View from above orbital plane
|
View from above satellite
|
Ground track
|
The orbit is defined by the following mean orbital elements,
1 29274U 26066.04321012 +.00000000 +00000-0 +33527-2 0 00002
2 29274 5.8423 243.7607 5602584 205.8445 109.7641 4.48720391 01
| Epoch (UTC): | 07 March 2026 01:02:13 |
| Eccentricity: | 0.5602584 |
| inclination: | 5.8423° |
| perigee height: | 450 km |
| apogee height: | 17848 km |
| right ascension of ascending node: | 243.7607° |
| argument of perigee: | 205.8445° |
| revolutions per day: | 4.48720391 |
| mean anomaly at epoch: | 109.7641° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
|
|