XIAOXIANG 2, 43155 (Decayed)

Orbit data source: Space-Track

XIAOXIANG 2, 43155 was a payload satellite owned by Changsha Tianyi (CN) in LEO that was launched on Fri, 19 Jan 2018 UTC via a CHANG ZHENG 11 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

XIAOXIANG 2 details

Identifier	43155, 2018-008A
Orbit	Decayed
Last TLE update	4 months ago
Origin	Changsha Tianyi (CN / PRC)
Manufacturer	Changsha Tianyi
Mission	Decayed Commercial Communications
Bus & Motor	CUBESAT 6U, Unknown motor
Mass	8 kg wet, 8 kg dry
Launch date (UTC)	2018-01-19 (7 years ago)
Launch vehicle	CHANG ZHENG 11
Launch site	Jiuquan Satellite Launch Center, China (JSC)
Object type	Payload Rocket body Debris
Shape & HBR	Box, 0.3 m
Radar Cross Section	0.080 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 4 months ago

0 XIAOXIANG 2
1 43155U 18008A   24235.75891043  .18791616  24620-5  29649-3 0  9999
2 43155  97.1927 292.6688 0013149 268.0079  91.9719 16.47546330365397

Epoch: 2024-08-22T18:12Z

Definitive object data (Epoch: 2024-08-22T18:12:49.861Z)

Latitude	-0.00002°
Longitude	47.91892°
Altitude	149.379 km
Speed	7.816 km/s
True Right ascension	19h 30m 40s
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	151.168 km
Perigee altitude	134.019 km
Semi-major axis	6,520.73 km
Eccentricity	0.0013149
Inclination	97.1927°
RAAN	292.6688°
Arg. of periapsis	268.0079°
True anomaly	92.12248°
Mean anomaly	91.9719°
Eccentric anomaly	92.04719°
Mean motion	4.12191 °/min
BSTAR	0.00029649
Orbital period	87.34 mins