TSUBAME, 40302 (Decayed)

Orbit data source: Space-Track

TSUBAME, 40302 was a Japanese payload satellite in LEO that was launched on Thu, 06 Nov 2014 UTC via a DNEPR launch vehicle from the Orenburg, Russia (OREN). 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

TSUBAME details

Identifier	40302, 2014-070E
Orbit	Decayed
Last TLE update	2 months ago
Origin	TIT/JAXA (JP / JPN)
Manufacturer	TITech
Mission	Decayed Amateur Astronomy
Bus & Motor	TSUBAME, Unknown motor
Mass	43 kg wet, 43 kg dry
Launch date (UTC)	2014-11-06 (10 years ago)
Launch vehicle	DNEPR
Launch site	Orenburg, Russia (OREN)
Object type	Payload Rocket body Debris
Shape & HBR	Box + 2 Pan, 1.2 m
Radar Cross Section	0.370 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 2 months ago

0 TSUBAME
1 40302U 14070E   24304.92016278  .14555910  24222-5  75248-3 0  9995
2 40302  97.0699 313.9580 0008498 243.4054 116.6377 16.42023614554487

Epoch: 2024-10-30T22:05Z

Definitive object data (Epoch: 2024-10-30T22:05:02.064Z)

Latitude	-0.00002°
Longitude	-57.01134°
Altitude	166.184 km
Speed	7.805 km/s
True Right ascension	20h 55m 49s
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	162.769 km
Perigee altitude	151.662 km
Semi-major axis	6,535.352 km
Eccentricity	0.0008498
Inclination	97.0699°
RAAN	313.958°
Arg. of periapsis	243.4054°
True anomaly	116.7247°
Mean anomaly	116.6377°
Eccentric anomaly	116.68121°
Mean motion	4.10809 °/min
BSTAR	0.00075248
Orbital period	87.63 mins