| Vostok 8K72K
|
|
|
| Stages
| 3
|
| 0 - Strap-on Boosters
| Engines
| 4 x RD-107-8D74-1959
|
| Thrust
| 4 x 970.86 kN = 3,883.4 kN
|
| Burn time
| 118 seconds
|
| Fuels
| Lox/Kerosene
|
| 1 - Core Stage
| Engines
| 1 x RD-108-8D75-1959
|
| Thrust
| 912 kN
|
| Burn time
| 301 seconds
|
| Fuels
| Lox/Kerosene
|
| 2 - Final Stage
| Engine
| 1 x RD-0109
|
| Thrust
| 54.5 kN
|
| Burn time
| 365 seconds
|
| Fuels
| Lox/Kerosene
|
| Launch Vehicle
| 1st Launch December 22, 1960
|
| Payload LEO 65-deg
| 4,725 kg
|
| Payload Lunar probe
| 500 kg
|
The Vostok rocket (Russian Восток, translated as "East") was a derivative of the Soviet R-7 ICBM designed for the human spaceflight programme but later used for other satellite launches.
The major versions of the rocket were:
On March 18, 1980 a Vostok-2M rocket exploded on its launch pad at Plesetsk during a fueling operation, killing 48. An investigation into a similar -- but avoided -- accident revealed that the substitution of lead-based for tin-based solder in hydrogen peroxide filters had resulted in the breakdown of the H2O2 and the resulting explosion.
Vostok 8K72K specifications
- Stage Number: 0 - Strap-on Boosters; 4 x Vostok 8K72K-0
- Gross Mass: 43,300 kg
- Empty Mass: 3,710 kg
- Thrust (vac): 4 x 99,000 kgf (971 kN) = 3.88 MN
- Isp: 313 kgf·s/kg (3.07 kN·s/kg)
- Burn time: 118 s
- Isp(sl): 256 kgf·s/kg (2.51 kN·s/kg)
- Diameter: 2.68 m
- Span: 8.35 m
- Length: 19.00 m
- Propellants: Lox/Kerosene
- Engines: 1 x RD-107-8D74-1959 per booster = 4
- Stage Number: 1 - Core stage; 1 x Vostok 8K72K-1
- Gross Mass: 100,400 kg
- Empty Mass: 6,800 kg
- Thrust (vac): 912 kN
- Isp: 315 kgf·s/kg (3.09 kN·s/kg)
- Burn time: 301 s
- Isp(sl): 248 kgf·s/kg (2.43 kN·s/kg)
- Diameter: 2.99 m
- Length: 28.00 m
- Propellants: Lox/Kerosene
- Engine: 1 x RD-108-8D75-1959
- Stage Number: 2 - Final stage; 1 x Vostok 8K72K-2
- Gross Mass: 7,775 kg
- Empty Mass: 1,440 kg
- Thrust (vac): 54.5 kN
- Isp: 326 kgf·s/kg (3.20 kN·s/kg)
- Burn time: 365 s
- Diameter: 2.56 m
- Span: 2.56 m
- Length: 2.84 m
- Propellants: Lox/Kerosene
- Engine: 1 x RD-0109
See also
