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 47805U 26144.98959086 +.00000000 +00000-0 +22591-2 0 00009
2 47805 53.1050 246.1516 0001957 358.6209 1.4781 15.21421279 05
| Epoch (UTC): | 24 May 2026 23:45:00 |
| Eccentricity: | 0.0001957 |
| inclination: | 53.1050° |
| perigee height: | 500 km |
| apogee height: | 503 km |
| right ascension of ascending node: | 246.1516° |
| argument of perigee: | 358.6209° |
| revolutions per day: | 15.21421279 |
| mean anomaly at epoch: | 1.4781° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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