MYRADAR1, 52419 (Decayed)

Orbit data source: Space-Track

MYRADAR1, 52419 was a payload satellite owned by ACME AtronOmatic (US) in LEO that was launched on Mon, 02 May 2022 UTC via an ELECTRON launch vehicle from the Rocket Lab Launch Complex (RLLC). 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

Identifier	52419, 2022-047AB
Orbit	Decayed
Last TLE update	7 months ago
Origin	ACME AtronOmatic (US)
Manufacturer	ACME AtronOmatic
Mission	Decayed Commercial Imaging
Bus & Motor	POCKETQUBE 1P, Unknown motor
Mass	0.25 kg wet, 0.25 kg dry
Launch date (UTC)	2022-05-02 (3 years ago)
Launch vehicle	ELECTRON
Launch site	Rocket Lab Launch Complex (RLLC)
Object type	Payload Rocket body Debris
Shape & HBR	Box, 0.05 m
Radar Cross Section	0.004 m², Small (<0.1 m²)

Expand to show TLE details & history

TLE from 7 months ago

0 MYRADAR1
1 52419U 22047AB  24233.98531526  .15245793  25412-5  43352-3 0  9994
2 52419  97.3504 328.5188 0014320 268.5058  91.4604 16.44088942130048

Epoch: 2024-08-20T23:38Z

Definitive object data (Epoch: 2024-08-20T23:38:51.238Z)

Latitude	0.00004°
Longitude	4.01131°
Altitude	158.458 km
Speed	7.811 km/s
True Right ascension	21h 54m 04s
True Declination	0° 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

Apogee altitude	161.099 km
Perigee altitude	142.397 km
Semi-major axis	6,529.885 km
Eccentricity	0.001432
Inclination	97.3504°
RAAN	328.5188°
Arg. of periapsis	268.5058°
True anomaly	91.62443°
Mean anomaly	91.4604°
Eccentric anomaly	91.54242°
Mean motion	4.11325 °/min
BSTAR	0.00043352
Orbital period	87.52 mins