TIANPING 1A, 43712 (Decayed)

Orbit data source: Space-Track

TIANPING 1A, 43712 was a payload satellite owned by Guoxing (CN) in LEO that was launched on Mon, 19 Nov 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

TIANPING 1A details

Identifier	43712, 2018-094C
Orbit	Decayed
Last TLE update	3 months ago
Origin	Guoxing (CN / PRC)
Manufacturer	DFH Shenzhen
Mission	Decayed Commercial Calibration
Bus & Motor	PINA, Unknown motor
Mass	10 kg wet, ~10 kg dry
Launch date (UTC)	2018-11-19 (6 years ago)
Launch vehicle	CHANG ZHENG 2D
Launch site	Jiuquan Satellite Launch Center, China (JSC)
Object type	Payload Rocket body Debris
Shape & HBR	Box + 2 Pan, 0.5 m
Radar Cross Section	0.048 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 3 months ago

0 TIANPING 1A
1 43712U 18094C   24281.68573998  .08479845  25126-5  75773-3 0  9999
2 43712  97.3042 314.5786 0006534 252.5471 257.5819 16.39148558329014

Epoch: 2024-10-07T16:27Z

Definitive object data (Epoch: 2024-10-07T16:27:27.934Z)

Latitude	29.73209°
Longitude	-124.9236°
Altitude	172.961 km
Speed	7.805 km/s
True Right ascension	09h 15m 00s
True Declination	29° 34' 16"
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	169.148 km
Perigee altitude	160.598 km
Semi-major axis	6,543.01 km
Eccentricity	0.0006534
Inclination	97.3042°
RAAN	314.5786°
Arg. of periapsis	252.5471°
True anomaly	257.50879°
Mean anomaly	257.5819°
Eccentric anomaly	257.54534°
Mean motion	4.10088 °/min
BSTAR	0.00075773
Orbital period	87.79 mins