Kosmos 379


Kosmos 379
Soviet lunar lander drawing.svg
A standard LK
OperatorSoviet Union
COSPAR ID1970-099A
SATCAT no.04760Edit this on Wikidata
Spacecraft properties
Spacecraft typeT2K
Launch mass7,495 kilograms (16,524 lb)
Start of mission
Launch date24 November 1970, 11:00:00 (1970-11-24UTC11Z) UTC
Launch siteBaikonur 31/6
Orbital parameters
Reference systemGeocentric
RegimeLow Earth
Perigee altitude198 kilometres (123 mi)
Apogee altitude253 kilometres (157 mi)
Inclination51.6 degrees
Period88.7 m

Kosmos 379 (Russian: Космос 379 meaning "Cosmos 379") was an unmanned test of the LK (the Soviet counterpart of the Apollo Lunar Module) in Earth orbit.


Earth orbit simulated propulsion system operations of a nominal lunar landing mission. Kosmos 379 entered a 192 to 232 km low Earth orbit. After three days it fired its motor to simulate hover and touchdown on the moon, in imitation of a descent to the lunar surface after separation of the Blok D lunar crasher propulsion module. The engine firing changed its orbit from 192 km X 233 km to 196 km X 1206 km (delta-V = 263 m/s).

After a simulated stay on the Moon, it increased its speed by 1.518 km/s, simulating ascent to lunar orbit making the final apogee 14,035 km. These main maneuvers were followed by a series of small adjustments simulating rendezvous and docking with the Soyuz 7K-L3. The LK lander tested out without major problems and decayed from orbit on September 21, 1983.[1]


  • Spacecraft: T2K
  • Mass: 5500 kg
  • Crew: None
  • Launched: November 24, 1970
  • Landed: Reentered September 21, 1983
  • Orbit: 192 km


  1. ^ http://www.astronautix.com/s/soyuz11a511l.html

External links

  • Mir Hardware Heritage
    • Mir Hardware Heritage - NASA report (PDF format)
    • Mir Hardware Heritage (wikisource)