KEPLER-12 (BOBA), 47446 (Decayed)

Orbit data source: Space-Track

KEPLER-12 (BOBA), 47446 was a payload satellite owned by Kepler Comms (CA) 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). Payload-class satellites include a variety of spacecraft 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.

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https://www.satcat.com/sats-embedded/47446?theme=dark&initialShowStats=false

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Identifier	47446, 2021-006AK
Orbit	Decayed
Last TLE update	6 months ago
Origin	KEPLER (CA)
Manufacturer	KEPLER/UTIAS
Mission	Decayed Commercial Communications
Bus & Motor	CUBESAT 6U, Unknown motor
Mass	15 kg wet, 15 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, 1.08 m
Radar Cross Section	0.196 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 6 months ago

0 KEPLER-12 (BOBA)
1 47446U 21006AK  24284.45247648  .16290543  25048-5  62844-3 0  9995
2 47446  97.2833 346.8369 0010266 263.3369  96.6764 16.43111867206560

Epoch: 2024-10-10T10:51Z

Definitive object data (Epoch: 2024-10-10T10:51:33.967Z)

Latitude	-0.00006°
Longitude	164.40856°
Altitude	161.584 km
Speed	7.809 km/s
True Right ascension	23h 07m 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	161.042 km
Perigee altitude	147.63 km
Semi-major axis	6,532.473 km
Eccentricity	0.0010266
Inclination	97.2833°
RAAN	346.8369°
Arg. of periapsis	263.3369°
True anomaly	96.79322°
Mean anomaly	96.6764°
Eccentric anomaly	96.73481°
Mean motion	4.1108 °/min
BSTAR	0.00062844
Orbital period	87.57 mins