Soyuz LV - Credit: © Mark Wade. 1,483 bytes. 71 x 353 pixels.

Rus project was to result in first major propulsion upgrade to R-7 family in forty years, using first stage engines derived from those developed for Zenit second stage to boost performance. It would have permitted launches from Plesetsk with same or greater payload than launch of standard Soyuz-U from Baikonur, permitting move of more launch operations back onto Russian territory. Instead the more modest Soyuz ST / Soyuz FG upgrades were made.

LEO Payload: 7,900 kg. to: 200 km Orbit. Payload: 2,900 kg. to a: Geosynchronous transfer trajectory. Liftoff Thrust: 441,980 kgf. Total Mass: 309,180 kg. Core Diameter: 3.0 m. Total Length: 45.0 m. Flyaway Unit Cost $: 3.00 million. in 1985 unit dollars.

• Stage Number: 0. 4 x Soyuz M-0 Gross Mass: 42,200 kg. Empty Mass: 3,000 kg. Thrust (vac): 89,000 kgf. Isp: 336 sec. Burn time: 145 sec. Isp(sl): 298 sec. Diameter: 2.7 m. Span: 2.7 m. Length: 20.0 m. Propellants: Lox/Kerosene No Engines: 1. RD-120K

• Stage Number: 1. 1 x Soyuz M-1 Gross Mass: 100,500 kg. Empty Mass: 6,000 kg. Thrust (vac): 89,000 kgf. Isp: 336 sec. Burn time: 310 sec. Isp(sl): 298 sec. Diameter: 3.0 m. Span: 3.0 m. Length: 28.0 m. Propellants: Lox/Kerosene No Engines: 1. RD-120K

• Stage Number: 2. 1 x Soyuz 11A511U-2 Gross Mass: 25,200 kg. Empty Mass: 2,355 kg. Thrust (vac): 30,400 kgf. Isp: 330 sec. Burn time: 250 sec. Diameter: 2.7 m. Span: 2.7 m. Length: 6.7 m. Propellants: Lox/Kerosene No Engines: 1. RD-0110

• Stage Number: 3. 1 x Soyuz M-3 Gross Mass: 5,000 kg. Empty Mass: 1,000 kg. Thrust (vac): 2,040 kgf. Isp: 360 sec. Burn time: 700 sec. Isp(sl): 0 sec. Diameter: 2.4 m. Span: 2.4 m. Length: 2.7 m. Propellants: Lox/Kerosene No Engines: 1. RD-161

• 89 - Semenov, Yu. P., S P Korolev Space Corporation Energia, RKK Energia, 1994.
• 138 - Vick, Charles P, Spaceflight, "KB Photon Releases 'Rus' Modified Soyuz-TM Booster Details", 1993, Volume 35, page 370.