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 27004U 26159.45784590 +.00000000 +00000-0 +32382-4 0 00003
2 27004 99.8079 336.1531 0020048 163.2079 251.8216 13.70262040 01
| Epoch (UTC): | 08 June 2026 10:59:17 |
| Eccentricity: | 0.0020048 |
| inclination: | 99.8079° |
| perigee height: | 984 km |
| apogee height: | 1013 km |
| right ascension of ascending node: | 336.1531° |
| argument of perigee: | 163.2079° |
| revolutions per day: | 13.70262040 |
| mean anomaly at epoch: | 251.8216° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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