SPACEMOBILE-001, 61047
Orbit data source: Space-Track
SPACEMOBILE-001, 61047 is a payload satellite owned by AST & Science (US) in LEO that was launched on Thu, 12 Sep 2024 UTC via an FALCON 9 launch vehicle from the Air Force Eastern Test Range (AFETR). Payload-class satellites include a variety of spacecraft equipped with specific instruments for various scientific and technological missions. These include communications satellites like Starlink; space stations such as the ISS; scientific satellites like the Hubble; Earth observation satellites from companies like Planet Labs, Umbra, and HawkEye 360; GPS; miniature CubeSats for education and research; and military/defense satellites.
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61047 intel report (Beta)
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Edit Public Description
Identifier
Orbit
Country
USRelated business
Manufacturer
AST & Science
Mission
Operational Commercial Communications
Bus & Motor
BW3, Unknown motor
Mass
1,500 kg wet, 1,500 kg dry
Launch date (UTC)
Launch vehicle
Launch site
Object type
Shape & HBR
Box + 1 Plate, 6.5 m
Radar Cross Section
32.590 m², Large (>1 m²)
Expand to show TLE details & historyLast TLE update: 13 hours ago
TLE from 13 hours ago
0 SPACEMOBILE-001
1 61047U 24163C 25288.49827910 .00003786 00000-0 18423-3 0 9994
2 61047 52.9719 354.6927 0011273 108.6401 251.5818 15.20756863 60529Epoch: 2025-10-15T11:57Z
TLE epoch observation values (Epoch: 2025-10-15T11:57:31.314Z)
Latitude
-0.00002°
Longitude
151.04072°
Altitude
506.891 km
Speed
7.61 km/s
True Right ascension
23h 38m 46s
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
19:12:40
Azimuth
Unknown
Elevation
Unknown
Doppler factor
Unknown
Orbital elements
Apogee altitude
511.6 km
Perigee altitude
496.084 km
Semi-major axis
6,881.979 km
Eccentricity
0.00113
Inclination
52.9719°
RAAN
354.6927°
Arg. of periapsis
108.6401°
True anomaly
251.45929°
Mean anomaly
251.5818°
Eccentric anomaly
251.52054°
Mean motion
3.80166 °/min
Orbital period
94.7 mins
BSTAR
0.00018423
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Other satellites on launch #163 in the year 2024 (2024-09-12 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.SPACEMOBILE-001 Visibility forecast
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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. |
|---|---|---|---|---|---|---|---|
| 7 mins | 2025-10-16 07:02:58.991Z | 219.992° SW | 2025-10-16 07:06:58.991Z | 101.284° ESE | 41.755° | 2025-10-16 07:09:58.991Z | 55.772° ENE |
| 4 mins | 2025-10-16 08:43:58.991Z | 302.228° NW | 2025-10-16 08:45:58.991Z | 347.299° N | 20.415° | 2025-10-16 08:47:58.991Z | 22.92° NE |
| 5 mins | 2025-10-16 13:41:58.991Z | 320.957° NNW | 2025-10-16 13:43:58.991Z | 16.098° NNE | 41.34° | 2025-10-16 13:46:58.991Z | 116.308° SE |
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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CAUTION: Conjunctions in this section are generated from low-fidelity TLE screenings
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