Showing default

XIAOXIANG 1, 41842

Orbit data source: Space-Track

XIAOXIANG 1, 41842 is a payload satellite owned by Changsha Tianyi (CN) in LEO that was launched on Wed, 09 Nov 2016 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 1 details

Identifier	41842, 2016-066B
Orbit	LEO
Last TLE update	4 months ago
Origin	Changsha Tianyi (CN / PRC)
Manufacturer	Changsha Tianyi
Mission	Decayed Amateur Technology
Bus & Motor	CUBESAT 6U, Unknown motor
Mass	8 kg wet, 8 kg dry
Launch date (UTC)	2016-11-09 (8 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	0.105 m², Small (<0.1 m²)

Expand to show TLE details & history

TLE from 4 months ago

0 XIAOXIANG 1
1 41842U 16066B   24239.82917430  .15290837  25672-5  14151-3 0  9999
2 41842  97.3077 273.1412 0013464 246.9911 112.9975 16.50962723435203

Epoch: 2024-08-26T19:54Z

Definitive object data (Epoch: 2024-08-26T19:54:00.659Z)

Latitude	-0°
Longitude	-0.91552°
Altitude	143.508 km
Speed	7.818 km/s
True Right ascension	18h 12m 33s
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	142.358 km
Perigee altitude	124.823 km
Semi-major axis	6,511.728 km
Eccentricity	0.0013464
Inclination	97.3077°
RAAN	273.1412°
Arg. of periapsis	246.9911°
True anomaly	113.13943°
Mean anomaly	112.9975°
Eccentric anomaly	113.06847°
Mean motion	4.13046 °/min
BSTAR	0.00014151
Orbital period	87.16 mins