In 1988, the leadership of the Soviet Union signed an agreement according to which it undertook to eliminate short- and medium-range missiles. At that time, the USSR had several missile systems that fell under these parameters. Among them was the Pioneer strategic missile system . Of course, it was quite new, since it began to be used only in the mid-1970s, however, it was subject to disposal. Information on the creation history, structure and performance characteristics of the Pioneer missile system is contained in this article.
Acquaintance
The Pioneer missile system in the technical documentation is listed under the GRAU 15P645 RSD-10 index. In NATO and the USA it is classified as mod.1 Saber SS-20, which in translation means "saber" in Russian. It is a mobile ground-based missile system (PGRK) using a 15Zh45 solid-propellant two-stage ballistic missile of medium range. Developed at the Moscow Institute of Heat Engineering (MIT). The Pioneer missile system has been in service since 1976.
A bit of history
In 1950 in the Soviet Union, rocket science, according to experts, was carried out in the "liquid" direction. It was only in July 1959 that Resolution No. 839-379 was issued, according to which it was decided to fill ground-to-ground combat missile systems with solid fuel. The initiator of this direction, as well as the decree itself, was Ustinov D.F. At that time he was the chairman of the Commission dealing with military-industrial issues.
It was planned to design completely new operational-tactical complexes, designed for a flight range of 600 km, strategic (2,500 km) and intercontinental (10 thousand km) that would run on solid fuel. In 1961, the Soyuz scientific research chemical-technological institute (NIHTI) developed the formulation of a solid fuel mixture. In the same year, the first domestic solid-fuel complex “Temp-S” (SS-12) was created using a guided ballistic missile with a range of 900 km. In 1972, a preliminary design of the Temp-2C complex (SS-16) was prepared, and in 1974 the PGRK itself. It was on the basis of Temp-2C that the Pioneer missile system was made (photo of this PGRK is below).
About SS-20 Design
The creation of the Pioneer missile system began in 1971 at MIT. The process was led by A. D. Nadiradze. The engineers were tasked with developing a new medium-range missile, through which it would be possible to destroy a target at a distance of up to 5 thousand km. In addition, the designers worked on the remaining elements of the complex. For example, above a movable launcher, which was planned to be placed on a wheeled chassis. To facilitate the process, engineers used the Temp-2C intercontinental missile as a basis. The main work was carried out by the employees of MIT. In addition, organizations such as NPO Soyuz and TsKB Titan were involved in the design of the Pioneer missile system. For the reason that some elements were borrowed from the SS-16 project, they planned to complete the construction of the new complex in 1974.
About testing
The Pioneer RSD-10 missile system was tested in September 1974. During testing, some elements were subject to refinement, after which they were again tested. According to experts, it took almost two years. In March 1976, Soviet designers reported to the State Commission on the successful completion of the project. After signing the relevant act, the new 16P645 missile system entered service with the Strategic Missile Forces.
About launcher
The main elements of the Pioneer missile system are represented by the 15Zh45 ballistic missile and the 15U106 self-propelled launcher. Due to this architecture, with the help of PGRK it was possible to patrol at a great distance from the base, and having received the order, to launch a rocket in a short period of time. Self-propelled launcher was created by the Volgograd Central Design Bureau "Titan". As the basis for the machine, the engineers used the MAZ-547V chassis, which has a 12 x 12 wheel arrangement.
15U106 in length turned out to be more than 19 m, and weighed 80 tons (if a transport-launch container and a rocket were installed on it). The presence of the V-38 diesel engine, designed for 650 horsepower, made it possible to accelerate the installation to 40 km / s on a flat road. According to experts, the 15U106 was able to overcome rises of up to 15 degrees, three-meter ditches, cross water obstacles if the depth did not exceed 1.1 m. the machine was equipped with a lifting unit. It could be controlled with hydraulic drives.
About TPK
Engineers used fiberglass as the material for the manufacture of the transport launch container 15Y107. In order to make TPK stronger, it was reinforced with titanium rings. The container had a multilayer structure, namely, two fiberglass cylinders were separated by a heat-insulating layer. The length of the TPK turned out to be no more than 19 m. A hemispherical cover was attached to the front (upper) end with pyro bolts. For the mortar launch of the rocket, the rear (lower) end of the container was equipped with a PAD housing (pressure powder accumulator).
How did the complex work?
To launch the Pioneer rocket, the cold method was used. The bottom of the container was equipped with a powder charge, due to the combustion of which the rocket was ejected from the TPK. In an effort to improve the design, the engineers decided to connect the powder accumulator with a separate element of a cylindrical shape. In other words, it turned out a retractable glass inside the container. When the rocket launched, powder gases acted on it and on the "glass". As a result, he fell to the ground, thus forming an additional support for the entire transport and launch container. This part also performed another task. In case of abnormal burning of the charge, which could harm the rocket, the pressure release inside the container was carried out by means of a "glass". Rocket retention inside the TPK was carried out by detachable support-leading belts (AFP), which were also used as an obturator. After the rocket took off, these belts were shot. As a result, they scattered to a distance of up to 170 m. According to experts, because of this feature, it was impossible to carry out a group launch on one site. Otherwise, the starting PGRK would severely damage surrounding objects.
About the rocket
The Pioneer launched the 15J45 twin-march ballistic missiles. In its design there were stages of breeding and the instrument compartment. The length of the first stage was 8.5 m. It weighed 26.6 tons. A 15D66 solid-fuel engine in a fiberglass casing running on mixed fuel was attached to it. To reduce the length of the rocket, the engineers slightly drowned the nozzle of the power unit into the body. The engine was controlled by gas-jet rudders, for the manufacture of which heat-resistant material was used. On the outside of the rocket were lattice and aerodynamic rudders, which are connected to gas-jet. The second stage in the composition of the rocket had a length of 4.6 m, weighed 8.6 tons. A 15D205 solid-fuel engine was placed in it. To change the flight range, engineers equipped the second march stage with a traction-cutting system.
According to experts, the engineers decided not to borrow this system from the Temp-2C project, but created it from scratch. Like the first, this stage was also controlled by gas rudders. Four solid propellant engines 15D69P were used in the breeding stage. The location of these small-sized power units was the side surface under the combat units, which were used in 15Zh45 as military equipment.
There were three of them. The power of one reached 150 ct. Missile with a circular probable deviation (CVO) of not more than 550 m.
TTX
The Pioneer complex has the following characteristics:
- By type, it is a medium-range ballistic missile.
- The accuracy rate (KVO) was 0.55 km.
- Range of action - up to 5 thousand m.
- Rocket launch is possible from an open area and from the Krona special protected structure.
- Chance to hit is 98%.
Composition
PGRK was completed:
- Fixed and mobile command post with communication and control facilities.
- Three combat missile systems from three divisions.
- Transport and loading facilities.
- The stationary structure, which housed the launchers. This ensured the combat duty of the PGRK, ready for launch.
About modifications
RSD-10 "Pioneer" served as the basis for the creation of new complexes. Engineers developed PGRK 15P656 "Horn". It uses 15Zh56 as a command missile. Previously, the Pioneer-UTX missile system with the 15Zh53 missile was created. According to experts, it has improved combat characteristics. Structurally, it practically does not differ from 15Zh45.
However, it changed the management system and the combat unit. As a result, the CVO amounted to 450 m, and the flight range increased to 5,500 km.