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 69016U 26145.43575624 +.00000000 +00000-0 +12767-3 0 00005
2 69016 97.4055 43.6935 0009433 122.8073 237.4073 15.21214977 01
| Epoch (UTC): | 25 May 2026 10:27:29 |
| Eccentricity: | 0.0009433 |
| inclination: | 97.4055° |
| perigee height: | 496 km |
| apogee height: | 509 km |
| right ascension of ascending node: | 43.6935° |
| argument of perigee: | 122.8073° |
| revolutions per day: | 15.21214977 |
| mean anomaly at epoch: | 237.4073° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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