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DECAYED
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LEMUR 2 EMMACULATE, 55037 (Decayed)

Orbit data source: Space-Track

LEMUR 2 EMMACULATE, 55037 was an American payload satellite in LEO that was launched on Tue, 03 Jan 2023 UTC via an FALCON 9 launch vehicle from the Air Force Eastern Test Range (AFETR). 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
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LEMUR 2 EMMACULATE details
Identifier
55037, 2023-001AE
Orbit
Decayed
Last TLE update5 months ago
Origin
Flag of USSPIREL/MYRI (US)
ManufacturerSpire/Glasgow
MissionDecayed Commercial Com/MetRO
Bus & MotorCUBESAT 3U, Unknown motor
Mass8.3 kg wet, 8.1 kg dry
Launch date (UTC)
2023-01-03 (2 years ago)
Launch vehicle
FALCON 9
Launch site
Air Force Eastern Test Range (AFETR)
Object type
Payload
Rocket body
Debris
Shape & HBRBox + 2 Pan, 0.7 m
Radar Cross Section0.054 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 5 months ago
0 LEMUR 2 EMMACULATE
1 55037U 23001AE  24144.83707817  .18410834  25877-5  41010-3 0  9994
2 55037  97.4040 216.6886 0012725 265.0585  94.9264 16.45604697 77692
Epoch: 2024-05-23T20:05Z
Definitive object data (Epoch: 2024-05-23T20:05:23.553Z)
Latitude-0.00012°
Longitude33.41521°
Altitude154.918 km
Speed7.813 km/s
True Right ascension14h 26m 45s
True Declination0° 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
Apogee156.04 km
Perigee139.432 km
Semi-major axis6,525.873 km
Eccentricity0.0012725
Inclination97.404°
RAAN216.6886°
Arg. of periapsis265.0585°
True anomaly95.07166°
Mean anomaly94.9264°
Eccentric anomaly94.99903°
Mean motion4.11704 °/min
BSTAR0.0004101
Period87.44 mins
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LEMUR 2 EMMACULATE Visibility forecast

Observer location: undefined°, undefined

This satellite is decayed
Span
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Start Az.
Max El. time (UTC)
Max El. Az.
Max El.
End time (UTC)
End Az.
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