LEMUR 2 ROCINANTE, 59147 (Decayed)
Orbit data source: Space-Track
LEMUR 2 ROCINANTE, 59147 was an American payload satellite in SSO that was launched on Mon, 04 Mar 2024 UTC via an FALCON 9 launch vehicle from the Air Force Western Test Range (AFWTR). Payload-class satellites include a variety of spacecraft 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.
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59147 intel report (Beta)
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Edit Public Description
Identifier
Orbit
Country
USRelated business
Manufacturer
Spire/Glasgow
Mission
Decayed Commercial Communications
Bus & Motor
CUBESAT 16U, Unknown motor
Mass
22 kg wet, 22 kg dry
Launch date (UTC)
Launch vehicle
Launch site
Object type
Shape & HBR
Box + 4 Pan, 1.4 m
Radar Cross Section
0.326 m², Medium (>0.1 m² and < 1m²)
Expand to show TLE details & historyLast TLE update: 1 week ago
TLE from 1 week ago
0 LEMUR 2 ROCINANTE
1 59147U 24043BB 26024.87567953 .04062886 24694-5 25479-2 0 9996
2 59147 97.4905 173.6716 0011273 298.4507 61.5644 16.17664757106061Epoch: 2026-01-24T21:00Z
TLE epoch observation values (Epoch: 2026-01-24T21:00:58.711Z)
Latitude
-0.00002°
Longitude
94.23311°
Altitude
225.58 km
Speed
7.773 km/s
True Right ascension
11h 34m 41s
True Declination
0° 00' 00"
Sunlit
Visualization orbit readout
Latitude
Unknown
Longitude
Unknown
Altitude
Unknown
Speed
Unknown
Apparent Right ascension
Unknown
Apparent Declination
Unknown
Sunlit
Visualization observer readout
Local Sidereal Time
17:08:08
Azimuth
Unknown
Elevation
Unknown
Doppler factor
Unknown
Orbital elements
Apogee altitude
230.182 km
Perigee altitude
215.299 km
Semi-major axis
6,600.878 km
Eccentricity
0.00113
Inclination
97.4905°
RAAN
173.6716°
Arg. of periapsis
298.4507°
True anomaly
61.67807°
Mean anomaly
61.5644°
Eccentric anomaly
61.62123°
Mean motion
4.04707 °/min
Orbital period
88.95 mins
BSTAR
0.0025479
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Other satellites on launch #43 in the year 2024 (2024-03-04 UTC)
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You can import UDL-sourced sensor .json files into the Sandbox to generate a visibility chart that accounts for multi-vendor sensor geometry.LEMUR 2 ROCINANTE Visibility
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Span | Click to sort rows by Start time (UTC) header in descending order | Start Az. | Max El. time (UTC) | Max El. Az. | Max El. | End time (UTC) | End Az. |
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| This satellite is decayed. |
Co-orbital & Co-planar RSOs
Thresholds — Semi-major Axis: ±100 km, RAAN: ±3°, Inclination: ±5°
TCA is derived from TLE conjunctions
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CAUTION: Conjunctions in this section are generated from low-fidelity TLE screenings
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