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 05580U 26088.20050182 +.00000000 +00000-0 +42461-3 0 00003
2 05580 82.0430 1.0327 0503030 96.4389 269.4290 14.01441916 03
| Epoch (UTC): | 29 March 2026 04:48:43 |
| Eccentricity: | 0.0503030 |
| inclination: | 82.0430° |
| perigee height: | 523 km |
| apogee height: | 1254 km |
| right ascension of ascending node: | 1.0327° |
| argument of perigee: | 96.4389° |
| revolutions per day: | 14.01441916 |
| mean anomaly at epoch: | 269.4290° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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