LK lander | |
| Mission type | Spacecraft test |
|---|---|
| Operator | Soviet space program |
| COSPAR ID | 1970-099A |
| SATCATno. | 4760 |
| Mission duration | 12 years, 9 months and 28 days |
| Spacecraft properties | |
| Spacecraft type | T2K No.1 |
| Manufacturer | OKB-1 |
| Launch mass | 7,495 kilograms (16,524 lb) |
| Start of mission | |
| Launch date | 24 November 1970, 11:00:00 (1970-11-24UTC11Z) UTC |
| Rocket | Soyuz-L |
| Launch site | Baikonur31/6 |
| End of mission | |
| Decay date | 21 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 (Russian:Космос 379 meaning "Cosmos 379"), also known asT2K No.1, was an uncrewed test of theLK (the Soviet counterpart of theApollo Lunar Module) in Earth orbit.
Earth orbit simulated propulsion system operations of a nominallunar landing mission. Kosmos 379 entered a 192 to 232 km lowEarth 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 theBlok 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 theSoyuz 7K-L3. The LK lander tested out without major problems and decayed from orbit on September 21, 1983.[1]
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