Is it possible to do fatigue analysis of composite structure (winglet, wing, fuselage etc.)? There is no any article for that. nCode provides just fiber composite, but not appropriate for other composites.
Typically we do not do metal structure type fatigue analysis (crack imitation and growth) for aircraft composites. Carbon fiber composites for aircraft are certified to "no-growth" of damages under fatigue loads. The "no-growth" stress or strain levels are validated by test data, not by analysis. See FAA AC20-107B. See also Composite Materials Handbook, CMH-17, Volume 3 Chapter 12 (Durability and Damage Tolerance) - currently Rev G is published; Rev H will be published in a year or so, and will have a lot more info.