LEMUR 2 JOHNNYTRUONG, 59146
Orbit data source: Space-Track
LEMUR 2 JOHNNYTRUONG, 59146 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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59146 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: 1 day ago
TLE from 1 day ago
0 LEMUR 2 JOHNNYTRUONG
1 59146U 24043BA 26033.37802359 .00033907 00000-0 59643-3 0 9991
2 59146 97.5225 177.9011 0005051 315.7569 44.3278 15.50395191107083Epoch: 2026-02-02T09:04Z
TLE epoch observation values (Epoch: 2026-02-02T09:04:21.238Z)
Latitude
0.00001°
Longitude
-90.76157°
Altitude
416.245 km
Speed
7.663 km/s
True Right ascension
11h 51m 36s
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
13:51:48
Azimuth
Unknown
Elevation
Unknown
Doppler factor
Unknown
Orbital elements
Apogee altitude
415.932 km
Perigee altitude
409.072 km
Semi-major axis
6,790.639 km
Eccentricity
0.00051
Inclination
97.5225°
RAAN
177.9011°
Arg. of periapsis
315.7569°
True anomaly
44.36826°
Mean anomaly
44.3278°
Eccentric anomaly
44.34803°
Mean motion
3.87862 °/min
Orbital period
92.82 mins
BSTAR
0.00059643
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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 JOHNNYTRUONG 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. |
|---|---|---|---|---|---|---|---|
| 4 mins | 2026-02-03 22:48:34.419Z | 347.388° N | 2026-02-03 22:50:34.419Z | 287.474° WNW | 31.516° | 2026-02-03 22:52:34.419Z | 225.734° WSW |
| 4 mins | 2026-02-04 09:14:34.419Z | 128.968° SE | 2026-02-04 09:15:34.419Z | 97.436° ESE | 31.628° | 2026-02-04 09:18:34.419Z | 5.66° 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 descending order |
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CAUTION: Conjunctions in this section are generated from low-fidelity TLE screenings
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