature range and a lower output in the positive temperature range, i.e., the heating limits itself until temperature equalization has been reached.

Abstract: Fluid conduit segments are provided that include, but are not limited to integrated heating systems for protection against freezing. To this effect PTC-fabric heating elements are provided that are integrated in the fluid conduit segments and that in the negative temperature range include, but are not limited to a PTC-temperature-dependent resistance. The heating system thus provides a higher output in the negative temperature range and a lower output in the positive temperature range, i.e., the heating limits itself until temperature equalization has been reached.

Abstract: The invention is directed to a device for heating lock elements in aircraft, in particular to prevent icing up of door locks and emergency slide locks. The object of the invention, to find a novel possibility for heating lock elements in aircraft, particularly for preventing icing of door locks and emergency slide locks, which reliably eliminates icing of the lock elements without requiring frequent maintenance and repair due to high mechanical, chemical and thermal stresses, is met according to the invention in that a base body which is mounted in the floor of the aircraft and contains an insert profile has an integrated, inserted sliding plate and in that the sliding plate is hollowed out from the bottom over a large surface to receive a heating foil, wherein the heating foil is embedded in the hollowed out recess in a sandwich-type construction, and the sliding plate is hermetically sealed from the bottom.

Abstract: The invention is directed to a device for heating lock elements in aircraft, in particular to prevent icing up of door locks and emergency slide locks. The object of the invention, to find a novel possibility for heating lock elements in aircraft, particularly for preventing icing of door locks and emergency slide locks, which reliably eliminates icing of the lock elements without requiring frequent maintenance and repair due to high mechanical, chemical and thermal stresses, is met according to the invention in that a base body which is mounted in the floor of the aircraft and contains an insert profile has an integrated, inserted sliding plate and in that the sliding plate is hollowed out from the bottom over a large surface to receive a heating foil, wherein the heating foil is embedded in the hollowed out recess in a sandwich-type construction, and the sliding plate is hermetically sealed from the bottom.

Abstract: An aircraft floor heating panel is constructed for mechanical strength and to meet special heating requirements next to a door in an aircraft. The panel has a lightweight core. Each surface of the core is first covered with at least one carbon-fiber reinforced composite layer for protection against deterioration. Each carbon fiber layer in turn is covered by a glass fiber reinforced composite layer for mechanical strength. A foil heater is arranged inside the composite panel coextensive with at least a portion of the panel area. A heat distributing metal plate covers the panel as an upper step-on surface. A heat insulating layer is bonded to the panel opposite the heat distributing metal plate. A triple heat control is provided for an increased safety against fire hazards.

Abstract: An aircraft floor heating panel is constructed for mechanical strength and to meet special heating requirements next to a door in an aircraft. The panel has a lightweight core. Each surface of the core is first covered with at least one carbon-fiber reinforced composite layer for protection against deterioration. Each carbon fiber layer in turn is covered by a glass fiber reinforced composite layer for mechanical strength. A foil heater is arranged inside the composite panel coextensive with at least a portion of the panel area. A heat distributing metal plate covers the panel as an upper step-on surface. A heat insulating layer is bonded to the panel opposite the heat distributing metal plate. A triple heat control is provided for an increased safety against fire hazards.

Abstract: A heater arrangement such as a heating band is especially suitable for providing freeze protection for water pipes in an aircraft, because it is resistant to vibrations, greatly varying temperatures, low pressure conditions, and aggressive chemicals, while achieving a reliable seal against the penetration of moisture or liquid into the areas of the electrical connections. The heater arrangement includes a heating element with a heater band matrix and heating conductors extending therein, as well as a fluoropolymer protective layer thereover. A connecting element or a terminating element is connected to exposed ends of the heating conductors. To seal the area at which the connecting element or terminating element is connected to the heater arrangement, a fluoropolymer is extruded over this area, and/or a fluoropolymer molded part is used as a connection block or end cap. The fluoropolymer materials are thermally fused together to form a continuous integral seal.