تحدید إحداثیات الموقع والسرعة للقمر الاصطناعي في كل من مداري القطع الناقص والزائد باستخدام طریقة نیوتن – رافسن.
satellite orbit determination
elliptical orbit
hyperbola orbit.
The present work determination astronomical ephemeris for satellites (determination position and velocity of satellite and orbital elements) in elliptical orbit where orbital elements in perigee point were known, therefore kepler's equation for elliptical orbit was solved by using Newton-Rephson method for numerical approximation.For the hyperbola orbit which represent orbit of shuttle (discovery join) far rang where solve kepler equation for hyperbola by use the same method pervious and then determination the coordinates of position and velocity for satellite or shuttle and the required programs are designing
