LEMUR-2-SLICERS, 46500 (Decayed)

Orbit data source: Space-Track

LEMUR-2-SLICERS, 46500 was an American payload satellite in LEO that was launched on Mon, 28 Sep 2020 UTC via a SOYUZ-2-1B launch vehicle from the Plesetsk Missile And Space Complex (PKMTR). 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-SLICERS details

Identifier	46500, 2020-068Q
Orbit	Decayed
Last TLE update	2 months ago
Origin	SPIREL/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)	2020-09-28 (4 years ago)
Launch vehicle	SOYUZ-2-1B
Launch site	Plesetsk Missile And Space Complex (PKMTR)
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-SLICERS
1 46500U 20068Q   24283.24428904  .15908144  28963-5  70936-3 0  9996
2 46500  97.7150 265.1575 0008148 219.4621 140.6086 16.42724125222907

Epoch: 2024-10-09T05:51Z

Definitive object data (Epoch: 2024-10-09T05:51:46.573Z)

Latitude	-0.00003°
Longitude	158.86748°
Altitude	165.93 km
Speed	7.804 km/s
True Right ascension	17h 40m 37s
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	160.708 km
Perigee altitude	150.061 km
Semi-major axis	6,533.521 km
Eccentricity	0.0008148
Inclination	97.715°
RAAN	265.1575°
Arg. of periapsis	219.4621°
True anomaly	140.66781°
Mean anomaly	140.6086°
Eccentric anomaly	140.63821°
Mean motion	4.10981 °/min
BSTAR	0.00070936
Orbital period	87.6 mins