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 61717U 26145.27128927 +.00000000 +00000-0 +51693-4 0 00009
2 61717 53.1610 105.4752 0001441 81.0260 279.0904 15.30192612 02
| Epoch (UTC): | 25 May 2026 06:30:39 |
| Eccentricity: | 0.0001441 |
| inclination: | 53.1610° |
| perigee height: | 474 km |
| apogee height: | 476 km |
| right ascension of ascending node: | 105.4752° |
| argument of perigee: | 81.0260° |
| revolutions per day: | 15.30192612 |
| mean anomaly at epoch: | 279.0904° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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