Soyuz 11A511L

11A511 with reinforced second stage, large fairing for earth orbit test of LK lunar lander.

Manufacturer: Korolev. Launches: 3. Success Rate: 100.00%. First Launch Date: 1970-11-24. Last Launch Date: 1971-08-12. Launch data is: complete. LEO Payload: 5,500 kg (12,100 lb). to: 200 km Orbit. at: 51.60 degrees. Apogee: 400 km (240 mi). Associated Spacecraft: LK. Liftoff Thrust: 4,054.000 kN (911,375 lbf). Total Mass: 300,000 kg (660,000 lb). Core Diameter: 2.95 m (9.67 ft). Total Length: 50.00 m (164.00 ft).

1970 November 24 - 05:15 GMT - Launch Site: Baikonur. Launch Complex: LC31. Launch Pad: LC31. Launch Vehicle: Soyuz 11A511L. Model: Soyuz 11A511L.

• Cosmos 379 Nation: USSR. Program: Lunar L3. Payload: Lunar Craft T2K no. 1. Mass: 5,500 kg (12,100 lb). Class: Manned. Type: Lunar lander. Spacecraft: LK. Agency: MOM. Perigee: 198 km (123 mi). Apogee: 232 km (144 mi). Inclination: 51.60 deg. Period: 88.70 min. COSPAR: 1970-099A. USAF Sat Cat: 4760. Duration: 4,683.78 days. Decay Date: 1983-09-21. LK moon lander test using the T2K version. First use of the Soyuz 11A511L booster modified especially for this purpose. The spacecraft made a series of engine burns, simulating the lunar landing profile. After 3.5 days in orbit, the first burn was made in imitation of a descent to the lunar surface after separation of the Block D lunar crasher stage. The orbit changed from 192 km X 233 km to 196 km X 1206 km orbit; delta V: 263 m/s. After 4 days in orbit, a large manoeuvre was made simulating the ascent from the lunar surface. The orbit was changed from 188 km X 1198 km to 177 km X 14,041 km; delta V: 1518 m/s. These main manoeuvres were followed by a series of small adjustments simulating rendezvous and docking with the LOK. The LK tested out without major problems and decayed from orbit on September 21, 1983.References: 1, 2, 6.

• Cosmos 398 Nation: USSR. Program: Lunar L3. Payload: Lunar Craft T2K no. 2. Mass: 5,500 kg (12,100 lb). Class: Manned. Type: Lunar lander. Spacecraft: LK. Agency: MOM. Perigee: 186 km (115 mi). Apogee: 1,958 km (1,216 mi). Inclination: 51.50 deg. Period: 106.70 min. COSPAR: 1971-016A. USAF Sat Cat: 4966. Duration: 8,463.78 days. Decay Date: 1995-12-10. Second space test of the LK moon lander test using the T2K version. Followed the same programme as Cosmos 379.
  Maneuver Summary:
  189km X 252km orbit to 186km X 1189km orbit. Delta V: 251 m/s
  186km X 1189km orbit to 200km X 10905km orbit. Delta V: 1320 m/s
  Total Delta V: 2832 m/s.
  Officially: Investigation of the upper atmosphere and outer space.References: 1, 2, 6.

• Cosmos 434 Nation: USSR. Program: Lunar L3. Payload: Lunar Craft T2K no. 3. Mass: 5,500 kg (12,100 lb). Class: Manned. Type: Lunar lander. Spacecraft: LK. Agency: MOM. Perigee: 193 km (119 mi). Apogee: 1,253 km (778 mi). Inclination: 51.60 deg. Period: 99.30 min. COSPAR: 1971-069A. USAF Sat Cat: 5407. Duration: 8,296.77 days. Decay Date: 1981-08-22. Final LK moon lander test using the T2K version.
  Maneuver Summary:
  188km X 267km orbit to 190km X 1261km orbit. Delta V: 266 m/s
  188km X 1262km orbit to 180km X 11384km orbit. Delta V: 1333 m/s
  Total Delta V: 1599 m/s. Ten years later the spacecraft was due to re-enter over Australia soon after the Skylab scare. The Soviet Union told the people of Australia not to worry, it was only an experimental lunar cabin - the first inadvertent admission that their manned lunar project even existed!References: 1, 2, 6.

• McDowell, Jonathan, Jonathan's Space Home Page, Harvard University, 1997-present. Jonathan McDowell's complete on-line listing of all objects orbited and over 20,000 rocket launches Accessed at: http://www.planet4589.org/jsr.html.

• Semenov, Yu. P., S P Korolev Space Corporation Energia, RKK Energia, 1994. ISBN: 1896522815. Dual English/Russian language picture book of the history of the Energia Corporation. Many unique photos and drawings of Korolev's rockets and spacecraft. Republished by Apogee books in 2000. More at amazon.com...