Title :
A fast initial alignment method for strapdown inertial navigation system on stationary base
Author :
Jiang Cheng Fang ; De Jun Wan
Author_Institution :
Dept. of Instrum. Sci. & Eng., Southeast Univ., Nanjing
fDate :
10/1/1996 12:00:00 AM
Abstract :
In this paper a strapdown inertial navigation system (SINS) error model is introduced, and the observability of the SINS error model is analyzed. Then, on the basis of this SINS error model and the analysis of computer simulation results, a fast estimation method of the azimuth error ΦD is proposed for the initial alignment of SINS on stationary base. Consequently, the time of initial alignment is reduced greatly. The computer simulation results illustrate the efficiency of this fast initial alignment method
Keywords :
Kalman filters; aircraft navigation; inertial navigation; observability; azimuth error; computer simulation; error model; estimation method; initial alignment method; observability; stationary base; strapdown inertial navigation system; Azimuth; Computer errors; Computer simulation; Error analysis; Gravity; Inertial navigation; Marine vehicles; Observability; Rockets; Silicon compounds; State estimation;
Journal_Title :
Aerospace and Electronic Systems, IEEE Transactions on
