NUSAT-6 HYPATIA, 46272 (Decayed)

Orbit data source: Space-Track

NUSAT-6 HYPATIA, 46272 was a payload satellite owned by URUGUS S.A. (AR) in LEO that was launched on Thu, 03 Sep 2020 UTC via a VEGA launch vehicle from the French Guiana (FRGUI). 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

NUSAT-6 HYPATIA details

Identifier	46272, 2020-061A
Orbit	Decayed
Last TLE update	3 months ago
Origin	URUGUS S.A. (AR / ARGN)
Manufacturer	URUGUS S.A.
Mission	Decayed Commercial Imaging
Bus & Motor	ALEPH, Unknown motor
Mass	44 kg wet, 37 kg dry
Launch date (UTC)	2020-09-03 (4 years ago)
Launch vehicle	VEGA
Launch site	French Guiana (FRGUI)
Object type	Payload Rocket body Debris
Shape & HBR	Box, 0.75 m
Radar Cross Section	0.380 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 3 months ago

0 NUSAT-6 HYPATIA
1 46272U 20061A   24258.01176362  .15675468  25096-5  15830-3 0  9996
2 46272  97.2016 336.5654 0010782 254.7991 105.2123 16.50620335225504

Epoch: 2024-09-14T00:16Z

Definitive object data (Epoch: 2024-09-14T00:16:56.376Z)

Latitude	-0°
Longitude	-21.1451°
Altitude	142.825 km
Speed	7.819 km/s
True Right ascension	22h 26m 15s
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	141.509 km
Perigee altitude	127.466 km
Semi-major axis	6,512.624 km
Eccentricity	0.0010782
Inclination	97.2016°
RAAN	336.5654°
Arg. of periapsis	254.7991°
True anomaly	105.33148°
Mean anomaly	105.2123°
Eccentric anomaly	105.27189°
Mean motion	4.12961 °/min
BSTAR	0.0001583
Orbital period	87.18 mins