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 06080U 26088.19560968 +.00000000 +00000-0 +90569-4 0 00008
2 06080 81.2397 149.6973 0047763 288.7069 70.8916 14.01292751 05
| Epoch (UTC): | 29 March 2026 04:41:40 |
| Eccentricity: | 0.0047763 |
| inclination: | 81.2397° |
| perigee height: | 855 km |
| apogee height: | 924 km |
| right ascension of ascending node: | 149.6973° |
| argument of perigee: | 288.7069° |
| revolutions per day: | 14.01292751 |
| mean anomaly at epoch: | 70.8916° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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