The effect of strain rate on compressive behavior and failure mechanism of CMDB propellant

The compressive mechanical behavior of composite modified double base(CMDB)propellant was investigated across a wide scope of strain rates ranging from 10^(-3) s^(-1) to 4210 s^(-1) at room temperature,by applying a conventional universal testing machine and a split Hopkinson tension bar(SHPB),respectively.The derived stress-strain curves at different strain rates show a strong rate dependence,indicated that yield stress,ultimate stress and strain energy density of CMDB propellant all increase with strain rate by following a power law function,while the amplification of increase are different.The deformation and damage modes of CMDB propellant has changed from a typical ductile manner(cracking along the axial direction)to a brittle manner(maximum shear failure)with increasing of strain rate.Scanning electron microscopy(SEM)was employed to explore the microscopic failure characteristics of CMDB propellant.Under quasi-static loading,the nearly parallel micro-cracks propagating along the axial direction and the debonding of RDX particle without particle crushing can be observed.While under dynamic loading,the micro-crack is 45 angle to the axial direction,and multiple cracking modes of RDX particles appeared.Finally,the correlation between strain energy density and failure mechanisms of CMDB propellant was revealed by developing four characteristic failure modes.The findings of this study is very important to evaluate the structural integrity of CMDB propellant.

Evaluation of Thermal Hazard of Composite Modified Double-base Propellant by Microcalorimetery Method

The thermal decomposition behavior of composite modified double-base（CMDB） propellant containing cyclotrimethylene trinitramine（RDX） was studied via a Calvet microcalorimeter at five different heating rates. The activation energy（E） and the pre-exponential factor（A） of two obvious exothermic processes were obtained by Kissinger＇s method and Ozawa＇s method. The entropy of activation（△S^≠）, the enthalpy of activation（△H^≠）, and the free energy of activation（△G^≠） of the first stage were calculated. To evaluate the thermal hazard of the RDX-CMDB propellant, the critical temperature of thermal explosion（Tb）, the self acceleration decomposition temperature（Tsgox）, the adiabatic decomposition temperature increment（ATad） and the time-to-explosion of adiabatic system（t） were presented as 145.3 ℃, 138.15 ℃, 1634 K and 583.71 s（n=0） and 586.28 s（n=1）, respectively.