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 61904U 26145.59850779 +.00000000 +00000-0 +50657-3 0 00007
2 61904 97.4140 216.8477 0069652 83.9534 276.9626 15.07702024 08
| Epoch (UTC): | 25 May 2026 14:21:51 |
| Eccentricity: | 0.0069652 |
| inclination: | 97.4140° |
| perigee height: | 495 km |
| apogee height: | 591 km |
| right ascension of ascending node: | 216.8477° |
| argument of perigee: | 83.9534° |
| revolutions per day: | 15.07702024 |
| mean anomaly at epoch: | 276.9626° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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