The efficiently calculate of the attitude matrix is an important subject in the Strap-down Inertial Navigation System (SINS), because the precision of its solution directly effects on the system performance. A new method of 3^rd order minimal parameter solution for the orthogonal matrix differential equation is used to solve the quaternion differential equation of SINS in this paper, and the numerical simulation is done as well. From the simulation result, we can see that when the new algorithm is used, the precision of the solved attitude angles is two orders higher than the classical method, and the floating-point operations is only abort half of the old one.

Date Published: 4 January 2006
PDF: 5 pages
Proc. SPIE 5985, International Conference on Space Information Technology, 598544 (4 January 2006); doi: 10.1117/12.658258

Published in SPIE Proceedings Vol. 5985:
International Conference on Space Information Technology
Cheng Wang; Shan Zhong; Xiulin Hu, Editor(s)