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Mil V-10 / Mi-10


The V-10 prototype was a development of the Mi-6 heavylift helicopter, but optimised for the flying-crane role. Retaining basically the same rotor, transmission and powerplant, the V-10 had a slender fuselage and appears (falsely) to be much greater in length. The Mi-10 is 31.8cm shorter than the Mi-6. Wide-track stalky quadricycle landing gear is provided, so that the helicopter can taxi over a bulky load that is to be carried externally, and because it is intended to be used more extensively in the heavylift role than the Mi-6, it dispenses with the stub wings of this earlier helicopter. First flown during 1960, the V-10 entered production as the Mil Mi-10, then gaining the NATO reporting name 'Harke', and was first demonstrated publicly at Tushino in July 1961,
Development aircraft had trapeze wires from above flight deck to front wheels for emergency crew escape in low hover. To counter side-thrust at tail and torque effects right legs 300mm shorter than left, crew cabin being canted to keep it laterally level on ground. The fuselage cabin is 14.04m long, 2.5m wide and 1.68m high for cargo and with 28 tip-up wall seats.

(Korotkonogii, short-legged) presaged by special Mi-10 flown 1965 with single centerline nose gear and single spatted main gears of min length and weight, used to lift 25,105kg to 2840m. This was restored to Mi-10R standard, but in 1966 OKB flew Mi-10K with four short landing gears reducing door sill height from almost 4 to 1.8m. New crew compartment with single pilot at original level and second in central all-glazed gondola facing aft with full controls for helicopter and load. Larger internal fuel cells, giving total with two external tanks of 9000 litres. Tail bumper and much narrower tail fin. Cleared for production October 1966, about 20 built. The Mi-10K differs from the Mi-10 by having an uprated 6500shp Soloviev D-25VF turboshafts in fully developed models. This allows a payload of 14,000kg in the slung mode, compared with the Mi-10's 8000kg. The main cabin can be used for freight and/or passengers, the latter totalling 28 on tip-up seats.

First displayed publicly in Moscow on 26 March 1966, the USSR revealed for the first time the Mi-10K. At least one Mi-10K has been seen with a conventional tricycle undercarriage; this may have been the machine which in May 1965 established a new load-to-altitude record by lifting a weight of 25105kg to a height of 2840m.



Items which are interchangeable between the Mi-6 and Mi-10 include the power plant, transmission system and reduction gearboxes, swashplate assembly, main and tail rotors, control system and most items of equipment. The power of the Soloviev turboshaft engines remains constant up to 3,000m and to an ambient temperature of 40 deg C at sea level. The aircraft will maintain level flight on one engine. Full navigation equipment and an autopilot permit all-weather operation, by day and night.

The tall long-stroke quadricycle landing gear, with wheel track exceeding 6.0m and clearance under the fuselage of 3.75m with the aircraft fully loaded, enables the Mi-10 to taxi over a load it is to carry and to accommodate loads as bulky as a prefabricated building.

Use can be made of interchangeable wheeled cargo platforms which are held in place by hydraulic grips controllable from either the cockpit or a remote panel. Using these grips without a platform, cargoes up to 20m long, 10m wide and 3.1m high can be lifted and secured in 1.5 to 2 minutes. The cabin can accommodate additional freight or passengers.

The standard Mi-10 rotor system is the same as for the Mi-6, except that main rotor shaft is inclined forward at an angle of only 0 deg 45'. The landing gear is a non-retractable quadricycle type, with twin wheels on each unit. All units fitted with oleo-pneumatic shock-absorbers. Telescopic main legs. Main wheels size 1,230 x 260mm each with brake. Levered-suspension castoring nose units. Nosewheels size 950 x 250mm. All landing gear struts are faired. The port nose gear fairing incorporates steps to the crew door. Despite the height of the gear, the Mi-10 can make stable landing and take-off runs at speeds up to 100km/h.

Two 4,101kW Soloviev D-25V turboshaft engines, are mounted side by side above cabin, forward of main rotor drive-shaft. Single fuel tank in fuselage (731 litres) and two external tanks (3500 litres each) on sides of cabin 2400 litres (1920kg), with total capacity of 6,184kg. Provision for carrying two auxiliary tanks in cabin, to give total fuel capacity of 8,260kg. Provision for pressure-fuelling from ground whilst hovering. Engine cowling side panels (opened and closed hydraulically) can be used as maintenance platforms when open.

The maximum payload is 11000kg, but this can be increased to 14000kg by installing Soloviev D-25VF engines, each of which yield 6500shp.

Two pilots and flight engineer accommodated on flight deck, which has bulged side windows to provide an improved downward view. Flight deck is heated and ventilated and has provision for oxygen equipment. Crew door is immediately aft of flight deck on port side. Main cabin can be used for freight and/or passengers, 28 tip-up seats being installed along the side walls. Freight is loaded into this cabin through a door on the starboard side, aft of the rear landing gear struts, with the aid of a boom and 200kg capacity electric winch. In addition to the cargo platform described earlier, the Mi-10 has external sling gear as standard equipment. This can be used in conjunction with a winch controlled from a portable control panel inside the cabin. The winch can also be used to raise loads of up to 500kg while the aircraft is hovering on rescue and other duties, via a hatch in the cabin floor. AI-8 turbine APU permanently installed for elctric/hydraulic power without main engines.
Equipped with anticing as the Mi-6A.


A closed-circuit TV system, with cameras scanning forward from under the rear fuselage and downward through the sling hatch, is used to observe the payload and main landing gear, touchdown being by this reference. The TV system replaces the retractable undernose 'dustbin' fitted originally.

Construction of both versions totalled 55 when production ended in 1971; manufacture was resumed briefly in 1977, but no new production figures have been quoted. Harke is operated by Aeroflot and by the Soviet forces in comparatively small num-bers. The Mi-10K is not known to be in military service.
All versions were grounded in August 1992.



Engine: 2 x D-25V turboshaft, rated at 4045kW
Main rotor diameter: 35.0m
Length without rotors: 32.86m
Height: 7.8m
Max take-off weight: 43450kg
Empty weight: 24680kg
Max speed: 235km/h
Cruising speed: 220km/h
Service ceiling: 3000m
Range with 8,000kg payload: 420km
Payload: 8000-12000kg

Engines: 2 x Soloviev D-25V single-shaft free-turbine engines driving common R-7 gearbox, 5,500 shp each.
Main rotor diameter: 114 ft 10 in (35 m)
Overall length (rotors turning): 137 ft 5½ in (41.89 m)
Fuselage length: 107 ft 9¾ in (32.86 m)
Height: 32 ft 2 in (9.8 m)
Empty weight 60,185 lb (27.300 kg)
Max loaded weight 96,340 lb (43.700 kg)
Max speed: 124 mph (200 km/ h)
Service ceiling: 9,842 ft (3000 m)
Range: (with 12,000 kg platform load) 155 miles (250 km)
Armament: normally none

Engine: 2 x Solovyov D-25V turboshaft, 4101kW
Main rotor diameter: 114 ft 10 in (35 m)
Overall length (rotors turning): 137 ft 5½ in (41.89 m)
Fuselage length: 107 ft 9¾ in (32.86 m)
Height: 25 ft 7 in (7.8 m)
Empty weight 54,410 lb (24,680 kg)
Max loaded weight 83,776 lb (38,000 kg)
Service ceiling: 9,842 ft (3000 m)
Armament: normally none.
Range with typical payload: 250km
Max payload: 11000kg







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