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 51085U 22002DF 25333.89742758 .08611116 24880-5 48957-3 0 9998
2 51085 97.2882 55.3307 0009398 266.8492 93.1733 16.41487561216509
| Epoch (UTC): | 29 November 2025 21:32:17 |
| Eccentricity: | 0.0009398 |
| inclination: | 97.2882° |
| perigee height: | 156 km |
| apogee height: | 168 km |
| right ascension of ascending node: | 55.3307° |
| argument of perigee: | 266.8492° |
| revolutions per day: | 16.41487561 |
| mean anomaly at epoch: | 93.1733° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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