TECHEDSAT 13, 51095 (Decayed)

Orbit data source: Space-Track

TECHEDSAT 13, 51095 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

TECHEDSAT 13 details

Identifier	51095, 2022-003B
Orbit	Decayed
Last TLE update	6 months ago
Origin	ARC/SJSU (US)
Manufacturer	ARC
Mission	Decayed Civil Technology
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 + 1 Truss + 1 Sail, 0.8 m
Radar Cross Section	0.035 m², Small (<0.1 m²)

Expand to show TLE details & history

TLE from 6 months ago

0 TECHEDSAT 13
1 51095U 22003B   24194.23040869  .04907095  10302-4  89464-3 0  9997
2 51095  44.9616 175.9616 0003365 130.6448 229.4767 16.31437883140196

Epoch: 2024-07-12T05:31Z

Definitive object data (Epoch: 2024-07-12T05:31:47.31Z)

Latitude	-0.00003°
Longitude	162.40477°
Altitude	190.108 km
Speed	7.793 km/s
True Right ascension	11h 43m 50s
True Declination	0° 00' 00"
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	192.577 km
Perigee altitude	188.156 km
Semi-major axis	6,568.503 km
Eccentricity	0.0003365
Inclination	44.9616°
RAAN	175.9616°
Arg. of periapsis	130.6448°
True anomaly	229.4474°
Mean anomaly	229.4767°
Eccentric anomaly	229.46205°
Mean motion	4.07703 °/min
BSTAR	0.00089464
Orbital period	88.3 mins