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This paper aims to numerically study the pre-fatigue, low-velocity impact(LVI) and fatigue progressive damage behaviours of a full-scale compositehelicopter tail structure under multipoint coordinated loading spectrum. First,a fatigue progressive damage model (PDM) incorporating multiaxial fatigueresidual strength degradation rule, fatigue failure criteria based on fatigueresidual strength concept and sudden stiffness degradation rule was proposed.Then, an LVI progressive damage model for plain-weave (PW) and unidirectional(UD) composites was developed. Moreover, a full-process analysis algorithm witha reasonable damage transfer strategy for pre-fatigue, LVI and fatigueprogressive damage analysis was proposed. Finally, a highly computationalefficient and accurate full-scale global-local finite element (FE) model ofhelicopter tail structure was built to predict strain distribution under twoflight working conditions, to predict LVI damage under impact loading, and toassess fatigue damage behaviours under multipoint coordinated loading spectrum.The numerical predictions agree well with test results from this work andliterature data, indicating that the developed pre-fatigue, LVI, fatigue PDMsand algorithms, as well as the global-local FE modelling based onshell-to-solid coupling, can effectively analyse the impact damage tolerance offull-scale aircraft structures.

Modelling Pre-fatigue, Low-velocity Impact and Fatigue behaviours of  Composite Helicopter Tail Structures under Multipoint Coordinated Loading  Spectrum