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 62025U 26145.47741352 +.00000000 +00000-0 +77896-3 0 00009
2 62025 53.1597 171.2955 0001267 73.0520 287.0622 15.34398948 01
| Epoch (UTC): | 25 May 2026 11:27:28 |
| Eccentricity: | 0.0001267 |
| inclination: | 53.1597° |
| perigee height: | 462 km |
| apogee height: | 464 km |
| right ascension of ascending node: | 171.2955° |
| argument of perigee: | 73.0520° |
| revolutions per day: | 15.34398948 |
| mean anomaly at epoch: | 287.0622° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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