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 31789U 07028A 25245.88404721 .11966368 80134-5 21942-3 0 9999
2 31789 64.4512 105.1818 0013664 269.3145 90.6474 16.46419746 6505
| Epoch (UTC): | 02 September 2025 21:13:01 |
| Eccentricity: | 0.0013664 |
| inclination: | 64.4512° |
| perigee height: | 140 km |
| apogee height: | 158 km |
| right ascension of ascending node: | 105.1818° |
| argument of perigee: | 269.3145° |
| revolutions per day: | 16.46419746 |
| mean anomaly at epoch: | 90.6474° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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