BUCCANEER RMM, 43014 (Decayed)

Orbit data source: Space-Track

BUCCANEER RMM, 43014 was an Australian payload satellite in LEO that was launched on Sat, 18 Nov 2017 UTC via a DELTA 7920-10C launch vehicle from the Air Force Western Test Range (AFWTR). 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

BUCCANEER RMM details

Identifier	43014, 2017-073B
Orbit	Decayed
Last TLE update	3 months ago
Origin	UNSWC/DSTO (AU / AUS)
Manufacturer	U. NSW
Mission	Decayed Amateur Technology
Bus & Motor	CUBESAT 3U, Unknown motor
Mass	4 kg wet, 4 kg dry
Launch date (UTC)	2017-11-18 (7 years ago)
Launch vehicle	DELTA 7920-10C
Launch site	Air Force Western Test Range (AFWTR)
Object type	Payload Rocket body Debris
Shape & HBR	Box + 2 Pan + 1 Ant, 3.2 m
Radar Cross Section	0.235 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 3 months ago

0 BUCCANEER RMM
1 43014U 17073B   24278.17140040  .19254492  26913-5  69830-3 0  9991
2 43014  97.5302 175.5823 0013399 193.6636 166.4304 16.42982460373739

Epoch: 2024-10-04T04:06Z

Definitive object data (Epoch: 2024-10-04T04:06:48.994Z)

Latitude	-0.00002°
Longitude	100.53227°
Altitude	169.648 km
Speed	7.799 km/s
True Right ascension	11h 42m 19s
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	163.444 km
Perigee altitude	145.937 km
Semi-major axis	6,532.827 km
Eccentricity	0.0013399
Inclination	97.5302°
RAAN	175.5823°
Arg. of periapsis	193.6636°
True anomaly	166.46637°
Mean anomaly	166.4304°
Eccentric anomaly	166.44839°
Mean motion	4.11047 °/min
BSTAR	0.0006983
Orbital period	87.58 mins