KAITUO 1A, 40904 (Decayed)

Orbit data source: Space-Track

KAITUO 1A, 40904 was a payload satellite owned by DFH Shenzhen (CN) in LEO that was launched on Sat, 19 Sep 2015 UTC via a CHANG ZHENG 6 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

KAITUO 1A details

Identifier	40904, 2015-049F
Orbit	Decayed
Last TLE update	1 month ago
Origin	DFH Shenzhen (CN / PRC)
Manufacturer	DFH Shenzhen
Mission	Decayed Civil Technology
Bus & Motor	Unknown
Mass	130 kg wet, 130 kg dry
Launch date (UTC)	2015-09-19 (9 years ago)
Launch vehicle	CHANG ZHENG 6
Launch site	Taiyaun Space Center, China (TSC)
Object type	Payload Rocket body Debris
Shape & HBR	Box, 1 m
Radar Cross Section	1.500 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 1 month ago

0 KAITUO 1A
1 40904U 15049F   24317.71731501  .16110311  27416-5  24573-3 0  9991
2 40904  97.4358 343.2801 0007635 230.2557 129.8075 16.48327697507660

Epoch: 2024-11-12T17:12Z

Definitive object data (Epoch: 2024-11-12T17:12:56.016Z)

Latitude	-0.00001°
Longitude	32.72248°
Altitude	150.195 km
Speed	7.814 km/s
True Right ascension	22h 53m 07s
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	145.518 km
Perigee altitude	135.564 km
Semi-major axis	6,518.678 km
Eccentricity	0.0007635
Inclination	97.4358°
RAAN	343.2801°
Arg. of periapsis	230.2557°
True anomaly	129.87467°
Mean anomaly	129.8075°
Eccentric anomaly	129.84109°
Mean motion	4.12386 °/min
BSTAR	0.00024573
Orbital period	87.3 mins