In order to ensure the safe application of solid rocket motors in complex battlefield environments， it is necessary to conduct in-depth research on the response characteristics of NEPE high-energy solid propellants under impact loads. A one-dimensional Lagrange test system was established to measure the pressure wave at different Lagrange location. The unreacted shock adiabatic curve of the measured propellant was obtained through the momentum conservation relationship before and after the shock wavefront， and the JWL EOS of the unreacted NEPE propellant were obtained by using a genetic algorithm. A Φ50 mm NEPE propellant probe-type cylinder test platform was constructed and a 12-channel probe with radial displacement difference was used to record the time of copper cylinder expansion to different probe positions and the time curve of cylinder expansion velocity was obtained. Based on the results of the Φ50 mm cylinder test， the JWL-Miller EOS parameters of the detonation product of NEPE propellant was calibrated by Gurney model and genetic algorithm. Finally， the pressure curves at different Lagrange position were fitted with the ignition and growth model. The results show that the fitting correlation coefficients of JWL EOS parameter curves for unreacted propellant and detonation products are high enough and the obtained ignition and growth model parameters well simulate shock initiation experimental results and the obtained parameters can provide reference for the safety evaluation of solid rocket motors.