Abstract: The effects of temperature shock on the damage properties of HTPB composite solid propellant were studied by temperature shock experiments, acoustic emission(AE) and uniaxial tension tests. The results showed that the HTPB propellant shocked by thermal heat for different cycles all existed three failure phases including the damage nucleation, crack expansions and macro crack. The longer the time of the propellant was shocked, the less the AE cumulative energy was released and the more significant the inner damage was caused. The longer the time of the HTPB propellant being shocked, the earlier the damage threshold would appear.