RESURS P1, 39186 (Decayed)

Orbit data source: Space-Track

RESURS P1, 39186 was a Commonwealth of Independent States-origin payload satellite in LEO that was launched on Tue, 25 Jun 2013 UTC via a SOYUZ-2-1B launch vehicle from the Tyuratam Missile And Space Complex (TTMTR). 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

RESURS P1 details

Identifier	39186, 2013-030A
Orbit	Decayed
Last TLE update	1 month ago
Origin	TSSKBP? (CIS)
Manufacturer	TSSKBP?
Mission	Decayed Civil Imaging
Bus & Motor	RESURS P, Unknown motor
Mass	5,691 kg wet, ~5,600 kg dry
Launch date (UTC)	2013-06-25 (11 years ago)
Launch vehicle	SOYUZ-2-1B
Launch site	Tyuratam Missile And Space Complex (TTMTR)
Object type	Payload Rocket body Debris
Shape & HBR	Cyl + 2 Pan, 13 m
Radar Cross Section	27.080 m², Large (>1 m²)

Expand to show TLE details & history

TLE from 1 month ago

0 RESURS P1
1 39186U 13030A   24322.87932346  .19438957  23624-5  15676-3 0  9995
2 39186  96.9560  16.4419 0007950 262.9077 216.9341 16.52387254639808

Epoch: 2024-11-17T21:06Z

Definitive object data (Epoch: 2024-11-17T21:06:13.546Z)

Latitude	59.59066°
Longitude	-165.59906°
Altitude	147.405 km
Speed	7.821 km/s
True Right ascension	13h 53m 28s
True Declination	59° 25' 34"
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	135.003 km
Perigee altitude	124.655 km
Semi-major axis	6,507.966 km
Eccentricity	0.000795
Inclination	96.956°
RAAN	16.4419°
Arg. of periapsis	262.9077°
True anomaly	216.8794°
Mean anomaly	216.9341°
Eccentric anomaly	216.90675°
Mean motion	4.13405 °/min
BSTAR	0.00015676
Orbital period	87.08 mins