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The information here is based on writings in 1991 and is dated but still generally correct
Developed in 1966, the F type booster "Cyclone or Tsyklon" is not well described by the Sheldon numbering system. Due to their nature, the satellites launched by theTsyklon influence the designation. The Tsyklon booster was based on the SS-9 missile. All Tsyklon were launched from Baykonur until 1977 when the F-2 varient was developed and new launch facilities were opened at Plesetsk. The first stage is 3 m diameter plus verniers. The payload shroud is 2.7 m diameter. The Tsyklon booster second stage used the RD-219 variable thrust engine with 90,000 kg. maximum thrust, which burned UDMH/nitrogen tetroxide. The second stages empty weight was 1500 kg.. For most flights the second stage was modified and made a part of the payload satellite. This was very similar to many U.S. military satellites which were built on the Lockheed Agena upper stage.
Launch conditions must be -40 to +50 degrees C, and less than 20 m/s winds. Maximum time needed after payoad integration for launch is 24 hours.
The SL-10 (F-1r) was first used to launch Fractional Orbital Bombardment System (FOBS) test flights, including the Sept., 1966, Kosmos U1 ("U" for unannounced launch) test. The booster could be used to deliver a bomb to any point on Earth by orbiting and then deorbiting the warhead. Suspected use of this feature would be a surprise attack on the United States coming over the South Pole, instead of the traditional and shorter sub-orbital ballistic path over the North pole.
The SL-11 (F-1m) version was used for RORSAT (Radar Ocean Reconnaissance) launches. The payload, which searches the oceans for U.S. Navy task forces and other shipping was built onto the Tsyklon upper stage. Ion thrusters mounted on the upper stage countered natural orbital decay for precise orbit control, and thus the "m", for maneuverable, designation. The RORSAT's nuclear power source was boosted to a higher orbit by a small solid rocket when the satellites mission was over.
The F-1s version was used for EORSAT (Electronic Ocean Reconnaissance) launches. The upper stage remained attached to the payload for the duration of the mission and fired small sustainer rockets to counter aerodynamic drag and keep the orbit a precise 93.3 minutes. The EORSAT was used to detect electronic counter measures (ECM) signals from U.S. Navy task forces and shipping which used the ECM to defeat the Soviet RORSAT's radar detection equipment.
The SL-14 (F-2) Tsyklon booster replaced the Soyuz type for launching many Elint, Meteor and other civilian satellites. Payload to low Earth orbit was 5500 kg. and thus too low to replace the Soyuz for launching 7000 kg. Soyuz or Progress flights. Payload to 90° inclination 200 km. orbit (± 25 km. altitude, ±12 sec. period, ±5 sec. inclination), was 3600 kg.. The F-2 was an F-1 booster with an additional third stage. The total height of the booster was 39.27 meters and the diameter was three meters. During flight testing at Baykonur, the F-2 was flown to 75.8° inclination orbits. The F-2 was also used to orbit reconnaissance satellites at 82.3° and 82.5° orbits. Since its first launch in 1977, the F-2 had failed only two out of 63 launches by 1987. By 1992, 93 of 97 launches were successful.
Johnson, Nicholas L. Soviet Military Strategy in Space. Janes, London, 1987, pp. 156
"The development of the booster-launhcers in the USSR", V.P. Mishin, IAF-92-0197, aug. 28, 1992
Clark, Phillip S. "Soviet Launch Vehicles: An Overview." Journal of the British Interplanetary Society, Vol. 35, No. 2, Feb., 1982, pp. 53
"Rocket Space Transportation Systems Produced by Yuzhnoye Rocket-Space Association", by YA Smetanin, IAF-92-0862, Aug, 28, 1992
"Soviets Step Up Efforts to Market Commercial Launch Services." Aviation Week & ST, March 21, 1988, pp. 30
"Rocket Space Transportation Systems Produced by Yuzhnoye Rocket-Space Association", by YA Smetanin, IAF-92-0862, Aug, 28, 1992
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