DECAYED

STARLINK-1180, 45076 (Decayed)

Orbit data source: Space-Track

STARLINK-1180, 45076 was a payload satellite owned by SpaceX/Seattle (US) in LEO that was launched on Wed, 29 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-1180 details

Identifier	45076, 2020-006AJ
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)	2020-01-29 (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-1180
1 45076U 20006AJ  24229.54014994  .11693124  11860-4  50391-2 0  9992
2 45076  53.0404 234.3542 0000684 153.5309 348.5353 16.21971783252147

Epoch: 2024-08-16T12:57Z

Definitive object data (Epoch: 2024-08-16T12:57:48.954Z)

Latitude	29.51651°
Longitude	-130.57224°
Altitude	215.374 km
Speed	7.782 km/s
True Right ascension	01h 57m 10s
True Declination	29° 21' 26"
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	214.941 km
Perigee altitude	214.039 km
Semi-major axis	6,592.627 km
Eccentricity	0.0000684
Inclination	53.0404°
RAAN	234.3542°
Arg. of periapsis	153.5309°
True anomaly	348.53374°
Mean anomaly	348.5353°
Eccentric anomaly	348.53452°
Mean motion	4.05467 °/min
BSTAR	0.0050391
Orbital period	88.79 mins