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 00018U 59005 A 59269.32477950 .04655228 +00000-0 +00000-0 0 00146
2 00018 079.9899 251.4819 0140209 012.7649 347.4143 16.16111033006800
| Epoch (UTC): | 26 September 1959 07:47:40 |
| Eccentricity: | 0.0140209 |
| inclination: | 79.9899° |
| perigee height: | 137 km |
| apogee height: | 323 km |
| right ascension of ascending node: | 251.4819° |
| argument of perigee: | 12.7649° |
| revolutions per day: | 16.16111033 |
| mean anomaly at epoch: | 347.4143° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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