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

DOI

10.2991/icmse-15.2015.216How to use a DOI?

Keywords

MIMU; SINS; algorithm model; missile motion parameters

Abstract

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.

Copyright

© 2015, the Authors. Published by Atlantis Press.

Open Access

This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).

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TY  - CONF
AU  - Wei-Wei Bian
AU  - Zhen-Fang Xin
AU  - Jin-Xin Zhao
AU  - Jia-Hui Li
PY  - 2015/12
DA  - 2015/12
TI  - Strapdown Inertial Navigation Algorithm Based on MIMU and Its Application in Missile Ejection Test
BT  - Proceedings of the 2015 6th International Conference on Manufacturing Science and Engineering
PB  - Atlantis Press
SP  - 1187
EP  - 1190
SN  - 2352-5401
UR  - https://doi.org/10.2991/icmse-15.2015.216
DO  - 10.2991/icmse-15.2015.216
ID  - Bian2015/12
ER  -