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 25490U 26088.03598875 +.00000000 +00000-0 +89497-4 0 00003
2 25490 85.0643 293.0713 0016010 140.2529 219.9861 14.71646991 08
| Epoch (UTC): | 29 March 2026 00:51:49 |
| Eccentricity: | 0.0016010 |
| inclination: | 85.0643° |
| perigee height: | 645 km |
| apogee height: | 667 km |
| right ascension of ascending node: | 293.0713° |
| argument of perigee: | 140.2529° |
| revolutions per day: | 14.71646991 |
| mean anomaly at epoch: | 219.9861° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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