Strapdown Inertial Navigation Algorithm Based on MIMU and Its Application in Missile Ejection Test
- 10.2991/icmse-15.2015.216How to use a DOI?
- MIMU; SINS; algorithm model; missile motion parameters
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.
- © 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/).
Cite this article
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 -