| 摘要 |
<p>1. Method for determining the course in aircraft which are equipped with at least one inertial navigation system including at least two accelerometers and comprising a device for receiving and for processing data for speed computation support which are obtained from the signals of navigation satellites, in which positional data with respect to the earth's perpendicular are determined on the ground by an initial alignment of the inertial navigation system before operation of the aircraft and are stored and the accelerations occurring during operation of the aircraft are measured with respect to an aircraft-fixed coordinate system and are converted into a coordinate system (KH) with horizontal alignment, characterized in that the course is determined by forming the difference between the acceleration vector (a1 **N,E ) in the coordinate system (KH) with horizontal alignment and the acceleration vector (as **N,E ), determined from the satellite data, and in that the difference angle (vphi Z) is formed continuously or at time intervals and is supplied to an azimuth filter.</p> |
