Soyuz 7K-L1E Credit - RKK Energia

Modification of Soyuz circumlunar configuration used in propulsion tests of the Block D stage. The L1E provided guidance to the Block D and was equipped with television cameras that viewed the behavior of the Block D stage propellants under zero-G conditions. Probably included a dummy descent module (not recovered).

Mass: 10,380 kg (22,880 lb). Main Engine: KTDU-53.

• 1969 November 28 - Soyuz 7K-L1E s/n 1 - first stage malfunction - Program: Luna. Launch Site: Baikonur. Launch Complex: LC81/23. Launch Vehicle: Proton. FAILURE: First stage malfunction. Mass: 10,380 kg (22,880 lb).
  Attempted test flight of Block D upper stage in N1 lunar crasher configuration. Payload was a modified Soyuz 7K-L1 circumlunar spacecraft, which provided guidance to the Block D and was equipped with television cameras that viewed the behavior of the Block D stage propellants under zero-G conditions. Mission flown successfully over a year later as Cosmos 382.

• 1970 December 2 - Cosmos 382 - Program: Lunar L3. Launch Site: Baikonur. Launch Complex: LC81/23. Launch Vehicle: Proton. Mass: 10,380 kg (22,880 lb). Perigee: 2,384 km (1,481 mi). Apogee: 5,269 km (3,273 mi). Inclination: 55.90 deg. Period: 171.00 min. Duration: 8,549.30 days.
  Test of Block D upper stage in its N1 lunar crasher configuration in earth orbit. The three maneuvers simulated the lunar orbit insertion burn; the lunar orbit circularization burn; and the descent burn to bring the LK lunar lander just over the surface. Payload was a modified Soyuz 7K-L1 circumlunar spacecraft, which provided guidance to the Block D and was equipped with television cameras that viewed the behavior of the Block D stage propellants under zero-G conditions.
  Maneuver Summary:
  190km X 300km orbit to 303km X 5038km orbit. Delta V: 982 m/s
  318km X 5040km orbit to 1616km X 5071km orbit. Delta V: 285 m/s
  1616km X 5071km orbit to 2577km X 5082km orbit. Delta V: 1311 m/s
  Total Delta V: 2578 m/s.