FLOCK 4Y 1, 55039 (Decayed)

Orbit data source: Space-Track

FLOCK 4Y 1, 55039 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 1 details

Identifier	55039, 2023-001AG
Orbit	Decayed
Last TLE update	2 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, Small (<0.1 m²)

Expand to show TLE details & history

TLE from 2 months ago

0 FLOCK 4Y 1
1 55039U 23001AG  24353.43107608  .14727356  25828-5  50962-3 0  9994
2 55039  97.3855  62.9638 0009653 258.5172 101.5046 16.43712787109472

Epoch: 2024-12-18T10:20Z

Definitive object data (Epoch: 2024-12-18T10:20:44.973Z)

Latitude	0.00003°
Longitude	-179.74898°
Altitude	160.465 km
Speed	7.809 km/s
True Right ascension	04h 11m 51s
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	159.051 km
Perigee altitude	146.442 km
Semi-major axis	6,530.884 km
Eccentricity	0.0009653
Inclination	97.3855°
RAAN	62.9638°
Arg. of periapsis	258.5172°
True anomaly	101.61297°
Mean anomaly	101.5046°
Eccentric anomaly	101.55879°
Mean motion	4.1123 °/min
BSTAR	0.00050962
Orbital period	87.54 mins