Advanced　composite　laminated　cylindrical　shells　are　increasingly　being　desired　in　modern　aerospace　structures,　for　improving　their　structural　efficiency　and　performance.　In　this　paper,　compared　with　the　previous　failure　analysis,　which　considered　buckling-failure　only,　a　competitive　failure　analysis　framework　for　composite　laminated　cylindrical　shells　is　presented,　in　which　linear　buckling　interacting　curve　method　was　considered　for　buckling-failure　analysis　and　strength　ratio　based　on　Tsai-Wu　failure　criterion　was　used　for　stress-failure　analysis.　The　proposed　framework　agreed　well　with　the　published　data,　which　verified　it＇s　feasibility.　The　competitive　failure　analysis　of　composite　laminated　cylindrical　shells　and　parametric　studies　were　conducted　to　reveal　the　failure　mode.　It　is　found　that　the　higher　ratios　of　longitudinal　compressive　strength　to　longitudinal　modulus　and　shear　strength　to　longitudinal　modulus　of　composite　materials,　the　more　likely　buckling-failure　occurs;　otherwise,　stress-failure　occurs.　As　the　ratio　of　radius　to　thickness　reduces,　the　possibility　of　occurrence　of　stress-failure　increases.　Moreover,　the　stress-failure　for　[90°/0°/90°]　stacking　sequence　is　more　likely　to　occur　than　[θ/0°/θ],　and　0°　©　2020