UVSQ-SAT, 47438 (Decayed)

Orbit data source: Space-Track

UVSQ-SAT, 47438 was a French payload satellite in LEO that was launched on Sun, 24 Jan 2021 UTC via an FALCON 9 launch vehicle from the Air Force Eastern Test Range (AFETR). Payload-class satellites include a variety of spacecraft 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.

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https://www.satcat.com/sats-embedded/47438?theme=dark&initialShowStats=false

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Identifier	47438, 2021-006AB
Orbit	Decayed
Last TLE update	5 months ago
Origin	UVSQ (FR)
Manufacturer	LATMOS/ISISBV
Mission	Decayed Amateur Science
Bus & Motor	CUBESAT 1U, Unknown motor
Mass	1.6 kg wet, 1.6 kg dry
Launch date (UTC)	2021-01-24 (4 years ago)
Launch vehicle	FALCON 9
Launch site	Air Force Eastern Test Range (AFETR)
Object type	Payload Rocket body Debris
Shape & HBR	Box, Unknown HBR
Radar Cross Section	0.015 m², Small (<0.1 m²)

Expand to show TLE details & history

TLE from 5 months ago

0 UVSQ-SAT
1 47438U 21006AB  24298.11681880  .03670113  23594-5  18855-2 0  9991
2 47438  97.2775   3.3666 0006581 273.2868  86.7668 16.20433421208899

Epoch: 2024-10-24T02:48Z

Definitive object data (Epoch: 2024-10-24T02:48:13.144Z)

Latitude	-0.00006°
Longitude	-71.6932°
Altitude	221.362 km
Speed	7.774 km/s
True Right ascension	00h 13m 27s
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	219.542 km
Perigee altitude	210.864 km
Semi-major axis	6,593.34 km
Eccentricity	0.0006581
Inclination	97.2775°
RAAN	3.3666°
Arg. of periapsis	273.2868°
True anomaly	86.8421°
Mean anomaly	86.7668°
Eccentric anomaly	86.80445°
Mean motion	4.05401 °/min
BSTAR	0.0018855
Orbital period	88.8 mins