VELOX 2, 41171 (Decayed)

Orbit data source: Space-Track

VELOX 2, 41171 was a payload satellite owned by NTU (SG) in LEO that was launched on Wed, 16 Dec 2015 UTC via a PSLV 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

VELOX 2 details

Identifier	41171, 2015-077F
Orbit	Decayed
Last TLE update	4 months ago
Origin	NTU (SG / SING)
Manufacturer	NTU
Mission	Decayed Amateur Technology
Bus & Motor	CUBESAT 6U, Unknown motor
Mass	13 kg wet, 13 kg dry
Launch date (UTC)	2015-12-16 (9 years ago)
Launch vehicle	PSLV
Launch site	Sirharikota (SRI)
Object type	Payload Rocket body Debris
Shape & HBR	Box + 2 Pan, 0.6 m
Radar Cross Section	0.051 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 4 months ago

0 VELOX 2
1 41171U 15077F   24200.22842821  .01761728  20491-2  21891-2 0  9994
2 41171  14.9815 159.0057 0006929 222.3342 137.6457 16.06834981476786

Epoch: 2024-07-18T05:28Z

Definitive object data (Epoch: 2024-07-18T05:28:56.197Z)

Latitude	-0.00001°
Longitude	140.24991°
Altitude	256.074 km
Speed	7.755 km/s
True Right ascension	10h 36m 01s
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	266.122 km
Perigee altitude	256.921 km
Semi-major axis	6,639.659 km
Eccentricity	0.0006929
Inclination	14.9815°
RAAN	159.0057°
Arg. of periapsis	222.3342°
True anomaly	137.69916°
Mean anomaly	137.6457°
Eccentric anomaly	137.67243°
Mean motion	4.01166 °/min
BSTAR	0.0021891
Orbital period	89.74 mins