Ice protection system for a multi-segment aircraft component

A method of joining first and second aircraft components to form a leading edge of an aircraft surface, the method comprising:

• (a) providing a first component having a first exterior surface, a first end, and a first electric ice protection heater element immediately adjacent the first end;
• (b) providing a second component having a second exterior surface, a second end, and a second electric ice protection heater element immediately adjacent the second end;
• and
• (c) joining the first end of the first component to the second end of the second component such that the first and second exterior surfaces combine to form a substantially continuous and selectively heatable leading edge surface along a juncture between the first and second ends;
• wherein at least a portion of each of the first and second electric ice protection heater elements is disposed between the first and second ends of the first and second components.

An aircraft component comprising:

• (a) a first segment comprising a first exterior surface, a first end, and a first electric heater element having a first edge proximate to the first end;
• (b) a second segment comprising a second exterior surface, a second end, and a second electric heater element having a second edge proximate to the second end, wherein the second end is joined to the first end such that the first external surface and the second external surface combine to form at least a portion of a substantially continuous leading edge surface;
• (c) a first bus bar connected to the first edge of the first heater element;
• and
• (d) a second bus bar connected to the second edge of the second heater element;
• (e) wherein the first and second bus bars are disposed between the first end and the second end when the first end is joined to the second end.

An aircraft engine nacelle having a circumferentially extending inlet lip, the inlet lip comprising:

• (a) a first circumferentially extending inlet lip section having a first circumferentially extending lip surface and an axially extending first edge surface, and a second circumferentially extending inlet lip section having a second circumferentially extending lip surface and an axially extending second edge surface, the first and second inlet lip sections being arranged such that the first and second edge surfaces are adjacent to each other and define a gap therebetween;
• (b) a first heater element embedded in the first inlet lip section and extending along the first lip surface and the first edge surface, and a second heater element embedded in the second inlet lip section and extending along the second lip surface and the second edge surface;
• and
• (c) a splice plate extending across the gap between the first and second edge surfaces, and securing the first and second inlet lip sections together.

An aircraft component comprising:

• (a) a first segment having a first leading edge surface extending to a first end of the first segment;
• (b) a second segment having a second leading edge surface extending to a second end of the second segment, wherein the second end is substantially adjacent to the first end of the first segment;
• (c) wherein the first leading edge surface includes at least one first electrical heating element that extends at least to the first end of the first segment, and the second leading edge surface includes at least one second electrical heating element that extends at least to the second end of the second segment;
• and
• (d) wherein the first end of the first segment and the second end of the second segment are at least partially connected by at least one splice member that extends across a gap between the first end and the second end.