MP42, 52169 (Decayed)

Orbit data source: Space-Track

MP42, 52169 was a Lithuanian payload satellite 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

MP42 details

Identifier	52169, 2022-033N
Orbit	Decayed
Last TLE update	2 months ago
Origin	NANAV/OQT (LT / LTU)
Manufacturer	NanoAvionics
Mission	Decayed Commercial Communications
Bus & Motor	MP42, Unknown motor
Mass	~40 kg wet, ~40 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 + 2 Pan, 3.5 m
Radar Cross Section	0.688 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 2 months ago

0 MP42
1 52169U 22033N   24294.37605446  .15399449  25241-5  25580-3 0  9995
2 52169  97.2984  28.2979 0013066 270.7453  89.2354 16.47246543143310

Epoch: 2024-10-20T09:01Z

Definitive object data (Epoch: 2024-10-20T09:01:31.105Z)

Latitude	0.00005°
Longitude	-136.39968°
Altitude	149.758 km
Speed	7.816 km/s
True Right ascension	01h 53m 11s
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	151.911 km
Perigee altitude	134.869 km
Semi-major axis	6,521.527 km
Eccentricity	0.0013066
Inclination	97.2984°
RAAN	28.2979°
Arg. of periapsis	270.7453°
True anomaly	89.38512°
Mean anomaly	89.2354°
Eccentric anomaly	89.31026°
Mean motion	4.12116 °/min
BSTAR	0.0002558
Orbital period	87.35 mins