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 49305U 26145.43085870 +.00000000 +00000-0 -24923-3 0 00001
2 49305 87.8944 294.2459 0001944 95.1890 264.9461 13.14501300 08
| Epoch (UTC): | 25 May 2026 10:20:26 |
| Eccentricity: | 0.0001944 |
| inclination: | 87.8944° |
| perigee height: | 1204 km |
| apogee height: | 1207 km |
| right ascension of ascending node: | 294.2459° |
| argument of perigee: | 95.1890° |
| revolutions per day: | 13.14501300 |
| mean anomaly at epoch: | 264.9461° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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