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 22208U 26069.40046958 +.00000000 +00000-0 +79150-4 0 00002
2 22208 82.9226 172.0934 0035268 143.9352 283.2839 13.75432412 09
| Epoch (UTC): | 10 March 2026 09:36:40 |
| Eccentricity: | 0.0035268 |
| inclination: | 82.9226° |
| perigee height: | 954 km |
| apogee height: | 1006 km |
| right ascension of ascending node: | 172.0934° |
| argument of perigee: | 143.9352° |
| revolutions per day: | 13.75432412 |
| mean anomaly at epoch: | 283.2839° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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