SUCHAI-2, 52192 (Decayed)

Orbit data source: Space-Track

SUCHAI-2, 52192 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-2 details

Identifier	52192, 2022-033AM
Orbit	Decayed
Last TLE update	3 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 3 months ago

0 SUCHAI-2
1 52192U 22033AM  24280.41582610  .16355900  25290-5  20957-3 0  9990
2 52192  97.2596  13.1096 0010468 260.4666  99.5456 16.49110273141185

Epoch: 2024-10-06T09:58Z

Definitive object data (Epoch: 2024-10-06T09:58:47.375Z)

Latitude	0.00002°
Longitude	-152.1459°
Altitude	146.086 km
Speed	7.818 km/s
True Right ascension	00h 52m 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	145.291 km
Perigee altitude	131.647 km
Semi-major axis	6,516.606 km
Eccentricity	0.0010468
Inclination	97.2596°
RAAN	13.1096°
Arg. of periapsis	260.4666°
True anomaly	99.66387°
Mean anomaly	99.5456°
Eccentric anomaly	99.60474°
Mean motion	4.12583 °/min
BSTAR	0.00020957
Orbital period	87.26 mins