Kosmos 379

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Kosmos 379
Soviet lunar lander drawing.svg
LK lander
Mission typeSpacecraft test
OperatorSoviet space program
COSPAR ID 1970-099A OOjs UI icon edit-ltr-progressive.svg
SATCAT no. 4760
Mission duration12 years, 9 months and 28 days
Spacecraft properties
Spacecraft type T2K No.1
Manufacturer OKB-1
Launch mass7,495 kilograms (16,524 lb)
Start of mission
Launch date24 November 1970, 11:00:00 (1970-11-24UTC11Z) UTC
Rocket Soyuz-L
Launch site Baikonur 31/6
End of mission
Decay date21 September 1983
Orbital parameters
Reference system Geocentric
Regime Low Earth
Eccentricity 0.004161
Perigee altitude 198 kilometres (123 mi)
Apogee altitude 253 kilometres (157 mi)
Inclination 51.6 degrees
Period 88.7 min
T2K No.2  

Kosmos 379 ( ‹See Tfd› Russian : Космос 379 meaning "Cosmos 379"), also known as T2K No.1, was an uncrewed test of the LK (the Soviet counterpart of the Apollo Lunar Module) in Earth orbit.

Contents

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[ clarification needed ] propulsion module. The engine firing changed its orbit from 192 km × 233 km to 196 km × 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]

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References

  1. Mark Wade. "Soyuz 11A511L". Encyclopedia Astronautica. Retrieved 27 December 2016.