Initial Attitude Impact on Error Propagation of Single-axis Rotation Inertial Navigation System
Wen Hu, Zhili Zhang, Zhaofa Zhou, He Chen, ZiHao Xu
Available Online May 2017.
- https://doi.org/10.2991/icmeit-17.2017.129How to use a DOI?
- SINS, single-axis rotation, error propagation character, gyro constant drift
- The rotation modulation technology of Inertial Navigation System (INS) is an error auto-compensation technique. In order to study the effects of the initial attitude to the influence of error propagation character of single-axis rotation INS, the single-axis rotation INS error model was built, and error propagation equations of Strap down Inertial Navigation System(SINS) was deduced and obtained from which the function between equivalent constant error of inertial device, then analysis the modulation form of gyro constant drift in single-axis continuous rotation and those influences to systemic error, and design the simulation experiments in arbitrary initial attitude, which shows that the best rotation modulation result appeared in horizontal condition
- Open Access
- This is an open access article distributed under the CC BY-NC license.
Cite this article
TY - CONF AU - Wen Hu AU - Zhili Zhang AU - Zhaofa Zhou AU - He Chen AU - ZiHao Xu PY - 2017/05 DA - 2017/05 TI - Initial Attitude Impact on Error Propagation of Single-axis Rotation Inertial Navigation System BT - Proceedings of the 2nd International Conference on Mechatronics Engineering and Information Technology (ICMEIT 2017) PB - Atlantis Press SP - 712 EP - 716 SN - 2352-538X UR - https://doi.org/10.2991/icmeit-17.2017.129 DO - https://doi.org/10.2991/icmeit-17.2017.129 ID - Hu2017/05 ER -