Inertial Navigation System Aiding Using Vision

The aiding of an INS using measurements over time of the line of sight of ground features as they come into view of an onboard camera is investigated. The objective is to quantify the reduction in the navigation states\u27 errors by using bearings-only measurements over time of terrain features in the aircraft\u27s field of view. INS aiding is achieved through the use of a Kalman Filter. The design of the Kalman Filter is presented and it is shown that during a long range, wings level cruising flight at constant velocity and altitude, a 90% reduction in the aided INS-calculated navigation state errors compared to a free INS, is possible