TITAN 3C TRANSTAGE DEB, 8832
Orbit data source: Space-Track
TITAN 3C TRANSTAGE DEB, 8832 is space debris in GEO originally from a launch on Mon, 15 Mar 1976 UTC launched from the Air Force Eastern Test Range (AFETR). 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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8832 intel report (Beta)
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Expand to show TLE details & historyLast TLE update: 1 day ago
TLE from 1 day ago
0 TITAN 3C TRANSTAGE DEB
1 8832U 76023J 26314.54272904 -.00000258 00000-0 00000+0 0 9993
2 8832 22.1481 40.8667 0137511 103.9818 277.2221 0.98261282119046Epoch: 2026-11-10T13:01Z
TLE epoch observation values (Epoch: 2026-11-10T13:01:31.789Z)
Latitude
7.30329°
Longitude
174.06379°
Altitude
36,293.673 km
Speed
3.059 km/s
True Right ascension
03h 56m 35s
True Declination
7° 17' 46"
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
13:33:59
Azimuth
Unknown
Elevation
Unknown
Doppler factor
Unknown
Orbital elements
Apogee altitude
36,948.343 km
Perigee altitude
35,772.932 km
Semi-major axis
42,738.775 km
Eccentricity
0.01375
Inclination
22.1481°
RAAN
40.8667°
Arg. of periapsis
103.9818°
True anomaly
275.65565°
Mean anomaly
277.2221°
Eccentric anomaly
276.43919°
Mean motion
0.24565 °/min
Orbital period
1,465.52 mins
BSTAR
0
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Other satellites on launch #23 in the year 1976 (1976-03-15 UTC)
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You can import UDL-sourced sensor .json files into the Sandbox to generate a visibility chart that accounts for multi-vendor sensor geometry.TITAN 3C TRANSTAGE DEB Visibility
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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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| TITAN 3C TRANSTAGE DEB is likely not visible in the next few days. |
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8832 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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