AIRCRAFT ICING DETECTOR

• US 20150115105A1
• Filed: 10/23/2014
• Published: 04/30/2015
• Est. Priority Date: 10/24/2013
• Status: Active Grant

• Current Assignee: Board of Regents of the University of Michigan (University of Michigan)
• Original Assignee: Board of Regents of the University of Michigan (University of Michigan)
• Inventors: RENN, NILTON O.
• Granted Patent: US 9,302,777 B2
• Time in Patent Office: Days
• US Class Current: 244/134.F
• CPC Class Codes: B64D 15/20 Means for detecting icing or initiating de-icing

Abstract

A system capable of detecting the hazardous accumulation of ice on the surfaces, engines, instruments and air intakes of aircrafts or other objects of interest. The system consists of an electromagnetic microwave resonator capable of detecting the formation of ice directly where it could cause problems. The sensor could be mounted around the air intake of pitot tubes, static ports, engines intake, engines core, and can be embedded in the aircraft skin. The system uses algorithms based on the variations of the complex dielectric permittivity of water substance with frequency to distinguish the various types of ice from each other and from water.

Claims

1. A system for detecting ice formation on aircrafts comprising:

an electromagnetic resonator operating at microwave frequencies; and

a data processing unit with non-transitory software implementing an algorithm to detect at least one of the presence of ice, ice type and ice thickness and output at least one of a warning and an alert, the algorithm including;

a) measuring resonance frequencies (f_i) and associated quality factors (Q_d) using distribution of power of a transmitted signal (S₂₁) of said electromagnetic resonator;

b) determining power of a transmitted signal associated with said reasonance frequencies;

c) using analytical expressions or lookup tables to determine a real part of a complex dielectric permittivity (ε

′

) at each of said resonance frequencies based on said resonance frequencies (f_i), associated quality factors (Q_d), and distribution of power of said transmitted signal (S₂₁);

d) using analytical expressions or lookup tables to determine an imaginary part of said complex dielectric permittivity (ε

″

) at each of said resonance frequencies and a thickness of a layer of water or ice based on said resonance frequencies (f_i), associated quality factors (Q_d), and distribution of power of said transmitted signal (S₂₁); and

e) using analytical expressions or lookup tables to refine the calculations and confirm or refute the presence of water or ice.

2. The system according to claim 1 wherein said measuring a distribution of power of said transmitted signal associated with said reasonable frequencies further comprises measuring a power of a reflected signal.

3. The system according to claim 2 wherein said using analytical expressions or lookup tables to determine said real part of a complex dielectric permittivity (ε

′

) at each of said resonance frequencies based on said distribution of power of said transmitted signal (S₂₁) further comprises using analytical expressions or lookup tables to determine a real part of a complex dielectric permittivity (ε

′

) at each of said resonance frequencies based on said distribution of power of said reflected signals (S₁₁).

4. The system according to claim 2 wherein said using analytical expressions or lookup tables to determine an imaginary part of said complex dielectric permittivity (ε

″

) at each of said resonance frequencies and a thickness of a layer of water or ice based on said distribution of power of said transmitted signal (S₂₁) further comprises using analytical expressions or lookup tables to determine an imaginary part of said complex dielectric permittivity (ε

″

) at each of said resonance frequencies and a thickness of a layer of water or ice based on said distribution of power of said reflected signals (S₁₁).

5. The system according to claim 1, further comprising:

an interface for outputting the at least one warning and alert to a flight display of the aircraft.

6. The system according to claim 1, further comprising:

an interface for actuating a deicing system of the aircraft in response to the at least one warning and alert.

7. The system according to claim 1, further comprising:

an interface system operably receiving the at least one warning and alert, said interface system preventing unsafe flight configurations of the aircraft in response to the at least one warning and alert.

8. A method for detecting ice formation and its type on an area of interest, said method comprising:

measuring one or more resonance frequencies (f_i) and their associated amplitude (|S₂₁|²);

measuring a quality factor (Q_d) of said one or more resonance frequencies (f_i) based on a half-power (3 dB) amplitude;

using said one or more resonance frequencies, said quality factors, and analytical expressions or look-up tables to determine the real part of a complex dielectric permittivity (ε

′

) at said one or more resonance frequencies;

using said one or more resonance frequencies, said quality factors, and analytical expressions or look-up tables to determine the imaginary part of a complex dielectric permittivity (ε

″

) at each frequency;

if said complex dielectric permittivity (ε

′

, ε

″

) at said one or more resonance frequencies is within a predetermined range then determining the type of ice and estimating a thickness of the ice;

if a temporal rate of change of said complex dielectric permittivity (ε

′

, ε

″

) at said one or more resonance frequencies is within said predetermined range then estimating a rate of accumulation of the ice on the area of interest.