FOSSASAT2E16 (FEROX), 56932 (Decayed)

Orbit data source: Space-Track

FOSSASAT2E16 (FEROX), 56932 was a payload satellite owned by Fossa Systems (ES) in LEO that was launched on Mon, 12 Jun 2023 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

FOSSASAT2E16 (FEROX) details

Identifier	56932, 2023-084A
Orbit	Decayed
Last TLE update	7 months ago
Origin	Fossa Systems (ES / SPN)
Manufacturer	Fossa Systems
Mission	Decayed Commercial Communications
Bus & Motor	FLAT CUBESAT, Unknown motor
Mass	2 kg wet, 2 kg dry
Launch date (UTC)	2023-06-12 (1 year ago)
Launch vehicle	FALCON 9
Launch site	Air Force Western Test Range (AFWTR)
Object type	Payload Rocket body Debris
Shape & HBR	Box, 0.6 m
Radar Cross Section	0.015 m², Small (<0.1 m²)

Expand to show TLE details & history

TLE from 7 months ago

0 FOSSASAT2E16 (FEROX)
1 56932U 23084A   24123.49189288  .21632981  26402-5  64018-3 0  9996
2 56932  97.4920 249.7387 0016231 288.2634  71.6900 16.43619973 49694

Epoch: 2024-05-02T11:48Z

Definitive object data (Epoch: 2024-05-02T11:48:19.544Z)

Latitude	-0.0001°
Longitude	-148.22916°
Altitude	156.127 km
Speed	7.814 km/s
True Right ascension	16h 38m 57s
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	163.598 km
Perigee altitude	142.397 km
Semi-major axis	6,531.135 km
Eccentricity	0.0016231
Inclination	97.492°
RAAN	249.7387°
Arg. of periapsis	288.2634°
True anomaly	71.86669°
Mean anomaly	71.69°
Eccentric anomaly	71.77833°
Mean motion	4.11207 °/min
BSTAR	0.00064018
Orbital period	87.55 mins