| Kosmos 379 | |
| Mission Type: | Spacecraft test |
| Operator: | Soviet space program |
| Cospar Id: | 1970-099A |
| Satcat: | 4760 |
| Spacecraft Type: | T2K No.1 |
| Manufacturer: | OKB-1 |
| Launch Mass: | 7495kg (16,524lb) |
| Launch Date: | UTC |
| Launch Site: | Baikonur 31/6 |
| Decay Date: | 21 September 1983 |
| Orbit Reference: | Geocentric |
| Orbit Regime: | Low Earth |
| Orbit Periapsis: | 198km (123miles) |
| Orbit Apoapsis: | 253km (157miles) |
| Orbit Inclination: | 51.6 degrees |
| Orbit Eccentricity: | 0.004161 |
| Orbit Period: | 88.7 min |
| Apsis: | gee |
| Programme: | LK (spacecraft) |
| Next Mission: | T2K No.2 |
| Programme2: | Kosmos (satellites) |
| Previous Mission2: | Kosmos 378 |
| Next Mission2: | Kosmos 380 |
Kosmos 379 (ru|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.
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 × 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.