CP11 (ISX), 43856 (Decayed)

Orbit data source: Space-Track

CP11 (ISX), 43856 was a payload satellite owned by Cal Poly (US) in LEO that was launched on Sun, 16 Dec 2018 UTC via an ELECTRON launch vehicle from the Rocket Lab Launch Complex (RLLC). 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

CP11 (ISX) details

Identifier	43856, 2018-104H
Orbit	Decayed
Last TLE update	7 months ago
Origin	Cal Poly (US)
Manufacturer	Cal Poly
Mission	Decayed Amateur Technology
Bus & Motor	CUBESAT 3U, Unknown motor
Mass	3.5 kg wet, 3.5 kg dry
Launch date (UTC)	2018-12-16 (6 years ago)
Launch vehicle	ELECTRON
Launch site	Rocket Lab Launch Complex (RLLC)
Object type	Payload Rocket body Debris
Shape & HBR	Box + 2 Pan, 0.3 m
Radar Cross Section	0.035 m², Small (<0.1 m²)

Expand to show TLE details & history

TLE from 7 months ago

0 CP11 (ISX)
1 43856U 18104H   24137.54898874  .09084474 -14778-5  12966-2 0  9995
2 43856  84.9711 295.3142 0013845 258.8411 101.1335 16.34609461302249

Epoch: 2024-05-16T13:10Z

Definitive object data (Epoch: 2024-05-16T13:10:32.627Z)

Latitude	-0.00001°
Longitude	-137.06353°
Altitude	185.251 km
Speed	7.794 km/s
True Right ascension	19h 41m 15s
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	185.982 km
Perigee altitude	167.831 km
Semi-major axis	6,555.043 km
Eccentricity	0.0013845
Inclination	84.9711°
RAAN	295.3142°
Arg. of periapsis	258.8411°
True anomaly	101.28911°
Mean anomaly	101.1335°
Eccentric anomaly	101.21131°
Mean motion	4.08959 °/min
BSTAR	0.0012966
Orbital period	88.03 mins