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Kosmos Launch Vehicle "C"

THE FLEXABLE INTERMEDIATE LAUNCH VEHICLE (“C”)

Interkosmos/Kosmos-3M Series SL-8

Overview, Supporting Facilities and Launch Vehicles of the

Soviet Space Program *

C-1 Post 1988

Until 1993 the smallest Russian launch vehicle in use was the Kosmos-3M booster, derived from the R-14 (NATO designator SS-5) medium range ballistic missile. Originally designed by the Yangel Design Bureau in Ukraine (now the Yuzhnoye [Southern] Design Bureau) and the Prikladnoi Mekhaniki (Applied Mechanics) Scientific Production Association in Russia, the Kosmos-3M has been manufactured by the Polet (Flight) Design Bureau for nearly 30 years. Eleven Kosmos-3M launches were conducted during 1993-1994, and all were successful.

The two-stage booster burns UDMH as a fuel and either nitric acid or N204 as the oxidizer. The first stage employs two 11 D614 (RD216) main engines, while the second stage relies on a single, restart able 11D49 main engine. The second stage also carries an independent propulsion system for coast and spacecraft deployment operations. Used only for LEO missions, the Kosmos-3M has a demonstrated payload capacity of 1,500 kg to a low altitude, 51 degree-inclination parking orbit. However, since 1988 all Kosmos-3M missions have originated from the Plesetsk Cosmodrome (Complexes 132 left and right and 133) with inclinations of 66 degrees or more. The first commercial use of Kosmos-3M was scheduled for early 1995 when small American and Swedish spacecraft were to accompany a Russian navigation satellite into orbit. An improved model of the launch vehicle, the Kosmos-3MU (aka Vzlet), may begin operations by 1998 with a LEO payload capacity of 1.8 metric tons (References 202-205).

Kosmos

Background Information First Launch: 1964 Flight Rate: 28 per year (maximum recorded launch rate) Launch Site: Plesetsk and *Kapustin Yar, Russia; *Baikonur, Kazakhstan Capability: 3,000 lb to LEO History Originated in 1950s as the SS-5 ballistic missile Developed into a launch vehicle by NPO Yuzhnoye (Ukraine) First used in 1964 for multiple launch of small satellites Production transferred to NPO Polyot in Omsk, Russia More than 430 produced since 1964 Description Two-stage liquid-fueled vehicle Stage 1 has two RD-216 booster engines burning N2O4/UDMH propellant fed from stage 1 tanks, generating a total of 387,500 lb of thrust Stage 2 has restart capability for orbit circularization Profile Length: 105 ft Launch Weight: 264,000 lb Diameter 7.9 ft Liftoff Thrust: 387,500 lb Payload Fairing: 15.5 ft x 7.2 ft