View from above orbital plane
|
View from above satellite
|
Ground track
|
The orbit is defined by the following mean orbital elements,
1 60565U 26145.51643743 +.00000000 +00000-0 +94889-3 0 00007
2 60565 97.6961 233.8918 0004414 123.5424 236.6233 15.20961922 02
| Epoch (UTC): | 25 May 2026 12:23:40 |
| Eccentricity: | 0.0004414 |
| inclination: | 97.6961° |
| perigee height: | 500 km |
| apogee height: | 506 km |
| right ascension of ascending node: | 233.8918° |
| argument of perigee: | 123.5424° |
| revolutions per day: | 15.20961922 |
| mean anomaly at epoch: | 236.6233° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
|
|