Rotor blade de-icing system

1. An aircraft, comprising:

an airfoil susceptible to an ice buildup;

a heat absorbent material carried by the airfoil, the heat absorbent material, having:

a first heat absorbent material secured to a suction surface of the airfoil;

a second heat absorbent material secured to a pressure surface of the airfoil; and

a port extending a length of the second heat absorbent material;

wherein a portion of the heat energy passes through the port and is absorbed by the first heat absorbent material;

a transmitter for transmitting heat energy to the heat absorbent material;

a control system operably associated with the transmitter; and

a sensor for detecting the presence of the airfoil as the airfoils passes over the sensor and, wherein the heat absorbent material absorbs the heat energy that in turn warms the airfoil and breaks apart ice buildup formed thereon.

2. The aircraft of claim 1 , the control system comprising:

a second sensor for detecting the ice buildup;

wherein upon detection of the ice buildup, the second sensor relays the sensed information to the control system, which in turn activates the transmitter.

3. The aircraft of claim 2 , wherein the second sensor detects conditions likely to create the ice buildup.

4. The aircraft of claim 1 , further comprising:

a heat conductor conductively coupling the first heat absorbent material to the second heat absorbent material;

wherein the heat conductor transfers the heat energy from the second heat absorbent material to the first heat absorbent material.

5. The aircraft of claim 1 , wherein the heat absorbent material is disposed within the thickness of the airfoil.

6. The aircraft of claim 1 , wherein:

the aircraft is a helicopter; and

the airfoil is a rotor blade of the helicopter.

7. The aircraft of claim 1 , wherein:

the transmitter transmits microwave energy; and

the heat absorbent material absorbs microwave energy.