ZHOU ENLAI, 43156 (Decayed)

Orbit data source: Space-Track

ZHOU ENLAI, 43156 was a Chinese payload satellite 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

ZHOU ENLAI details

Identifier	43156, 2018-008B
Orbit	Decayed
Last TLE update	5 months ago
Origin	HQZS/NJUST (CN / PRC)
Manufacturer	Ling Zhong
Mission	Decayed Amateur Technology
Bus & Motor	CUBESAT 2U, Unknown motor
Mass	2 kg wet, 2 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, 0.2 m
Radar Cross Section	0.025 m², Small (<0.1 m²)

Expand to show TLE details & history

TLE from 5 months ago

0 ZHOU ENLAI
1 43156U 18008B   24198.66905212  .17296646  24655-5  28398-3 0  9992
2 43156  97.2151 256.8209 0016593 258.3712 101.5729 16.46899832359648

Epoch: 2024-07-16T16:03Z

Definitive object data (Epoch: 2024-07-16T16:03:26.103Z)

Latitude	-0.00004°
Longitude	80.97753°
Altitude	152.968 km
Speed	7.813 km/s
True Right ascension	17h 07m 17s
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	155.125 km
Perigee altitude	133.48 km
Semi-major axis	6,522.439 km
Eccentricity	0.0016593
Inclination	97.2151°
RAAN	256.8209°
Arg. of periapsis	258.3712°
True anomaly	101.7591°
Mean anomaly	101.5729°
Eccentric anomaly	101.66601°
Mean motion	4.12029 °/min
BSTAR	0.00028398
Orbital period	87.37 mins