| 摘要 |
The device has a geometrically predetermined support surface made of glass fiber reinforced fabric or aluminum honeycomb plates and coated with specifically mixed components of a carbon nano tube (CNT) dispersion or matrix. The surface is electrically contacted, digitally controlled and regulated and acts against icing of aircraft wings. The support surface is formed of the glass fiber reinforced fabric with different spatial expansions such that active and passive heating of icing prone wing segments occurs during takeoff and landing of the aircraft. The electrical resistance layer is made of polymer composite. An INDEPENDENT CLAIM is also included for a method for varying temperature of an electrical resistance layer.
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