|Mil Mi-10K of Vzlet in 2006.|
|Manufacturer||Mil Moscow Helicopter Plant|
|First flight||15 June 1960|
|Developed from||Mil Mi-6|
The Mil Mi-10 (NATO reporting name Harke), given the product number izdeliye 60, was a Soviet military transport helicopter of flying crane configuration, developed from the Mi-6, entering service in 1963.
Design and development
The advent of the Mi-6 gave the Soviet Union the very useful ability to move and place large, bulky or heavy loads with precision. Limitations of the Mi-6 in the flying crane role included a weight to payload ratio and the inability of the crew to easily see the load and its intended final position. A Council of Ministers directive of 20 February 1958 tasked OKB-329 (OKB Mil) with the development of a dedicated flying crane helicopter for carrying bulky loads unable to be carried in the hold of a Mi-6.
The Mil OKB's response drew heavily on the Mi-6, utilising the dynamic components and 4,100 kW (5,500 hp) Soloviev D-25V turboshaft engines, on a slim fuselage sitting on four tall strut braced undercarriage legs, with a wide track allowing the helicopter to taxi over loads, or for mobile loads to be moved underneath. The fuselage can carry 28 passengers inside the cabin as well as 3 t (3,000 kg; 6,600 lb) of cargo loaded through a side door in the aft fuselage, by an integral boom and winch. Underslung loads can be attached directly to the fuselage by hydraulically operated clamps, or carried on a 8.5 m × 3.6 m (28 ft × 12 ft) pallet lifted by the winch and braced by cables and/or struts to the undercarriage legs. The external sling system, with a capacity of 8 t (8,000 kg; 18,000 lb), of the Mi-6 could also be fitted under the centre fuselage.
The first prototype V-10 emerged with canted main undercarriage legs with single wheels on all four legs, as well as a retractable emergency escape chute extending below the cockpit and external auxiliary fuel tanks either side of the centre fuselage. As development progressed the main undercarriage legs were replaced with vertical units carrying twin wheels, twin nose undercarriage wheels after a period retaining the single wheels, an Auxiliary power unit (APU) installed behind the cockpit on the starboard side and emergency escape slide cables for use when the pallet is carried.
The first prototype V-10 was completed in 1959 and was soon allocated the service designation Mi-10. The first flight took place on 15 June 1960 and flight testing continued successfully until in May 1960 the first prototype crashed during a precautionary landing resulting from loss of gearbox oil pressure, only the Navigator/ radio operator surviving. After joining the flight test programme the second prototype began a series of world record breaking altitude/payload flights for turbine powered helicopters. State acceptance trials were passed successfully in 1961, but production did not commence until 5 March 1964 at the Rostov-on-Don factory, with first flight of a production aircraft on 10 September 1964, leading to a total of forty of the long-legged Mi-10 helicopters built, from 1964 to 1969.
Mi-10K (short legged version)
The limitations of the Mi-10 in the slung load mission soon became obvious, chiefly, the loss of payload due to the heavy and complicated undercarriage, and more importantly the almost complete lack of oversight of the slung load, despite the inclusion of a CCTV (closed circuit television) system intended for observation of slung loads.
Foregoing the requirement to carry palleted or podded cargoes, Mil redesigned the Mi-10 with a much shorter, fixed, four-leg undercarriage and replaced the extendible escape chute with a gondola fitted with flying controls for a pilot to fly the aircraft during slung load operations. The remainder of the aircraft is essentially identical with the long-legged version. Seventeen of the new flying crane were produced as the Mi-10K, including two conversions from Mi-10s from 23 March 1974 to 1977.
The operational service of the Mi-10 was of moderate success, being distributed mainly to units of the VVS (Voyenno-Vozdushnyye Sily - Soviet Air Force) which already operated the Mi-6. Operations with no load were found to be unstable, and the best procedure for take-off was found to be a rolling take-off, which usually also resulted in nose-wheel shimmy when lightly loaded. The main mission of the early Mi-10 virtually evaporated with the improvements in contemporary ballistic missiles; thus the majority of the long-legged variants were converted to Mi-10PP, (or mi-10P), airborne Electronic Counter-Measures helicopters, carrying a large ST-900 Step' (Step' - Steppe) ECM pod under the fuselage mounted on a pallet.
Other Mi-10 long legged aircraft were converted to carry out a wide variety of missions but usually only as single prototypes. Of special note was the Mi-10R (R - recordnyy- record) record breaking helicopter, converted from a production machine, with the undercarriage of a Mi-6 fitted with fairings and spats, as well as a tail bumper to reduce the risk of damage to the rear fuselage on landing. Other variants are noted or described below in the variants section.
Data from:Mil's heavylift helicopters : Mi-6, Mi-10, V-12 and Mi-26 The Mi-10R has held seven world records, none of which are still current, in the FAI E1 General class for rotorcraft powered by turbine engines.
|23 September 1961||Mi-10||Altitude with 15,000 kg (33,000 lb) payload||2,326 m (7,631 ft)||G.V. Alfyorov|
|23 September 1961||Mi-10||Maximum load to 2,000 m (6,600 ft)||15,103 kg (33,296 lb)||B.V. Zemskov|
|26 May 1965||Mi-10R||Altitude with 2,000 kg (4,400 lb) payload||7,151 m (23,461 ft)||V.P. Koloshenko|
|28 May 1965||Mi-10R||Altitude with 5,000 kg (11,000 lb) / 5,175 kg (11,409 lb) payload||7,151 m (23,461 ft)||V.P. Koloshenko|
|28 May 1965||Mi-10R||Altitude with 15,000 kg (33,000 lb) payload||2,840 m (9,320 ft)||G.V. Alfyorov|
|28 May 1965||Mi-10R||Altitude with 20,000 kg (44,000 lb) payload||2,840 m (9,320 ft)||G.V. Alfyorov|
|28 May 1965||Mi-10R||Altitude with 25,000 kg (55,000 lb) payload||2,840 m (9,320 ft)||G.V. Alfyorov|
|28 May 1965||Mi-10R||Maximum load to 2,000 m (6,600 ft)||25,105 kg (55,347 lb)||G.V. Alfyorov|
- izdeliye 60
- Product / article number.
- Prototypes of the Mil Mi-10 helicopter.
- Initial standard long-legged production helicopter
- A single production Mi-10 fitted with Grebeshok (Comb) direction finding equipment, for ELINT (Electronic Intelligence) duties, in a pod slung between the undercarriage legs.
- (K - kortkonogly - short legged) (NATO - Harke-B) Flying crane helicopter with short-legged narrow-track undercarriage and a ventral gondola for a second pilot.
- (RVK - raketno-vertolyotnyy kompleks - heliborne missile system) Numerous variations of heliborne missile systems were envisaged, but only the 9K74 (aka S-5V) system reached the flight test stage. Missiles on launchers were carried complete with tractor units to be deployed on landing. Due to the increased take-off weight of 44.6 t (44,600 kg)), the VRK was fitted with low-pressure tyres. Development was abandoned when the 4K95 cruise missile element was discontinued.
- (PP - Postanovschik Pomekh jammer) ECM (Electronic Counter-Measures) helicopter, preferred military alternative designation.
- Company / government designation for the ECM Mi-10PP.
- (R - recordnyy - redords) (NATO - Harke-A) A single standard production model fitted with a conventional undercarriage taken from the Mi-6 modified with spats and fairings, as well as a twin wheeled tail bumper. Some Western sources erroneously cite this aircraft as the Mi-10K.
- (ooniversahl'naya polevaya laboratoriya universal mineral laboratory) A single prototype modified to carry a detachable mobile laboratory module for ore analysis.
- Mi-10 flying crane
- A single prototype modified with 4,800 kW (6,500 hp) Soloviev D-25VF engines, new equipment and an up-rated transmission system.
- Crew: 4 or 5 (pilot, copilot, flight engineer, navigator/radio operator and optional technician)
- 28 passengers or
- 3 t (3,000 kg; 6,600 lb) internally
- up to 15 t (15,000 kg; 33,000 lb) payload on platform or
- 8 t (8,000 kg; 18,000 lb) max slung payload
- Length: 32.86 m (107 ft 10 in) , Mi-10K 32.4 m (106 ft) ignoring rotors
- Empty weight: 27,100 kg (59,745 lb) , Mi-10K 25,450 kg (56,110 lb)
- Gross weight: 43,550 kg (96,011 lb) , Mi-10K 37,000 kg (82,000 lb)
- Max takeoff weight: 43,700 kg (96,342 lb) , Mi-10K 38,000 kg (84,000 lb)Ground clearance under fuselage: 3.75 m (12.3 ft)
- Powerplant: 2 × Soloviev D-25V turboshaft, 4,100 kW (5,500 hp) each
- Main rotor diameter: 35 m (114 ft 10 in)
- Main rotor area: 962 m2 (10,350 sq ft)
- Maximum speed: 335 km/h (208 mph; 181 kn) , Mi-10K 350 km/h (220 mph; 190 kn)
- Cruising speed: 180 km/h (112 mph; 97 kn) , Mi-10K 228 km/h (142 mph; 123 kn)
- Range: 430 km (267 mi; 232 nmi) , Mi-10K 500 km/h (310 mph; 270 kn)
- Disk loading: 45.27 kg/m2 (9.27 lb/sq ft) , Mi-10K - 38.46 kg/m² (7.87 lb/sqft) at normal AUW
- Hovering ceiling out of ground effect: Mi-10 3,000 m (9,800 ft), Mi-10K 1,000 m (3,300 ft)
- Hovering ceiling in ground effect: Mi-10K 3,000 m (9,800 ft)
- Dynamic ceiling: Mi-10K 4,750 m (15,580 ft)
- Related development
- Aircraft of comparable role, configuration and era
- Gordon, Yefim; Dimitriy and Sergey Komissarov (2005). Mil's heavylift helicopters : Mi-6, Mi-10, V-12 and Mi-26. Red Star 22 (2nd edition ed.). Hinckley: Midland Publishing. ISBN 1-85780-206-3.
- "UTair helicopter Mi-10K". heli.utair.ru. Retrieved 10 March 2013.
- "Aeroflot in the 1980s". globalsecurity.org. Retrieved 10 March 2013.
- "Aeroflot Mil Mi-10". Demand media. Retrieved 10 March 2013.
- "MI-6 and Mi-10". 16va.be. Retrieved 10 March 2013.
- "Soviet Air Force Mil-Mi-10". Demand media. Retrieved 10 March 2013.
- J W R Taylor, ed. (1975). Jane's All The World's Aircraft,1975-76. London: Macdonald & Co. ISBN 0-354-00521-9.
|Wikimedia Commons has media related to Mil Mi-10.|