ELYUSIUM/LOWER FREE FLYE, 43760 (Decayed)

Orbit data source: Space-Track

ELYUSIUM/LOWER FREE FLYE, 43760 was a payload satellite owned by Spaceflight Ind (US) in LEO that was launched on Mon, 03 Dec 2018 UTC via an FALCON 9 launch vehicle from the Air Force Western Test Range (AFWTR). 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

ELYUSIUM/LOWER FREE FLYE details

Identifier	43760, 2018-099C
Orbit	Decayed
Last TLE update	1 week ago
Origin	Spaceflight Ind (US)
Manufacturer	Spaceflight Ind
Mission	Decayed Commercial Technology
Bus & Motor	SFL-LFF, Unknown motor
Mass	421 kg wet, 260 kg dry
Launch date (UTC)	2018-12-03 (6 years ago)
Launch vehicle	FALCON 9
Launch site	Air Force Western Test Range (AFWTR)
Object type	Payload Rocket body Debris
Shape & HBR	Cyl + 1 Sail, 4 m
Radar Cross Section	2.337 m², Large (>1 m²)

Expand to show TLE details & history

TLE from 1 week ago

0 ELYUSIUM/LOWER FREE FLYE
1 43760U 18099C   24340.97643840  .22687725  25922-5  37698-3 0  9991
2 43760  97.4552  54.3313 0009931 279.3000 200.1657 16.47590242329764

Epoch: 2024-12-05T23:26Z

Definitive object data (Epoch: 2024-12-05T23:26:04.277Z)

Latitude	59.83214°
Longitude	-179.50198°
Altitude	162.015 km
Speed	7.811 km/s
True Right ascension	16h 29m 03s
True Declination	59° 40' 08"
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	148.965 km
Perigee altitude	136.014 km
Semi-major axis	6,520.626 km
Eccentricity	0.0009931
Inclination	97.4552°
RAAN	54.3313°
Arg. of periapsis	279.3°
True anomaly	200.12651°
Mean anomaly	200.1657°
Eccentric anomaly	200.1461°
Mean motion	4.12201 °/min
BSTAR	0.00037698
Orbital period	87.34 mins