LEMUR 2 HIMOMANDDAD, 44860 (Decayed)

Orbit data source: Space-Track

LEMUR 2 HIMOMANDDAD, 44860 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 HIMOMANDDAD details

Identifier	44860, 2019-089J
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)	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, Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 4 months ago

0 LEMUR 2 HIMOMANDDAD
1 44860U 19089J   24226.60983811  .08331924  36718-5  26113-2 0  9996
2 44860  36.9527 321.7975 0005553  24.7413 335.3635 16.25377994257925

Epoch: 2024-08-13T14:38Z

Definitive object data (Epoch: 2024-08-13T14:38:10.012Z)

Latitude	-0.00001°
Longitude	139.73139°
Altitude	200.743 km
Speed	7.79 km/s
True Right ascension	21h 27m 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	211.716 km
Perigee altitude	204.402 km
Semi-major axis	6,586.196 km
Eccentricity	0.0005553
Inclination	36.9527°
RAAN	321.7975°
Arg. of periapsis	24.7413°
True anomaly	335.33696°
Mean anomaly	335.3635°
Eccentric anomaly	335.35023°
Mean motion	4.06061 °/min
BSTAR	0.0026113
Orbital period	88.66 mins