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 20150U 26022.27051764 +.00000000 +00000-0 +10311-3 0 00004
2 20150 82.9410 283.7205 0029369 147.8239 332.3916 13.75900675 04
| Epoch (UTC): | 22 January 2026 06:29:32 |
| Eccentricity: | 0.0029369 |
| inclination: | 82.9410° |
| perigee height: | 957 km |
| apogee height: | 1000 km |
| right ascension of ascending node: | 283.7205° |
| argument of perigee: | 147.8239° |
| revolutions per day: | 13.75900675 |
| mean anomaly at epoch: | 332.3916° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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