LEMUR 2 YNDRD, 44413 (Decayed)

Orbit data source: Space-Track

LEMUR 2 YNDRD, 44413 was a payload satellite owned by Spire (US) in LEO that was launched on Fri, 05 Jul 2019 UTC via a SOYUZ-2-1B launch vehicle from the Vostochny Cosmodrome (VOSTO). 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 YNDRD details

Identifier	44413, 2019-038AD
Orbit	Decayed
Last TLE update	8 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)	2019-07-05 (5 years ago)
Launch vehicle	SOYUZ-2-1B
Launch site	Vostochny Cosmodrome (VOSTO)
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 8 months ago

0 LEMUR 2 YNDRD
1 44413U 19038AD  24118.54845355  .15903007  28318-5  44698-3 0  9998
2 44413  97.6172 122.0256 0009235 214.8249 145.2449 16.44797926267264

Epoch: 2024-04-27T13:09Z

Definitive object data (Epoch: 2024-04-27T13:09:46.386Z)

Latitude	-0.00004°
Longitude	68.56838°
Altitude	161.28 km
Speed	7.806 km/s
True Right ascension	08h 08m 06s
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	155.91 km
Perigee altitude	143.853 km
Semi-major axis	6,528.019 km
Eccentricity	0.0009235
Inclination	97.6172°
RAAN	122.0256°
Arg. of periapsis	214.8249°
True anomaly	145.30517°
Mean anomaly	145.2449°
Eccentric anomaly	145.27504°
Mean motion	4.11501 °/min
BSTAR	0.00044698
Orbital period	87.48 mins