SPACEBEE-143, 52394 (Decayed)

Orbit data source: Space-Track

SPACEBEE-143, 52394 was a payload satellite owned by Swarm Tech (US) in LEO that was launched on Mon, 02 May 2022 UTC via an ELECTRON launch vehicle from the Rocket Lab Launch Complex (RLLC). 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

Identifier	52394, 2022-047A
Orbit	Decayed
Last TLE update	10 months ago
Origin	Swarm Tech (US)
Manufacturer	Swarm Tech
Mission	Decayed Commercial Communications
Bus & Motor	CUBESAT 0.25U, Unknown motor
Mass	0.284 kg wet, 0.284 kg dry
Launch date (UTC)	2022-05-02 (3 years ago)
Launch vehicle	ELECTRON
Launch site	Rocket Lab Launch Complex (RLLC)
Object type	Payload Rocket body Debris
Shape & HBR	Box + 2 Ant, 0.9 m
Radar Cross Section	0.016 m², Small (<0.1 m²)

Expand to show TLE details & history

TLE from 10 months ago

0 SPACEBEE-143
1 52394U 22047A   24121.05613099  .16628333  25733-5  29064-3 0  9992
2 52394  97.3659 216.4690 0016324 284.4454  75.5037 16.46554337112789

Epoch: 2024-04-30T01:20Z

Definitive object data (Epoch: 2024-04-30T01:20:49.717Z)

Latitude	-0.00006°
Longitude	-22.22379°
Altitude	149.035 km
Speed	7.818 km/s
True Right ascension	14h 25m 52s
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	155.871 km
Perigee altitude	134.574 km
Semi-major axis	6,523.359 km
Eccentricity	0.0016324
Inclination	97.3659°
RAAN	216.469°
Arg. of periapsis	284.4454°
True anomaly	75.6849°
Mean anomaly	75.5037°
Eccentric anomaly	75.59429°
Mean motion	4.11942 °/min
BSTAR	0.00029064
Orbital period	87.39 mins