| 摘要 |
<p>The present invention pertains to the field of radio-navigation and essentially relates to methods based on ephemeredes for determining the current values of the orbital position of an artificial satellite which is part of a satellite radio-navigation system. This invention can be used when carrying out measurements in the installation of users of signals from said satellite radio-navigation systems. This invention also relates to variants of a faster method for determining the co-ordinates of a satellite. This method involves determining the satellite co-ordinates at given nodal points of the orbit which are spaced from each other by a predetermined time interval, and also determining the velocity of the satellite at said nodal points. The method also involves determining, in an inertial geocentric co-ordinate system or in a Greenwich geocentric co-ordinate system, the satellite co-ordinates at points located between the nodal points according to special formulae or using a Taylor's second-order or third-order polynomial, a Taylor's sixth-order polynomial being used at the nodal points.</p> |
