PROXIMA II, 43696 (Decayed)

Orbit data source: Space-Track

PROXIMA II, 43696 was a payload satellite owned by Fleet Space (AU) in LEO that was launched on Sun, 11 Nov 2018 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

PROXIMA II details

Identifier	43696, 2018-088G
Orbit	Decayed
Last TLE update	7 months ago
Origin	Fleet Space (AU / AUS)
Manufacturer	Fleet Space
Mission	Decayed Commercial Communications
Bus & Motor	CUBESAT 1.5U, Unknown motor
Mass	2 kg wet, 2 kg dry
Launch date (UTC)	2018-11-11 (6 years ago)
Launch vehicle	ELECTRON
Launch site	Rocket Lab Launch Complex (RLLC)
Object type	Payload Rocket body Debris
Shape & HBR	Box, 0.15 m
Radar Cross Section	0.026 m², Small (<0.1 m²)

Expand to show TLE details & history

TLE from 7 months ago

0 PROXIMA II
1 43696U 18088G   24141.55445783  .13836683 -15010-5  24324-3 0  9995
2 43696  84.9873 191.6715 0011974 253.9476 106.0514 16.47055474308402

Epoch: 2024-05-20T13:18Z

Definitive object data (Epoch: 2024-05-20T13:18:25.156Z)

Latitude	-0.0001°
Longitude	113.37691°
Altitude	152.592 km
Speed	7.813 km/s
True Right ascension	12h 46m 41s
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	151.618 km
Perigee altitude	135.999 km
Semi-major axis	6,521.946 km
Eccentricity	0.0011974
Inclination	84.9873°
RAAN	191.6715°
Arg. of periapsis	253.9476°
True anomaly	106.18321°
Mean anomaly	106.0514°
Eccentric anomaly	106.11731°
Mean motion	4.12076 °/min
BSTAR	0.00024324
Orbital period	87.36 mins