Mil Mi-2 "Hoplite"

Mil Mi-2

The Mil Mi-2 (NATO reporting name Hoplite) is a small, lightly armored turbine-powered transport helicopter that could also provide close air support when armed with 57 mm rockets and a 23 mm cannon.Chronologically later than Mi-4 and Mi-6, Mi-2 was planned 1958-59 as modernized turbine derivative of Mi-1, just as Mi-8 was to Mi-4. Originally Mi-1 dynamic parts retained and mated with completely new fuselage, all light-alloy monocoque with steel forgings at concentrated loads, with twin turboshaft engines above cabin ahead of gearbox. Structural basis deep floor box carrying wheel or ski landing gears and housing flexible fuel cell of 600 lit. Normal accommodation for pilot and passenger (on right) with main cabin for 700kg cargo or seat unit for three passengers facing forward and three facing aft, with eighth passenger seat on right opposite rear door. Option of four stretchers and attendant, or slung load of 1.2t or two 600 lit ag containers. All versions plumbed for two 250-lit auxiliary tanks on sides.

First flight of V-2 Sept 1961. Subsequently developed as production Mi-2 with bonded/welded fuselage, hub with hydraulic instead of friction dampers, bleed-air anticed intakes, tail rotor with bonded-metal honeycomb blades and electro-thermal de-icing on all blades. Whole program transferred to WSK-Swidnik in Poland in Jan 1964. All production and development subsequently at WSK, involving 12 series versions including SAR, photo, anti-armour and gunship. Total by 1993 over 5320. ASCC name "Hoplite".

The Mi-2 was first introduced into the Soviet Air Force in 1965. The Mi-2 is used by mainly former Soviet and Eastern Bloc countries, although it was also purchased by Mexico and Myanmar armed forces. Most of the armed Mi-2 variants were used by Poland. Some were also used by the former East Germany (with machine gun and unguided rocket armament only).

North Korea still maintains a large active fleet of over 160 Mi-2s.

General characteristics

• Crew: One
• Capacity: 8 passengers or 700 kg (1,543 lb) internal, 800 kg (1,764 lb) external cargo
• Length: 11.40 m (37 ft 4¾ in)
• Rotor diameter: 14.50 m (47 ft 6⅞ in)
• Height: 3.75 m (12 ft 3½ in)
• Disc area: 165.13 m² (1,777.44 ft²)
• Empty weight: 2,372 kg (5,218 lb)
• Loaded weight: 3,550 kg (7,826 lb)
• Max. takeoff weight: 3,700 kg (8,157 lb)

Performance

• Maximum speed: 200 km/h (108 knots, 124 mph)
• Range: 440 km (237 nmi, 273 mi)(max internatal fuel, no reserves)
• Service ceiling: 4,000 m (13,125 ft)
• Rate of climb: 4.5 m/s (885 ft/min)
• Disc loading: 22.41 kg/m² (4.59 lb/ft²)