MI-10RVK 9K74 / 9P116 missile-helicopter
The helicopter launcher ZIL-135V (GRAU-9P116 index) was created in accordance with the secret PSM dated February 5, 1962. In the ZIL-135V installation, not only the most original and bold technical solutions and findings were realized, but also the equally bold but absurd idea of secretly delivering the wheeled vehicle through the air and landing it in the rear of the enemy or in hard-to-reach places for the production of a single sudden missile strike. According to the designers, the distance from the takeoff point of the helicopter to the launch point was up to 270 km.
The duties of SKB ZIL included a general design, which resulted in the development of three versions of a helicopter launcher. After selecting the most optimal version in September 1962, the first prototype was built at ZIL. To transport the ZIL-135V launcher, it was intended to use the external rigid suspension of a heavy Mi-10 helicopter, known as a "flying crane". The entire system (helicopter + launcher) was named the Mi-10RVK rocket-and-helicopter complex (GRAU-9K74 index).
Plant "Dzerzhinets" was engaged in the development and manufacture of electrical equipment, and then assembled three more units. For the first time in domestic practice, an electric transmission was introduced with four motor-wheels and gearboxes of SKB ZIL design.
A unique self-propelled machine was a streamlined support body - a massive container with a diameter of 1.8 m mounted on four uni-directional 20-inch wheels and a fueled ["charged"] cruise missile S-5B (4K95), about 10 m in length and the launch weight of the order of 4 m. Mass without TLU The rocket was about 5.5 tons, the full one - 12 tons. The maximum height of the cab in the transport position is 3.3 meters. The time of bringing to the combat position is 5 minutes. The take-off mass of the RVK complex reached 44.6 tons.
In front of it was a wide glazed 2-seater control cabin with fiberglass facing. On its sides and behind were a power unit, a direct current generator, a hydraulic pump and fiberglass fuel tanks, for access to which on both sides of the body led stairs and latticed working platforms.
Leading electric motors DT-22 with a power of 22 kW with forced ventilation and reducing planetary gearboxes received electric power from a 120-kilowatt DG-120 direct-current generator driven by a compact GTD-350 gas-turbine engine of the design of the V.Ya. Klimov plant in Leningrad.
This power unit was designed for the Mi-2 helicopter, had a dry mass of only 139.5 kg, a length of 1350 mm and developed a nominal power of 316 liters. from. All wheels were fixed to the body rigidly without suspension. The front ones were controllable and mounted on vertical pivot pivots, the rear mounted at the ends of electro-hydraulic lifting racks to bring the HPU into a combat inclined position.
The 9P116 could move independently at a speed of 18 km / h for a distance of up to 40 km from the landing site and after launching the rocket was returned to the helicopter, fixed to its suspension and transported in the opposite direction. The 9P116 launcher for the "shot" lifted its rear part on the hydraulic jacks, the lid was opened, and then the rocket was launched. During the tests that took place in Faustovo, several C-5B were launched from the 9P116 helicopter launcher.
During the tests, a number of significant deficiencies of the 9K74 helicopter complex were revealed. Among the shortcomings were the large "sail" of the helicopter with the launcher on board and its demolition by the wind, the range of the helicopter was much less than estimated. In addition, the reason for not accepting the launcher was the removal of missiles from the armament for which it was designed.
On November 11, 1965, the Council of Ministers issued a decree on the termination of work on the helicopter launcher.
|Mi-10RVK missile-helicopter system|
|Main propeller diameter, m||35.00;|
|The diameter of the tail rotor, m||6,30;|
|Weight, kg||empty - 25000, maximum takeoff - 44600;|
|Type of engine||2 GTE Aviadvigatel (Soloviev) D-25V;|
|Power, kW||2 ? 4045;|
|Maximum speed, km / h||200;|
|Cruising speed, km / h||185;|
|Practical range, km||650;|
|Radius of action, km||250;|
|Practical ceiling, m||3000;|
|Static ceiling, m||2200;|
|missile launcher 9P116|
|missile||S-5B (4K95) cruise missile|
|Weight without rocket, t||5,5;|
|Gross weight, t||12;|
|Height in the cab in the transport position, m||3,3;|
|Electric motor-wheels||4 x with power -22 kW;|
|gas-turbine engine||GTE-350 power - 350 hp;|
|Armament||cruise missile S-5V;|
|Time of transition to combat position, min||up to 5;|
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