R-29 submarine ballistic missile (RSM-40)

R-29 two-stage, monoblock missile.

Among the many problems that arose in the development of the D-9 complex, the most difficult were: the achievement of acceptable dimensions of the rocket with a significant increase in tactical and technical characteristics, the creation of fundamentally new small-size launchers and qualitatively new propulsion systems, achieving significant progress in combat units, on-board and ship control systems, automation of service, preparation of launch and multiple launch firing of the rocket set, the implementation of factory refueling of missiles with tank amputation.

The main solution, which dramatically reduced the missile's dimensions, was the introduction of a "recessed scheme" of the propulsion system - the location of engines in fuel or oxidizer tanks. It led to the reduction of the rocket's dimensions, elimination of dry compartments on the rocket to accommodate propulsion systems, the engines were created a new class: without any maintenance after manufacture, without any detachable connections and at the same time have a new higher level of energy mass characteristics. Solutions for all-welded multistage missile bodies, placement of steering drives in the fuel component, use of wafer shells, creation of permanent adapters from the engine steel elements to the aluminium casing of the missile, as well as solutions for rocking combustion chambers located in the fuel component, have yielded significant benefits. See the photo of the second stage engine.

The missile stages were separated by tearing the hull with an elongated detonation charge.

The upper bottom of the tank had a conical cavity, which housed a warhead with a 1 Mt charge. The VHF was kind of upside down in relation to the direction of flight. As a countermeasure against missile defense systems, the tank bottom of the second stage, in special cylinders, contained decoys that had an effective scattering surface (ESF) comparable to that of the BC. This solution was used for the first time in sea-based ballistic missiles. False targets were released when the head end was separated. See combat unit hull photo after test launch.

In developing a brand new hull for a small-size missile that can withstand increased overloads and excess external pressure, the prerequisites were created for designing new missile launch systems with a joint layout of the missile and the launcher.

The design of the launcher was based on fundamentally new solutions:

• instead of rigidly attaching the missile to the launch shaft, it was freely suspended in the shaft on elastic bonds with nonlinear force characteristics, and oscillations with respect to the mine were allowed during operation;
• instead of transferring point force loads to the missile through special devices, it was proposed to distribute these forces over several circular zones located at different levels along the length of the missile, using rubber-metal shock absorbers;
• instead of the direction of motion of the missile during loading and launch, using a pair of boogie guides, the inner wall of the mine or the shell of the missile itself were used for this purpose.

The total effect was very high. The ring gap and mass of the launch system were reduced by an order of magnitude, and the rocket increased accordingly almost to the size of the launch shaft itself; the huge tanks of the ring gap were reduced many times, and the filling of the ring gap ceased to limit the pre-launch preparation time, resulting in a reduced post-start imbalance of the submarine and its impact on speed.

The principle for marine missile systems was to ensure high accuracy of firing and to prepare flight missions when firing in any direction, at any time, from any point of the ocean within the reach of missiles. The peculiarity of this task is the specific requirements to the control systems for marine complexes: the launch of the missile from a movable base with non-zero initial conditions under very unfavorable dynamic characteristics of the missile as a control object. In this case, the complex must have the properties of all-weather and invariance to the launch site, as well as, within certain limits, to the accuracy of knowledge of the azimuthal direction. The control equipment should also provide practically automatic carrying out of routine checks, prelaunch preparation and launch of all missiles intended for launch (up to the complete set of the boat).

In the 1960s, attempts to solve the functions and tasks assigned to the control system with the help of analogue equipment, as well as the level of development of navigation support for submarines did not leave any hopes for their successful implementation and realization of acceptable accuracy for medium- and, moreover, intercontinental range missiles. A way out was found. This is the development and application on board the R-29 missile of precision gyroscopic devices operating in vacuum, as well as astro-correction systems (astrovizir - see photo), the transition from analog to digital analogue and then completely to digital systems with the use of high-performance small-size on-board digital computing systems and shipborne digital computing systems with special mathematical support. Introduction of trajectory correction by external reference points became a stage and priority solution for combat missiles.

As a result, the prelaunch preparation and salvo firing of a set of missiles began to be carried out centrally: by one operator from the control panel of the missile weapon, a single automated complex of control systems, including the control system itself, the ship's digital computer system, sighting system and control equipment for ship's systems of daily and prelaunch services. The start was carried out from a depth of up to 55 meters, with a sea wave of up to 8 points.

In addition to the increased efficiency and combat capabilities of the R-29 missile, another important achievement was a jump in the performance of liquid-propellant missiles. Among the many technical solutions that provide this jump, the main one is the factory refueling of the rocket, which ends in amputation of tanks by welding the filling valves. It provided a significant increase in warranty life and environmental perfection of marine missiles, as it excluded refueling operations on fleets and possible spillage of components.

Close cooperation of the developers with Zlatoust Machine-Building Plant (Director V. Zlatoustov) contributed to successful solution of technological and production problems, which allowed to develop and implement factory refueling and amputation of missiles, advanced methods of forming and machining of "wafer" shells and other case-shaped parts of missiles, argon-arc and electron-beam welding, strong-dense joints of dissimilar metals, highly effective composite materials. N. Konovalov and V. Doguzhiev), Krasnoyarsk Engineering Works (V. Kotelnikov and V. Gupalov are directors), Omsk Aviation Plant (S. Bovkun is director).