Dual-axis rotational modulation method based on SINS tetrahedron redundancy configuration

被引：3
|
作者：
Cheng J. [1 ]
Mou H. [1 ]
Sun X. [1 ]
Chen D. [1 ]
机构：
[1] College of Automation, Harbin Engineering University, Harbin
来源：
| 1801年 / Chinese Institute of Electronics卷 / 39期
关键词：
Accuracy; Dual-axis rotational modulation; Redundancy configuration; Reliability; Strapdown inertial navigation system (SINS) technology;
D O I：
10.3969/j.issn.1001-506X.2017.08.20
中图分类号：
学科分类号：
摘要：
Traditional strapdown inertial navigation system (SINS) with three-axis orthogonal configuration is out of order due to a single sensor fault, and navigation error is accumulated quickly with time increasing. In order to solve the problems, a dual-axis rotational modulation SINS method based on four-gyro redundancy configuration is proposed. Depending on the criterion of multi-index constraints, a four-gyro tetrahedron redundancy configuration is designed in device level. And an eight sequence dual-axis rotation modulation scheme is brought to decrease three-axis gyro equivalent drift. The simulation results show the proposed method can improve reliability performance and navigation precision. It has important value in engineering application. © 2017, Editorial Office of Systems Engineering and Electronics. All right reserved.
引用
收藏
页码：1801 / 1807
页数：6
相关论文
共 22 条
  • [1] Wang X., Wu J., Wang T.X.W., Analysis and verification of rotation modulation effects on inertial navigation system based on MEMS sensors, Journal of Navigation, 66, 5, pp. 751-772, (2013)
  • [2] Nie Q., Gao X., Liu Z., Research on accuracy improvement of INS with continuous rotation, Proc. of the IEEE International Conference on Information and Automation, pp. 870-874, (2009)
  • [3] Wang L., Wang W., Zhang Q., Et al., Self-calibration method based on navigation in high-precision inertial navigation system with fiber optic gyro, Optical Engineering, 53, 6, (2014)
  • [4] Gao P., Li K., Wang L., Et al., Four-position heading effect calibration algorithm for rotation inertial navigation system based on fiber optic gyro, Optical Engineering, 55, 7, pp. 1051-1058, (2016)
  • [5] Li K., Gao P., Wang L., Et al., Analysis and improvement of attitude output accuracy in rotation inertial navigation system, Plasma & Fusion Research, 2015, 1, pp. 1-10, (2015)
  • [6] Cho S.Y., Lee H.K., Chan G.P., Adaptive redundant inertial measurement unit/global positioning system integration filter structure for fault tolerant navigation, Journal of Dynamic Systems Measurement & Control, 136, 2, pp. 10091-10097, (2013)
  • [7] Fu L., Wang X.L., Yue Y.Z., Method for investigation of the optimal redundant gyros number based on reliability analysis, Journal of Beijing University of Aeronautics and Astronautics, 36, 9, pp. 1030-1033, (2010)
  • [8] Jafari M., Roshanian J., Inertial navigation accuracy increasing using redundant sensors, Journal of Science and Engineering, 1, 1, pp. 55-66, (2013)
  • [9] Wang M.G., Fan Y.P., Cui W.C., Et al., A study of the redudancy system using four gyroscopes, Journal of Projectiles, Rockets, Missiles and Guidance, 26, 3, pp. 40-42, (2006)
  • [10] Skoogh D., Lennartsson A., A method for multiple fault detection and isolation of redundant inertial navigation sensor configurations, Proc. of the IEEE Position, Location, and Navigation Symposium, pp. 415-425, (2006)
123