ELECTRON R/B, 59589 (Decayed)
Orbit data source: Space-Track
ELECTRON R/B, 59589 was space debris in LEO originally from a launch on Tue, 23 Apr 2024 UTC launched from the Rocket Lab Launch Complex (RLLC). Debris objects in space refer to the collection of defunct objects orbiting the Earth. Examples of debris include non-operational satellites, rocket bodies, and fragments generated from explosions, collisions, or faulty payload assembly.
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59589 intel report (Beta)
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Edit Public Description
Identifier
Orbit
Country
USRelated business
Manufacturer
Rocket Lab
Mission
Decayed spacecraft
Bus & Motor
ELECTRON ST2, Unknown motor
Mass
250 kg wet, ~250 kg dry
Launch date (UTC)
Launch vehicle
Unknown
Launch site
Object type
Shape & HBR
Unknown
Radar Cross Section
Medium (>0.1 m² and <1 m²)
Expand to show TLE details & historyLast TLE update: 1 year ago
TLE from 1 year ago
0 ELECTRON R/B
1 59589U 24077C 24120.11832866 .25703934 18435-5 42399-3 0 9999
2 59589 97.3717 201.4229 0049442 202.9026 244.9909 16.41921092 828Epoch: 2024-04-29T02:50Z
TLE epoch observation values (Epoch: 2024-04-29T02:50:23.596Z)
Latitude
82.22266°
Longitude
-129.09537°
Altitude
188.031 km
Speed
7.792 km/s
True Right ascension
08h 44m 15s
True Declination
82° 10' 21"
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
12:54:09
Azimuth
Unknown
Elevation
Unknown
Doppler factor
Unknown
Orbital elements
Apogee altitude
189.814 km
Perigee altitude
125.187 km
Semi-major axis
6,535.638 km
Eccentricity
0.00494
Inclination
97.3717°
RAAN
201.4229°
Arg. of periapsis
202.9026°
True anomaly
244.4788°
Mean anomaly
244.9909°
Eccentric anomaly
244.73472°
Mean motion
4.10782 °/min
Orbital period
87.64 mins
BSTAR
0.00042399
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Other satellites on launch #77 in the year 2024 (2024-04-23 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.ELECTRON R/B 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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