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Baikonur LC110L

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First Launch: 1971-06-26. Last Launch: 1988-11-15. Number: 3 . Longitude: 63.30 deg. Latitude: 45.96 deg.

• Design work starts on N1 launch complex. - . Nation: Russia. Program: Lunar L3.

• Construction begins of N1 launch complex - . Nation: Russia. Program: Lunar L3.

• Construction start of N1 launch complex 110 east - . Nation: Russia. Program: Lunar L3.

• Construction starts on N1 launch pad 110 west. - . Nation: Russia. Program: Lunar L3.

• N-1 mockup 1M1 rolled out to launch pad - . Nation: Russia. Program: Lunar L3. Stays on pad until 12 December for facilities checks. Photographed by US reconnsat on 11 December. 1M1 mockup scrapped in 1975..

• N1 launch pad 110 west completed - . Nation: Russia. Program: Lunar L3.

• N1 on launch pad 110 west. - . Nation: Russia. Program: Lunar L3. This was the first new launch vehicle erection activity detected by US reconnsats after the destruction of pad 110 east in the July launch failure. The all-white launch vehicle, with no payload, is believed to be either N1 mockup 1M1 or flight vehicle 6L..

• N1 erected on launch pad 110 west. - . Nation: Russia. Program: Lunar L3. US reconnsat detects N1 being installed on the pad. It remained there, without payload, at least through 4 June..

• N1 6L - . Payload: Soyuz 7K-LOK / LK Mockups. Mass: 9,850 kg (21,710 lb). Nation: Russia. Agency: RVSN. Program: Lunar L3. Class: Manned. Type: Manned spacecraft. Spacecraft Bus: Soyuz. Spacecraft: Soyuz 7K-LOK. Decay Date: 1971-07-21 . Apogee: 1.00 km (0.60 mi).

  Superbooster failure of N1 serial number 6L. This was a substantially improved vehicle, incorporating filters in the propellant lines to prevent any foreign objects from getting into the pumps. The shape of the tail of the booster was modified, and ventilation and refrigeration systems were added to keep the engine compartment cool. It was painted white overall to reduce temperatures while sitting on the pad. After liftoff and ascent, an axial rotation was introduced by gas dynamics interactions of the thirty engines with the air slipstream. The launch vehicle developed a roll beyond the capability of the control system to compensate. and began to break up as it went through Max Q. Control was lost at 50.2 seconds into the flight and it was destroyed by range safety a second later. The engines functioned well and did not shut down up to the point of vehicle destruction. No functional payload was carried. It has been stated that this launch did not have a working launch escape system. Additional Details: here....

• N1 7L - . Payload: Soyuz 7K-LOK / LK Mockups. Mass: 9,850 kg (21,710 lb). Nation: Russia. Agency: RVSN. Program: Lunar L3. Class: Manned. Type: Manned spacecraft. Spacecraft Bus: Soyuz. Spacecraft: Soyuz 7K-LOK. Decay Date: 1972-11-23 . Apogee: 40 km (24 mi).

  Unmanned test of manned lunar mission launch vehicle serial number 7L. This article incorporated significant changes to the previous model, including roll 'steering' engines to prevent the loss of control that destroyed 6L. The rocket ascended into the sky, and the engines ran 106.93 seconds, only seven seconds before completion of first stage burnout. Programmed shutdown of some engines to prevent overstressing of the structure led to propellant line hammering, rupture of propellant lines, and an explosion of engine number 4. The vehicle disintegrated. Additional Details: here....

• Buran - . Payload: Buran OK-1K s/n 711. Mass: 79,400 kg (175,000 lb). Nation: Russia. Agency: MOM. Program: Buran. Class: Manned. Type: Manned spaceplane. Spacecraft: Buran. Duration: 0.14 days. Decay Date: 1988-11-15 . USAF Sat Cat: 19637 . COSPAR: 1988-100A. Apogee: 256 km (159 mi). Perigee: 247 km (153 mi). Inclination: 51.60 deg. Period: 89.50 min.

  Unmanned test of Soviet shuttle. Landed November 15, 1988 06:25 GMT. Buran was first moved to the launch pad on 23 October 1988. The launch commission met on 26 October 1988 and set 29 October 06:23 Moscow time for the first flight of the first Buran orbiter (Flight 1K1). 51 seconds before the launch, when control of the countdown switched to automated systems, a software problem led the computer program to abort the lift-off. The problem was found to be due to late separation of a gyro update umbilical. The software problem was rectified and the next attempt was set for 15 November at 06:00 (03:00 GMT). Came the morning, the weather was snow flurries with 20 m/s winds. Launch abort criteria were 15 m/s. The launch director decided to press ahead anyway. After 12 years of development everything went perfectly. Buran, with a mass of 79.4 tonnes, separated from the Block Ts core and entered a temporary orbit with a perigee of -11.2 km and apogee of 154.2 km. At apogee Burn executed a 66.6 m/s manoeuvre and entered a 251 km x 263 km orbit of the earth. In the payload bay was the 7150 kg module 37KB s/n 37071. 140 minutes into the flight retrofire was accomplished with a total delta-v of 175 m/s. 206 minutes after launch, accompanied by Igor Volk in a MiG-25 chase plane, Buran touched down at 260 km/hr in a 17 m/s crosswind at the Jubilee runway, with a 1620 m landing rollout. The completely automatic launch, orbital manoeuvre, deorbit, and precision landing of an airliner-sized spaceplane on its very first flight was an unprecedented accomplishment of which the Soviets were justifiably proud. It completely vindicated the years of exhaustive ground and flight test that had debugged the systems before they flew.

• 37KB module s/n 37070 - . Payload: 37KB s/n 37070. Mass: 7,150 kg (15,760 lb). Nation: Russia. Agency: UNKS. Program: Buran. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: 37K. Spacecraft: 37KB. COSPAR: 1988-100xx.