APPARATUS AND METHOD FOR DETECTING AIRCRAFT ICING CONDITIONS

• US 20120274938A1
• Filed: 04/29/2011
• Published: 11/01/2012
• Est. Priority Date: 04/29/2011
• Status: Active Grant

• Current Assignee: Rosemount Aerospace, Inc. (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Rosemount Aerospace, Inc. (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Ray, Mark D.
• Granted Patent: US 8,338,785 B2
• Time in Patent Office: Days
• US Class Current: 356/342
• CPC Class Codes: B64D 15/20 Means for detecting icing or initiating de-icing
• CPC Class Codes: G01S 17/95 for meteorological use
• CPC Class Codes: G01S 7/499 using polarisation effects
• CPC Class Codes: Y02A 90/10 Information and communication technologies [ICT] supporting adaptation to climate change, e.g. for weather forecasting or climate simulation

Abstract

An apparatus for detecting icing conditions on an aircraft includes a laser system configured to direct a light signal into a cloud, a lens component configured to collect echo signals from a cloud caused by the light signal directed into the cloud, a beam splitter component configured to redirect signals received and passing through the lens component into at least first and second paths and a supercooled large droplet (SLD) detector to receive the redirected signals. The SLD includes a first signal detector component configured to perform a first color measurement on the first redirected signal, and a second signal detector component configured to perform a second color measurement on the second redirected signal. The SLD detector is configured to use the first and second color measurements to determine liquid water content and droplet diameter distribution for the cloud.

Claims

1. An air-borne apparatus for detecting icing conditions, the apparatus comprising:

a laser system configured and operative to generate a light signal and direct the light signal into a cloud;

a lens component configured and operative to collect echo signals from a cloud caused by the light signal directed into the cloud by the laser system;

a beam splitter component configured and operative to redirect signals received and passing through the lens component into at least first and second paths;

a supercooled large droplet (SLD) detector positioned to receive the redirected signals from the beam splitter, the SLD detector including;

a first signal detector component configured and operative to perform a first color measurement on the first redirected signal; and

a second signal detector component configured and operative to perform a second color measurement on the second redirected signal wherein the SLD detector is configured and operative to use the first and second color measurements to determine liquid water content and droplet diameter distribution for the cloud in which the light signal was directed into by the laser system.

2. An apparatus as recited in claim 1, wherein the liquid water content and the droplet diameter distribution for a cloud are estimated from 1 μ

m to 500 μ

m by the SLD detector.

3. An apparatus as recited in claim 1, wherein the first signal detector component is a near-infrared detector.

4. An apparatus as recited in claim 1, wherein the near-infrared detector receives a 1.5 μ

m signal.

5. An apparatus as recited in claim 1, wherein the second signal detector component is an optical ice detector (OID).

6. An apparatus as recited in claim 5, the OID includes polarization optics.

7. An apparatus as recited in claim 6, wherein the OID receives a 1.064 μ

m signal.

8. An apparatus as recited in claim 1, wherein the apparatus is configured for use on an aircraft for detecting icing conditions around an aircraft.

9. An apparatus as recited in claim 1 wherein the laser system is configured and operative to generate a 1.5 μ

m signal.

10. An apparatus as recited in claim 1 wherein the laser system includes a pulsed 1.064 μ

m microchip operative to pump an optical parametric oscillator to generate a 1.5 μ

m signal.

11. An apparatus as recited in claim 10 wherein the 1.064 μ

m microchip is operative and configured to perform a parametric down conversion on a generated signal to generate the 1.5 μ

m signal.

12. An apparatus as recited in claim 10 wherein both the 1.064 μ

m microchip and generated signal linearly polarized exit the laser system together.

13. An apparatus as recited in claim 12 further including a quarter wave plate configured to perform the circular polarization.

14. An apparatus as recited in claim 1 wherein the beam splitter is configured and operative to direct at least a portion of the received signal from the lens component at one of 1.064 μ

m or 1.5 μ

m into the SLD detector.

15. An apparatus as recited in claim 14 further including a dichroic mirror and collimating lens positioned intermediate the beam splitter and the SLD detector.

16. An apparatus as recited in claim 1 wherein the SLD detector includes a diffractive scattering SLD having an internally reflective cone configured and operative to determine water droplet size.

17. An apparatus as recited in claim 1 wherein the laser system includes at least one pulsed diode laser.