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 59388U 26145.66668980 +.00000000 +00000-0 +91575-3 0 00003
2 59388 53.1602 258.2249 0001575 92.4842 329.0889 15.33523919 01
| Epoch (UTC): | 25 May 2026 16:00:01 |
| Eccentricity: | 0.0001575 |
| inclination: | 53.1602° |
| perigee height: | 464 km |
| apogee height: | 466 km |
| right ascension of ascending node: | 258.2249° |
| argument of perigee: | 92.4842° |
| revolutions per day: | 15.33523919 |
| mean anomaly at epoch: | 329.0889° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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