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 23223U 94054A 25093.39197103 0.00000000 00000-0 00000-0 0 09
2 23223 13.1261 13.4918 0028888 75.0452 285.2981 1.00270000 06
| Epoch (UTC): | 03 April 2025 09:24:26 |
| Eccentricity: | 0.0028888 |
| inclination: | 13.1261° |
| perigee height: | 35665 km |
| apogee height: | 35908 km |
| right ascension of ascending node: | 13.4918° |
| argument of perigee: | 75.0452° |
| revolutions per day: | 1.00270000 |
| mean anomaly at epoch: | 285.2981° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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