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 65434U 26145.31494854 +.00000000 +00000-0 +57336-3 0 00008
2 65434 97.4486 359.4580 0002569 80.7040 279.4478 15.05654783 02
| Epoch (UTC): | 25 May 2026 07:33:31 |
| Eccentricity: | 0.0002569 |
| inclination: | 97.4486° |
| perigee height: | 548 km |
| apogee height: | 551 km |
| right ascension of ascending node: | 359.4580° |
| argument of perigee: | 80.7040° |
| revolutions per day: | 15.05654783 |
| mean anomaly at epoch: | 279.4478° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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