DEMOSAT 2, 43127 (Decayed)

Orbit data source: Space-Track

DEMOSAT 2, 43127 was a payload satellite owned by Astranis (US) in LEO that was launched on Fri, 12 Jan 2018 UTC via a PSLV-XL launch vehicle from the Sirharikota (SRI). 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

DEMOSAT 2 details

Identifier	43127, 2018-004S
Orbit	Decayed
Last TLE update	6 months ago
Origin	Astranis (US)
Manufacturer	Astranis
Mission	Decayed Commercial Communications
Bus & Motor	CUBESAT 3U, Unknown motor
Mass	4 kg wet, 4 kg dry
Launch date (UTC)	2018-01-12 (7 years ago)
Launch vehicle	PSLV-XL
Launch site	Sirharikota (SRI)
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 6 months ago

0 DEMOSAT 2
1 43127U 18004S   24176.32678182  .15905452  25464-5  13530-3 0  9999
2 43127  97.2890 266.4816 0013986 264.1495  95.8217 16.51504212360160

Epoch: 2024-06-24T07:50Z

Definitive object data (Epoch: 2024-06-24T07:50:33.949Z)

Latitude	0.00004°
Longitude	-124.12287°
Altitude	139.584 km
Speed	7.822 km/s
True Right ascension	17h 45m 55s
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	141.27 km
Perigee altitude	123.06 km
Semi-major axis	6,510.302 km
Eccentricity	0.0013986
Inclination	97.289°
RAAN	266.4816°
Arg. of periapsis	264.1495°
True anomaly	95.98111°
Mean anomaly	95.8217°
Eccentric anomaly	95.90141°
Mean motion	4.13182 °/min
BSTAR	0.0001353
Orbital period	87.13 mins