Modeling and error spreading speciality of strapdown inertial navigation system on moving base

The strapdown inertial navigation system (SINS) has held more and more important status in the navigation and guidance of weapon systems at present, and especially has been widely used to all kinds of guided missile systems. Based on the request of how to improve navigation precision of weapon systems mounted on aerocrafts, the error differential equation of SINS and inertial apparatus had been established on moving base, and the integrated error state equation of SINS had been founded on moving base. The dominating error elements which effecting the performance of SINS had been analyzed, and the quantificational analyzing conclusions had been gained. The simulating experiments had been done. The study results could offer academic basis for designing of SINS.