Patent ID: 8612067
Filing Date: 2013-12-17
Classification: B64D

Abstract:
1. A system for deicing and/or defogging an aircraft surface, comprising: an electric supply system situated in a central electric system of the aircraft; a calculator situated in an avionics bay of the aircraft; an information network connecting the electric supply system and the calculator; a temperature sensor situated close to the surface and configured to generate a temperature information stream; the calculator being configured to generate a control information stream from the temperature information stream and to send the control information stream over the information network of the aircraft; the electric supply system being configured to receive the control information stream over the information network and including a switch configured to be switched as a function of the control information stream; and a heating element situated close to the surface and supplied electrically via the switch, wherein the information network is an AFDX network, wherein the calculator stores in advance a plurality of correspondence tables that include a temperature setpoint, the control information stream is obtained as a function of the temperature information stream and the temperature setpoint based on the correspondence tables, and wherein the electric supply system includes a microprocessor that connects to the information network, the microprocessor is configured to receive the control information stream, determine a cyclic ratio with which the switch must be alternately opened and closed to approach the temperature setpoint by determining the cyclic ratio that releases a desired heating power at the heating element in accordance with the control information stream, and command the switch to switch as a function of the control information stream, by way of a signal that has the determined cyclic ratio.