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Tsyklon

The Tsyklon family of launch vehicles is derived from Yuzhnoye's R-36 (NATO designator SS-9) ICBM and is used in two primary configurations. The two-stage Tsyklon 2 launch vehicle has been launched exclusively from the Baikonur Cosmodrome from Complex 90 left and right for high-value military missions: the co-orbital ASAT, RORSAT, EORSAT, and FOBS (Fractional Orbit Bombardment System). Only the EORSAT program is still operational; thus, the launch rate of the Tsyklon-2 is now only a few per year. Both stages employ hypergolic propellants, the first stage powered by three 11D69 (RD-218) engines and the second stage by one 11D26 (RD-219) engine.

The Tsyklon-3 launch vehicle appeared more than a decade after the Tsyklon-2 for use in both civilian and military space programs. The Tsyklon-3 is launched only from the Plesetsk Cosmodrome from Complex 32 left and right. The restartable third stage of the Tsyklon-3 is powered by the Ukrainian 11 D25(RD-861) which also uses UDMH and N204. A total of 11 Tsyklon-3 launch vehicles were flown during 1993-1994 with one failure occurring on 25 May 1994. The cause of that failure was determined to be a short circuit which prevented a successful separation of the second and third stages. Like its Baikonur cousin, the Tsyklon-3 can be transported to the launch pad, erected, fueled, and launched - all automatically and within only a few hours (References 440-444).

Tsyklon

Background Information First Launch: September 1966 Flight Rate: 15 per year (maximum recorded launch rate) Launch Site: Plesetsk, Russia; Baikonur, Kazakhstan Capability: 7,900 lb to LEO History Originated in 1960s as the SS-9 ballistic missile Developed into a launch vehicle by NPO Yuzhnoye (Ukraine) Originally used for launching electronic ocean reconnaissance satellites Features automated propellant loading and launch processing Third stage introduced in 1977 Description Three-stage liquid-fueled vehicle Stage 1 has one RD-218 booster engine (one turbopump with six separate combustion chambers) burning N2O4/UDMH fed from stage 1 tanks, generating a total of 617,000 lb of thrust Stage 2 has one RD-219 engine burning N2O4/UDMH, generating 223,000 lb of thrust Stage 3 burns N2O4/UDMH, generating 17,500 lb of thrust Profile Length: 128.8 ft Launch Weight: 397,000 lb Diameter 9.2 ft Liftoff Thrust: 617,000 lb Payload Fairing: 19.4 ft x 8.9 ft

• 440. Specifications on Application of the Tsyklon Carrier Rocket, GLAVKOSMOS, 1987.
• 441. S. Sergeyev, Aviatsiya I Kosmosnavtika, March-April 1994, pp. 38-41.
• 442. K. Lantratov, Novosti Kosmonavtiki, 15-28 January 1994, pp.31-34.
• 443. Cyclone, technical brochure distributed by Yuzhnoye Design Bureau, undated.
• 444. Novosti Kosmonavtiki, 22 October - 4 November 1994, pp.52-53.

Sources and Resources

• Adapted from: Europe and Asia in Space 1993-1994, Nicholas Johnson and David Rodvold [Kaman Sciences / Air Force Phillips Laboratory]

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