ZACUBE-2, 43907 (Decayed)

Orbit data source: Space-Track

ZACUBE-2, 43907 was a payload satellite owned by CPUT (ZA) in LEO that was launched on Thu, 27 Dec 2018 UTC via a SOYUZ-2-1A launch vehicle from the Vostochny Cosmodrome (VOSTO). 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

ZACUBE-2 details

Identifier	43907, 2018-111AH
Orbit	Decayed
Last TLE update	8 months ago
Origin	CPUT (ZA / SAFR)
Manufacturer	CPUT
Mission	Decayed Amateur Communications
Bus & Motor	CUBESAT 3U, Unknown motor
Mass	4 kg wet, 4 kg dry
Launch date (UTC)	2018-12-27 (6 years ago)
Launch vehicle	SOYUZ-2-1A
Launch site	Vostochny Cosmodrome (VOSTO)
Object type	Payload Rocket body Debris
Shape & HBR	Box, 0.3 m
Radar Cross Section	0.035 m², Small (<0.1 m²)

Expand to show TLE details & history

TLE from 8 months ago

0 ZACUBE-2
1 43907U 18111AH  24114.92533070  .15259846  24014-5  22612-3 0  9998
2 43907  97.0532 359.0530 0012240 247.7734 112.2272 16.48029140297694

Epoch: 2024-04-23T22:12Z

Definitive object data (Epoch: 2024-04-23T22:12:28.572Z)

Latitude	-0.00009°
Longitude	173.49113°
Altitude	150.832 km
Speed	7.814 km/s
True Right ascension	23h 56m 12s
True Declination	0° 00' 00"
Sunlit	Object was in daylight 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	149.292 km
Perigee altitude	133.333 km
Semi-major axis	6,519.45 km
Eccentricity	0.001224
Inclination	97.0532°
RAAN	359.053°
Arg. of periapsis	247.7734°
True anomaly	112.35696°
Mean anomaly	112.2272°
Eccentric anomaly	112.29209°
Mean motion	4.12313 °/min
BSTAR	0.00022612
Orbital period	87.31 mins