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 55420U 26145.43287216 +.00000000 +00000-0 +18663-5 0 00009
2 55420 69.9992 210.9804 0003562 269.8301 90.2450 14.98329065 08
| Epoch (UTC): | 25 May 2026 10:23:20 |
| Eccentricity: | 0.0003562 |
| inclination: | 69.9992° |
| perigee height: | 570 km |
| apogee height: | 575 km |
| right ascension of ascending node: | 210.9804° |
| argument of perigee: | 269.8301° |
| revolutions per day: | 14.98329065 |
| mean anomaly at epoch: | 90.2450° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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