DECAYED

STARLINK-1082, 44938 (Decayed)

Orbit data source: Space-Track

STARLINK-1082, 44938 was a payload satellite owned by SpaceX/Seattle (US) in LEO that was launched on Tue, 07 Jan 2020 UTC via an FALCON 9 launch vehicle from the Air Force Eastern Test Range (AFETR). Payloads include a variety of satellites, spacecraft, and rockets 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.

Not visible in the next 10 days

STARLINK-1082 details

Identifier	44938, 2020-001AA
Orbit	Decayed
Last TLE update	4 months ago
Origin	SpaceX/Seattle (US)
Manufacturer	SpaceX/Seattle
Mission	Decayed Commercial Communications
Bus & Motor	STARLINK, Unknown motor
Mass	260 kg wet, ~248 kg dry
Launch date (UTC)	2020-01-07 (5 years ago)
Launch vehicle	FALCON 9
Launch site	Air Force Eastern Test Range (AFETR)
Object type	Payload Rocket body Debris
Shape & HBR	Box + 1 Pan, 8.86 m
Radar Cross Section	13.562 m², Large (>1 m²)

Expand to show TLE details & history

TLE from 4 months ago

0 STARLINK-1082
1 44938U 20001AA  24234.10048814  .27086174  12311-4  34264-2 0  9990
2 44938  53.0254 271.8482 0005729 328.3067 140.5337 16.35148036255904

Epoch: 2024-08-21T02:24Z

Definitive object data (Epoch: 2024-08-21T02:24:42.175Z)

Latitude	49.25934°
Longitude	25.4215°
Altitude	187.236 km
Speed	7.798 km/s
True Right ascension	02h 06m 01s
True Declination	49° 04' 28"
Sunlit	Object was in daylight at TLE epoch

Visualization observer readout

Observer readout values are unavailable because the object's trajectory could not be propagated. This is usually caused when the trajectory data is faulty or the object's orbit has decayed.

Visualization observer readout

Observer readout values are unavailable because the object's trajectory could not be propagated. This is usually caused when the trajectory data is faulty or the object's orbit has decayed.

Orbital elements

Apogee altitude	182.788 km
Perigee altitude	175.275 km
Semi-major axis	6,557.169 km
Eccentricity	0.0005729
Inclination	53.0254°
RAAN	271.8482°
Arg. of periapsis	328.3067°
True anomaly	140.57541°
Mean anomaly	140.5337°
Eccentric anomaly	140.55455°
Mean motion	4.0876 °/min
BSTAR	0.0034264
Orbital period	88.07 mins