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 61914U 26145.23554837 +.00000000 +00000-0 +51918-3 0 00006
2 61914 42.9999 209.0341 0001492 259.0108 101.0576 15.27585785 08
| Epoch (UTC): | 25 May 2026 05:39:11 |
| Eccentricity: | 0.0001492 |
| inclination: | 42.9999° |
| perigee height: | 482 km |
| apogee height: | 484 km |
| right ascension of ascending node: | 209.0341° |
| argument of perigee: | 259.0108° |
| revolutions per day: | 15.27585785 |
| mean anomaly at epoch: | 101.0576° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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