GOMX4-B, 43196 (Decayed)

Orbit data source: Space-Track

GOMX4-B, 43196 was a Danish payload satellite in LEO that was launched on Fri, 02 Feb 2018 UTC via a CHANG ZHENG 2D launch vehicle from the Jiuquan Satellite Launch Center, China (JSC). 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

GOMX4-B details

Identifier	43196, 2018-015E
Orbit	Decayed
Last TLE update	3 months ago
Origin	GOMSP/ESA (DK / DEN)
Manufacturer	GOMSpace
Mission	Decayed Civil Technology
Bus & Motor	CUBESAT 6U, Unknown motor
Mass	8 kg wet, 8 kg dry
Launch date (UTC)	2018-02-02 (7 years ago)
Launch vehicle	CHANG ZHENG 2D
Launch site	Jiuquan Satellite Launch Center, China (JSC)
Object type	Payload Rocket body Debris
Shape & HBR	Box, 0.3 m
Radar Cross Section	0.105 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 3 months ago

0 GOMX4-B
1 43196U 18015E   24283.56674783  .07825702  26886-5  28016-3 0  9999
2 43196  97.5747 108.8545 0010089 257.9555 102.0615 16.43491331373587

Epoch: 2024-10-09T13:36Z

Definitive object data (Epoch: 2024-10-09T13:36:07.012Z)

Latitude	-0.00005°
Longitude	-113.83851°
Altitude	161.166 km
Speed	7.809 km/s
True Right ascension	07h 15m 25s
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	159.932 km
Perigee altitude	146.753 km
Semi-major axis	6,531.48 km
Eccentricity	0.0010089
Inclination	97.5747°
RAAN	108.8545°
Arg. of periapsis	257.9555°
True anomaly	102.17453°
Mean anomaly	102.0615°
Eccentric anomaly	102.11802°
Mean motion	4.11174 °/min
BSTAR	0.00028016
Orbital period	87.55 mins