DECAYED

STARLINK-31915, 59796 (Decayed)

Orbit data source: Space-Track

STARLINK-31915, 59796 was a payload satellite owned by SpaceX/Seattle (US) in LEO that was launched on Sat, 18 May 2024 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-31915 details

Identifier	59796, 2024-093Q
Orbit	Decayed
Last TLE update	7 months ago
Origin	SpaceX/Seattle (US)
Manufacturer	SpaceX/Seattle
Mission	Decayed spacecraft
Bus & Motor	STARLINK V2M, Unknown motor
Mass	730 kg wet, ~700 kg dry
Launch date (UTC)	2024-05-18 (8 months ago)
Launch vehicle	FALCON 9
Launch site	Air Force Eastern Test Range (AFETR)
Object type	Payload Rocket body Debris
Shape & HBR	Unknown
Radar Cross Section	Large (>1 m²)

Expand to show TLE details & history

TLE from 7 months ago

0 STARLINK-31915
1 59796U 24093Q   24155.76002328  .26324036  92744-5  35200-2 0  9998
2 59796  42.9880 275.4664 0006477 337.3134 139.2662 16.34370322  3868

Epoch: 2024-06-03T18:14Z

Definitive object data (Epoch: 2024-06-03T18:14:26.011Z)

Latitude	37.70356°
Longitude	-126.3726°
Altitude	185.964 km
Speed	7.799 km/s
True Right ascension	02h 39m 42s
True Declination	37° 31' 22"
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	187.107 km
Perigee altitude	178.608 km
Semi-major axis	6,560.995 km
Eccentricity	0.0006477
Inclination	42.988°
RAAN	275.4664°
Arg. of periapsis	337.3134°
True anomaly	139.3146°
Mean anomaly	139.2662°
Eccentric anomaly	139.2904°
Mean motion	4.08403 °/min
BSTAR	0.00352
Orbital period	88.15 mins