R-16 strategic missile system with 8K64 missile (R-16U/8K64U)

The 8K64 missile was made in tandem with sequential separation of steps. The first stage consisted of an adapter to which the second stage was attached by means of four breaking bolts, an oxidizer tank, an instrument compartment, a fuel tank and a tail compartment with a power ring. The second stage, which served to accelerate the missile to a speed corresponding to a given range, had a similar design, but was made shorter and smaller in diameter.

The fuel tanks of the first stage and the "G" tank of the second stage were of a panel design, while the "O" tank of the second stage was made of sheet material using chemical milling. In order to ensure stable operation of the LRD, all the tanks were supercharged. The "G" tank of both stages is inflated with nitrogen, the "O" tank of stage II is inflated with air from balloons placed in the instrument compartment, and the "O" tank of stage I is inflated with a high-speed head of the oncoming air flow. Oscillating chambers of steering engines were used for the first time as controls.

Separation of stages of the rocket is carried out according to the following scheme: on command for the separation of stages is turned off the main engine and reduces the thrust of the steering engine I stage, after the launch of the steering engine II stage there is a rupture of the links between the stages and braking the body of the I stage by the brake PRD. The main engine of stage II is started after reaching a distance of 10-15 m between the stages. The head end is separated by braking the housing of stage II by the braking PRDs after switching off the main motor and then the stage II steering motor.

At the I stage of the rocket was installed main engine 8D712, which consists of three dual-chamber engines 8D515, unified with the rocket engines 8K65. A four-chamber 8D63U engine was used as a steering. The II stage installed the main two-chamber engine 8D713 and the steering four-chamber engine 8D64U. The fuel supply system in all engines is turbo-pumped with the main fuel combustion products feeding the turbines. All rocket engines operated on self-combustible fuel components: oxidizer AK-27I and fuel - asymmetric dimethylhydrazine (NDMG).

The missile could be equipped with two types of NPS from 3 to 6Mt. At maximum range, the so called "light" HF was used, while at intermediate and minimum ranges it was "heavy" with a charge of more powerful TNT equivalent. The HF cone shape with a hemispherical top was attached to the second stage housing using three tearing bolts. Its separation was carried out by braking the second stage when the brake gunpowder rocket engines were triggered. The maximum flight range, which ranged from 11,000 to 13,000 km, depended on the power of the head part. Along with improvement of combat missiles, thermonuclear charges continued to be improved in the USSR. Thus, during the flight tests of 8K64 missiles in 1961, it was prescribed to replace the charges in the head units of 8K64 and 8K65 missiles. In this regard, in 1962 there were developed unified MS, suitable for equipping both missiles. Later on, the principle of intra- and interspecific unification of units and products was widely used in various developments of Yuzhnoye SDO.

The 8K64 missile had a protected autonomous inertial control system. It included automatic machines for angular stabilization, stabilization of the center of mass, a system for regulating apparent speed, a system for simultaneous emptying of tanks, and a range control machine. For the first time a gyrostabilized ball bearing platform was used as a sensitive element of the SU on Soviet intercontinental missiles. The control system instruments were located in instrument compartments on the first and second stages. In preparation for launch, the missile was mounted on the launcher so that the stabilization plane was in the firing plane.

8K64U did not differ from 8K64U structurally. To ensure the launch from the control panel was changed automation of the first stage propulsion system. On the missile body were made platforms for the installation of rods, fixing its position in the guides of the mine launcher. Fuel tanks began to be inflated with nitrogen.

BRK R-16 became the base for the creation of a group of intercontinental missiles of the Strategic Missile Forces. The ground-based launch complex included a combat position with two launchers, one common command post and a rocket fuel storage. The missile was launched after it was placed on the launch table, fueled with rocket fuel components and compressed gases, and aiming operations were performed. All these operations took quite a long time. In order to reduce it, four degrees of technical readiness were introduced, characterized by a certain time before a possible launch, which was necessary for a number of prelaunch and launch operations. The 8K64 ICBM could be on high alert after 30 minutes.

The 8K64U was deployed in much smaller numbers because it took more time to build mine complexes (such as Sheksna) than to bring a RK with ground-based boosters into service. At each starting position, there were three BCPs placed in line about 100 meters apart, an underground command post, fuel component storage facilities, and other facilities. The method of starting from the mine was gas-dynamic with its own engines. There are rods installed on the rocket for driving in the mine on rails, as well as for depreciation. Mine protective roof - flat, sliding on rails. The missile was placed inside on a special turning device with docked refueling system communications. For ballistic missile with 8K64U ICBMs three alert levels were installed. Launch time from full alert was 18 min.