DUAL-CHANNEL DEICING SYSTEM FOR A ROTARY WING AIRCRAFT
First Claim
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1. A dual primary deicing system for a rotary-wing aircraft comprising:
- an electrothermal heating element system; and
a controller in communication with said electrothermal heating element, said controller communicating a heating cycle to said electrothermal heating element system, said heating cycle defining a first electric pulse train associated with a main rotor blade assembly.
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Abstract
A dual primary deicing system for a rotary-wing aircraft, according to an exemplary aspect of the present disclosure includes, among other things, an electrothermal heating element system; and a controller in communication with said electrothermal heating element, said controller communicating a heating cycle to said electrothermal heating element system, said heating cycle defining a first electric pulse train associated with a main rotor blade assembly.
10 Citations
21 Claims
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1. A dual primary deicing system for a rotary-wing aircraft comprising:
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an electrothermal heating element system; and a controller in communication with said electrothermal heating element, said controller communicating a heating cycle to said electrothermal heating element system, said heating cycle defining a first electric pulse train associated with a main rotor blade assembly. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11)
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12. A method of deicing a rotary wing aircraft comprising the steps of:
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(1) communicating a heating cycle to an electrothermal heating element system, the heating cycle defining a first electric pulse train associated with a first set of main rotor blades; and (2) repeating the heating cycle after an off-time. - View Dependent Claims (13, 14, 15, 16, 17, 18, 19, 20, 21)
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Specification