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 66364U 26145.63680860 +.00000000 +00000-0 +66849-3 0 00009
2 66364 53.1605 235.2505 0000963 64.7198 295.3903 15.30216352 01
| Epoch (UTC): | 25 May 2026 15:17:00 |
| Eccentricity: | 0.0000963 |
| inclination: | 53.1605° |
| perigee height: | 475 km |
| apogee height: | 476 km |
| right ascension of ascending node: | 235.2505° |
| argument of perigee: | 64.7198° |
| revolutions per day: | 15.30216352 |
| mean anomaly at epoch: | 295.3903° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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