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 54680U 26145.26091981 +.00000000 +00000-0 +35375-4 0 00007
2 54680 87.9107 233.3259 0001957 85.9975 274.1380 13.16593118 02
| Epoch (UTC): | 25 May 2026 06:15:43 |
| Eccentricity: | 0.0001957 |
| inclination: | 87.9107° |
| perigee height: | 1196 km |
| apogee height: | 1199 km |
| right ascension of ascending node: | 233.3259° |
| argument of perigee: | 85.9975° |
| revolutions per day: | 13.16593118 |
| mean anomaly at epoch: | 274.1380° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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