Photos Russian and Soviet Strategic Rocket Forces and Infrastructures

[Ivan le Fou]

WOW Ivan, once again that is great stuff you've posted.....thank goodness these never got used!! Thanks for sharing

Thanks!

 

[Ivan le Fou]

Since, earlier in the thread, I made a post in which a distinction was made between the SS-3 Shyster and SS-4 Sandal, I thought perhaps it could be a good idea to make a post to talk about the differences between the two.



R-5/8A62, R5M/8K51, SS-3 Shyster.

The R-5 and R-5M were a single-stage MRBM with load-bearing tanks, a system for reducing unused fuel residues and a detachable warhead.
The R-5 was the world's first ballistic missile with load-bearing fuel tanks (both fuel and oxidizer).

Initial launches ended up with a flight range being no more than 1000 km due to the destruction of the warhead upon entering the dense layers of the atmosphere.
The warhead design was changed to accommodate a 6 mm thick heat-resistant coating.

Welded seams of the tanks are made by argon-arc welding.
Automated welding was used for the longitudinal seams of the shells and the welding of the bottoms; fittings and flanges was carried out by argon manual welding.


In order to save weight, the missile did not have a sealed instrument compartment.
The control system instruments are located in the tail (above the engine) and in the compartments in-between the tanks. The latter contains only vibration-sensitive gyro instruments and acceleration integrators.
Guidance to the target is carried out by turning the launch pad using topographic referencing data.
The missile is equipped with 4 steering mechanisms.
The antennas for the radio control system are mounted on the outer contour of the fuel tank casing.




R-5

The development of the R-5 started in 1951 as a continuation of the R3, divided in three stages.

The first took place in March-May 1953 and consisted of 8 launches, 6 of which were successful.
2 launches were carried out at a range of 270 km, one at 550 km, and 5 launches at a range of 1200 km (with 2 unsuccessful launches).
The first launch of the R-5 was on March 15, 1953, with The first successful launch at full range on April 19, 1953.


The second stage of testing began on October 30, 1953 with 7 launches at a range of 1185 km, (one of which was unsuccessful).
Its main goal was aimed at correcting the issues responsible for the failures of the first stage. The unsuccessful launches lead to the decision to modify the control system in order to reduce and eliminate the impact the rocket body's vibrations had on it.


The third and final test stage was on 12 August 1954, with 19 launches taking place from August 1954 to February 1955.

During the initial test launches it was discovered the engine jet was shielding the radio range control signals, once the issue resolved 4 more test launches were successfully performed, followed by yet another 10.

All tests were carried out at the Kapustin Yar test site and deemed completed by April 16, 1955.

The remaining R-5s and it manufacturing documentation were placed in mobilization reserve, and work on the nuclear capable R-5M started.




R-5M

The creation of a nuclear warhead was first proposed in a letter from developers to the curator of nuclear issues, L.P. Beria, in 1952.
Initially, the RDS-3M charge was proposed to be modified for the R-2 missile, but the idea was eventually rejected.
Later, the nuclear warhead for the R-5M missile was created on the basis of the RDS-4 charge (referred to as RDS-3M in its early stage of development).

The creation for the R-5M warhead was proposed following the testing of the tactical atomic bomb "Tatiana" with the RDS-4 charge (based on the FAB-3000 and tested from the Il-28 on August 23, 1953). A resolution on the development was issued on April 10, 1954.


The resolution established the a nuclear charge was to be ready by October 1954.
The project as a whole was to be ready by October 1954: 15 missiles (including 10 for flight tests, 5 for test launches).
Flight development (10 sighting tests) to be carried out in October-November 1954, and 5 launch tests in December 1954.

However, though development of the R-5M was officially started on April 20, 1954, work on the design of the missile began at the end of 1953.
The first launch occurred on January 21, 1955, and the final one of the first stage of tests A was on June 6, 1955.
The first round of these launches was to test simulated emergency situations, with scenario going from stabilization malfunction, steering issues and disconnected rudders.
The second sighting stage of flight took place in August-November 1955 with 10 launches. It mostly focused on studying the missiles behavior when loaded with different launch weights.
State tests were initially planned to be conducted in September-October 1955, but were eventually conducted from January 11 to February 6, 1956. During these tests, 4 missiles with mock nuclear warheads were launched and the last fifth missile was launched by a combat crew with a 80kt capable nuclear warhead on February 2, 1956, (Operation Baikal). The nuclear explosion (the warhead having been reduced to 0,3-0,4kt) was carried out in the Aral Karakum Desert, 1190 km away from the launch range, after a 11 minutes flight.

Serial production of R-5M missiles was carried out at the GSZ No. 586.
The first serial lot of 25 missiles began in 1955.
A total of 48 R-5M missiles were produced in 1956-1957, but it is possible that at least 48 more were produced later, to arm engineering brigades and missile divisions.


The R-5M/8K51 missile with a ground-based equipment complex was adopted into service in June 21, 1956, the first military unit begining service in May 1956.
It is worthy of note the R-5M predates the creation of the Strategic Missile Forces (SMF), meaning units with R-5M missiles were part of the Long-Range Aviation (8 brigades were deployed during this time).
The R-5M missiles were replaced by R-12 in 1961.

First public sighting of the R-5M, on November 7 1957.
Launch and ground equipment:
- The R-5 launch ground complex was created by unifying the launch complexes developed for the R-1 and R-2 missiles.

It consisted of a ground towed carriage-erector 8U212, towed by the AT-T tractor, launched from the 8U212 launch pad.
The launch complex includes several vehicles and trailers.

Launch pad 8U212.

Launch site organization.

- R-5M was launched from a 8U212 pad.
The missile is transported on a trailer-lifting ramp and lifted, fitted to the pad by a 8U25 installer vehicle.
Similarly to the R-5 the R-5M launch complex includes several vehicles and trailers. A similar launch complex with modifications was used on the R-12, R-14 and R-16.

8U25.

R-5M being fitted on a 8U212 pad by a 8U25.

Launch site diagram.
The auxiliary vehicles usually consisted of:
- 8N811 autonomous test vehicle;
- 8N14 horizontal test vehicle;
- 8G119 fuel tanker;
- 8G18 oxidizer tanker;



Performance characteristics of the missile:

R-5:
Length: 22,115m
Diameter: 1,650m
Span: 2,640m
Starting weight: 28.570kg
Warhead weight: 1000-1425kg standard.
Dry mass: 4200kg
Fuel mass: 24300kg
Maximum range: 1200km
Minimum range: 270km
Range with 2 suspended warheads: 810km
Range with 4 suspended warheads: 560km
KVO: +-6000m
Pre-launch preparation time: 2 hours.
Time spent in a fueled state of readiness for launch: up to 30 days


R-5M:
Length: 20,747m
Diameter: 1,650m
Span: 3,452m
Starting weight: 28610 / 29100 / 29500 kg
Warhead weight: 1300-1364 kg nuclear.
Dry mass: 4390 kg
Fuel mass: 24900 kg
Maximum range: 1200 km
Minimum range: 270 km
KVO: 2400 m / 3700 m
Pre-launch preparation time: 2 hours.
Time spent in a fueled state of readiness for launch: up to 30 days


Combat equipment:

R-5:

Warhead:
The warhead is of an ogive shape with a sharp nose and a conical stabilizing skirt in the tail section.
Heat-resistant coating based on sublimating materials.
The warhead is separated using a pneumatic pusher.
The warhead weight is 1450 kg.
The fuse is contact.

Regular payload:
-High explosive warhead.
Weight - 1000 kg.
-High-explosive warhead + 2 additional side suspended high-explosive warheads.
Weight of one additional warhead - 958 kg.
-High-explosive warhead + 4 additional side suspended high-explosive warheads.
Total warhead weight - 5282 kg (main + 4 suspended).

Special payload:
"Generator-5" was a R&D project for a dirty bomb.
Work was started on November 16, 1955.

R-5M:

Warhead:
4R warhead developed by KB-11.
The warhead is made shorter in order to reduce the speed of impact with the ground.
The warhead is separated using a pneumatic pusher.
The warhead weight is 1364 kg.
The fuse is contact.

Regular payload:
High explosive warhead for combat training and test launches.

Special payload:
- in service until 1968 - 40 kt.
- in service from from 1958 to 1960 - 300 kt.
- 1 Mt.

 

[Ivan le Fou]

R-12 / R-12 U - SS-4 Sandal

The design of the R-12 missile was based on the R-5M MRBM, with its dimensions identical to those of the R-5M missile. Later, in order to increase the operational range, the length of the fuel tanks was increased, and the design was strengthened to allow for the use a heavier nuclear warhead.
The general layout of the missile consists of a warhead, an adapter compartment, an oxidizer tank, an instrument compartment, a fuel tank, and a tail compartment.

The preliminary design of the new 8K63 missile was approved in March 1955.
The range of the missile was to be at least 1,200 km with a conventional warhead.
The length of the tanks was increased, the design was strengthened, and a the creation of a new RD-214 engine was proposed to accommodate the changed weight and dimensions. OKB-456 was put in charge of developing and testing the RD-214 engine from 1955 to 1957.
The technical design was released in October 1955, and the working drawings were transferred to production in December 1955.
The R-12 missile qualification tests were scheduled for September - October 1957 with the first test fire (M2-3) being conducted in March 1957 at R-I 229 in Zagorsk. Three more test fires were conducted immediately after for a total of 8 launches, including 1 emergency launch. Based on the results of the first stage of testing, the liquid nitrogen used for pressurizing the tanks was replaced with hydrogen peroxide.

Serial production of 8K63 missiles was carried out at several plants and production began in October 1958.

A total of 2,300 missiles were produced.


The R-12 / 8K63 missile was accepted into service in March 4, 1959.
R-12 missiles began as part of missile regiments in the Baltics (Plunge), Belarus (Slonim, Novogrudok, Pinsk, Gezgala), Ukraine and Kazakhstan in mid-1959. They were issued nuclear warheads as soon as the SFM was created.

On May 15, 1960, the following units entered combat duty with the 8K63:
- the 85th missile regiment of the 33rd missile division (Belarus)
- the 25th missile regiment of the 24th missile division (Kaliningrad)
- 94th Missile Regiment of the 23rd Missile Division (Estonia)
Further, the divisions and regiments were put on combat duty during 1960-1963. However some regiments were not equipped with warheads until April 1961.

The R-12 missile was removed from service in 1989 under the INF Treaty.



Launchers, ground equipment and organization.

- R-12:

The 8P863 launch complex consisted of a 8U217 launch pad, similar to the one used for the R-5M; and up to 12 vehicles, similar to the ones used for the R-5M with the exception of the 8U210 installer based on the MAZ-529V.

Time to prepare the complex for launch is about 2 hours.


- 1960: a missile regiment with R-12 included 2 to 3 divisions with 4 to 6 ground-based launchers.
The division included 2 to 4 batteries with 1 launcher each and an attached assembly brigade of the missile-technical battalion.

- 1962 - 1989: a missile regiment with R-12 included 2 divisions with 8 ground-based launchers and 1 division with 4 silo launchers.
The silo-based division included 2 batteries with 2 launchers each.
The missiles were stored in concrete storage facilities, with 2 units each.
The missile regiments had at least 5 ground launchers, 11 to 14 vehicles, 6 to 7 missile installers, 45 to 52 fuel trucks.

R-12 installation on a 8U217 launch pad.

R-12 8U210 missile installer.

Fuel tanker truck from the R-12.

R-12 on transport trailer without warhead.

R-12 warhead on transport truck.

Mobile launch site diagram.



- R-12U:

- 8P863 launch complex, with 8U217 launch pad and ground equipment complex, similar to R-12.
- experimental silo-based launcher "Mayak".
2 copies of the silo-based launcher were built for testing the experimental version of the 63Sh silo-based missile.

Later, the 63S1, designed for space launch vehicles, were tested and launched from the Mayak-2 silo.

Silo launchers "Mayak-2" (left) and 8P763P (possibly test site) with 63S1 and 11K63 respectively.


- 8P763 Dvina silo launch complex.

The silo was a concrete well 30 m deep and 7 m in diameter, at the bottom of which the rocket launch pad was installed.
When the engine was started, hot gases exited into the gas duct between the shaft of the silo and the launch metal cup.
In the upper part of the silo, the gas duct had an extension and guide vanes to divert hot gases to the side in order to reduce the thermal impact on the rocket.
The silo was protected by a multi-ton "roof" which slid along the a set of rails before the rocket was launched.

R-12 installation steps in a 8P763 "Dvina" silo complex.

Diagram of the 8P763 "Dvina" silo complex.


The Dvina complexes consisted of 4 silos located at the corners of a rectangle measuring 80 x 70 m, a command post, and a refueling system.

Performance characteristics.


Length - 22.768 m
Length without warhead - 17.7 m
Body diameter - 1.652 - 1.8 m
Engine "skirt" length - 3.3 m
Stabilizer span - 2.652 m

Weight - 41.800 / 42.200 kg
Warhead weight - 1.364 / 1.680 kg (light / heavy warheads)

Range:
- 1,000-1,200 km (8A63)
- 2,100 km (8K63, officially)
CEP:
- during tests at launches at 2,000 km - range deviation up to 1,100 m, course deviation up to 600 m
- up to 5,000 m (maximum according to performance characteristics)

Launch preparation time - up to 3 hours (from a ground launch pad)


Combat equipment:

- conventional warhead - high-explosive, 1.364 kg.

- thermonuclear warhead 8F12 / 8F12N / AA21, 1.150 kt.

- thermonuclear 8F126 / AA48-2, 2.3 Mt, weighing 1.680 kg. Developed by 1963

- thermonuclear 8F128 for the unified R-12U.

- "Tuman" cassette-type chemical warhead, developed in the early 1960s.

- experimental systems of false warheads and jamming for R-12 and R-12U, developed in 1967.


Variants :

- 8A63.
First version of the preliminary design.

- R-12 / 8K63.
Second version of the missile, a serial medium-range missile, development began on the basis of the 8A63 project with its modifications in 1954.

- R-12Sh / 63Sh / 8K63Sh.
Experimental missile, for experimental launches from the experimental silo launcher "Mayak".

- R-12U / 8K63U.
Unified (for ground and silo launchers) serial version of the R-12 missile.

- R-12N / 8K63U.
Unified R-12U missile (for ground and silo launchers) in a ground-based version with the 8P863 equipment complex.

- 8K63E / 8K63K / 8K63V / 8K63Kr.
Missiles equipped with false targets and jamming sources "List" (8K63E), "Kaktus" (8K63K), "Verba" (8K63V), "Krot" (8K63Kr).

- 63S1 / 8K63S1.
Launch vehicle for an artificial earth satellite.
The launch vehicle was created by adding a second stage to the R-12.

- 11K63 / 63S1M "Raduga".
Launch vehicle created on the basis of the 63S1.

- 8K63B.
Launch vehicle of the Bor-1 system.