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Mathematical Problems in Engineering
Volume 2015 (2015), Article ID 903054, 7 pages
http://dx.doi.org/10.1155/2015/903054
Research Article

SINS/CNS Nonlinear Integrated Navigation Algorithm for Hypersonic Vehicle

1College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Jiangsu, Nanjing 210016, China
2Navigation Research Center, Nanjing University of Aeronautics and Astronautics, Jiangsu, Nanjing 210016, China

Received 27 August 2014; Accepted 1 November 2014

Academic Editor: Bin Jiang

Copyright © 2015 Yong-jun Yu et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

Abstract

Celestial Navigation System (CNS) has characteristics of accurate orientation and strong autonomy and has been widely used in Hypersonic Vehicle. Since the CNS location and orientation mainly depend upon the inertial reference that contains errors caused by gyro drifts and other error factors, traditional Strap-down Inertial Navigation System (SINS)/CNS positioning algorithm setting the position error between SINS and CNS as measurement is not effective. The model of altitude azimuth, platform error angles, and horizontal position is designed, and the SINS/CNS tightly integrated algorithm is designed, in which CNS altitude azimuth is set as measurement information. GPF (Gaussian particle filter) is introduced to solve the problem of nonlinear filtering. The results of simulation show that the precision of SINS/CNS algorithm which reaches 130 m using three stars is improved effectively.