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 66362U 26145.63997769 +.00000000 +00000-0 +64649-3 0 00002
2 66362 53.1582 235.2733 0000909 82.7029 277.4076 15.30205931 02
| Epoch (UTC): | 25 May 2026 15:21:34 |
| Eccentricity: | 0.0000909 |
| inclination: | 53.1582° |
| perigee height: | 475 km |
| apogee height: | 476 km |
| right ascension of ascending node: | 235.2733° |
| argument of perigee: | 82.7029° |
| revolutions per day: | 15.30205931 |
| mean anomaly at epoch: | 277.4076° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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