Vostok rocket
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| Vostok 8K72K | ||
|---|---|---|
| Image:Wostok 1 Start.jpg | ||
| 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:
- 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 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.
[edit] 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 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: 1 - 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: 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 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
[edit] See also
| Current: |
Ariane 5 • Atlas V • Cosmos-3M • Delta II • Delta IV • Dnipro • Geosynchronous Satellite Launch Vehicle • H-IIA • Long March • Minotaur • Pegasus • Polar Satellite Launch Vehicle • Proton • Rockot • Soyuz • Taurus • Tsyklon • Zenit |
|---|---|
| Planned: | |
| Historical: |
Ariane 1 • Ariane 2/3 • Ariane 4 • Atlas ICBM • Atlas II • Atlas III • Black Arrow • Delta III • Diamant • Energia • Europa • M-V • N1 • R-7 Semyorka • Saturn I • Saturn IB • Saturn V • Saturn INT-21 • PGM-17 Thor • Titan (I, II, III, IV) • Voskhod • Vostok |
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