Russia Space Transportation |
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| Russian / CIS Name | Designation | Chronology | Payload ,000 kg | ||||
| DOD |
Sheldon | First flight |
Last flight |
LEO | MEO | GEO | |
| Sputnik | SL-1 | A | 1957 | 1957 | 0.5 | ||
| Sputnik 3 | SL-2 | A | 1958 | 1958 | 1.3 | ||
| Vostok | SL-3 | A-1 | 1960 | 1963 | 1.8 | ||
| Soyuz | SL-4 | A-2 | 1963 | 1976 | 7.0 | ||
| Polet | SL-5 | ASAT | 1963 | 1966 | 1.4 | ||
| Molniya | SL-6 | A-2-e | 1961 | 2010 | 2.0 | ||
| Kosmos | SL-7 | B-1 | 1964 | 1994 | 1.4 | ||
| Kosmos 3M | SL-8 | C-1 | 1966 | 2010 | 1.5 | ||
| Tsyklon | SL-10 | F-1r FOBS | 1965 | 1971 | 4.0 | ||
| Tsyklon | SL-11 | F-1 | 1967 | 2006 | 3.2 | ||
| Proton-K | SL-12 | D-1-e | 1967 | 2008 | 19.8 | 4.9 | 2.1 |
| Proton | SL-13 | D-1 | 1965 | 1966 | 12.2 | ||
| Tsyklon-3 | SL-14 | F-2 | 1977 | 2009 | 4.1 | ||
| N-1 | SL-15 | G-1 | 1969 | 1972 | 150.0 | ||
| UR-700 | none | none | none | none | 150.0 | ||
| R-56 | none | none | none | none | 40.0 | ||
| Zenit | SL-16 | J-1 | 1985 | 2001 | 13.8 | ||
| Energia | SL-17 | K-1 | 1988 | 1988 | 105 | ||
| Buran | SL-17 | K-1 | 1988 | 1988 | 30 | ||
| Start-1 | SL-18 | - | 1997 | 2006 | 0.6 | ||
| Rokot | SL-19 | - | 1994 | 1.9 | |||
| Start | SL-20 | - | 1993 | 1995 | 1.3 | ||
| Volna | N/A | - | 1975 | 0.1 | |||
| Shtil | SL-21 | - | 1983 | 0.9 | |||
| MiG-31S / Ishim | N/A | N/A | N/A | N/A | . | . | . |
| Soyuz-Ikar | SL-22 | - | 1999 | 1999 | 4.1 | ||
| Zenit-3SL | SL-23 | - | 1999 | 2013 | 5.0 | 6.1 | 2.3 |
| Dnepr-1 | SL-24 | - | 1999 | 2008 | 3.2 | ||
| Proton-M (Briz) | SL-25 | - | 2001 | 23.0 | 6.3 | 3.4. | |
| Soyuz-Fregat | SL-26 | - | 2000 | 7.2 | |||
| Strela | SL-27 | - | 2003 | 1.5 | |||
| Soyuz 2-ST | SL-28 ? | - | 2008 | 8.5 | 3.0 | ||
| Soyuz 2-1V | SL-29 ? | - | 2013 | 2.8 | |||
| Angara 1.2 | SL-30 ? | - | 2014 | 3.7 | |||
| Angara A5 | SL-31 ? | - | 2014 | 25.0 | 6.6 | 4.0 | |
| RUS-M, [PTK NP] | N/A | N/A | N/A | N/A | . | . | . |
| Taymyr | tbd | tbd | 2020 | 0.2 | . | . | |
| Sea Launch | tbd | tbd | 2022 | . | . | . | |
| Soyuz-5 / Phoenix | - | - | 2022 | 23.0 | |||
| Energia-5 | - | - | 2025 | 105.0 | 43.3 | 20.5 | |
| Amur LNG | tbd | tbd | 2026 | tbd | . | . | . |
| Angara A5V | - | - | 2027 | 37.5 | 13.0 | 8.0 | |
| Soyuz-5.3 / Phoenix | - | - | 2027 | 75.0 | 55.0 | ||
| KosmoKurs | tbd | tbd | tbd | tbd | 10.5 | . | . |
| KORONA | tbd | tbd | tbd | tbd | 7.0 | 12.0 | . |
| Yenisei | tbd | tbd | 2035 | tbd | 125.0 | . | . |
????-5 Soyuz-5, also named Irtysh, was formerly codenamed Fenix in Russian and Sunkar in Kazakh. Soyuz-5 was developed to ensure launches of automatic spacecraft into sun-synchronous, highly elliptical, geostationary and geostationary orbits, including using an upper stage, as well as launches of manned transport spacecraft. The Soyuz-5 launch vehicle is a two-stage, tandem-stage rocket. The diameter of the blocks is 4.1 meters. The RD171MV liquid rocket engine developed by JSC NPO Energomash is used as the first stage cruise engine. The RD0124MS liquid rocket engine developed by JSC KBKhA is used as the second stage cruise engine. The engines operate on a liquid oxygen + naphthyl fuel pair. An aluminum alloy with improved mechanical properties is used to manufacture the launch vehicle's fuel tanks. Automatic friction stir welding is used in the production of the launch vehicle's body elements. To reduce the weight and dimensions of the second stage block, the design uses a combined bottom of the oxidizer and fuel tanks, as well as an interstage compartment made of composite materials. For launches of the Soyuz-5 LV, which is capable of delivering up to 17 tons of payload to a low reference orbit, it is planned to use the ground-based space infrastructure of the Baiterek space complex at the Baikonur Cosmodrome, which is being created on the basis of the Zenit-M space complex, which provided launches of spacecraft of various purposes using the Zenit-3SLB launch vehicle. The use of an emergency engine protection system (EES) in the LV ensures the safety of the LV on the SC during engine start-up, as well as the implementation of the mission even in the event of failure of one of the second-stage engine blocks. Preparation of the Soyuz-5 LV on the SC is provided in a fully automatic mode. The launch vehicle can be used with a GC consisting of: – SZB with a diameter of 5.2 meters and a Fregat type RB or without RB; – SZB with a diameter of 4.11 meters and a Fregat-type RB or without a RB. The capabilities of the Soyuz-5 launch vehicle in a configuration with the Fregat upper stage make it possible to perform targeted launches of both the main payload and cluster launches of payloads with small spacecraft (as a secondary payload), as well as group launches of two spacecraft with similar mass and size characteristics." Number of steps
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