LEMUR 2 JPGSQUARED, 44855 (Decayed)

Orbit data source: Space-Track

LEMUR 2 JPGSQUARED, 44855 was a payload satellite owned by Spire (US) in LEO that was launched on Wed, 11 Dec 2019 UTC via a PSLV-QL launch vehicle from the Sirharikota (SRI). 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 JPGSQUARED details

Identifier	44855, 2019-089D
Orbit	Decayed
Last TLE update	3 months ago
Origin	Spire (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)	2019-12-11 (5 years ago)
Launch vehicle	PSLV-QL
Launch site	Sirharikota (SRI)
Object type	Payload Rocket body Debris
Shape & HBR	Box + 2 Pan, 0.7 m
Radar Cross Section	0.124 m², Small (<0.1 m²)

Expand to show TLE details & history

TLE from 3 months ago

0 LEMUR 2 JPGSQUARED
1 44855U 19089D   24258.07347154  .07480515  36235-5  26256-2 0  9992
2 44855  36.9605 127.9029 0012552 277.6070  82.3286 16.23858220262850

Epoch: 2024-09-14T01:45Z

Definitive object data (Epoch: 2024-09-14T01:45:47.941Z)

Latitude	-0.00001°
Longitude	107.91671°
Altitude	207.08 km
Speed	7.785 km/s
True Right ascension	08h 31m 36s
True Declination	0° 00' 00"
Sunlit	Object was in daylight 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	220.435 km
Perigee altitude	203.89 km
Semi-major axis	6,590.3 km
Eccentricity	0.0012552
Inclination	36.9605°
RAAN	127.9029°
Arg. of periapsis	277.607°
True anomaly	82.47118°
Mean anomaly	82.3286°
Eccentric anomaly	82.39989°
Mean motion	4.05682 °/min
BSTAR	0.0026256
Orbital period	88.74 mins