Rotor ice protection systems and methods

Patent metadata

Field	Value
Publication number	US-11279492-B2
Application number	US-201916684104-A
Country	US
Kind code	B2
Filing date	Nov 14, 2019
Priority date	Aug 2, 2012
Publication date	Mar 22, 2022
Grant date	Mar 22, 2022

Abstract

A method for managing icing conditions on a rotary aircraft via one or more ice protection controllers. The method includes steps for receiving an icing condition signal from an icing rate sensor at an ice protection controller, determining, in response to the icing condition signal, a de-icing signal based at least in part a liquid water content (LWC). The method further includes steps for transmitting, via a digital communication bus disposed in at least part of a slip ring assembly, the de-icing signal to a upper distributor to cause the upper distributor to transmit power to one or more heating elements for a respective rotor blade.

First claim

What is claimed is:

1. A rotor ice protection system for a rotary aircraft, comprising:
an icing rate sensor configured to detect an icing condition;
an ice protection controller in communication with the icing rate sensor and configured to generate an anti-icing signal and a de-icing signal based on the icing condition signal;
a first rotor heating element in communication with the ice protection controller via an alternating current (AC) rotor heater power line disposed at least partially in a rotor slip ring assembly, the AC rotor heater power line arranged to provide the anti-icing signal to the first rotor heating element;
a distributor in communication with the ice protection controller via a controller area network (CAN) bus disposed at least partially in a slip ring assembly of a second rotor and a power converter cutout unit, the CAN bus arranged to provide the de-icing signal to the distributor; and
a heating element within the second rotor in communication with the power converter cutout unit via a direct current (DC) power line disposed at least partially in the slip ring assembly of the second rotor.

2. The rotor ice protection system of claim 1 , wherein the power converter cutout unit is configured to provide DC power to the heating element of the second rotor.

3. The rotor ice protection system of claim 1 , wherein the power converter cutout unit is located between the slip ring assembly of the second rotor and the ice protection controller.

Assignees

• Rosemount Aerospace Inc

Inventors

• Garnett Harold Edward
• Webb Matthew Michael
• Skoglund Jason Lee

Classifications

• B64D15/14

  controlled cyclically along length of surface · CPC title

• B64D15/22 Primary

  Automatic initiation by icing detector · CPC title