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Soyuz Launch Vehicle

The most active Russian launch vehicle during 1993-1994 was the Soyuz-U2 (including the Soyuz U2 variant). Deri, Korolev's original R-7 ICBM (ISS-6) and the subsequent Sputnik, Luna, Vostok, and Voskhod launch vehicles, the first in 1966 and has since been flown approximately 750 times in various configurations with a reliability of more than 97%. The two-and-one-half-stage launch vehicle burns simple liquid oxygen and a form of kerosene. The first stage consists of a core vehicle powered by a 11D512 (RD-108) main engine and four strap-on boosters with 11D511(RD-107) main engines. The second stage carries a single, 4-nozzle 11D55 (RD-0110) main engine. The Soyuz- U/U2 launcher currently has a LEO payload capacity of approximately 7,300 kg for 52 degree inclination orbits. The Soyuz-U2 upgrade was introduced in 1986 to support the Soyuz-TM spacecraft and has also been used for Progress-M spacecraft and the sixth generation photographic reconnaissance satellites.

Two Soyuz-U launch pads are operational at the Baikonur Cosmodrome (Complexes 1 and 31) and three are available at the Plesetsk Cosmodrome (Complexes 16 and 43 left and right). All Soyuz-U/U2 launch vehicles are produced by the Samara Central Specialized Design Bureau and Progress Plant with engines designed by the Energomash Scientific Production Association. Of the 32 missions flown during 1993-1994 only one failed. A malfunction in the second stage of the 27 April 1993 flight led to the loss of its photographic reconnaissance payload (References 245-246).

In 1991 work began on a major Soyuz improvement program. Now known as Rus, the modernized launch vehicle will have an increased payload capacity (up to 8,000 kg for a 52 degree orbit) with a new flight control system, enlarged payload fairings, and modified main engines. Operations are expected to begin at the Plesetsk Cosmodrome in 1997. Test firings of a new Rus main engine were already underway in 1994 (References 247-253).

Soyuz

Copyright © Charles P. Vick

Background Information First Launch: November 1963 Flight Rate: 45 per year (maximum recorded launch rate) Launch Site: Plesetsk, Russia; Baikonur, Kazakhstan Capability: 15,400 lb to LEO History Developed from the Vostok Launch Vehicle originally derived from the SS-6 ICBM Incorporates upgraded second stage and avionics Used to launch every former Soviet Union piloted spacecraft since 1964 Also used to launch photo reconnaissance satellites, earth resource satellites, and progress resupply missions to the Mir space station Description Two-stage liquid fueled vehicle Stage 1 core has one RD-108 booster engine (one turbopump with four separate combustion chambers) burning LO2/kerosene fed from stage 1 tanks, generating 167,000 lb of thrust Stage 1 strap-ons each have one RD-107 engine (one turbopump with four separate combustion chambers) burning LO2/kerosene fed from stage 1 tank, generating a total of 740,000 lb of thrust Stage 2 has one RD-461 engine burning LO2/kerosene, generating 67,000 lb of thrust Profile Length: 162 ft Launch Weight: 639,000 lb Diameter 8.9 ft Liftoff Thrust: 907,000 lb Payload Fairing: 29.5 ft x 9.4 ft

• 245. Specifications on Application of the Soyuz Carrier Rocket , GLAVKOSMOS, Moscow, 1987.
• 246. Novosti Kosmonavtiki, 12-25 February 1994, p. 30.
• 247. B. Konovalov, Izvestlya, 24 March 1993, p. 5.
• 248. Krasnaya Zvezda, 27 March 1993.
• 249. Interfax News Agency, 14 October 1993 and 8 December 1994.
• 250. ITAR-TASS News Agency, 2 October 1994 and 12 March 1995.
• 251. "Rus Rocket to Replace Soyuz Booster Family", Space News, 10-16 May 1993, p.9.
• 252. P.B. de Selding, "Proton, Soyuz Upgrades Lead Other Priorities~, Space News, 6-12 December 1993, p.10.
• 253. V.V. Vakhnichenko and M.V. Sinelshchikov, "Russian Launch Vehicles' State-of-the-Art and Lines of their Improvement", Proceedings of the European Forum on Space Transportation Systems, ESA SP-362, March 1994, pp. 33-36.

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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