FLOCK 4Y 3, 55035 (Decayed)

Orbit data source: Space-Track

FLOCK 4Y 3, 55035 was a payload satellite owned by Planet (US) in LEO that was launched on Tue, 03 Jan 2023 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

FLOCK 4Y 3 details

Identifier	55035, 2023-001AC
Orbit	Decayed
Last TLE update	3 months ago
Origin	Planet (US)
Manufacturer	Planet
Mission	Decayed Commercial Imaging
Bus & Motor	CUBESAT 3U, Unknown motor
Mass	5.7 kg wet, 5.7 kg dry
Launch date (UTC)	2023-01-03 (2 years ago)
Launch vehicle	FALCON 9
Launch site	Air Force Eastern Test Range (AFETR)
Object type	Payload Rocket body Debris
Shape & HBR	Box + 2 Pan, 0.3 m
Radar Cross Section	0.108 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 3 months ago

0 FLOCK 4Y 3
1 55035U 23001AC  24326.06442861  .14238353  26596-5  12284-2 0  9993
2 55035  97.3836  31.9004 0005599 232.4414 127.6377 16.39474856105058

Epoch: 2024-11-21T01:32Z

Definitive object data (Epoch: 2024-11-21T01:32:46.631Z)

Latitude	-0.00006°
Longitude	-51.84542°
Altitude	172.691 km
Speed	7.801 km/s
True Right ascension	02h 07m 36s
True Declination	0° 00' 00"
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	167.67 km
Perigee altitude	160.344 km
Semi-major axis	6,542.144 km
Eccentricity	0.0005599
Inclination	97.3836°
RAAN	31.9004°
Arg. of periapsis	232.4414°
True anomaly	127.68849°
Mean anomaly	127.6377°
Eccentric anomaly	127.6631°
Mean motion	4.10169 °/min
BSTAR	0.0012284
Orbital period	87.77 mins