Beriev SD-MBR - Design
After carrying out studies on the choice of the layout of the aircraft for further work, a normal airplane scheme with a thin wing of a complex shape in plan was adopted. Analysis of the combat capabilities of the aircraft showed the reality of reaching a range of 20,000 km in the organization of two refueling from submarines. The aircraft equipment provided combat employment in difficult weather conditions at any time of the day in any geographical latitude.
An interesting feature of the supersonic long-range naval bomber-scout was its hydrodynamics. During the design process, various layouts were considered: both an editorial scheme and a ski-wing chassis. The draft adopted the last option. The basis for this was the results of model and full-scale tests conducted jointly with TsAGI. The main bearing element of the hydro-chassis was the underwater wing. In flight, it was flush with the bottom. Nasal hydrospin served to provide the angle of attack of the underwater wing, to obtain the required lift at the critical speeds of the seaplane during takeoff. The lower surface of the hydro-shed was supposed to be made in the shape of the bottom of the boat, flush with which it was in the retracted position. Aft damping ski, which was the rear reference point of the hydro-chassis, took up 10% of the load.
The submerged wing was located behind the center of gravity of the aircraft and at the take-off and landing modes perceived the bulk of the external load. When developing a seaplane that received designation SD MBR, great attention was paid to the convenience of operation and maintenance.
Most of its volume was occupied by fuel, located in the tank-compartments and tents. In the bow was the cabin crew and equipment. In the middle part, there was a cargo compartment 11 m long for a cruise missile, with bottom flaps and a deck cover. In the stern there was a tank-compartment for transferring fuel in flight, which was necessary for the displacement of the center of gravity back at the transition from subsonic to supersonic speed.
Research on the hydrodynamics of the displacement housing of the aircraft carried out in TsAGI made it possible to work out the configuration of the nose part of the aircraft, the bottom, the landing gear, the mechanization of the wing, and the placement of engines of the aircraft powerplant, ensuring the reliability and efficiency of the structure when basing on water (long stay on water during waves 3-4 points), movement at high speeds during takeoff and landing. The achieved level of overloads (which was determined by local overload of the structural elements in contact with water) made it possible to create an aircraft with the required flight characteristics.
The wing of the airplane was of a caisson type with fuel tanks-compartments. To prevent the destruction of the mechanization of the wing in the interaction with water in takeoff and landing modes, only simple slotted flaps and ailerons were adopted. The buoyancy of the aircraft was provided by a displacement displacement fuselage, unsinkability (survivability) - the presence in the fuselage of 14 watertight compartments. Stability of the aircraft afloat was provided by floats located at the ends of the wing.
As a takeoff and landing device used bow bowl, a submarine wing in the middle part of the aircraft, perceived the main load, and a forage damping hydro-razor. All the details of the skeleton and the plating of the airframe of the aircraft had an anticorrosive protective coating.
The entire boat was divided into 14 watertight compartments designed to provide the required buoyancy margin. But so as not to "carry air", they placed equipment and fuel. The fuel was placed in 14 fuselage tanks (three tanks with a total capacity of 17 tons tested with protection from 20 mm shells) and 8 wing tanks. In the aft part of the fuselage was a tank-compartment, used to provide the required alignment for the transition of the flight speed from subsonic to supersonic.
The wing of caisson type with fuel tanks-compartments had a sweep of 60° along the leading edge of the middle part and 35° at the consoles. On the wing there were slotted flaps and ailerons. All parts of the fuselage and plating had an anticorrosive protective coating. On the wing tips there were floats of lateral stability. The tail consisted of a swept keel and a controlled stabilizer.
The power plant consisted of four engines, located in two nacelles above the wing and in one engine nacelle for two engines above the fuselage. Two NK-10 two-loop engines were placed in the tail section of the aircraft in a common nacelle, and two others in pods above the wing. Power TRDD fuel and oil was carried out separately, provided for fire and neutral gas. The fuel was located in fourteen tanks in a boat and in eight wings. Three protected tanks provided for the protection of 17 tons of fuel from shells of 20 mm caliber and fragments weighing up to 25 g.
In the version of the reconnaissance target designator, the reconnaissance complex was additionally installed to detect surface targets, the equipment for the near transmission of a radar image to a submarine or to a coast station, the equipment for the long-distance transmission of radar images of targets to the shore with the aid of the Zvezda attachment and the Planeta system, and equipment of general radio-technical intelligence "Romb-2".
The main version of the weapons was a K-21 guided air-to-ship missile. The missile with folded wings was placed in the cargo compartment of the boat. In addition, freely falling bombs (articles of type "6") and mines with a total mass of up to 5000 kg could be suspended in the cargo compartment.
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