Abstract: A heating system for an aircraft or spacecraft with a control device which includes at least one power line data transmission transceiver and one sensor controller, and at least one remote component which has a sensor element and a heating element, the at least one power line data transmission transceiver being connected to the at least one remote component via a connecting cable, the control device being designed to supply the at least one heating element with power via the connecting cable and the sensor controller being designed to exchange first control signals with the sensor element via the connecting cable.

Abstract: A heating system for an aircraft or spacecraft with a control device which includes at least one power line data transmission transceiver and one sensor controller, and at least one remote component which has a sensor element and a heating element, the at least one power line data transmission transceiver being connected to the at least one remote component via a connecting cable, the control device being designed to supply the at least one heating element with power via the connecting cable and the sensor controller being designed to exchange first control signals with the sensor element via the connecting cable.

Abstract: An adsorption cooling system (1) for an aircraft comprises an evaporator (18), a first adsorber (2), which contains a first adsorption medium for adsorbing an adsorption coolant evaporated in the evaporator (18), and a second adsorber (4), which contains a second adsorption medium for adsorbing the adsorption coolant evaporated in the evaporator (18), the first and the second adsorber (2, 4) being adapted to be operated alternately in an adsorption mode and in a desorption mode, such that one adsorber (2, 4) can adsorb adsorption coolant and the other adsorber (2, 4) can be regenerated.