LEMUR 2 JEREMIAH, 46911 (Decayed)

Orbit data source: Space-Track

LEMUR 2 JEREMIAH, 46911 was a payload satellite owned by Spire (US) in LEO that was launched on Sat, 07 Nov 2020 UTC via a PSLV-DL 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 JEREMIAH details

Identifier	46911, 2020-081G
Orbit	Decayed
Last TLE update	2 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)	2020-11-07 (4 years ago)
Launch vehicle	PSLV-DL
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 2 months ago

0 LEMUR 2 JEREMIAH
1 46911U 20081G   24302.55856808  .02807238  13589-1  30660-2 0  9992
2 46911  36.9075 349.6530 0019912 104.3321 255.9668 16.11557093219662

Epoch: 2024-10-28T13:24Z

Definitive object data (Epoch: 2024-10-28T13:24:20.282Z)

Latitude	-0.00002°
Longitude	111.18543°
Altitude	244.871 km
Speed	7.76 km/s
True Right ascension	23h 18m 36s
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	258.823 km
Perigee altitude	232.445 km
Semi-major axis	6,623.771 km
Eccentricity	0.0019912
Inclination	36.9075°
RAAN	349.653°
Arg. of periapsis	104.3321°
True anomaly	255.74557°
Mean anomaly	255.9668°
Eccentric anomaly	255.85617°
Mean motion	4.02611 °/min
BSTAR	0.003066
Orbital period	89.42 mins