CYGFM06, 41889 (Decayed)

Orbit data source: Space-Track

CYGFM06, 41889 was an American payload satellite in LEO that was launched on Thu, 15 Dec 2016 UTC via a PEGASUS XL launch vehicle from the Pegasus Launch, Eastern Range Air Space (ERAS). 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

CYGFM06 details

Identifier	41889, 2016-078F
Orbit	Decayed
Last TLE update	6 months ago
Origin	LARCN/SWRIB (US)
Manufacturer	SST-US
Mission	Decayed Civil Science
Bus & Motor	CYGNSS, Unknown motor
Mass	29 kg wet, 29 kg dry
Launch date (UTC)	2016-12-15 (8 years ago)
Launch vehicle	PEGASUS XL
Launch site	Pegasus Launch, Eastern Range Air Space (ERAS)
Object type	Payload Rocket body Debris
Shape & HBR	Half Hex Cyl + 2 Pan, 1.7 m
Radar Cross Section	0.450 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 6 months ago

0 CYGFM06
1 41889U 16078F   24164.26093044  .04157679  41859-1  29123-2 0  9993
2 41889  34.9416 237.4606 0003084  12.6691 347.4129 16.19075887416268

Epoch: 2024-06-12T06:15Z

Definitive object data (Epoch: 2024-06-12T06:15:44.39Z)

Latitude	-0.00002°
Longitude	-117.54473°
Altitude	218.931 km
Speed	7.779 km/s
True Right ascension	15h 49m 50s
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	227.493 km
Perigee altitude	223.42 km
Semi-major axis	6,603.594 km
Eccentricity	0.0003084
Inclination	34.9416°
RAAN	237.4606°
Arg. of periapsis	12.6691°
True anomaly	347.4052°
Mean anomaly	347.4129°
Eccentric anomaly	347.40905°
Mean motion	4.04457 °/min
BSTAR	0.0029123
Orbital period	89.01 mins