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 61705U 26145.27948490 +.00000000 +00000-0 +24963-4 0 00001
2 61705 53.1590 159.8919 0001169 89.7088 270.4047 15.30190215 04
| Epoch (UTC): | 25 May 2026 06:42:27 |
| Eccentricity: | 0.0001169 |
| inclination: | 53.1590° |
| perigee height: | 474 km |
| apogee height: | 476 km |
| right ascension of ascending node: | 159.8919° |
| argument of perigee: | 89.7088° |
| revolutions per day: | 15.30190215 |
| mean anomaly at epoch: | 270.4047° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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