ORBWEAVER 2, 43785 (Decayed)

Orbit data source: Space-Track

ORBWEAVER 2, 43785 was a payload satellite owned by DARPA (US) in LEO that was launched on Mon, 03 Dec 2018 UTC via an FALCON 9 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

ORBWEAVER 2 details

Identifier	43785, 2018-099AD
Orbit	Decayed
Last TLE update	3 months ago
Origin	DARPA (US)
Manufacturer	Firmamentum
Mission	Decayed Defense Communications
Bus & Motor	CUBESAT 3U?, Unknown motor
Mass	5 kg wet, 5 kg dry
Launch date (UTC)	2018-12-03 (6 years ago)
Launch vehicle	FALCON 9
Launch site	Air Force Western Test Range (AFWTR)
Object type	Payload Rocket body Debris
Shape & HBR	Box, 0.3 m
Radar Cross Section	0.035 m², Medium (>0.1 m² and < 1m²)

Expand to show TLE details & history

TLE from 3 months ago

0 ORBWEAVER 2
1 43785U 18099AD  24280.13039146  .17149198  25641-5  21370-2 0  9995
2 43785  97.4710 354.8411 0013323 276.7056  83.2725 16.35879567320209

Epoch: 2024-10-06T03:07Z

Definitive object data (Epoch: 2024-10-06T03:07:45.822Z)

Latitude	0.00004°
Longitude	-67.3766°
Altitude	179.018 km
Speed	7.799 km/s
True Right ascension	23h 39m 21s
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	182.331 km
Perigee altitude	164.874 km
Semi-major axis	6,551.74 km
Eccentricity	0.0013323
Inclination	97.471°
RAAN	354.8411°
Arg. of periapsis	276.7056°
True anomaly	83.42415°
Mean anomaly	83.2725°
Eccentric anomaly	83.34832°
Mean motion	4.09268 °/min
BSTAR	0.002137
Orbital period	87.96 mins