KEPLER-5 (AMIDALA), 46498 (Decayed)

Orbit data source: Space-Track

KEPLER-5 (AMIDALA), 46498 was a payload satellite owned by Kepler Comms (CA) in LEO that was launched on Mon, 28 Sep 2020 UTC via a SOYUZ-2-1B launch vehicle from the Plesetsk Missile And Space Complex (PKMTR). 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

KEPLER-5 (AMIDALA) details

Identifier	46498, 2020-068N
Orbit	Decayed
Last TLE update	1 month ago
Origin	Kepler Comms (CA)
Manufacturer	KEPLER/UTIAS
Mission	Decayed Commercial Communications
Bus & Motor	CUBESAT 6U, Unknown motor
Mass	15 kg wet, 15 kg dry
Launch date (UTC)	2020-09-28 (4 years ago)
Launch vehicle	SOYUZ-2-1B
Launch site	Plesetsk Missile And Space Complex (PKMTR)
Object type	Payload Rocket body Debris
Shape & HBR	Box + 2 Pan, Unknown HBR
Radar Cross Section	0.109 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 1 month ago

0 KEPLER-5 (AMIDALA)
1 46498U 20068N   24323.66996777  .08031346  27792-5  18164-2 0  9997
2 46498  97.7773 304.2525 0007586 165.3960 194.7554 16.30122735228850

Epoch: 2024-11-18T16:04Z

Definitive object data (Epoch: 2024-11-18T16:04:45.215Z)

Latitude	0.00002°
Longitude	4.87267°
Altitude	200.258 km
Speed	7.783 km/s
True Right ascension	20h 17m 00s
True Declination	0° 00' 00"
Sunlit	Object was in daylight 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	194.03 km
Perigee altitude	184.066 km
Semi-major axis	6,567.185 km
Eccentricity	0.0007586
Inclination	97.7773°
RAAN	304.2525°
Arg. of periapsis	165.396°
True anomaly	194.73328°
Mean anomaly	194.7554°
Eccentric anomaly	194.74434°
Mean motion	4.07825 °/min
BSTAR	0.0018164
Orbital period	88.27 mins