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 26076.04882220 +.00000000 +00000-0 +10606-3 0 00008
2 27940 98.3822 251.5849 0011897 288.8982 71.0933 14.69379315 02
| Epoch (UTC): | 17 March 2026 01:10:18 |
| Eccentricity: | 0.0011897 |
| inclination: | 98.3822° |
| perigee height: | 655 km |
| apogee height: | 671 km |
| right ascension of ascending node: | 251.5849° |
| argument of perigee: | 288.8982° |
| revolutions per day: | 14.69379315 |
| mean anomaly at epoch: | 71.0933° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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