GEARRS-3, 51097 (Decayed)

Orbit data source: Space-Track

GEARRS-3, 51097 was an American payload satellite in LEO that was launched on Thu, 13 Jan 2022 UTC via an LAUNCHERONE launch vehicle from the Pegasus Launch, Western Range Air Space (WRAS). 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

GEARRS-3 details

Identifier	51097, 2022-003D
Orbit	Decayed
Last TLE update	5 months ago
Origin	NSL/AFRL (US)
Manufacturer	NearSpaceLaunch
Mission	Decayed Commercial Communications
Bus & Motor	CUBESAT 3U, Unknown motor
Mass	4 kg wet, 4 kg dry
Launch date (UTC)	2022-01-13 (3 years ago)
Launch vehicle	LAUNCHERONE
Launch site	Pegasus Launch, Western Range Air Space (WRAS)
Object type	Payload Rocket body Debris
Shape & HBR	Box, 0.3 m
Radar Cross Section	0.035 m², Small (<0.1 m²)

Expand to show TLE details & history

TLE from 5 months ago

0 GEARRS-3
1 51097U 22003D   24220.71171408  .13367639  10692-4  32982-3 0  9995
2 51097  44.9127  23.7043 0008286 294.0535  65.9524 16.45547106144304

Epoch: 2024-08-07T17:04Z

Definitive object data (Epoch: 2024-08-07T17:04:52.096Z)

Latitude	-0.00003°
Longitude	170.7763°
Altitude	148.876 km
Speed	7.82 km/s
True Right ascension	01h 34m 49s
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	158.206 km
Perigee altitude	147.382 km
Semi-major axis	6,530.931 km
Eccentricity	0.0008286
Inclination	44.9127°
RAAN	23.7043°
Arg. of periapsis	294.0535°
True anomaly	66.03915°
Mean anomaly	65.9524°
Eccentric anomaly	65.99577°
Mean motion	4.11226 °/min
BSTAR	0.00032982
Orbital period	87.54 mins