Voskhod rocket
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| Voskhod 11A57 | ||
|---|---|---|
|
| ||
| Stages | 3 | |
| 0 - Strap-on Boosters | Engines | 4 x RD-107-8D74K |
| Thrust | 4 x 101,500 kgf (995 kN) = 406,000 kgf (3.98 MN) | |
| Burn time | 119 seconds | |
| Fuels | Lox/Kerosene | |
| 1 - Core Stage | Engines | 1 x RD-108-8D75K |
| Thrust | 941.4 kN | |
| Burn time | 301 seconds | |
| Fuels | Lox/Kerosene | |
| 2 - Final Stage | Engine | 1 x RD-0108 |
| Thrust | 294.2 kN | |
| Burn time | 240 seconds | |
| Fuels | Lox/Kerosene | |
| Launch Vehicle | 1st Launch November 16, 1963 | |
| Payload LEO 65-deg | 5,900 kg | |
| Payload Lunar probe | 600 kg | |
The Voskhod rocket (Russian: Восход, translated as "Sunrise") was a derivative of the Soviet R-7 ICBM designed for the human spaceflight programme but later used for launching Zenit reconnaissance satellites. It combined the R-7 with an upper stage that had been originally designed to launch interplanetary probes.
There was only one main variant of the Voskhod, designated 11A57. Between 1963 and 1976 it was used for some 300 launches.
Voskhod 11A57
- Stage Number: 0 - Strap-on boosters; 4 x Voskhod 11A57-0
- *Gross Mass: 43,400 kg
- *Empty Mass: 3,800 kg.
- *Thrust (vac): 4 x 995.4 kN = 3,981.5 kN
- *Isp: 314 s (3.08 kN·s/kg)
- *Burn time: 119 s
- *Isp(sl): 257 s (2.52 kN·s/kg)
- *Diameter: 2.68 m
- *Span: 8 m
- *Length: 19.00 m
- *Propellants: Lox/Kerosene
- *Engines: 4 x RD-107-8D74K
- Stage Number: 1 - Core stage; 1 x Voskhod 11A57-1
- *Gross Mass: 100,500 kg
- *Empty Mass: 6,800 kg
- *Thrust (vac): 941.4 kN
- *Isp: 315 s (3.09 kN·s/kg)
- *Burn time: 301 s
- *Isp(sl): 248 s (2.43 kN·s/kg)
- *Diameter: 2.99 m
- *Span: 2.60 m
- *Length: 28.00 m
- *Propellants: Lox/Kerosene
- *Engine: 1 x RD-108-8D75K
- Stage Number: 2 - Final Stage; 1 x Voskhod 11A57-2
- *Gross Mass: 24,300 kg
- *Empty Mass: 2,000 kg
- *Thrust (vac): 294.2 kN
- *Isp: 330 s (3.24 kN·s/kg)
- *Burn time: 240 s
- *Diameter: 2.56 m
- *Length: 2.84 m
- *Propellants: Lox/Kerosene
- *Engine: 1 x RD-0108
See also
Voskhod program
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