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 58714U 26145.22111008 +.00000000 +00000-0 +35765-4 0 00001
2 58714 53.1603 234.3820 0000717 99.4977 260.6105 15.30191731 08
| Epoch (UTC): | 25 May 2026 05:18:23 |
| Eccentricity: | 0.0000717 |
| inclination: | 53.1603° |
| perigee height: | 475 km |
| apogee height: | 476 km |
| right ascension of ascending node: | 234.3820° |
| argument of perigee: | 99.4977° |
| revolutions per day: | 15.30191731 |
| mean anomaly at epoch: | 260.6105° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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