View from above orbital plane
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View from above satellite
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Ground track
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The orbit is defined by the following mean orbital elements,
1 21915U 92015 A 92093.33219542 .00123286 +00000-0 +31160-3 00309
2 21915 056.9940 239.9531 0007373 345.4591 014.6052 15.95029154001400
| Epoch (UTC): | 02 April 1992 07:58:21 |
| Eccentricity: | 0.0007373 |
| inclination: | 56.9940° |
| perigee height: | 283 km |
| apogee height: | 293 km |
| right ascension of ascending node: | 239.9531° |
| argument of perigee: | 345.4591° |
| revolutions per day: | 15.95029154 |
| mean anomaly at epoch: | 14.6052° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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