Vostok rocket
From Wikipedia, the free encyclopedia
| Vostok 8K72K | ||
|---|---|---|
 |
||
| Stages | 3 | |
| 1 - 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 | |
| 2 - Core Stage | Engines | 1 x RD-108-8D75-1959 |
| Thrust | 912 kN | |
| Burn time | 301 seconds | |
| Fuels | Lox/Kerosene | |
| 3 - 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: 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
[edit] See also
|
|
||
| Active: Cosmos-3M | Dnepr | Molniya | Proton | Rockot | Shtil' | Soyuz (U, 2) | START-1 | Strela | Tsyklon | Volna | Zenit | ||
| In Development: Angara | Onega | ||
| Past: Energia | N1 | Polyot | R-7 Semyorka | Voskhod | Vostok |
| Current: |
Ariane 5 · Atlas V · Cosmos-3M · Delta II · Delta IV · Dnepr · Geosynchronous Satellite Launch Vehicle · H-IIA · Long March · Minotaur · Molniya · Pegasus · Polar Satellite Launch Vehicle · Proton · Rockot · Shavit · Soyuz (U, 2) · 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 · H-II · J-I · Juno I · M-V · N1 · R-7 Semyorka · Saturn I · Saturn IB · Saturn V · Saturn INT-21 · Scout · Thor · Titan (I, II, III, IIIB, IV) · Vanguard · Voskhod · Vostok |
