ORBWEAVER 1, 43795 (Decayed)

Orbit data source: Space-Track

ORBWEAVER 1, 43795 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 1 details

Identifier	43795, 2018-099AP
Orbit	Decayed
Last TLE update	4 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 4 months ago

0 ORBWEAVER 1
1 43795U 18099AP  24253.91519606  .18606942  26314-5  63178-3 0  9993
2 43795  97.5002 332.3956 0018050 271.0475  88.8757 16.42652602316810

Epoch: 2024-09-09T21:57Z

Definitive object data (Epoch: 2024-09-09T21:57:52.939Z)

Latitude	-0.00008°
Longitude	13.4872°
Altitude	161.797 km
Speed	7.809 km/s
True Right ascension	22h 09m 34s
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	167.358 km
Perigee altitude	143.771 km
Semi-major axis	6,533.701 km
Eccentricity	0.001805
Inclination	97.5002°
RAAN	332.3956°
Arg. of periapsis	271.0475°
True anomaly	89.08251°
Mean anomaly	88.8757°
Eccentric anomaly	88.9791°
Mean motion	4.10964 °/min
BSTAR	0.00063178
Orbital period	87.6 mins