View from above orbital plane
|
View from above satellite
|
Ground track
|
The orbit is defined by the following mean orbital elements,
1 63384U 26145.13085059 +.00000000 +00000-0 -45821-3 0 00000
2 63384 53.1602 55.2157 0001758 74.2712 285.8485 15.35407321 03
| Epoch (UTC): | 25 May 2026 03:08:25 |
| Eccentricity: | 0.0001758 |
| inclination: | 53.1602° |
| perigee height: | 459 km |
| apogee height: | 461 km |
| right ascension of ascending node: | 55.2157° |
| argument of perigee: | 74.2712° |
| revolutions per day: | 15.35407321 |
| mean anomaly at epoch: | 285.8485° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
|
|