Carbon-carbon　(C/C)　composites,　in　which　a　carbon　matrix　is　reinforced　by　carbon　fibers,　are　mainly　used　as　thermo-structural　protections　in　the　aerospace　engineering.　The　ablation　of　C/C　composites　at　high-temperature　causes　mass　loss,　which　is　dominated　by　coupling　effect　of　physical,　chemical　and　mechanical　factors.　This　paper　classified　the　C/C　ablation　into　three　types　according　to　the　ablation　mechanism:　linear-rate　reaction,　parabolic-rate　reaction　and　logarithmic-rate　reaction.　In　this　work,　a　micromechanical　model　of　C/C　composite　with　high-temperature　heat　conduction　was　established.　A　linear　heat-transfer　finite　element　analysis　was　carried　out　for　revealing　the　damage　morphology　of　C/C　composites　at　an　ultra　high　temperature.　Copyright　©　(2013)　by　International　Conference　on　Fracture.