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 25400U 26022.28323829 +.00000000 +00000-0 +85689-4 0 00003
2 25400 98.8183 335.3401 0010408 143.9470 216.2413 14.26036879 05
| Epoch (UTC): | 22 January 2026 06:47:51 |
| Eccentricity: | 0.0010408 |
| inclination: | 98.8183° |
| perigee height: | 798 km |
| apogee height: | 812 km |
| right ascension of ascending node: | 335.3401° |
| argument of perigee: | 143.9470° |
| revolutions per day: | 14.26036879 |
| mean anomaly at epoch: | 216.2413° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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