View from above orbital plane
|
View from above satellite
|
Ground track
|
The orbit is defined by the following mean orbital elements,
1 59787U 26145.28177955 +.00000000 +00000-0 +26722-4 0 00004
2 59787 43.0017 135.9642 0000792 279.8172 80.2590 15.27580701 07
| Epoch (UTC): | 25 May 2026 06:45:45 |
| Eccentricity: | 0.0000792 |
| inclination: | 43.0017° |
| perigee height: | 483 km |
| apogee height: | 484 km |
| right ascension of ascending node: | 135.9642° |
| argument of perigee: | 279.8172° |
| revolutions per day: | 15.27580701 |
| mean anomaly at epoch: | 80.2590° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
|
|