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 62802U 26145.55464985 +.00000000 +00000-0 +13123-3 0 00008
2 62802 88.9714 86.0786 0016746 240.3964 119.5519 13.51012086 02
| Epoch (UTC): | 25 May 2026 13:18:41 |
| Eccentricity: | 0.0016746 |
| inclination: | 88.9714° |
| perigee height: | 1056 km |
| apogee height: | 1081 km |
| right ascension of ascending node: | 86.0786° |
| argument of perigee: | 240.3964° |
| revolutions per day: | 13.51012086 |
| mean anomaly at epoch: | 119.5519° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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