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 19922U 26017.16875845 +.00000000 +00000-0 +79984-4 0 00007
2 19922 82.9571 260.0338 0037649 99.8557 260.6854 13.77490341 01
| Epoch (UTC): | 17 January 2026 04:03:00 |
| Eccentricity: | 0.0037649 |
| inclination: | 82.9571° |
| perigee height: | 945 km |
| apogee height: | 1000 km |
| right ascension of ascending node: | 260.0338° |
| argument of perigee: | 99.8557° |
| revolutions per day: | 13.77490341 |
| mean anomaly at epoch: | 260.6854° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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