LEMUR 2 MMOLO, 55038 (Decayed)

Orbit data source: Space-Track

LEMUR 2 MMOLO, 55038 was a payload satellite owned by Spire/Lux (US) 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

LEMUR 2 MMOLO details

Identifier	55038, 2023-001AF
Orbit	Decayed
Last TLE update	4 months ago
Origin	Spire/Lux (US)
Manufacturer	Spire/Glasgow
Mission	Decayed Commercial Com/MetRO
Bus & Motor	CUBESAT 3U, Unknown motor
Mass	4.6 kg wet, 4.6 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 + 2 Pan, 0.7 m
Radar Cross Section	0.054 m², Small (<0.1 m²)

Expand to show TLE details & history

TLE from 4 months ago

0 LEMUR 2 MMOLO
1 55038U 23001AF  24293.80668559  .07326636  24760-5  19423-2 0  9992
2 55038  97.3876   6.5032 0009280 264.8961  95.1273 16.28341207100523

Epoch: 2024-10-19T19:21Z

Definitive object data (Epoch: 2024-10-19T19:21:37.634Z)

Latitude	-0.00007°
Longitude	47.33963°
Altitude	200.789 km
Speed	7.786 km/s
True Right ascension	00h 26m 00s
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	199.922 km
Perigee altitude	187.725 km
Semi-major axis	6,571.961 km
Eccentricity	0.000928
Inclination	97.3876°
RAAN	6.5032°
Arg. of periapsis	264.8961°
True anomaly	95.2332°
Mean anomaly	95.1273°
Eccentric anomaly	95.18025°
Mean motion	4.07381 °/min
BSTAR	0.0019423
Orbital period	88.37 mins