Patent ID: 8712227

Claim:
A self-regulating fluid conduit system for an aircraft configured to protect against icing, the self-regulating fluid conduit system comprising: an elongated first self-regulating fluid conduit segment having a first segment end and a second segment end, the first self-regulating fluid conduit segment comprising: a first inner hose configured to conduct a fluid; and a first heating device comprising a first PTC-fabric heating element that is integrated in the first self-regulating fluid conduit segment and includes a first resistance that changes substantially linearly in a temperature range between negative 63° Celsius and positive 80° Celsius; wherein each one of the first segment end and the second segment end has a connection of the same type; and an elongated second self-regulating fluid conduit segment having a third segment end and a fourth segment end, the second self-regulating fluid conduit segment comprising: a second inner hose configured to conduct a fluid; and a second heating device comprising a second PTC-fabric heating element that is integrated in the second self-regulating fluid conduit segment and includes a second resistance that changes substantially linearly in the temperature range between negative 63° Celsius and positive 80° Celsius; wherein each one of the third segment end and the fourth segment end has a connection of the same type as the first segment end and the second segment end of the first self-regulating fluid conduit segment; and a connecting element configured to mechanically and electrically connect any one of the first segment end and the second segment end of the first self-regulating fluid conduit segment to any one of the third segment end and the fourth segment end of the second self-regulating fluid conduit segment.