Abstract: An aircraft heating system (100) is provided which can be supplied with DC power from an onboard source (130). The system (100) comprises a heater (150) positioned to provide heat to an aircraft appliance (101), a sensor (160) situated to sense appliance-relevant temperatures, a reporter (170) reporting system faults, and an introducer (180) introducing temperature setpoints. A thermostat (200) integrates circuitries which together manage power supply, control heating, convey sensed temperatures, detect heater and/or sensor faults, and/or perform other advantageous functions.

Abstract: An aircraft heating system (100) is provided which can be supplied with DC power from an onboard source (130). The system (100) comprises a heater (150) positioned to provide heat to an aircraft appliance (101), a sensor (160) situated to sense appliance-relevant temperatures, a reporter (170) reporting system faults, and an introducer (180) introducing temperature setpoints. A thermostat (200) integrates circuitries which together manage power supply, control heating, convey sensed temperatures, detect heater and/or sensor faults, and/or perform other advantageous functions.

Abstract: An aircraft electrical appliance is provided with a ground-fault-interruption device (50) for protecting it in the event of problematic current loss due to, for example, a compromise in electrical insulation. The device (50) has a GFI circuit (60) comprising a current differential determiner (70), a trigger (80) that is activated upon the current differential corresponding to ground-fault situation, and an interrupter (90) that interrupts power supply to the appliance upon the trigger (80) being activated. The GFI circuit (60) is electrically independent of electrical controller components of the appliance, thereby avoiding expensive software configuration and confirmation.

Abstract: A sensing device (10) is provided for sensing whether an electrically-conductive fluid (14) has reached a predetermined level within a container (12). In this device (10), a first electrode (22) is electrically connected to a source (20) and a second electrode (24) is electrically connected to ground. When the electrode gap (26) is filled with the fluid (14), the sensing circuitry causes the electrodes (22, 24) to switch roles as the anode depending upon whether a positive voltage pulse or negative voltage pulse is being received from the source (20).

Abstract: An aircraft heated floor panel (10) comprising a heat-generating layer (20) including an electric heater (52) having current supply lines (54) and a controller (60) which controls the current supplied to the heater (52) via the supply lines (54) to thereby control the heat generated by the layer (20). The controller (60) is integrated into the floor panel (10) whereby the panel has a stand-alone control system which need only be connected to the on-board power source of the aircraft, but can be connected to a main controller for networking or other purposes.

Abstract: An aircraft electrical appliance is provided with a ground-fault-interruption device (50) for protecting it in the event of problematic current loss due to, for example, a compromise in electrical insulation. The device (50) has a GFI circuit (60) comprising a current differential determiner (70), a trigger (80) that is activated upon the current differential corresponding to ground-fault situation, and an interrupter (90) that interrupts power supply to the appliance upon the trigger (80) being activated. The GFI circuit (60) is electrically independent of electrical controller components of the appliance, thereby avoiding expensive software configuration and confirmation.

Abstract: A sensing device (10) is provided for sensing whether an electrically-conductive fluid (14) has reached a predetermined level within a container (12). In this device (10), a first electrode (22) is electrically connected to a source (20) and a second electrode (24) is electrically connected to ground. When the electrode gap (26) is filled with the fluid (14), the sensing circuitry causes the electrodes (22, 24) to switch roles as the anode depending upon whether a positive voltage pulse or negative voltage pulse is being received from the source (20).

Abstract: An aircraft heated floor panel (10) comprising a heat-generating layer (20) including an electric heater (52) having current supply lines (54) and a controller (60) which controls the current supplied to the heater (52) via the supply lines (54) to thereby control the heat generated by the layer (20). The controller (60) is integrated into the floor panel (10) whereby the panel has a stand-alone control system which need only be connected to the on-board power source of the aircraft, but can be connected to a main controller for networking or other purposes.