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A strapdown inertial navigation algorithm is proposed, which is suitable for the measurement of the parameters of missile in the ejection test with short movement time, small changes of velocity and position. The transformation relationship between the missile-boy coordinate frame and the navigation coordinate frame is described by the attitude matrix. The initial attitude angles of the missile are determined by the initial alignment processing static data. The navigation solution of missile motion parameters is realized by using the attitude update model, the velocity update model and the position update model. Numerical simulation results show that the proposed algorithm can calculate the position, velocity and attitude angles of the missile.

Strapdown Inertial Navigation Algorithm Based on MIMU and Its Application in Missile Ejection Test