SPACEBEE-63, 47442 (Decayed)

Orbit data source: Space-Track

SPACEBEE-63, 47442 was a payload satellite owned by Swarm Tech (US) in LEO that was launched on Sun, 24 Jan 2021 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

SPACEBEE-63 details

Identifier	47442, 2021-006AF
Orbit	Decayed
Last TLE update	5 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)	2021-01-24 (4 years ago)
Launch vehicle	FALCON 9
Launch site	Air Force Eastern Test Range (AFETR)
Object type	Payload Rocket body Debris
Shape & HBR	Box + 2 Ant, 0.9 m
Radar Cross Section	0.016 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 5 months ago

0 SPACEBEE-63
1 47442U 21006AF  24169.43250474  .12598525  25000-5  46982-3 0  9992
2 47442  97.2989 236.5836 0015377 262.4397  97.5158 16.42569016189155

Epoch: 2024-06-17T10:22Z

Definitive object data (Epoch: 2024-06-17T10:22:48.409Z)

Latitude	0.00003°
Longitude	174.71421°
Altitude	163.565 km
Speed	7.807 km/s
True Right ascension	15h 46m 20s
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	165.824 km
Perigee altitude	145.73 km
Semi-major axis	6,533.914 km
Eccentricity	0.0015377
Inclination	97.2989°
RAAN	236.5836°
Arg. of periapsis	262.4397°
True anomaly	97.69045°
Mean anomaly	97.5158°
Eccentric anomaly	97.60313°
Mean motion	4.10944 °/min
BSTAR	0.00046982
Orbital period	87.6 mins