View from above orbital plane
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View from above satellite
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Ground track
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The orbit is defined by the following mean orbital elements,
1 00009U 58005 A 59275.28696823 .00892850 +00000-0 +00000-0 0 9991
2 00009 050.2549 082.4216 0254534 057.7226 303.5234 15.51612549060703
| Epoch (UTC): | 02 October 1959 06:53:14 |
| Eccentricity: | 0.0254534 |
| inclination: | 50.2549° |
| perigee height: | 239 km |
| apogee height: | 585 km |
| right ascension of ascending node: | 82.4216° |
| argument of perigee: | 57.7226° |
| revolutions per day: | 15.51612549 |
| mean anomaly at epoch: | 303.5234° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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