INTELSAT 33E DEB, 61990
Orbit data source: Space-Track
INTELSAT 33E DEB, 61990 is space debris in GEO originally from a launch on Wed, 24 Aug 2016 UTC launched from the French Guiana (FRGUI). Debris objects in space refer to the collection of defunct objects orbiting the Earth. Examples of debris include non-operational satellites, rocket bodies, and fragments generated from explosions, collisions, or faulty payload assembly.
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61990 intel report (Beta)
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Edit Public Description
Expand to show TLE details & historyLast TLE update: 15 hours ago
TLE from 15 hours ago
0 INTELSAT 33E DEB
1 61990U 16053G 25251.29025761 -.00000275 00000-0 00000-0 0 9992
2 61990 0.7556 71.3041 0110320 344.5435 305.1982 1.01390982 3296
Epoch: 2025-09-08T06:57Z
TLE epoch observation values (Epoch: 2025-09-08T06:57:58.257Z)
Latitude
-0.72766°
Longitude
-92.08891°
Altitude
35,212.581 km
Speed
3.106 km/s
True Right ascension
00h 00m 00s
True Declination
0° 43' 37"
Sunlit
Visualization orbit readout
Latitude
Unknown
Longitude
Unknown
Altitude
Unknown
Speed
Unknown
Apparent Right ascension
Unknown
Apparent Declination
Unknown
Sunlit
Visualization observer readout
Local Sidereal Time
13:52:43
Azimuth
Unknown
Elevation
Unknown
Doppler factor
Unknown
Orbital elements
Apogee altitude
35,938.555 km
Perigee altitude
35,015.067 km
Semi-major axis
41,854.948 km
Eccentricity
0.01103
Inclination
0.7556°
RAAN
71.3041°
Arg. of periapsis
344.5435°
True anomaly
304.15695°
Mean anomaly
305.1982°
Eccentric anomaly
304.6784°
Mean motion
0.25347 °/min
Orbital period
1,420.3 mins
BSTAR
0
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Other satellites on launch #53 in the year 2016 (2016-08-24 UTC)
INTELSAT 33E DEB Visibility forecast
Observer location: undefined°, undefined°
Span | Click to sort rows by Start time (UTC) header in descending order | Start Az. | Max El. time (UTC) | Max El. Az. | Max El. | End time (UTC) | End Az. |
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1440 mins | 2025-09-08 21:40:23.509Z | 154.661° SSE | 2025-09-08 21:40:23.509Z | 154.661° SSE | 33.31° | 2025-09-09 21:40:23.509Z | 149.341° SSE |
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61990 neighbors
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Co-orbital & Co-planar RSOs
Thresholds — Semi-major Axis: ±100 km, RAAN: ±3°, Inclination: ±5°
TCA is derived from TLE conjunctions
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