DECAYED

STARLINK-1602, 46121 (Decayed)

Orbit data source: Space-Track

STARLINK-1602, 46121 was a payload satellite owned by SpaceX/Seattle (US) in LEO that was launched on Tue, 18 Aug 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-1602 details

Identifier	46121, 2020-057E
Orbit	Decayed
Last TLE update	1 week 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)	2020-08-18 (4 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 1 week ago

0 STARLINK-1602
1 46121U 20057E   25007.34181969  .09781165  12333-4  84943-3 0  9997
2 46121  53.0302  22.3522 0002755  75.7806 310.1744 16.38553887243134

Epoch: 2025-01-07T08:12Z

Definitive object data (Epoch: 2025-01-07T08:12:13.221Z)

Latitude	20.49623°
Longitude	168.39247°
Altitude	169.008 km
Speed	7.809 km/s
True Right ascension	02h 34m 23s
True Declination	20° 22' 25"
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	171.746 km
Perigee altitude	168.138 km
Semi-major axis	6,548.079 km
Eccentricity	0.0002755
Inclination	53.0302°
RAAN	22.3522°
Arg. of periapsis	75.7806°
True anomaly	310.15027°
Mean anomaly	310.1744°
Eccentric anomaly	310.16234°
Mean motion	4.09612 °/min
BSTAR	0.00084943
Orbital period	87.89 mins