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 62042U 26145.50803919 +.00000000 +00000-0 +55920-3 0 00004
2 62042 42.9991 182.5244 0001791 262.8570 97.2078 15.27597524 04
| Epoch (UTC): | 25 May 2026 12:11:34 |
| Eccentricity: | 0.0001791 |
| inclination: | 42.9991° |
| perigee height: | 482 km |
| apogee height: | 484 km |
| right ascension of ascending node: | 182.5244° |
| argument of perigee: | 262.8570° |
| revolutions per day: | 15.27597524 |
| mean anomaly at epoch: | 97.2078° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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