CICERO 10, 43690 (Decayed)

Orbit data source: Space-Track

CICERO 10, 43690 was a payload satellite owned by GeoOptics (US) in LEO that was launched on Sun, 11 Nov 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

CICERO 10 details

Identifier	43690, 2018-088A
Orbit	Decayed
Last TLE update	5 months ago
Origin	GeoOptics (US)
Manufacturer	Tyvak NSS
Mission	Decayed Commercial Meteo Radio Occ.
Bus & Motor	CUBESAT 6U, Unknown motor
Mass	10 kg wet, 10 kg dry
Launch date (UTC)	2018-11-11 (6 years ago)
Launch vehicle	ELECTRON
Launch site	Rocket Lab Launch Complex (RLLC)
Object type	Payload Rocket body Debris
Shape & HBR	Box + 2 Pan, 0.6 m
Radar Cross Section	0.079 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 5 months ago

0 CICERO 10
1 43690U 18088A   24202.07134880  .09413868 -14258-5  71711-3 0  9993
2 43690  84.9796 154.7562 0010648 197.6392 162.4546 16.40097779317440

Epoch: 2024-07-20T01:42Z

Definitive object data (Epoch: 2024-07-20T01:42:44.536Z)

Latitude	0.00005°
Longitude	-169.26744°
Altitude	175.5 km
Speed	7.797 km/s
True Right ascension	10h 19m 01s
True Declination	0° 00' 00"
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	169.224 km
Perigee altitude	155.296 km
Semi-major axis	6,540.397 km
Eccentricity	0.0010648
Inclination	84.9796°
RAAN	154.7562°
Arg. of periapsis	197.6392°
True anomaly	162.49134°
Mean anomaly	162.4546°
Eccentric anomaly	162.47297°
Mean motion	4.10334 °/min
BSTAR	0.00071711
Orbital period	87.73 mins