Aircraft De-Icing System Using Thermal Conductive Fibers

<p>The accumulation of ice on the leading edges of aircraft wing poses complications for flight control as drag is increased with a tendency for higher relative turbulence over the wing. Pre-emptive and reactive ice removal techniques have been employed in the past by electromechanical, thermal, chemical and pneumatic methods. In this thesis, a carbon fiber fabric is utilized as a heating de-icer for composites aircraft wing surface structures. Two prototypes are constructed, tested to generate temperature profiles, and an appropriate heating voltage is selected for effective de-icing via distinct avenues of heating system configurations. The heat transfer efficiency of the system is theoretically analyzed and validated through experimental results. The advantages of the carbon-fiber based de-icing system are addressed in terms of weight, flexibility, coverage area, safety and easiness of installation.</p>

Name thesis:degree_name

Master of Science in Aerospace Engineering

Level thesis:degree_level

Thesis - Open Access

Discipline thesis:degree_discipline

Aerospace Engineering

Year

2015

Author dc:creator

• Park, Min Soon

• de-icing
• aircraft
• thermal fibers
• Aeronautical Vehicles
• Aerospace Engineering

Repository record dc:identifier

https://commons.erau.edu/edt/276

OAI identifier oai:identifier

oai:commons.erau.edu:edt-1275