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 29155U 26032.14489262 +.00000000 +00000-0 +00000-0 0 00004
2 29155 4.1795 78.1050 0061650 270.9918 250.3601 0.98784381 00
| Epoch (UTC): | 01 February 2026 03:28:38 |
| Eccentricity: | 0.0061650 |
| inclination: | 4.1795° |
| perigee height: | 35946 km |
| apogee height: | 36471 km |
| right ascension of ascending node: | 78.1050° |
| argument of perigee: | 270.9918° |
| revolutions per day: | 0.98784381 |
| mean anomaly at epoch: | 250.3601° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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