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STERNULA-1, 55044

Orbit data source: Space-Track

STERNULA-1, 55044 is a payload satellite owned by Sternula (DK) in LEO that was launched on Tue, 03 Jan 2023 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

STERNULA-1 details

Identifier	55044, 2023-001AM
Orbit	LEO
Last TLE update	3 weeks ago
Origin	Sternula (DK / DEN)
Manufacturer	Space Inventor
Mission	Decayed Commercial Communications
Bus & Motor	CUBESAT 6U, Unknown motor
Mass	10 kg wet, 10 kg dry
Launch date (UTC)	2023-01-03 (2 years ago)
Launch vehicle	FALCON 9
Launch site	Air Force Eastern Test Range (AFETR)
Object type	Payload Rocket body Debris
Shape & HBR	Box + 1 Ant, 0.6 m
Radar Cross Section	0.093 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 3 weeks ago

0 STERNULA-1
1 55044U 23001AM  25007.32433407  .16698733  25718-5  38004-3 0  9993
2 55044  97.3682  82.0740 0009796 264.5771  95.4414 16.45838972112452

Epoch: 2025-01-07T07:47Z

Definitive object data (Epoch: 2025-01-07T07:47:02.463Z)

Latitude	-0.00005°
Longitude	-141.81939°
Altitude	154.189 km
Speed	7.813 km/s
True Right ascension	05h 28m 17s
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	153.507 km
Perigee altitude	140.722 km
Semi-major axis	6,525.252 km
Eccentricity	0.0009796
Inclination	97.3682°
RAAN	82.074°
Arg. of periapsis	264.5771°
True anomaly	95.55313°
Mean anomaly	95.4414°
Eccentric anomaly	95.49727°
Mean motion	4.11763 °/min
BSTAR	0.00038004
Orbital period	87.43 mins