View from above orbital plane
|
View from above satellite
|
Ground track
|
The orbit is defined by the following mean orbital elements,
1 06155U 26042.20674980 +.00000000 +00000-0 +19576-3 0 00001
2 06155 35.0012 100.9417 0033337 148.1796 212.0927 14.77608486 01
| Epoch (UTC): | 11 February 2026 04:57:43 |
| Eccentricity: | 0.0033337 |
| inclination: | 35.0012° |
| perigee height: | 613 km |
| apogee height: | 660 km |
| right ascension of ascending node: | 100.9417° |
| argument of perigee: | 148.1796° |
| revolutions per day: | 14.77608486 |
| mean anomaly at epoch: | 212.0927° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
|
|