AII-CHARLIE, 47440 (Decayed)

Orbit data source: Space-Track

AII-CHARLIE, 47440 was a Lithuanian payload satellite 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

AII-CHARLIE details

Identifier	47440, 2021-006AD
Orbit	Decayed
Last TLE update	4 months ago
Origin	AUINS/SPQAA (LT / LTU)
Manufacturer	NanoAvionics US
Mission	Decayed Commercial Sigint
Bus & Motor	CUBESAT 6U, Unknown motor
Mass	~10 kg wet, ~10 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 Pan, 0.6 m
Radar Cross Section	0.104 m², Small (<0.1 m²)

Expand to show TLE details & history

TLE from 4 months ago

0 AII-CHARLIE
1 47440U 21006AD  24219.45521343  .13297423  25095-5  30070-3 0  9993
2 47440  97.2886 287.9162 0014488 267.0731  92.8914 16.45301543196985

Epoch: 2024-08-06T10:55Z

Definitive object data (Epoch: 2024-08-06T10:55:30.44Z)

Latitude	0.00003°
Longitude	168.56693°
Altitude	155.49 km
Speed	7.813 km/s
True Right ascension	19h 11m 39s
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	157.989 km
Perigee altitude	139.077 km
Semi-major axis	6,526.67 km
Eccentricity	0.0014488
Inclination	97.2886°
RAAN	287.9162°
Arg. of periapsis	267.0731°
True anomaly	93.05719°
Mean anomaly	92.8914°
Eccentric anomaly	92.9743°
Mean motion	4.11629 °/min
BSTAR	0.0003007
Orbital period	87.46 mins