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 69001U 26145.00002315 +.00000000 +00000-0 +26465-2 0 00003
2 69001 97.7375 42.8657 0002978 205.4679 114.8982 14.91010040 00
| Epoch (UTC): | 25 May 2026 00:00:02 |
| Eccentricity: | 0.0002978 |
| inclination: | 97.7375° |
| perigee height: | 593 km |
| apogee height: | 597 km |
| right ascension of ascending node: | 42.8657° |
| argument of perigee: | 205.4679° |
| revolutions per day: | 14.91010040 |
| mean anomaly at epoch: | 114.8982° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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