DELTA 4 R/B, 40102
Orbit data source: Space-Track
DELTA 4 R/B, 40102 is space debris in GEO originally from a launch on Mon, 28 Jul 2014 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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40102 intel report (Beta)
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Edit Public Description
Expand to show TLE details & historyLast TLE update: 2 days ago
TLE from 2 days ago
0 DELTA 4 R/B
1 40102U 14043D 25240.48831535 -.00000012 00000-0 00000-0 0 9993
2 40102 8.5056 60.2150 0008243 294.8603 65.1925 0.98911043 23149
Epoch: 2025-08-28T11:43Z
TLE epoch observation values (Epoch: 2025-08-28T11:43:10.446Z)
Latitude
-0.00001°
Longitude
-92.40279°
Altitude
36,157.263 km
Speed
3.062 km/s
True Right ascension
04h 01m 21s
True Declination
0° 00' 00"
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
18:15:24
Azimuth
Unknown
Elevation
Unknown
Doppler factor
Unknown
Orbital elements
Apogee altitude
36,208.529 km
Perigee altitude
36,138.379 km
Semi-major axis
42,551.591 km
Eccentricity
0.00082
Inclination
8.5056°
RAAN
60.215°
Arg. of periapsis
294.8603°
True anomaly
65.27828°
Mean anomaly
65.1925°
Eccentric anomaly
65.23539°
Mean motion
0.24727 °/min
Orbital period
1,455.9 mins
BSTAR
0
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Other satellites on launch #43 in the year 2014 (2014-07-28 UTC)
DELTA 4 R/B 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 | 2025-08-30 02:41:40.815Z | 174.007° S | 2025-08-30 18:20:40.815Z | 177.116° S | 38.781° | 2025-08-31 02:41:40.815Z | 180.872° SSW |
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40102 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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