SINSCNS Nonlinear Integrated Navigation Algorithm for Hypersonic Vehicle

Abstract EN

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.