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 19650U 26134.10072253 +.00000000 +00000-0 -63281-4 0 00005
2 19650 71.0014 13.8638 0016554 271.0101 88.9125 14.16162789 06
| Epoch (UTC): | 14 May 2026 02:25:02 |
| Eccentricity: | 0.0016554 |
| inclination: | 71.0014° |
| perigee height: | 826 km |
| apogee height: | 850 km |
| right ascension of ascending node: | 13.8638° |
| argument of perigee: | 271.0101° |
| revolutions per day: | 14.16162789 |
| mean anomaly at epoch: | 88.9125° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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