Resistive-inductive de-icing of aircraft flight control surfaces

• US 9,457,909 B2
• Filed: 04/25/2013
• Issued: 10/04/2016
• Est. Priority Date: 04/25/2013
• Status: Active Grant

• Current Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Ribarov, Lubomir A., Gieras, Jacek F.
• Primary Examiner(s): MCFALL, NICHOLAS A
• Application Number:
  US13/870,403
• Publication Number:
  US 20140319278A1
• Time in Patent Office: 1,258 Days
• US Class Current: 1/1
• CPC Class Codes: B64D 15/00 De-icing or preventing icing on exterior surfaces of aircraft motor vehicles specially adapted for carrying de-icing equipment B60P
• CPC Class Codes: B64D 15/12 by electric heating electric heating elements in general H05B
• CPC Class Codes: B64D 15/14 controlled cyclically along length of surface

Abstract

Embodiments of the disclosure include a de-icing system for an aircraft. The de-icing system includes a plurality of resistive-inductive heating elements inserted adjacent to a flight control surface and a controller configured to provide a supply current to each of the plurality of resistive-inductive heating elements. Each of the plurality of resistive-inductive heating elements produces an electromagnetic field normal to the flight control surfaces and resistive heat in response to the supply current. The electromagnetic field induces an eddy current in the flight control surface.

Claims

1. A de-icing system for an aircraft comprising:

a flexible substrate incorporating a matrix of a plurality of resistive-inductive heating elements adapted to be carried by a flight control surface;

said matrix configuration of the plurality of resistive-inductive heating elements including an m×

n matrix with the m resistive-inductive heating elements connected in series and the n resistive-inductive heating elements in parallel;

said matrix configuration of the plurality of resistive-inductive heating elements being arranged such that adjacent resistive-inductive heating elements have opposite magnetic polarity;

a controller configured to provide a supply current to each of the plurality of resistive-inductive heating elements, wherein the controller may receive current from a plurality of current sources;

wherein each of the plurality of resistive-inductive heating elements produces an electromagnetic field and resistive heat in response to the supply current and wherein the electromagnetic field normal to the flight control surfaces induces an eddy current in the flight control surface;

and wherein the electromagnetic field produced by each of the plurality of resistive-inductive heating elements is strong enough to totally penetrate the flight control surface.

2. The de-icing system of claim 1, further comprising:

one or more sensors configured to monitor the ambient conditions of the flight control surface, wherein the controller is configured to receive information from the one or more sensors.

3. The de-icing system of claim 2, wherein the controller is configured to responsively control the supply current provided to each of the plurality of resistive-inductive heating elements based on the information received from the one or more sensors.

4. The de-icing system of claim 1, wherein the controller may receive current from a source external to the aircraft.

5. The de-icing system of claim 1, wherein the controller may receive current from both an on-board source or external source which includes one or more of an electric supply of power from an auxiliary power unit, an engine generator, a storage battery, and an external power (EP) ground cart.

6. The de-icing system of claim 5, wherein the de-icing system may be activated on the ground while the aircraft is stationary and the engines are turned off by using electric supply power from the auxiliary power unit.