Parameters Online Identification and Prediction of Solid Rocket Motor

Considering the ground-to-flight difference in solid rocket motor and uncertainties on motor performance parameters at the shutdown point, this paper proposes a method for online identification and prediction of solid rocket motor performance. The calculation model of the nozzle throat diameter and the propellant burning rate are established based on the analysis of internal correlation between motor parameters. Then by means of the real-time measured data from the missile-borne sensor, throat diameter and burning rate can be calculated. After the model parameters of throat diameter and burning rate were identified by the recursive least square algorithm, the shutdown time and thrust-time characteristics can be predicted based on identification results and prediction model. The simulation results show that this method has high identification and prediction accuracy, and could provide a feasible solution for online identification and prediction of the performance parameters of solid rocket motor.