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 02680U 26106.07912584 +.00000000 +00000-0 +31287-3 0 00004
2 02680 39.4393 14.8108 0698903 48.6830 317.1948 13.41916665 00
| Epoch (UTC): | 16 April 2026 01:53:56 |
| Eccentricity: | 0.0698903 |
| inclination: | 39.4393° |
| perigee height: | 579 km |
| apogee height: | 1625 km |
| right ascension of ascending node: | 14.8108° |
| argument of perigee: | 48.6830° |
| revolutions per day: | 13.41916665 |
| mean anomaly at epoch: | 317.1948° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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