Vostok rocket

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:

*8K72 - used to launch the early Luna spacecraft and the prototype Vostok spacecraft
*8K72K - a refined version of the above. This was the version actually used for human spaceflight
*8A92 - used for launching Zenit reconnaissance satellites throughout the 1960s
*8A92M - modified version for launching Meteor weather satellites into high orbits.

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 similarndash but avoidedndash 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: 1 - 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 s (3.07 kN·s/kg)
**Burn time: 118 s
**Isp(sl): 256 s (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: 2 - Core stage; 1 x Vostok 8K72K-1
**Gross Mass: 100,400 kg
**Empty Mass: 6,800 kg
**Thrust (vac): 912 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
**Length: 28.00 m
**Propellants: Lox/Kerosene
**Engine: 1 x RD-108-8D75-1959

*Stage Number: 3 - Final stage; 1 x Vostok 8K72K-2
**Gross Mass: 7,775 kg
**Empty Mass: 1,440 kg
**Thrust (vac): 54.5 kN
**Isp: 326 s (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

References

http://www.spiritus-temporis.com/vostok-rocket/vostok-8k72k-specifications.html

ee also

*Vostok spacecraft
*Vostok program
*Vostok 1