The problem of calculating earth satellite entry/exit positions and times through the earth's umbra and penumbra for elliptical satellite orbits is solved in closed form; i.e., without iteration, by reducing the problem to that of finding the roots of a quartic polynomial in a cartesian coordinate. Typical results from an algorithm constructed from the method are shown.
Calculating satellite umbra/penumbra entry and exit positions and times
1991-12-01
Sonstige
Keine Angabe
Englisch
On Satellite Umbra/Penumbra Entry and Exit Positions
Online Contents | 1998
|On Satellite Umbra/Penumbra Entry and Exit Positions
Springer Verlag | 1998
|TECHNICAL NOTE - On Satellite Umbra-Penumbra Entry and Exit Positions
Online Contents | 1998
|On Satellite Umbra/Penumbra Entry and Exit Positions (AAS 97-155)
British Library Conference Proceedings | 1997
|Umbra and penumbra eclipse factors for satellite orbits
AIAA | 1964
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