DECAYED

STARLINK-1483, 45743 (Decayed)

Orbit data source: Space-Track

STARLINK-1483, 45743 was a payload satellite owned by SpaceX/Seattle (US) in LEO that was launched on Sat, 13 Jun 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-1483 details

Identifier	45743, 2020-038P
Orbit	Decayed
Last TLE update	5 days 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)	2020-06-13 (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 5 days ago

0 STARLINK-1483
1 45743U 20038P   24356.51811432  .14234212  12477-4  33850-3 0  9997
2 45743  53.0105 331.2274 0003994 146.5353 317.7231 16.46121251251688

Epoch: 2024-12-21T12:26Z

Definitive object data (Epoch: 2024-12-21T12:26:05.077Z)

Latitude	50.8938°
Longitude	167.01454°
Altitude	153.597 km
Speed	7.822 km/s
True Right ascension	05h 36m 24s
True Declination	50° 42' 35"
Sunlit	Object was in full shadow 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	152.471 km
Perigee altitude	147.257 km
Semi-major axis	6,528.001 km
Eccentricity	0.0003994
Inclination	53.0105°
RAAN	331.2274°
Arg. of periapsis	146.5353°
True anomaly	317.6923°
Mean anomaly	317.7231°
Eccentric anomaly	317.7077°
Mean motion	4.11503 °/min
BSTAR	0.0003385
Orbital period	87.48 mins