DECAYED

STARLINK-4682, 53597 (Decayed)

Orbit data source: Space-Track

STARLINK-4682, 53597 was a payload satellite owned by SpaceX/Seattle (US) in LEO that was launched on Sun, 28 Aug 2022 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-4682 details

Identifier	53597, 2022-104K
Orbit	Decayed
Last TLE update	2 months ago
Origin	SpaceX/Seattle (US)
Manufacturer	SpaceX/Seattle
Mission	Decayed Commercial Communications
Bus & Motor	STARLINK, Unknown motor
Mass	300 kg wet, ~290 kg dry
Launch date (UTC)	2022-08-28 (2 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 2 months ago

0 STARLINK-4682
1 53597U 22104K   24315.10974424  .15208099  12543-4  24306-3 0  9995
2 53597  53.1987 223.2083 0004566 247.8684 249.1904 16.48069179122278

Epoch: 2024-11-10T02:38Z

Definitive object data (Epoch: 2024-11-10T02:38:01.902Z)

Latitude	33.20335°
Longitude	-75.18416°
Altitude	147.732 km
Speed	7.821 km/s
True Right ascension	00h 56m 18s
True Declination	33° 01' 52"
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	147.666 km
Perigee altitude	141.709 km
Semi-major axis	6,522.824 km
Eccentricity	0.0004566
Inclination	53.1987°
RAAN	223.2083°
Arg. of periapsis	247.8684°
True anomaly	249.1415°
Mean anomaly	249.1904°
Eccentric anomaly	249.16595°
Mean motion	4.11993 °/min
BSTAR	0.00024306
Orbital period	87.38 mins