纬度未知条件下捷联惯导系统晃动基座的初始对准

Abstract

Abstract:

To solve the problem of initial alignment of the strapdown inertial navigation system (SINS) under swaying base with geographic latitude uncertainty, a new latitude estimation algorithm and initial alignment method are presented. The former uses the angle between the two gravities in the inertial frames of different times to extract latitude, while the latter utilizes the continuous attitude update to record the attitude changes caused by sway interrupt, and then uses the estimation of the initial attitude to determinate the attitude of the body. Theoretical analysis results show that the estimation error of latitude is mainly dependent on the accelerometer errors, while the error caused by gyro errors and swaying interrupt is tiny. The simulation results show that the proposed latitude estimation algorithm and initial alignment method can be used with good results under swaying base environments with latitude uncertainties.

Key words: navigation systems, strapdown inertial navigation system, swaying base, initial alignment, latitude, inertial frame

CLC Number:

V249.3

WANG Yuegang, YANG Jiasheng, YANG Bo. SINS Initial Alignment of Swaying Base Under Geographic Latitude Uncertainty[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, 33(12): 2322-2329.

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SINS Initial Alignment of Swaying Base Under Geographic Latitude Uncertainty

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