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 40262U 26022.30082840 +.00000000 +00000-0 +27063-3 0 00005
2 40262 98.3771 238.5974 0040533 290.4362 69.2496 14.76190376 00
| Epoch (UTC): | 22 January 2026 07:13:11 |
| Eccentricity: | 0.0040533 |
| inclination: | 98.3771° |
| perigee height: | 613 km |
| apogee height: | 670 km |
| right ascension of ascending node: | 238.5974° |
| argument of perigee: | 290.4362° |
| revolutions per day: | 14.76190376 |
| mean anomaly at epoch: | 69.2496° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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