| 摘要 |
An electrothermal zoned de-icing system for an aircraft employs a heat- conducting tape bonded to the leading edge of an aircraft structure subject to an impinging airstream during flight. The heat-conducting tape has a spanwis e parting strip area, and first and second ice accumulation and shedding zones (132, 134). The tape comprises a non-metallic electrical and heat-conducting layer consisting of flexible expanded graphite foil laminated to an outer he at- conducting layer, in which the thickness of the flexible expanded graphite foil layer in the parting strip area is always greater than the thickness of the foil layer in either of the ice accumulation and shedding zones. Therefo r, the parting strip area has a decreased electrical resistance, a greater flow of current, and becomes hotter than the zones in which the foil layer is thinner. Because the flexible expanded graphite foil is a monolithic structu re that may be shaped, sculptured or layered to form different thicknesses in different areas, only a single control mechanism for a single set of electri c terminals is necessary to produce temperature differentials in the parting strip and ice accumulation and shedding zones for a cycled zoned de-icing system.
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