RT-2

RT-2 in assembly
Credit - RKK Energia

Intercontinental ballistic missile. Year: 1969. IOC: 1969. Family: RT. Country: Russia. Other Designations: RS-12. Department of Defence Designation: SS-13 Mod.1. ASCC Reporting Name: Savage. Article Number: 8K98. Manufacturer's Designation: RT-2. Launch System: 15P098. Complex: 8K98.

Development of the RT-2, the Soviet Union's first solid propellant ICBM, was undertaken by Sergei Korolev and his successor from 1961-1968. It was a huge technical challenge, involving technology in which the Russians had no prior experience. The high-priority RT-2 preoccupied Korolev and his team throughout the period of the moon race, and could be considered a factor in the loss of that race to the Americans. In the end only sixty were deployed, but these provided the technical basis for Russian ballistic missiles of the 1980's and beyond.

The RT-2 was the Soviet Union's first solid propellant ICBM. It represented Korolev's conviction that the best technical solution for a military missile involved the use of solid propellants, as opposed to the dangerous storable liquid propellants favoured by the rest of the Soviet military-industrial complex. Design of this equivalent to the Minuteman was only beginning when the US ICBM was being test-fired. Development proceeded slowly due to technical problems, opposition from other chief designers, and possibly limited availability of certain key materials that could only be surreptitiously purchased in the United States.

Unusually for a missile that became operational, the RT-2 was displayed in a Moscow Parade on 9 May 1965, possibly indicating that the leadership considered it a dead project. The peak deployment of 60 missiles was only attained in 1971, at a time when 1,000 Minutemen were in service. Service life was only a few years, possibly indicating problems in solid fuel ageing. 60 remained the total number of solid propellant Soviet ICBM's deployed until the 1980's, when the mobile RT-12M and RT-23 finally began replacing liquid propellant ICBM's.

Development of the RT-2 by Korolev's OKB-1 was authorised by decree 316-137 of 4 April 1961. This work was to proceed in parallel with the RT-1. The RT-1 represented an interim solution of clustering smaller solid rocket motors to achieve an early operational date, while the RT-2 represented a high-performance long-term solution using single rocket motors in each stage, each with four nozzles. Sardovskiy was put in charge of preparation of the project. The concept was for a modular three stage RT-2 ICBM, with shorter range missiles composed of the second and third stages (RT-15) and first and third stages (RT-25). Development of each of these missiles was accomplished in parallel by different design bureaux, and each bureau was made responsible for development of one of the individual stages:

The first stage was developed by NII-130 in Perm under the leadership of M Yu Tsirulnikov, who was also responsible for development of the RT-15 variant. The stage was built at Factory 98 in Perm and the original polyfurite-binder propellant was to be formulated by NII-130 Perm.
The second stage was developed by TsKB-7 (Arsenal) in Leningrad under the supervision of P A Tyurin, who was also responsible for the RT-25 variant. The stage was built at the Morozov Factory and the polyurethane-binder propellant was to be by V S Shpak at GIPKh.
The third stage was originally to be developed by TsKB-7, with an alternate design by Zhukov and NII-125.
The common miniaturised inertial guidance system for all variants was by Pilyugin.

All stages used ammonium perchlorate/aluminium as oxidiser and fuel in the solid propellant, as originally developed at Altaisk by Yakov F Savchenko. However the search for a proper solid propellant binder took several years. The contendors were:

A polyurethane-binder propellant, designed by Vladimir Shpak at GIPKh Leningrad (State Institue for Chemical Research). This was available at the start of development and was used for stand tests of the second stage. But it did not have a high enough performance.
A polyfurite-binder propellant, designed by Leonid Kozlov at NII-130 in Perm. This was used in stand tests of the first stage but found to be too inelastic for use in such a large stage. It was however adopted for use in the third stage.
A terminated polybutadiene-binder propellant, designed by Boris Zhukov at NPO Soyuz in Lyuberetsk and Yakov Savchenko at Altaisk NII in 1963. This was tested in the third stage but was still not considered elastic enough use in the larger first and second stages.
A rubberised butyl binder propellant, tested by Savchenko in mid-1965. This finally exhibited the necessary high performance and elastic properties, and was adopted for both the first and second stages of the missile.

At the end of development the production missile motors were built as follows:

Stage 1 - motor designer SKB-172 Perm, rubberised butyl binder propellant by Altaisk ANII
Stage 2 - motor designer TsKB Arsenal Leningrad, rubberised butyl binder propellant by Altaisk ANII
Stage 3 - motor designer SKB-172 Perm, polyfurite-binder propellant by NII-130 Perm

The silo was designed by TsKB-34 Spetsmash. Originally two variants were considered - single isolated silos with a launch group, and groups of silos controlled from a single hardened command point. The final variant in the development phase consisted of one command point per ten silos. All were equipped with hydraulic shock absorber devices. The water in the system was spilled onto the flame pit, and the steam generated helped to accelerate the missile out of the silo. The command point was provided with supplies for three years of autonomous operation. Pilyugin developed the SDUK command and control system, which allowed RSVN headquarters southwest of Moscow to securely order launch of all missiles within three minutes of the 'go' order.

The TTT specification and development schedule was completed on 29 January 1962. This envisioned use of the missile with two alternate light nuclear warheads, the larger one with a yield of 1.65 MT. Two different types of silo launcher were proposed, and one train-launched version. The draft project was completed in March 1963. Flights of the third stage on the RT-1-63 test vehicle were conducted between September and November 1965 from Kapustin Yar. Seven initial trials of the RT-2 itself on short-range shots were conducted from LC-87 at Kapustin Yar from 5 February to July 1966, using a silo originally designed for the R-14. The first launch attempt was unsuccessful, the missile guidance failing in the silo two seconds before launch, and the missile roared off unguided. The second attempt on 25 February was also unsuccessful, but a successful test was achieved the next day. The tests then moved to Plesetsk for longer-range flights. 25 test flights were made between 4 November 1966 and 3 October 1968, of which 16 were successful. The missile was accepted by the military on 18 December 1968.

Production of the missile was entrusted to PZKhO Factory 98 in Perm, operated by Arsenal Leningrad. A missile regiment consisted of one hardened 15B52 command point per ten 15P798 silos, all designed by V V Chernetskiy at TsKB-34. Each silo was seperated from the other by 10-12 km and were designed to have a 20 year life. Construction of silos began in 1967, and the first unit became operational at Yoshkar-Ola on 28 August 1968. By 1971 the total deployment there had reached the final total of six regiments / 60 silos. Even though service tests from Plesetsk indicated an allowable storage life of 15 to 17 years, the first-generation RT-2 was replaced from 1972 by the RT-2P. The final RT-2 was retired in 1976. The RT-2 was flown on a total of 44 development flights and 19 operational test flights to 1974, including 5 shots from operational silos at Yoshkar-Ola.

The train-based version was designed, but like the rail-launched Minuteman, never tested or deployed. The missile train would have consisted of four cars with RT-2 missiles, one power generation car, two cars with equipment for test and preparation of the missiles, one command car, one sleeping car, and one car with common crew rest and eating facilities.

Manufacturer: Korolev. Guidance contractor: Pilyugin. Launches: 40. Failures: 2. Success Rate: 95.00%. First Launch Date: 1966-01-01. Last Launch Date: 1974-01-01. Launch data is: incomplete. Apogee: 1,000 km (600 mi). Liftoff Thrust: 860.000 kN (193,330 lbf). Total Mass: 51,000 kg (112,000 lb). Core Diameter: 1.84 m (6.03 ft). Total Length: 21.27 m (69.78 ft). Span: 3.62 m (11.87 ft). Standard warhead mass: 600 kg (1,320 lb). Maximum range: 9,600 km (5,900 mi). Number Standard Warheads: 1. Standard RV: 15F1. Standard warhead yield: 600 KT. Standard warhead CEP: 2.00 km (1.20 mi). Alternate warhead mass: 1,400 kg (3,000 lb). Maximum range with alternate warhead: 4,000 km (2,400 mi). Number Alternate Warheads: 1. Alternate warhead yield: 1,650 KT. Boost Propulsion: Solid. Boost engine: 15D23. Cruise Propulsion: Solid. Cruise engine: 15D24. Cruise Thrust: 323.000 kN (72,613 lbf). Stage 3 Engine: 15D25. Stage 3 Thrust: 137.000 kN (30,798 lbf). Guidance: Inertial. Total Number Built: 123. Total Development Built: 44. Total Production Built: 79.

Model: RT-2M. Year: 1969. Family: RT. Country: Russia. Status: Study 1968-1969. Article Number: 8K98M. Manufacturer's Designation: RT-2M. Complex: 8K98M.

The RT-2M was a modernised RT-2, developed under Savodskiy at Korolev's bureau beginning in the late 1960's in parallel with the RT-2P and using alternate new engines. This increased both range and payload compared to the RT-20. However the RT-2P was selected for further development.

Manufacturer: Korolev. Total Mass: 50,000 kg (110,000 lb). Core Diameter: 1.84 m (6.03 ft). Total Length: 21.13 m (69.32 ft). Span: 3.62 m (11.87 ft). Standard warhead mass: 800 kg (1,760 lb). Maximum range: 10,000 km (6,000 mi). Number Standard Warheads: 1. Standard warhead yield: 900 KT. Standard warhead CEP: 1.80 km (1.10 mi). Boost Propulsion: Solid. Guidance: Inertial.

Model: RT-2P. IOC: 1973. Country: Russia. Other Designations: RS-12UTTKh. Department of Defence Designation: SS-13 Mod.2. ASCC Reporting Name: Savage. Article Number: 8K98P. Manufacturer's Designation: RT-2P. Launch System: 15P098P. Complex: 8K98P.

Development of the improved RT-2P version of the basic missile was authorised by decree 1004-365 of 18 December 1968. The overriding concern was imminent deployment by the Americans of the Safeguard anti-ballistic missile system, and the need for the missile to have the necessary countermeasures to defeat those defences. This was a considerable challenge given the marginal payload available in the original design. Performance of the missile would be improved using new solid rocket motors with lighter high strength steel casings. All stages would now use the T9-BK-4 propellant using ammonium perchlorate oxidiser and butyl rubber binder. These would allow the missile to have 70 kg greater payload, increased range by 400 km, provide a wider firing corridor, improve accuracy by 20%, and provide the ability to carry countermeasures. A new fail-safe launch system prevented unauthorised launch of the missile.

Trials flights were conducted from December 1969 to 14 January 1972 and consisted of 15 launches, of which 2 were unsuccessful. The missile was accepted for military service on 28 December 1972, but series production did not begin until 1974 and continued to 1982. The missile had a guranteed storage life of 15 years and served at 60 silos at Yoshkar-Ola from February 1976 to September 1988. The original design service life of the missile was seven years, but this was increased several times as verified by service tests. By 1990 the number of operational silos had declined to 40, and from 1992-1995 all silos were demolished in accordance with agreements between Russia and the United States. Tests of decommissioned missiles showed the motors still functiioned well after 18.5 years of storage.

The missile was equipped with the Berez countermeasures suite by Vitaliy Gerasimenko at TsNIRTI. This consisted of noise and deception jammers to spoof enemy radar; stealth coatings on the warhead to reduce its radar signature; and unfolding decoys to provide false targets. Some RT-2P's were equipped with special command and control payloads which would be launched into space to provide emergency communications and relay missile-launch orders in the event of nuclear war.

Mishin led the design team at OKB-1, with Tyurin at TsKB-7 Arsenal being the primary subcontractor for production. Arsenal would take over full engineering responsibility for the missile in 1973 after development was completed. The new compact warhead was designed by Samuel Kocharyants at Arazamas-16. Motors were produced at the PZKhO chemical products factory in Perm.

Manufacturer: Korolev. Liftoff Thrust: 980.000 kN (220,310 lbf). Total Mass: 51,900 kg (114,400 lb). Core Diameter: 1.84 m (6.03 ft). Total Length: 21.27 m (69.77 ft). Span: 3.62 m (11.87 ft). Standard warhead mass: 470 kg (1,030 lb). Maximum range: 10,200 km (6,300 mi). Number Standard Warheads: 1. Standard warhead yield: 750 KT. Standard warhead CEP: 1.50 km (0.90 mi). Boost Propulsion: Solid. Boost engine: 15D23P. Cruise Propulsion: Solid. Cruise engine: 15D24P. Cruise Thrust: 437.300 kN (98,309 lbf). Stage 3 Engine: 15D94. Stage 3 Propellants: Solid propellant. Stage 3 Thrust: 176.000 kN (39,566 lbf). Guidance: Inertial. Total Number Built: 90.

RT-2 Chronology

1961 April 4 - Launch Vehicle: RT-1, RT-2.

Development of the RT-2 ICBM authorised by a decree in parallel with the RT-1. Nation: USSR. Development of the RT-2 ICBM was authorised by a decree of 4 April 1961 in parallel with the RT-1.

1963 March - Launch Vehicle: RT-2.

RT-2 draft project completed Nation: USSR. Korolev completed the draft project in March 1963. The modular design had three stages, each with three nozzles.

During 1965 - Launch Vehicle: N1, R-9, RT-1, RT-2, GR-1.

N1 development issues Nation: USSR. Program: Lunar L3. Spacecraft: Luna E-6, LK, Soyuz 7K-LOK. There were two camps on the N1-L3 control systems. One group was within OKB-1, and had developed the systems for the Vostok and Zenit spacecraft, under the personal oversight of Korolev. They stressed the maximum quality and reliability in their systems. The second group had worked with Pilyugin, and had designed the systems for the Mars, Venus, Luna E-6 probes, the R-9, RT-1, RT-2, and GR-1 missiles; and piloted spacecraft. Their design emphasis was on maximum usability and output. Pilyugin had been named chief designer of the control system for the N1-L3.Additional Details: N1 development issues(51154). References: 367.

1966 - Launch Site: Kapustin Yar. Launch Complex: PL87. Launch Vehicle: RT-2.

Test mission Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi). References: 1864.

1966 - Launch Site: Kapustin Yar. Launch Complex: PL87. Launch Vehicle: RT-2.

Test mission Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi). References: 1864.

1966 - Launch Site: Kapustin Yar. Launch Complex: PL87. Launch Vehicle: RT-2.

Test mission Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi). References: 1864.

1966 February 5 - Launch Site: Kapustin Yar. Launch Complex: PL87. Launch Vehicle: RT-2. FAILURE: Failure.

Test mission Nation: USSR. Agency: RVSN. Apogee: 10 km (6 mi). References: 1577.

1966 February 25 - Launch Site: Kapustin Yar. Launch Complex: PL87. Launch Vehicle: RT-2. FAILURE: Failure.

Test mission Nation: USSR. Agency: RVSN. Apogee: 10 km (6 mi). References: 475.

1966 February 26 - Launch Site: Kapustin Yar. Launch Complex: PL87. Launch Vehicle: RT-2.

Test mission Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi). References: 475.

1966 March 6 - Launch Vehicle: N1, R-9, RT-2.

Soviet design bureaux reorganised and renamed. Nation: USSR. Spacecraft: LK, Soyuz 7K-LOK, Soyuz 7K-OK, Soyuz 7K-L1. Decree 'On renaming OKB-1 as TsKBEM and OKB-52 as TsKBM' was issued. In 1966 Afanasyev reorganised the military industrial complex. OKB-1 was redesignated TsKBEM. Sergei Osipovich Opakhin was made First Deputy within the new organization.
However within TsKBEM there were no relative priorities for the projects competing for resources. The R-9 and RT-2 ICBM's, the orbital, circumlunar, and lunar orbiter versions of Soyuz, the LK lunar lander, the N1 booster -- all were 'equal'. It seemed folly to be pursuing the orbital ferry version of the Soyuz when no space station had to be funded. But it was felt flying the spacecraft would solve reliability questions about the design, so it was pursued in parallel with the L1 and L3 versions.References: 367, 474.

1966 Jul - Launch Site: Kapustin Yar. Launch Complex: PL87. Launch Vehicle: RT-2.

Test mission Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi). References: 1864.

September 1966 - Launch Vehicle: N1, R-9, RT-2.

N1 two-launch moon scenario proposed Nation: USSR. Program: Lunar L3, Lunar L1, Soyuz. Spacecraft: LK, Soyuz 7K-LOK, Soyuz 7K-OK, Soyuz 7K-L1, Soyuz 7K-LOK, Molniya-1. Bushuyev proposed a two launch variation on Korolev's single-launch scheme. The increased-payload version of the N1 with six additional engines was not planned to fly until vehicle 3L. 1L and 2L were to be technology articles for ground test with only the original 24 engine configuration. At that time the first Apollo test flight was planned by the end of 1966, and the US moon landing no later than 1969. The Soviets expected the first test of their LK lander in 1969, and concluded they could not expect to land a Soviet man on the moon until 1972.Additional Details: N1 two-launch moon scenario proposed(51158). References: 367.

1966 November 4 - 08:00 GMT - Launch Site: Plesetsk. Launch Vehicle: RT-2.

Test mission Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi). References: 1821.