GNOMES-2, 48910 (Decayed)

Orbit data source: Space-Track

GNOMES-2, 48910 was a payload satellite owned by PlanetiQ (US) in LEO that was launched on Wed, 30 Jun 2021 UTC via an FALCON 9 launch vehicle from the Air Force Eastern Test Range (AFETR). 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

GNOMES-2 details

Identifier	48910, 2021-059AH
Orbit	Decayed
Last TLE update	8 months ago
Origin	PlanetiQ (US)
Manufacturer	Blue Canyon
Mission	Decayed Commercial Communications
Bus & Motor	XSAT, Unknown motor
Mass	~30 kg wet, ~30 kg dry
Launch date (UTC)	2021-06-30 (4 years ago)
Launch vehicle	FALCON 9
Launch site	Air Force Eastern Test Range (AFETR)
Object type	Payload Rocket body Debris
Shape & HBR	Box + 2 Pan, 0.6 m
Radar Cross Section	0.162 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 8 months ago

0 GNOMES-2
1 48910U 21059AH  24131.55719574  .17347472  27438-5  21614-3 0  9994
2 48910  97.5948 291.7408 0012035 255.9239 104.0727 16.49126212160263

Epoch: 2024-05-10T13:22Z

Definitive object data (Epoch: 2024-05-10T13:22:21.711Z)

Latitude	-0.00007°
Longitude	-137.68564°
Altitude	146.812 km
Speed	7.817 km/s
True Right ascension	19h 26m 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	146.285 km
Perigee altitude	130.599 km
Semi-major axis	6,516.579 km
Eccentricity	0.0012035
Inclination	97.5948°
RAAN	291.7408°
Arg. of periapsis	255.9239°
True anomaly	104.20642°
Mean anomaly	104.0727°
Eccentric anomaly	104.13957°
Mean motion	4.12585 °/min
BSTAR	0.00021614
Orbital period	87.25 mins