Abstract: An aircraft heating system wherein the heater includes a haven (34) constructed from dielectric layers (40-50), conductive lanes (60), bus bars (70), and strips (80-150). Façade sections (41, 51, 61) of the dielectric layers (40-50) and the lanes (60) form the primary heating surface (31). The strips (80-150), along with sections (42, 52, 62) of the layers/lanes, form havens (34) for harbor sections (72) of the bus bars (70).

Abstract: An aircraft electric power supply system (10) for supplying electric power to onboard electric devices (20) during flight. To reduce the devices' power draw, the electric power is supplied via modulation at an increment-percentage that is determined by present conditions. An optimum portfolio can be established for the electrical devices (20) collectively, this portfolio being selected in accordance with an energy-management criterion or other aircraft objectives.

Abstract: An aircraft heating system wherein the heater includes a haven (34) constructed from dielectric layers (40-50), conductive lanes (60), bus bars (70), and strips (80-150). Façade sections (41, 51, 61) of the dielectric layers (40-50) and the lanes (60) form the primary heating surface (31). The strips (80-150), along with sections (42, 52, 62) of the layers/lanes, form havens (34) for harbor sections (72) of the bus bars (70).

Abstract: An aircraft electric power supply system (10) for supplying electric power to onboard electric devices (20) during flight. To reduce the devices' power draw, the electric power is supplied via modulation at an increment-percentage that is determined by present conditions. An optimum portfolio can be established for the electrical devices (20) collectively, this portfolio being selected in accordance with an energy-management criterion or other aircraft objectives.

Abstract: An all solid state timer-controller for the timed, sequential application of electrical current to loads within a circuit at high amperage, the circuit finding utility in the application of electrical current to de-icers employed aboard aircraft.

Abstract: In a circuit having an electro-mechanical relay, the contacts of which are subject to arcing, bridging across the electro-mechanical relay in a manner configured to begin conducting electrical current around the electro-mechanical relay prior to closing the electro-mechanical relay and to continue conducting electrical power around the electro-mechanical relay for a predetermined time after the onset of separation of contacts of the electro-mechanical relay pursuant to discontinuance of current flow through the electro-mechanical relay. An optical coupler is provided to ascertain a current flow through the relay coil effected to close the electro-mechanical relay contacts, and activates a shunt device in bridging electrical current flow around the electro-mechanical relay. The shunt device is provided to be substantially non-load carrying while the electro-mechanical relay is closed. Utility is found in protecting electro-mechanical relay contacts against damage due to arcing.

Abstract: In a circuit having a electro-mechanical relay the contacts of which are subject to arcing, a shunt across the electro-mechanical relay configured to begin conducting electrical current across the electro-mechanical relay prior to closing the electro-mechanical relay contacts and to continue conducting electrical power across the electro-mechanical relay for a predetermined time after the onset of separation of electro-mechanical relay contacts pursuant to discontinuance of current flow through the elecro-mechanical relay. An optical coupler is employed to detect the current flow through the relay coil and activate a shunt device to initiate current flow around the electro-mechanical relay. The shunt device is configured to be substantially non-current load carrying while the electro-mechanical relay is closed. Utility is found in protecting relay contacts against damage due to arcing.