Abstract:

The method of error coefficients separation and compensation for strap-down inertial measure unit (SIMU) is given in order to solve the excursion of SIMU error coefficients in-flight and further improve the inertial navigation precision. The separation model for zero drift values and proportionality coefficients of both accelerometer and gyroscope is given using the characteristic that the missile is forced earth gravitation and inertial force by angular rotation only through vacuum flying, combined with several SIMU instrument error coefficients correction models before launching. The inertial navigation error by the excursion of SIMU instrument error coefficients is calculated and the corrected method is given. Experiment result shows that about fifty-six percent decrease in inertial navigation error and an effective improvement in inertial navigation precision via this method.