Kosmos 379
A standard LK
OperatorSoviet Union
COSPAR ID1970-099A Edit this at Wikidata
SATCAT no.04760Edit this on Wikidata
Mission duration12 years, 9 months and 27 days
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
RocketSoyuz-L
Launch siteBaikonur 31/6
End of mission
Decay date21 September 1983
Orbital parameters
Reference systemGeocentric
RegimeLow Earth
Eccentricity0.004161
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.

Mission

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]

Parameters

References

  1. ^ "Soyuz 11A511L". Archived from the original on December 27, 2016.