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 50002U 26144.04709963 +.00000000 +00000-0 +00000-0 0 00005
2 50002 0.0233 286.9024 0001726 149.4113 283.7007 1.00273690 02
| Epoch (UTC): | 24 May 2026 01:07:49 |
| Eccentricity: | 0.0001726 |
| inclination: | 0.0233° |
| perigee height: | 35779 km |
| apogee height: | 35793 km |
| right ascension of ascending node: | 286.9024° |
| argument of perigee: | 149.4113° |
| revolutions per day: | 1.00273690 |
| mean anomaly at epoch: | 283.7007° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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