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 20465U 26020.24197562 +.00000000 +00000-0 +34766-3 0 00005
2 20465 82.4670 95.1535 0010928 135.0092 225.2025 15.10849490 03
| Epoch (UTC): | 20 January 2026 05:48:26 |
| Eccentricity: | 0.0010928 |
| inclination: | 82.4670° |
| perigee height: | 526 km |
| apogee height: | 541 km |
| right ascension of ascending node: | 95.1535° |
| argument of perigee: | 135.0092° |
| revolutions per day: | 15.10849490 |
| mean anomaly at epoch: | 225.2025° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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