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 20624U 26039.47014243 +.00000000 +00000-0 -89483-4 0 00009
2 20624 71.0394 81.9223 0017289 252.1390 107.7847 14.14825222 09
| Epoch (UTC): | 08 February 2026 11:17:00 |
| Eccentricity: | 0.0017289 |
| inclination: | 71.0394° |
| perigee height: | 830 km |
| apogee height: | 855 km |
| right ascension of ascending node: | 81.9223° |
| argument of perigee: | 252.1390° |
| revolutions per day: | 14.14825222 |
| mean anomaly at epoch: | 107.7847° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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