Accuracy Enhancement of SINS/CNS Integrated Navigation Using Virtual Observations for Automated Transfer Vehicles

被引：0

作者：

Wang D.-J. ^{[1
]}

Lv H.-F. ^{[1
]}

Wu J. ^{[1
]}

机构：

[1] College of Aerospace Science and Engineering, National University of Defense Technology, Changsha

来源：

Wu, Jie (wujie_nudt@sina.com) | 1600年 / China Spaceflight Society卷 / 38期

关键词：

Automated transfer vehicle (ATV); Celestial navigation system (CNS); Integrated navigation; Strapdown inertial navigation system (SINS); Virtual observation;

D O I：

10.3873/j.issn.1000-1328.2017.05.011

中图分类号：

学科分类号：

摘要：

A method for designing accurate autonomous navigation system is proposed in this paper for automated transfer vehicles (ATV). This paper devises an accuracy enhancement approach for traditional integrated navigation of a strapdown inertial navigation system (SINS) and a celestial navigation system (CNS) with the virtual observations. This approach benefits from the use of the fact that ATV is in complete weightlessness in orbit without maneuvers. The improved state equations and virtual observation equations are established based on such a constraint, and an extended Kalman filter is used to accomplish the state estimation from SINS, CNS and virtual observations in different data rates.The simulation results indicate that the proposed algorithm can improve both the position and velocity accuracies without loss of attitude estimation accuracy by about 82.33% and 93.87% compared with standalone inertial navigation, by about 98.35% and 98.72% compared with traditional SINS/CNS integration. The introduction of virtual observations can resist the divergence of position and velocity errors due to inaccurate accelerometer bias estimation effectively. This is of significant importance in engineering because the navigation accuracy is improved without the aid of other sensors, meaning it reduces the reliance on the external information for SINS. © 2017, Editorial Dept. of JA. All right reserved.

引用

页码：526 / 532

页数：6

共 18 条

[1]

Wen Y.-Z., Navigation methods for automated transfer vehicle on high earth orbits, (2011)

[2]

Quan W., Li J.L., Gong X.L., Et al., INS/CNS/GNSS Integrated Navigation Technology, (2015)

[3]

Ye B., Zhang H.-B., Wu J., Study on quick ascertaining method of optimal single star in celestial-inertial integrated guidance, Journal of Astronautics, 30, 4, pp. 1371-1375, (2009)

[4]

Zhang L.J., Yang H.B., Zhang S.F., Et al., Strapdown stellar-inertial guidance system for launch vehicle, Aerospace Science and Technology, 33, 1, pp. 122-134, (2014)

[5]

Zhang H.B., Zheng W., Tang G.J., Stellar/inertial integrated guidance for responsive launch vehicles, Aerospace Science and Technology, 18, 1, pp. 35-41, (2012)

[6]

David H.T., John L.W., Strapdown Inertial Navigation Technology, (2004)

[7]

Wang X.-G., Xu H.-L., Li A.-H., A novel strong tracking EKF algorithm in application of missile attitude determination by star observations, Journal of Astronautics, 29, 3, pp. 873-877, (2008)

[8]

Jamshaid A., Fang J.C., Realization of an autonomous integrated suite of strapdown astro-inertial navigation systems using unscented particle filtering, Computers and Mathematics with Applications, 57, 2, pp. 169-187, (2009)

[9]

Xu F., Fang J.C., Velocity and position error compensation using inertial navigation system/celestial navigation system integration based on ensemble neural network, Aerospace Science and Technology, 12, 4, pp. 302-307, (2008)

[10]

Ning X.L., Liu L.L., A two-mode INS/CNS navigation method for lunar rovers, IEEE Transactions on Instrumentation and Measurement, 63, 9, pp. 2170-2179, (2014)

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