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 28384U 04034A 25049.82708287 0.00000000 00000-0 00000-0 0 01
2 28384 63.9236 276.3532 7375911 259.8969 17.5110 2.00643157 08
| Epoch (UTC): | 18 February 2025 19:50:59 |
| Eccentricity: | 0.7375911 |
| inclination: | 63.9236° |
| perigee height: | 589 km |
| apogee height: | 39760 km |
| right ascension of ascending node: | 276.3532° |
| argument of perigee: | 259.8969° |
| revolutions per day: | 2.00643157 |
| mean anomaly at epoch: | 17.5110° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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