YAOGAN 23, 40305 (Decayed)

Orbit data source: Space-Track

YAOGAN 23, 40305 was a payload satellite owned by PLA GAD (CN) in LEO that was launched on Fri, 14 Nov 2014 UTC via a CHANG ZHENG 2C launch vehicle from the Taiyaun Space Center, China (TSC). 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

YAOGAN 23 details

Identifier	40305, 2014-071A
Orbit	Decayed
Last TLE update	2 weeks ago
Origin	PLA GAD (CN / PRC)
Manufacturer	SAST
Mission	Decayed Defense Radar Imaging
Bus & Motor	JB-7, Unknown motor
Mass	~2,000 kg wet, ~2,000 kg dry
Launch date (UTC)	2014-11-14 (10 years ago)
Launch vehicle	CHANG ZHENG 2C
Launch site	Taiyaun Space Center, China (TSC)
Object type	Payload Rocket body Debris
Shape & HBR	Box + 2 Pan, 4 m
Radar Cross Section	5.141 m², Large (>1 m²)

Expand to show TLE details & history

TLE from 2 weeks ago

0 YAOGAN 23
1 40305U 14071A   24347.60733468  .14564652  28361-5  28964-3 0  9992
2 40305  97.6603 349.9044 0005156 249.1520 259.6825 16.47071669560373

Epoch: 2024-12-12T14:34Z

Definitive object data (Epoch: 2024-12-12T14:34:33.716Z)

Latitude	30.97561°
Longitude	-125.91712°
Altitude	151.83 km
Speed	7.818 km/s
True Right ascension	11h 38m 02s
True Declination	30° 48' 36"
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	147.231 km
Perigee altitude	140.506 km
Semi-major axis	6,522.006 km
Eccentricity	0.0005156
Inclination	97.6603°
RAAN	349.9044°
Arg. of periapsis	249.152°
True anomaly	259.62438°
Mean anomaly	259.6825°
Eccentric anomaly	259.65344°
Mean motion	4.1207 °/min
BSTAR	0.00028964
Orbital period	87.36 mins