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 69010U 26145.64603191 +.00000000 +00000-0 +11453-3 0 00004
2 69010 97.4065 43.8737 0007081 103.1126 257.0900 15.20318912 06
| Epoch (UTC): | 25 May 2026 15:30:17 |
| Eccentricity: | 0.0007081 |
| inclination: | 97.4065° |
| perigee height: | 500 km |
| apogee height: | 510 km |
| right ascension of ascending node: | 43.8737° |
| argument of perigee: | 103.1126° |
| revolutions per day: | 15.20318912 |
| mean anomaly at epoch: | 257.0900° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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