SBS 4 R/B(PAM-D), 15245
Orbit data source: Space-Track
SBS 4 R/B(PAM-D), 15245 is space debris in HEO originally from a launch on Thu, 30 Aug 1984 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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15245 intel report (Beta)
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Edit Public Description
Identifier
Orbit
Last TLE update
1 day ago
Origin
Manufacturer
Thiokol/TE
Mission
Spacecraft
Bus & Motor
STAR 48, Unknown motor
Mass
132 kg wet, 132 kg dry
Launch date (UTC)
Launch vehicle
Unknown
Launch site
Object type
Shape & HBR
Sphere + Cone, 1.1 m
Radar Cross Section
2.822 m², Large (>1 m²)
Expand to show TLE details & history
TLE from 1 day ago
0 SBS 4 R/B(PAM-D)
1 15245U 84093F 25196.91200153 .00000499 00000-0 57177-3 0 9997
2 15245 22.9870 1.6911 6853721 226.2234 51.6238 2.79234231380265Epoch: 2025-07-15T21:53Z
TLE epoch observation values (Epoch: 2025-07-15T21:53:16.932Z)
Latitude
-0.00008°
Longitude
99.37078°
Altitude
15,110.471 km
Speed
4.288 km/s
True Right ascension
00h 06m 45s
True Declination
0° 00' 00"
Sunlit
Visualization orbit readout
Latitude
8.47428°
Longitude
119.20158°
Altitude
23,296.627 km
Speed
2.855 km/s
Apparent Right ascension
01h 59m 34s
Apparent Declination
0° 38' 11"
Sunlit
Visualization observer readout
Local Sidereal Time
21:56:43
Azimuth
109.298° ESE
Elevation
22.478°
Doppler factor
1
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Other satellites on launch #93 in the year 1984 (1984-08-30 UTC)
SBS 4 R/B(PAM-D) 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. |
|---|---|---|---|---|---|---|---|
| 338 mins | 2025-07-17 09:15:23.223Z | 109.321° ESE | 2025-07-17 13:06:23.223Z | 106.114° ESE | 33.908° | 2025-07-17 14:53:23.223Z | 90.138° ESE |
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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