SUCHAI-3, 52191 (Decayed)

Orbit data source: Space-Track

SUCHAI-3, 52191 was a payload satellite owned by SPEL/UCH (CL) 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

SUCHAI-3 details

Identifier	52191, 2022-033AL
Orbit	Decayed
Last TLE update	7 months ago
Origin	SPEL/UCH (CL / CHLE)
Manufacturer	SPEL/UCH
Mission	Decayed Amateur Technology
Bus & Motor	CUBESAT 3U, Unknown motor
Mass	~4 kg wet, ~4 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	0.035 m², Small (<0.1 m²)

Expand to show TLE details & history

TLE from 7 months ago

0 SUCHAI-3
1 52191U 22033AL  24146.50949412  .15429445  25297-5  22962-3 0  9997
2 52191  97.2978 240.3180 0016695 271.5522  88.3869 16.47492065120493

Epoch: 2024-05-25T12:13Z

Definitive object data (Epoch: 2024-05-25T12:13:40.291Z)

Latitude	-0.00008°
Longitude	173.32645°
Altitude	148.924 km
Speed	7.817 km/s
True Right ascension	16h 01m 16s
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	153.628 km
Perigee altitude	131.855 km
Semi-major axis	6,520.878 km
Eccentricity	0.0016695
Inclination	97.2978°
RAAN	240.318°
Arg. of periapsis	271.5522°
True anomaly	88.57815°
Mean anomaly	88.3869°
Eccentric anomaly	88.48252°
Mean motion	4.12177 °/min
BSTAR	0.00022962
Orbital period	87.34 mins