Astroinertial System Research Articles

Algorithmic Methods for Correcting Aircraft Astro-Inertial Systems

The paper studies the aircraft astro-inertial navigation system, which consists of an astronomical navigation system installed on a gyro-stabilized platform of inertial navigation system. The errors of this system arising from various disturbing factors are investigated. Methods based on system correction channels formation and using adaptive estimation algorithm are proposed for reducing these errors. A simulation using semi-natural experiment data was carried out for determining the accuracy of error compensation. The results demonstrate the accuracy and effectiveness of the proposed methods in correcting astro-inertial navigation systems.

Звёздные датчики ориентации в астроинерциальных системах летательных аппаратов

Звёздные датчики ориентации в астроинерциальных системах летательных аппаратов

Neuronal Model for Correction of an Astroinertial System

A multimodel algorithm based on an expanded interpretation of the Kalman filter algorithm is proposed. The results of a numerical simulation are presented.

System for neuromorphic estimation of rotation of a mobile technological platform

A model of an astroinertial system with a correction algorithm is suggested. This algorithm is an extended interpretation of a Kalman-type algorithm. The results of computational experiment are reported.

Theory of Three-Axis Stable Systems Employing External Information

I (l) and astronomical (2) systems may be used to compute x, y, z (coordinates in three-dimensional space) and x, y, z (the corresponding velocities). An inertial system can give the velocities reliably, but the coordinates are subject to major errors because of drift in the gyros and instability in the system generally. An astronomical system can give the coordinates accurately, but the velocities, which are deduced b} differentiation, are subject to very large errors. A combined (astro-inertial) system can give coordinates and velocities with the desired accuracy. Previous work (1-3) forms the basis of the present treatment of a three-axis astro-inertial system; we assume that the astronomical information is used not merely to correct the coordinate readings but also to control the response of the inertial system (to suppress instability, to cause damping, and to reduce the response time).