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 00432U 62051 A 65106.86109634 .00000000 +00000-0 +00000-0 0 9998
2 00432 033.6000 212.2097 8681490 141.0172 333.9797 00.66732046001228
| Epoch (UTC): | 16 April 1965 20:39:58 |
| Eccentricity: | 0.8681490 |
| inclination: | 33.6000° |
| perigee height: | 915 km |
| apogee height: | 96958 km |
| right ascension of ascending node: | 212.2097° |
| argument of perigee: | 141.0172° |
| revolutions per day: | 0.66732046 |
| mean anomaly at epoch: | 333.9797° |
The dashed part of the orbit path shows where the satellite is in the earth's shadow,
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