KSF2-C, 52189 (Decayed)

Orbit data source: Space-Track

KSF2-C, 52189 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-C details

Identifier	52189, 2022-033AJ
Orbit	Decayed
Last TLE update	5 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 5 months ago

0 KSF2-C
1 52189U 22033AJ  24227.64857431  .03433073  24018-5  15065-2 0  9992
2 52189  97.3173 323.3444 0009837 253.1063 106.9149 16.22368386133133

Epoch: 2024-08-14T15:33Z

Definitive object data (Epoch: 2024-08-14T15:33:56.82Z)

Latitude	-0.00002°
Longitude	126.30945°
Altitude	218.252 km
Speed	7.774 km/s
True Right ascension	21h 33m 22s
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	216.437 km
Perigee altitude	203.475 km
Semi-major axis	6,588.093 km
Eccentricity	0.0009837
Inclination	97.3173°
RAAN	323.3444°
Arg. of periapsis	253.1063°
True anomaly	107.02271°
Mean anomaly	106.9149°
Eccentric anomaly	106.96881°
Mean motion	4.05886 °/min
BSTAR	0.0015065
Orbital period	88.69 mins