Vostok (rocket family)

Template:Short description Template:Infobox Rocket Vostok (Russian: Восток, translated as "East") was a family of rockets derived from the Soviet R-7 Semyorka ICBM and was designed for the human spaceflight programme. This family of rockets launched the first artificial satellite (Sputnik 1) and the first crewed spacecraft (Vostok) in human history. It was a subset of the R-7 family of rockets.

On March 18, 1980, a Vostok-2M rocket exploded on its launch pad at Plesetsk during a fueling operation, killing 48 people. An investigation into a similarTemplate:Spaced ndashbut avoidedTemplate:Spaced ndashaccident revealed that the substitution of lead-based for tin-based solder in hydrogen peroxide filters allowed the breakdown of the H₂O₂, thus causing the resultant explosion.

Variants

The major versions of the rocket were:

Luna 8K72 – used to launch the early Luna spacecraft<ref name=":0" />
Vostok-L 8K72 – Variant of the Luna, used to launch prototype Vostok spacecraft<ref name=":0">Template:Cite web</ref>
Vostok-K 8K72K – a refined version of the above. This was the version actually used for human spaceflight<ref name=":1">Template:Cite web</ref>
Vostok-2 8A92 – used for launching Zenit reconnaissance satellites throughout the 1960s<ref>Template:Cite web</ref>
Vostok-2M 8A92M – modified version for launching Meteor weather satellites into higher orbits.<ref>Template:Cite web</ref>
Soyuz/Vostok 11A110 – hybrid of Soyuz and Vostok rockets used as an interim for two launches<ref>Template:Cite web</ref>

Vostok 8K72K<ref name=":1" /><ref name=":0" />

First Stage — Block B, V, G, D (four strap-on boosters)
- Gross mass: 43,300 kg
- Empty mass: 3,710 kg
- Thrust (vac): 4 x 99,000 kgf (971 kN) = 3.88 MN
- Isp: Template:Convert
- Burn time: 118 s
- Isp(sl): Template:Convert
- 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
Second Stage — Block A (core stage)
- Gross mass: 100,400 kg
- Empty mass: 6,800 kg
- Thrust (vac): 912 kN
- Isp: Template:Convert
- Burn time: 301 s
- Isp(sl): Template:Convert
- Diameter: 2.99 m
- Length: 28.00 m
- Propellants: Lox/Kerosene
- Engine: 1 x RD-108-8D75-1959
Third Stage — Block E
- Gross mass: 7,775 kg
- Empty mass: 1,440 kg
- Thrust (vac): 54.5 kN
- Isp: Template:Convert
- Burn time: 365 s
- Diameter: 2.56 m
- Span: 2.56 m
- Length: 2.84 m
- Propellants: Lox/Kerosene
- Engine: 1 x RD-0109