Segmented nacelle inlet lip with electric anti-icing system

An assembly for an aircraft propulsion system, comprising:

• a nacelle inlet structure extending axially along and circumferentially around a centerline, the nacelle inlet structure including an inlet lip, an inner barrel, an outer barrel, a bulkhead, a plurality of structure segments and an internal cavity;
• the inlet lip forming a leading edge of the nacelle inlet structure;
• the inner barrel projecting axially aft away from the inlet lip;
• the outer barrel projecting axially aft away from the inlet lip, and the outer barrel radially outboard of and axially overlapping the inner barrel;
• the bulkhead connected to the inner barrel and the outer barrel, and the bulkhead radially tapering as the bulkhead extends axially towards the leading edge;
• each of the plurality of structure segments attached to the inner barrel and the bulkhead, each of the plurality of structure segments comprising an exterior skin, and the exterior skin forming a respective circumferential section of the inlet lip;
• and
• the internal cavity extending axially within the nacelle inlet structure from the exterior skin of each of the plurality of structure segments to the bulkhead;
• wherein each of the plurality of structure segments further comprises a mount bonded to the exterior skin and mechanically attached to the bulkhead and the inner barrel.