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Soyuz 7K-L1E

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Soyuz 7K-L1E Credit: RKK Energia

AKA: 7K-L1E. Status: Operational 1969. First Launch: 1969-11-28. Last Launch: 1970-12-02. Number: 2 . Gross mass: 10,380 kg (22,880 lb).

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).

Photo Gallery

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Zond Credit: Manufacturer Image

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• Mishin's lunar plans - . Related Persons: Mishin. Spacecraft: Soyuz 7K-L1E, LK, LKR, , Luna Ye-8. Mishin notes that: 1. T1K, T2K, L1E are essential. 2. One more time reviewed the scheme for a lunar expedition of LK + LK-R + Ye-8. (Mishin Diaries 2-158).

• Soyuz 7K-L1E s/n 1 - first stage malfunction - . Payload: Soyuz 7K-L1E s/n 1. Mass: 10,380 kg (22,880 lb). Nation: Russia. Agency: RVSN. Program: Luna. Class: Moon. Type: Manned lunar spacecraft. Spacecraft Bus: Block D. Spacecraft: Soyuz 7K-L1E. Decay Date: 1969-11-16 .

  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.

• Cosmos 382 - . Payload: Soyuz 7K-L1E s/n 2K. Mass: 10,380 kg (22,880 lb). Nation: Russia. Agency: MOM. Program: Lunar L3. Class: Manned. Type: Manned spacecraft. Spacecraft Bus: Block D. Spacecraft: Soyuz 7K-L1E. Duration: 8,549.30 days. USAF Sat Cat: 4786 . COSPAR: 1970-103A. Apogee: 5,269 km (3,273 mi). Perigee: 2,384 km (1,481 mi). Inclination: 55.90 deg. Period: 171.00 min.

  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.