NUSAT-19 (ROSALIND), 48905 (Decayed)

Orbit data source: Space-Track

NUSAT-19 (ROSALIND), 48905 was a payload satellite owned by URUGUS S.A. (AR) in LEO that was launched on Wed, 30 Jun 2021 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

NUSAT-19 (ROSALIND) details

Identifier	48905, 2021-059AC
Orbit	Decayed
Last TLE update	3 months ago
Origin	URUGUS S.A. (AR / ARGN)
Manufacturer	URUGUS S.A.
Mission	Decayed Commercial Imaging
Bus & Motor	NEWSAT IV, Unknown motor
Mass	44 kg wet, 37 kg dry
Launch date (UTC)	2021-06-30 (4 years ago)
Launch vehicle	FALCON 9
Launch site	Air Force Eastern Test Range (AFETR)
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-19 (ROSALIND)
1 48905U 21059AC  24296.61828834  .04676707  25871-5  11711-2 0  9994
2 48905  97.5684  99.7066 0007249 266.7612  93.2852 16.29026708185831

Epoch: 2024-10-22T14:50Z

Definitive object data (Epoch: 2024-10-22T14:50:20.112Z)

Latitude	-0.00001°
Longitude	-154.40522°
Altitude	198.665 km
Speed	7.787 km/s
True Right ascension	06h 38m 49s
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	196.749 km
Perigee altitude	187.224 km
Semi-major axis	6,570.123 km
Eccentricity	0.0007249
Inclination	97.5684°
RAAN	99.7066°
Arg. of periapsis	266.7612°
True anomaly	93.36813°
Mean anomaly	93.2852°
Eccentric anomaly	93.32666°
Mean motion	4.07552 °/min
BSTAR	0.0011711
Orbital period	88.33 mins