System for detecting ice on an aircraft

• US 6,166,661 A
• Filed: 01/22/1999
• Issued: 12/26/2000
• Est. Priority Date: 01/22/1999
• Status: Expired due to Term

• Current Assignee: Rockwell Collins, Inc. (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Rockwell Collins, Inc. (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Woytassek, Mark A., Anderson, Roger D.
• Primary Examiner(s): Lee, Benjamin C.
• Application Number:
  US09/235,542
• Time in Patent Office: 704 Days
• Field of Search: 244/134 R, 244/134 F, 340/968, 340/962, 340/691, 702/172, 342/26, 342/59, 342/115
• US Class Current: 340/962
• CPC Class Codes: B64D 15/20 Means for detecting icing or initiating de-icing

Abstract

An aircraft ice detector system includes a radar system. The radar system provides a radar signal to a surface of the aircraft and determines whether ice is present based upon a reflected radar signal. The system can determine the type and the quantity of ice present based upon the reflected radar signal. The system can be mounted within a wing or on an external surface of the aircraft. The radar signal is preferably a low power signal.

Claims

1. An icing detector for an aircraft, comprising:

an antenna attached to the aircraft; and

a control circuit coupled to the antenna, the control circuit providing a radar signal to the antenna and receiving a reflected radar signal, the control circuit providing an indication of presence of ice in response to the reflected radar signal;

wherein the antenna provides the radar signal through a radome in the wing.

2. The detector of claim 1, wherein the reflected signal is greater when ice forms on the radome.

3. A method of determining a presence of ice on a portion of an aircraft, the method comprising:

providing a radar signal to the portion of the aircraft;

receiving a reflected radar signal from the portion of the aircraft, and providing an indication of ice on the portion when the reflected radar signal is in a predetermined relationship with a threshold;

wherein the predetermined relationship exceeds the threshold.

4. The method of claim 3, wherein the radar signal is provided through a radome.

5. The method of claim 4, wherein the radome is disposed in a leading edge of a wing of the aircraft.