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 19274U 26040.20239687 +.00000000 +00000-0 +34501-3 0 00001
2 19274 82.4702 291.8945 0011327 278.4240 81.5717 15.31079694 01
| Epoch (UTC): | 09 February 2026 04:51:27 |
| Eccentricity: | 0.0011327 |
| inclination: | 82.4702° |
| perigee height: | 465 km |
| apogee height: | 480 km |
| right ascension of ascending node: | 291.8945° |
| argument of perigee: | 278.4240° |
| revolutions per day: | 15.31079694 |
| mean anomaly at epoch: | 81.5717° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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