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 26042.09768199 +.00000000 +00000-0 +34006-3 0 00005
2 19274 82.4704 289.9703 0011248 270.4051 89.5901 15.31116784 02
| Epoch (UTC): | 11 February 2026 02:20:39 |
| Eccentricity: | 0.0011248 |
| inclination: | 82.4704° |
| perigee height: | 465 km |
| apogee height: | 480 km |
| right ascension of ascending node: | 289.9703° |
| argument of perigee: | 270.4051° |
| revolutions per day: | 15.31116784 |
| mean anomaly at epoch: | 89.5901° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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