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 19574U 26021.43815117 +.00000000 +00000-0 +94220-4 0 00001
2 19574 82.5300 86.4120 0020437 190.3881 180.0908 14.85600278 00
| Epoch (UTC): | 21 January 2026 10:30:56 |
| Eccentricity: | 0.0020437 |
| inclination: | 82.5300° |
| perigee height: | 597 km |
| apogee height: | 626 km |
| right ascension of ascending node: | 86.4120° |
| argument of perigee: | 190.3881° |
| revolutions per day: | 14.85600278 |
| mean anomaly at epoch: | 180.0908° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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