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 39120U 26146.00167515 +.00000000 +00000-0 +00000-0 0 00002
2 39120 4.4426 52.4875 0002128 4.3774 137.5199 1.00271207 01
| Epoch (UTC): | 26 May 2026 00:02:24 |
| Eccentricity: | 0.0002128 |
| inclination: | 4.4426° |
| perigee height: | 35778 km |
| apogee height: | 35796 km |
| right ascension of ascending node: | 52.4875° |
| argument of perigee: | 4.3774° |
| revolutions per day: | 1.00271207 |
| mean anomaly at epoch: | 137.5199° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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