GOMX4-A, 43197 (Decayed)

Orbit data source: Space-Track

GOMX4-A, 43197 was a payload satellite owned by FMI (DK) 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-A details

Identifier	43197, 2018-015F
Orbit	Decayed
Last TLE update	4 months ago
Origin	FMI (DK / DEN)
Manufacturer	GOMSpace
Mission	Decayed Defense Imaging/Com
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 4 months ago

0 GOMX4-A
1 43197U 18015F   24231.57785391  .12036390  27077-5  33718-3 0  9993
2 43197  97.5695  57.6561 0009227 255.6517 104.3760 16.44816160365796

Epoch: 2024-08-18T13:52Z

Definitive object data (Epoch: 2024-08-18T13:52:06.577Z)

Latitude	-0.00008°
Longitude	-117.79238°
Altitude	157.776 km
Speed	7.811 km/s
True Right ascension	03h 50m 37s
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	155.855 km
Perigee altitude	143.808 km
Semi-major axis	6,527.968 km
Eccentricity	0.0009227
Inclination	97.5695°
RAAN	57.6561°
Arg. of periapsis	255.6517°
True anomaly	104.47839°
Mean anomaly	104.376°
Eccentric anomaly	104.4272°
Mean motion	4.11506 °/min
BSTAR	0.00033718
Orbital period	87.48 mins