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 68265U 26144.79420647 +.00000000 +00000-0 +58195-3 0 00007
2 68265 53.1581 326.4285 0000851 79.0816 281.0281 15.30202623 03
| Epoch (UTC): | 24 May 2026 19:03:39 |
| Eccentricity: | 0.0000851 |
| inclination: | 53.1581° |
| perigee height: | 475 km |
| apogee height: | 476 km |
| right ascension of ascending node: | 326.4285° |
| argument of perigee: | 79.0816° |
| revolutions per day: | 15.30202623 |
| mean anomaly at epoch: | 281.0281° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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