LEMUR 2 ROCINANTE, 59147
Orbit data source: Space-Track
LEMUR 2 ROCINANTE, 59147 is 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
Operational 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: 10 hours ago
TLE from 10 hours ago
0 LEMUR 2 ROCINANTE
1 59147U 24043BB 25289.13870830 .00081569 00000-0 13185-2 0 9994
2 59147 97.5158 65.4792 0007675 327.1574 32.9200 15.52540989 90250Epoch: 2025-10-16T03:19Z
TLE epoch observation values (Epoch: 2025-10-16T03:19:44.397Z)
Latitude
-0.00005°
Longitude
-9.35851°
Altitude
408.069 km
Speed
7.668 km/s
True Right ascension
04h 21m 55s
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
08:29:04
Azimuth
Unknown
Elevation
Unknown
Doppler factor
Unknown
Orbital elements
Apogee altitude
411.444 km
Perigee altitude
401.03 km
Semi-major axis
6,784.374 km
Eccentricity
0.00077
Inclination
97.5158°
RAAN
65.4792°
Arg. of periapsis
327.1574°
True anomaly
32.96784°
Mean anomaly
32.92°
Eccentric anomaly
32.94391°
Mean motion
3.88399 °/min
Orbital period
92.69 mins
BSTAR
0.0013185
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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 forecast
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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. |
|---|---|---|---|---|---|---|---|
| 5 mins | 2025-10-16 22:26:12.805Z | 356.915° N | 2025-10-16 22:29:12.805Z | 283.319° WNW | 33.036° | 2025-10-16 22:31:12.805Z | 222.19° SW |
| 4 mins | 2025-10-17 08:52:12.805Z | 125.845° SE | 2025-10-17 08:53:12.805Z | 96.756° ESE | 28.808° | 2025-10-17 08:56:12.805Z | 8.441° NNE |
Co-orbital & Co-planar RSOs
Thresholds — Semi-major Axis: ±100 km, RAAN: ±3°, Inclination: ±5°
TCA is derived from TLE conjunctions
Click to sort rows by RSO header in ascending order | Click to sort rows by Country header in ascending order | Click to sort rows by Type header in ascending order | Click to sort rows by Inclination Δ header in ascending order | Click to sort rows by RAAN Δ header in ascending order | Click to sort rows by Coplanar Angle header in ascending order | Click to sort rows by SMA Δ header in ascending order | Click to sort rows by Orbital period header in ascending order | Click to sort rows by <5km Md TCA header in ascending order |
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CAUTION: Conjunctions in this section are generated from low-fidelity TLE screenings
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