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 03118U 68009 A 68044.12992503 .00164908 +00000-0 +00000-0 0 00088
2 03118 064.9409 266.7051 0093825 051.6946 309.2503 16.03701635001096
| Epoch (UTC): | 13 February 1968 03:07:05 |
| Eccentricity: | 0.0093825 |
| inclination: | 64.9409° |
| perigee height: | 202 km |
| apogee height: | 326 km |
| right ascension of ascending node: | 266.7051° |
| argument of perigee: | 51.6946° |
| revolutions per day: | 16.03701635 |
| mean anomaly at epoch: | 309.2503° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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