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 27940U 26075.23166450 +.00000000 +00000-0 +11971-3 0 00004
2 27940 98.3821 250.7464 0011920 291.6986 68.2949 14.69378592 09
| Epoch (UTC): | 16 March 2026 05:33:35 |
| Eccentricity: | 0.0011920 |
| inclination: | 98.3821° |
| perigee height: | 655 km |
| apogee height: | 671 km |
| right ascension of ascending node: | 250.7464° |
| argument of perigee: | 291.6986° |
| revolutions per day: | 14.69378592 |
| mean anomaly at epoch: | 68.2949° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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