KSF2-A, 52194 (Decayed)

Orbit data source: Space-Track

KSF2-A, 52194 was a payload satellite owned by Kleos Space (LU) in LEO that was launched on Fri, 01 Apr 2022 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

KSF2-A details

Identifier	52194, 2022-033AP
Orbit	Decayed
Last TLE update	4 months ago
Origin	Kleos Space (LU / LUXE)
Manufacturer	ISIS BV
Mission	Decayed Commercial Sigint
Bus & Motor	CUBESAT 6U, Unknown motor
Mass	~10 kg wet, ~10 kg dry
Launch date (UTC)	2022-04-01 (3 years ago)
Launch vehicle	FALCON 9
Launch site	Air Force Eastern Test Range (AFETR)
Object type	Payload Rocket body Debris
Shape & HBR	Box, 0.3 m
Radar Cross Section	0.080 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 4 months ago

0 KSF2-A
1 52194U 22033AP  24225.22868160  .06204621  24152-5  21707-2 0  9998
2 52194  97.3246 322.1114 0013028 285.6978  74.2876 16.25019637132546

Epoch: 2024-08-12T05:29Z

Definitive object data (Epoch: 2024-08-12T05:29:18.09Z)

Latitude	-0.00003°
Longitude	-81.37701°
Altitude	206.879 km
Speed	7.784 km/s
True Right ascension	21h 28m 26s
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	211.356 km
Perigee altitude	194.208 km
Semi-major axis	6,580.919 km
Eccentricity	0.0013028
Inclination	97.3246°
RAAN	322.1114°
Arg. of periapsis	285.6978°
True anomaly	74.43137°
Mean anomaly	74.2876°
Eccentric anomaly	74.35948°
Mean motion	4.06549 °/min
BSTAR	0.0021707
Orbital period	88.55 mins