| R-7A | |
|---|---|
_misil.svg) A 2-view drawing of the R-7 Semyorka (NATO code-name SS-6 Sapwood) | |
| Type | Ballistic missile |
| Place of origin | Soviet Union |
| Service history | |
| In service | 9 February 1959 – 1968 |
| Used by | Strategic Missile Troops |
| Wars | Cold War |
| Production history | |
| Designer | Sergei Korolev |
| Designed | From 1953 |
| Variants | SeeVariants |
| Specifications | |
| Mass | 280 metric tons (280 long tons; 310 short tons) |
| Height | 37 m (121 ft) |
| Diameter | 10.3 m (34 ft) |
| Effective firing range | 8,000–8,800 km (5,000–5,500 mi) |
| Warhead | A single KB-11-derived, 5,300–5,500 kg (11,700–12,100 lb), 7.27 m (23.9 ft) diameter, 3 to 5 Mt, thermonuclear warhead |
| Engine | 4x jettisonable four-chamberRD-107 engines on boosters each with 2x vernier rocket engines, plus 1x four-chamberRD-108 engine on the central core with 4x vernier rocket engines.
|
| Propellant | LOX/T-1 |
Steering system | 12x vernier thrusters arranged around the booster clusters and the core engines |
| Accuracy | 2.5–5.0 km (1.6–3.1 mi), max. deviation: 10 km (6.2 mi) |
TheR-7 Semyorka (Russian:Р-7 Семёрка,lit. 'number seven',GRAU index:8K71) was aSoviet missile developed during theCold War, and the world's firstintercontinental ballistic missile. The R-7 made 28 launches between 1957 and 1961. A derivative, theR-7A, was operational from 1960 to 1968. To the West it was unknown until its launch (later it would get theNATO reporting nameSS-6 Sapwood). In modified form, it launchedSputnik 1, the first artificial satellite, into orbit, and became the basis for theR-7 family which includesSputnik,Luna,Molniya,Vostok, andVoskhodspace launchers, as well as laterSoyuz variants. Various modifications are still in use and it has become the world's most reliable space launcher.
The R-7 was 34 m (112 ft) long, 10.3 m (34 ft) in diameter and weighed 280 metric tons (280 long tons; 310 short tons); it had a single stage with four strap on boosters powered byrocket engines usingliquid oxygen (LOX) andkerosene and capable of delivering its payload up to 8,000 km (5,000 mi), with an accuracy (CEP) of around 5 km (3.1 mi). A singlethermonuclear warhead could be carried with a nominal yield of 3megatons of TNT. The launch was boosted by four strap-onliquid rocket boosters with a central 'sustainer' engine powering the central core. Each strap-on booster included twovernier thrusters and the core stage included four. The guidance system was inertial with radio control of the vernier thrusters.[1]
The widely used nickname for the R-7 launcher, "Semyorka", is a rough translation of "old number seven" in Russian.[2]
Design work began in 1953 atOKB-1 in Kaliningrad in Moscow Oblast (presentlyKorolyov, Moscow Oblast) and other divisions with the requirement for a missile with a launch mass of 170 to 200 tons, range of 8,500 km and carrying a 3,000 kg (6,600 lb) nuclear warhead, powerful enough to launch a nuclear warhead against the United States. In late 1953 the warhead's mass was increased to 5.5 to 6 tons to accommodate the then plannedthermonuclear bomb. On 20 May 1954 theUSSR Council of Ministers approved the development of the R-7.[3][4]
The principle of a staged missile, also known as a "rocket packet", was first proposed byMikhail Tikhonravov at NII-4 in 1947. Korolev became aware of this proposal in 1948 and supported further base studies at NII-4 in 1949–50. This was further refined byDmitry Okhotsimsky'sDepartment of Applied Mathematics in 1951 and expanded by Korolev's OKB-1 in 1952–53, which concluded that a core and four strap on boosters as the preferred model, which the R-7 used.[5][6]
To lift the 5.5 ton payload required a redesign of the existing RD-105 and RD-106 engines.Valentin Glushko's OKB-456 combined four combustion chambers using a single turbo pump, which provided a cumulative higher thrust than a single engine. Other advantages included an overall lower engine weight and simpler design, test and construction, via standardisation. The main engines for the central core and strap on boosters all used the four combustion chamber configuration. The four strap on propulsion engines were powered by theRD-107 engine providing a sea level thrust of 83 tons, each with twovernier engines to assist with steering. The central core'sRD-108 engine provided sea level thrust of 75 tons and included four vernier engines utilized for steering.[7][8]
The rocket had some key features to it that made it unique. Instead of using jet vanes for control, which increased resistance generated at the engine nozzle exhaust outlet, the R-7 used special control engines for steering. These same engines served as the last stage'svernier thrusters.[9] Because of clustered design, each booster had its own propellant tanks. The design team had to develop a system to regulate the propellant component consumption ratio and to synchronize the consumption between the boosters.[10]
Instead of a free-standing missile which was launched from a horizontal pad, it turned out that assembling a cluster of a central core and four boosters on the pad is almost impossible without it falling apart. Also, a wind gust could knock the unfuelled missile off of the pad. The solution was to eliminate the pad and to suspend the entire rocket in thetrusses that bear both vertical weight load as well as horizontal wind forces. The launch system simulated flight conditions with strap-on boosters pushing the central core forward.[11]
The existing testing site atKapustin Yar was inadequate for the testing required for the R-7. Therefore a new site in Kazakhstan that would eventually become theBaikonur Cosmodrome was approved on 12 February 1955.[12] The first series of test commenced when a flight-ready vehicle was delivered on 1 May 1957, and flown on 15 May. A fire broke out in one of the strap-on boosters almost immediately at liftoff. The missile broke away from the booster 88 seconds after liftoff and crashed 400 kilometres (250 mi; 220 nmi) downrange. During the next attempt on 11 June an electrical short caused the missile to start rolling uncontrollably and disintegrate 33 seconds after liftoff.[13]
The first successful long flight, of 6,000 kilometres (3,700 mi; 3,200 nmi), was made on 21 August 1957 with the missile reaching the target atKamchatka, however the dummy warhead disintegrated in the upper atmosphere. Five days later, TASS announced that the Soviet Union had successfully tested the worlds's first intercontinental ballistic missile.[14][4] A second successful test took place on 7 September 1957, with the missile again travelling 6,000 km (3,700 mi; 3,200 nmi). However again the dummy warhead disintegrated in the upper atmosphere. The first series of tests concluded on 10 July 1958.[15]
The second test series incorporating improvements commenced on 24 December 1958 and concluded on 27 December 1959. Seven of the eight test launches were successful. Problems were resolved during these intensive tests and the missile was declared operational on 20 January 1960.[16]
Amodified version of the missile (8K71PS) launched the world's first satellite into orbit whenSputnik 1 lifted off from Baikonur on 4 October 1957.Sputnik 2 followed on 3 November 1957. Sputnik (8A91) subsequently launchedSputnik 3 on 15 May 1958.[17]
The first strategic-missile unit went on alert status on 15 December 1959 atPlesetsk in the north-west of the USSR. An improved version, theR-7A with a lighter warhead, all inertial guidance system and a range of 12,000 km, became the standard version once it reached operational status on 12 September 1960.[16][18]
The costs of the system were high, mostly due to the difficulty of constructing in remote areas the large launch sites required. Besides the cost, the missile system faced other operational challenges. With theU-2 overflights, the huge R-7 launch complexes could not be hidden and therefore could be expected to be destroyed quickly in any nuclear war. Also, the R-7 took almost twenty hours to prepare for launching, and it could not be left on alert for more than a day due to itscryogenic fuel system. Therefore, the Soviet force could not be kept on permanent alert and could have been subject to an air strike before launching. These issues meant that the original planned fifty launch complexes were reduced to six, five for strategic forces, Site 31 at Baikonur and Sites 16, 41 and 43 (2 pads) atPlesetsk and one for space launches atSite 1,Baikonur.[16][19]
The limitations of the R-7 pushed the Soviet Union into rapidly developing second-generation missiles which would be more viable weapons systems, particularly theR-16.[20] The R-7 was phased out of military service by mid-1968.[21]
The R-7 turned out to be impractical as a weapon, but it became the basis for a series of Sovietexpendable space launch vehicles, includingVostok family of launchers,Molniya andSoyuz family of launchers.[21] As of 2024[update], modified and modernized versions (Soyuz 2 and the boosterless2.1v variant) remain in service, having launched over 1,840 times. The R-7 is also a record holder in terms of longevity, with more than 50 years of service with its various modifications and has become the world's most reliable space launcher.[22][23]
First is the Sputnik, most known for carrying Sputnik 1. Second is the Vostok, which carried Vostok-1 through Vostok-6. It also carried Voskhod along with the better-known Voskhod-2 because of its first spacewalk and Monilya, which is less known due to its retirement. It also carries Soyuz, which is still in operation after 60 years. Soyuz is Russia's most reliable rocket in use[citation needed].
Soviet Union
