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 62324U 26145.56792487 +.00000000 +00000-0 +43014-4 0 00002
2 62324 86.5029 351.0253 0001522 81.8287 278.3019 13.24409108 04
| Epoch (UTC): | 25 May 2026 13:37:48 |
| Eccentricity: | 0.0001522 |
| inclination: | 86.5029° |
| perigee height: | 1167 km |
| apogee height: | 1169 km |
| right ascension of ascending node: | 351.0253° |
| argument of perigee: | 81.8287° |
| revolutions per day: | 13.24409108 |
| mean anomaly at epoch: | 278.3019° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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