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 26160.21299163 +.00000000 +00000-0 +90026-4 0 00004
2 27940 98.3873 337.9777 0013547 27.4277 332.7640 14.69480978 05
| Epoch (UTC): | 09 June 2026 05:06:42 |
| Eccentricity: | 0.0013547 |
| inclination: | 98.3873° |
| perigee height: | 653 km |
| apogee height: | 672 km |
| right ascension of ascending node: | 337.9777° |
| argument of perigee: | 27.4277° |
| revolutions per day: | 14.69480978 |
| mean anomaly at epoch: | 332.7640° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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