Strong tracking filter based SINS initial alignment for large misalignment angles

被引：0

作者：

Peng, Zhuo ^{[1
,2
]}

Zhang, Rong ^{[1
]}

Guo, Mei-Feng ^{[1
]}

Liu, Gang ^{[1
]}

Luo, Shou-Hong ^{[1
]}

机构：

[1] Department of Precision Instrument, Tsinghua University, Beijing

[2] Astronaut Center of China, Beijing

来源：

Zhongguo Guanxing Jishu Xuebao/Journal of Chinese Inertial Technology | 2015年 / 23卷 / 05期

关键词：

Initial alignment; Large misalignment angles; SINS; Strong tracking filter;

D O I：

10.13695/j.cnki.12-1222/o3.2015.05.002

中图分类号：

学科分类号：

摘要：

Initial alignment is important for strapdown inertial navigation system. Coarse alignment is usually implemented before fine alignment to make the misalignment angles sufficiently small to meet the linear error model. Without coarse alignment, the misalignment angles will be large enough to need non-linear model and non-linear filter, which are complicated and inaccurate. For this reason, a new method is presented which don't need coarse alignment or non-linear model. This is achieved by choosing appropriate initial error covariance matrix and using feedback compensation structure and strong tracking filter. Simulation shows the new method is effective and robust for large misalignment angles. The heading error can ultimately converge to 0.05° after 300 s under arbitrary initial attitude, while the traditional fine alignment has almost the same accuracy and speed but needs additional time for coarse alignment, and the UKF only converges to 0.5° after 600 s which is much slower. © 2015, Editorial Department of Journal of Chinese Inertial Technology. All right reserved.

引用

页码：565 / 569

页数：4

共 14 条

[1] Jiang Y.F., Error analysis of analytic coarse alignment methods, IEEE Transactions on Aerospace and Electronic Systems, 34, 1, pp. 334-337, (1998)
[2] Liu H.-P., Zhang K., Li H.-N., Et al., Research on initial alignment of SINS with large misalignment angles, Aeronautical Computing Technique, 42, 4, pp. 39-42, (2012)
[3] Long R., Qin Y.-Y., Xia J.-H., Applying CDKF (Central Difference Kalman Filter) to initial alignment of sins for large misalignment angles, Journal of Northwestern Polytechnical University, 28, 3, pp. 364-368, (2010)
[4] Jamshaid A., Rasheeq M., Initial orientation of inertial navigation system realized through nonlinear modeling and filtering, Measurement, 44, 5, pp. 793-801, (2011)
[5] Wu X., Sun F., Simulation study for FOG strapdown inertial navigation nonlinear alignment based on SVD-cubature Kalman filter, Symposium on Photonics and Optoelectronics, pp. 1-4, (2012)
[6] Yan G.-M., Yan W.-S., Xu D.-M., A SINS nonlinear error model reflecting better characteristics of SINS errors, Journal of Northwestern Polytechnical University, 27, 4, pp. 511-516, (2009)
[7] Li H.-Z., Pan Q., Deng L., Et al., Pole assignment's influence on alignment performance of SINS gyrocompass, Journal of Chinese Inertial Technology, 22, 6, pp. 711-718, (2014)
[8] Hu J., Cheng X.-H., A new in-motion initial alignment for land-vehicle SINS/OD integrated system, 2014 Position, Location and Navigation Symposium, pp. 407-412, (2014)
[9] Sun Y.-C., Duan F.-Y., Chen P., Et al., Initial alignment method for SINS based on the analysis of the degree of observability, Piezoelectrics & Acousto-Optics, 36, 3, pp. 380-383, (2014)
[10] Wang L., Wu L., Guan Y., Et al., Online sensor fault detection based on an improved strong tracking filter, Sensors, 15, 2, pp. 4578-4591, (2015)

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