LEMUR 2 JINDRA, 46909 (Decayed)

Orbit data source: Space-Track

LEMUR 2 JINDRA, 46909 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 JINDRA details

Identifier	46909, 2020-081E
Orbit	Decayed
Last TLE update	4 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 4 months ago

0 LEMUR 2 JINDRA
1 46909U 20081E   24243.56434529  .01468094  11570-2  29119-2 0  9994
2 46909  36.8843 340.2867 0013719  50.5912 309.6073 15.98992038210785

Epoch: 2024-08-30T13:32Z

Definitive object data (Epoch: 2024-08-30T13:32:39.433Z)

Latitude	-0.00001°
Longitude	157.88684°
Altitude	270.479 km
Speed	7.751 km/s
True Right ascension	22h 41m 08s
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	289.396 km
Perigee altitude	271.126 km
Semi-major axis	6,658.398 km
Eccentricity	0.0013719
Inclination	36.8843°
RAAN	340.2867°
Arg. of periapsis	50.5912°
True anomaly	309.48605°
Mean anomaly	309.6073°
Eccentric anomaly	309.54669°
Mean motion	3.99474 °/min
BSTAR	0.0029119
Orbital period	90.12 mins