KEPLER-0 (KIPP), 43157 (Decayed)

Orbit data source: Space-Track

KEPLER-0 (KIPP), 43157 was a payload satellite owned by Kepler Comms (CA) 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

KEPLER-0 (KIPP) details

Identifier	43157, 2018-008C
Orbit	Decayed
Last TLE update	8 months ago
Origin	Kepler Comms (CA)
Manufacturer	AAC ClydeSpace
Mission	Decayed Commercial Communications
Bus & Motor	CUBESAT 3U, Unknown motor
Mass	3 kg wet, 3 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 + 2 Pan, 0.3 m
Radar Cross Section	0.035 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 8 months ago

0 KEPLER-0 (KIPP)
1 43157U 18008C   24103.03271106  .18194248  24335-5  16060-2 0  9991
2 43157  97.2162 161.4645 0013704 262.1472  97.8272 16.38947242344805

Epoch: 2024-04-12T00:47Z

Definitive object data (Epoch: 2024-04-12T00:47:06.235Z)

Latitude	-0.00002°
Longitude	-51.03238°
Altitude	173.094 km
Speed	7.802 km/s
True Right ascension	10h 45m 51s
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	174.373 km
Perigee altitude	156.438 km
Semi-major axis	6,543.542 km
Eccentricity	0.0013704
Inclination	97.2162°
RAAN	161.4645°
Arg. of periapsis	262.1472°
True anomaly	97.98274°
Mean anomaly	97.8272°
Eccentric anomaly	97.90497°
Mean motion	4.10038 °/min
BSTAR	0.001606
Orbital period	87.8 mins