System for Deicing and/or Defogging an Aircraft Surface, Method for Controlling Same, and Aircraft Equipped with Same

• US 20080258010A1
• Filed: 09/20/2006
• Published: 10/23/2008
• Est. Priority Date: 09/23/2005
• Status: Active Grant

• Current Assignee: Airbus Operations (European Aeronautic Defence and Space Company EADS NV)
• Original Assignee: Airbus France
• Inventors: Leon, Joseph, Vilain, Jean-Yves
• Granted Patent: US 8,612,067 B2
• Time in Patent Office: Days
• US Class Current: 244/134F
• CPC Class Codes: B64D 15/12 by electric heating electric heating elements in general H05B

Abstract

The invention concerns a system for deicing and/or defogging an aircraft surface (4) comprising: a temperature sensor (5) located proximate said surface (4) and adapted to generate a temperature information (TPT); a computer (20) adapted to generate a control information (CMD) based on the temperature information (TPT) and to transmit the control information (CMD) over a computer network (18) of the aircraft; an electric power supply system (8) located in the electrical center of the aircraft (18) and comprising a switch (12) adapted to be switched based on the control information (CMD); a heating element (6) located proximate said surface (4) and electrically powered via said switch (12). The invention also concerns a method for controlling such a system.

Claims

1. A system for deicing and/or defogging an aircraft surface, characterized by:

a temperature sensor (5) situated close to the said surface (4) and capable of generating a temperature information stream (TPT);

a calculator (20) capable of generating a control information stream (CMD) from the temperature information stream (TPT) and of sending the control information stream (CMD) over an information network (18) of the aircraft;

an electric supply system (8) situated in the central electric system of the aircraft, capable of receiving the control information stream (CMD) over the information network (18) and comprising a switch (12) capable of being switched as a function of the control information stream (CMD);

a heating element (6) situated close to the said surface (4) and supplied electrically via the said switch (12).

2. A system according to claim 1, characterized in that the electric supply system (8) comprises a microprocessor (14) connected to the information network (18).

3. A deicing system according to claim 2, characterized in that the microprocessor (14) is capable of receiving the control information stream (CMD) and of commanding the switch (12) to switch as a function of the control information stream (CMD).

4. A system according to claim 3, characterized in that the microprocessor (14) commands the switch (12) to switch by means of a signal whose cyclic ratio depends on the control information stream (CMD).

5. A system according to one of claims 1 to 4, characterized in that the calculator (20) receives the temperature information stream (TPT) of the sensor (5) via an analog link.

6. A deicing system according to one of claims 1 to 5, characterized in that the calculator is included in a heating management module (20) connected to the information network (18).

7. A system according to claim 6, characterized in that the heating management module (20) comprises means for monitoring the sensor (5) that are capable of sending an alarm over the information network (18) in the case of dysfunctioning of the sensor (5).

8. A system according to one of claims 1 to 7, characterized in that the electric supply system (8) is equipped with means (15) for measuring the current (I) passing through the switch (12) and capable of generating an alarm over the information network (18) if a threshold is crossed.

9. A system according to claim 7 or 8, characterized by an alarm management system (22) connected to the information network (18) and capable of causing display of a signal on a display device (24) of the cabin in the case of reception of the said alarm.

10. A system according to one of claims 1 to 9, characterized in that the electric supply system (8) is equipped with means (15) for measuring the current (I) passing through the switch (12) and capable of commanding the switch (12) to open if a threshold is crossed.

11. A system according to one of claims 1 to 10, characterized in that the information network (18) is of the Ethernet type.

12. A system according to one of claims 1 to 11, characterized in that the said surface is a window (4) of a pilot'"'"'s cabin of the aircraft.

16. An aircraft, characterized in that it is equipped with a system according to one of claims 1 to 12.

13. A method for controlling a system for deicing and/or defogging an aircraft surface (4), characterized by the following steps:

determining (E104) a control information stream (CMD) on the basis of a temperature information stream (TPT) received from a temperature sensor (5) situated close to the said surface (4);

sending (E106) the control information stream (CMD) over an information network (18) of the aircraft;

receiving (E106) the control information stream (CMD) by an electric supply system (8);

switching (E110), as a function of the control information stream (CMD), a switch (12) situated in the central electric system of the aircraft and through which there is electrically supplied a heating element (6) situated close to the said surface (4).

14. A method according to claim 13, characterized by a step (E106) in which the sensor (5) sends the temperature information stream (TPT) via an analog link.

15. A method according to claim 13 or 14, characterized in that, the said switching being commanded by a microprocessor (14) of the electric supply system (8), it comprises a step (E108) in which the said microprocessor (14) receives the control information stream (CMD).

17. An aircraft, characterized in that it is equipped with a means capable of implementing a method according to one of claims 13 to 15.