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Soyuz/Vostok

Soviet expendable carrier rocket

Field	Value
name	Vostok-2 (11A510)
function	Small-lift launch vehicle
manufacturer	OKB-1
country-origin	Soviet Union
height	NNNN m
diameter	NNNN m
mass	NNNN kg
stages	4
capacities	{{Infobox rocket/payload
location	LEO
kilos	4500 kg
family	R-7
status	Retired
sites	Baikonur, Site 31/6
launches	2
success	2
first	27 December 1965
last	20 July 1966
payloads	US-A
type	booster
diff	First stage
name	Block B, V, G & D
number	4
engines	1×RD-107
thrust	994.3 kN
total	{{#expr:994.3*4}} kN
SI	315 isp
burntime	118 seconds
fuel	LOX/RP-1
stageno	Second
type	stage
diff	core
name	Block A
engines	1×RD-108
thrust	977.7 kN
SI	315 isp
burntime	292 seconds
fuel	LOX/RP-1
stageno	Third
type	stage
engines	1×RD-0109
thrust	54.5 kN
SI	365 isp
burntime	365 seconds
fuel	LOX/RP-1
stageno	Fourth
type	stage
name	Unknown
thrust
SI
burntime
fuel

|country-origin = Soviet Union

The Soyuz/Vostok (GRAU index: 11A510) was an interim expendable carrier rocket used by the Soviet Union in 1965 and 1966. Two were launched with prototype US-A satellites.

The Soyuz/Vostok was launched from Site 31/6 at the Baikonur Cosmodrome. It consisted of the boosters (first stage) and second stage (core) from a Soyuz rocket combined with the third stage of the Vostok-2, and an unknown fourth stage. Along with the Voskhod-derived Polyot, it was built as an interim between the cancellation of the UR-200 development programme, and the introduction of the Tsyklon-2, which took over US-A launches once it entered service.

Notes

References

Wade, Mark. "Soyuz". Encyclopedia Astronautica.

Info: Wikipedia Source

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space-launch-vehicles-of-the-soviet-union r-7-(rocket-family) vehicles-introduced-in-1965

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