MICRODRAGON, 43935 (Decayed)

Orbit data source: Space-Track

MICRODRAGON, 43935 was a payload satellite owned by VNSC (JP) in LEO that was launched on Fri, 18 Jan 2019 UTC via an EPSILON launch vehicle from the Kagoshima Space Center University Of Tokyo (KSCUT). 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

MICRODRAGON details

Identifier	43935, 2019-003D
Orbit	Decayed
Last TLE update	3 months ago
Origin	VNSC (JP / JPN)
Manufacturer	VNSC
Mission	Decayed Civil Technology
Bus & Motor	MICRODRAGON, Unknown motor
Mass	50 kg wet, 50 kg dry
Launch date (UTC)	2019-01-18 (6 years ago)
Launch vehicle	EPSILON
Launch site	Kagoshima Space Center University Of Tokyo (KSCUT)
Object type	Payload Rocket body Debris
Shape & HBR	Box + 2 Pan, 1.5 m
Radar Cross Section	0.514 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 3 months ago

0 MICRODRAGON
1 43935U 19003D   24275.26385918  .16170828  23408-5  14762-3 0  9997
2 43935  97.0439 293.7887 0009366 285.9496  74.0778 16.51424394318676

Epoch: 2024-10-01T06:19Z

Definitive object data (Epoch: 2024-10-01T06:19:57.433Z)

Latitude	-0.00002°
Longitude	-171.68068°
Altitude	137.196 km
Speed	7.825 km/s
True Right ascension	19h 35m 09s
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	138.462 km
Perigee altitude	126.267 km
Semi-major axis	6,510.501 km
Eccentricity	0.0009366
Inclination	97.0439°
RAAN	293.7887°
Arg. of periapsis	285.9496°
True anomaly	74.18104°
Mean anomaly	74.0778°
Eccentric anomaly	74.12942°
Mean motion	4.13163 °/min
BSTAR	0.00014762
Orbital period	87.13 mins