MIL  MI-2
^"HOPLITE^"

 El Mi-2 voló por primera vez en septiembre de 1961, diseñado en la USSR por Mikhail L. Mil. El desarrollo de los dos prototipos continúo en la USSR hasta que el helicóptero completó su fase inicial de pruebas, luego, de acuerdo con el contrato firmado en enero de 1964, la producción y marketing del Mi-2 fue asignado a la industria polaca. El primer ejemplar de Mi-2 de esta industria voló el 4 de noviembre de 1965.

La producción en serie comenzó en 1965, y la compañía Swidnik construyó mas de 5250 máquinas para operadores civiles y militares, la mayoría de estos ejemplares fueron exportados. Entre los operadores se cuentan a Bulgaria, Checoslovaquia, Alemania, Hungría, Irak, Corea del Norte, Libia, Polonia (Mi-2CH, Mi2T, Mi-2URN, Mi-2URP y Mi-2US), Siria y la USSR, y operadores civiles en Europa y otros países.

Durante la producción, el Mi-2 estuvo bajo un continuo perfeccionamiento, siendo desarrollado con nuevas versiones para cumplir con requerimientos específicos de los clientes. Las principales versiones civiles en ser producidas recientemente son:

• Transporte de pasajeros y/o carga.
• Ambulancia y rescate (Mi-2R).
• Versión de agricultura.
• Versión carguera pura, con gancho de carga y grúa eléctrica.
• Versión de entrenamiento.
• Versión para fotografía aérea.

Las principales versiones militares son:

• Mi-2URN: Como el Mi-2US, pero con lanzacohetes Mars 2. En servicio desde 1973.
• Mi-2URP: Versión antitanque, con lanzadores de misiles a cada lado del fuselaje. En servicio desde 1976.
• Mi-2US: Versión cañonera, equipada con cañón de 23 mm y dos ametralladores de 7,62 mm.

Los detalles explicados a continuación son específicamente sobre el Mi-2 básico, excepto donde se indique lo contrario:

TIPO: Helicóptero bimotor liviano, de uso múltiple.

SISTEMA DE ROTOR: Compuesto por tres palas metálicas con amortiguadores hidráulicos. Sección NACA 230-12M. Las palas del rotor principal y las dos del rotor de cola son de duraluminio. Servos hidráulicos para el control lateral, longitudinal y pitch. Sistema eléctrico para deshielo de las palas de los dos rotores. Rotores no plegables. Freno de rotor.

FUSELAJE: Semi-monocoque realizado en tres partes principales: la nariz (incluida la cabina), la sección central y el cono de cola. Construido en hojas de duraluminio, pegadas y soldadas por puntos o remachadas . Las zonas principales de junturas son realizas de aleación de acero.

UNIDAD DE COLA: Tiene un estabilizador de incidencia variable controlado por la palanca del pitch.

TREN DE ATERRIZAJE: Tipo triciclo fijo, mas un esquí de cola. En la trompa posee dos ruedas y una sola en cada unidad del tren principal, estas con un amortiguador óleo-neumático. Frenos neumáticos sobre las ruedas principales. Tren de aterrizaje con esquíes opcional.

MOTOR: Dos turbinas Isotov GTD-350 de 298 kW (400 shp), montadas lado a lado sobre la cabina. Tanque de combustible único de 600 litros, bajo el piso de la cabina.

DISPOSICIÓN: Un piloto y asientos para hasta 8 pasajeros en una cabina con aire acondicionado, comprende bancos espalda contra espalda de tres pasajeros cada uno, con dos opcionales mas sentados al fondo de la cabina, uno detrás del otro. Todos los asientos son removibles pudiéndose llevar hasta 700 Kg. (1543 lb) de carga. La versión ambulancia puede llevar cuatro camillas y un médico. La calefacción, ventilación y aire acondicionado son estándar. Parabrisas con deshielador eléctrico.

SISTEMAS: Calefacción de cabina por medio de aire sangrado de la turbina; ventilación. Sistema hidráulico para los controles cíclico y colectivo. Sistema eléctrico de AC y 24 DC.

AVIONICA: Items estándar incluye dos radios MF/HF, giro compás, altímetro, etc. Algunas versiones militares poseen radar.

EQUIPAMIENTO: La versión de agricultura lleva unos silos a cada lado del fuselaje de 1000 litros (264 US gallons) en total y barras para aspersión. En la versión de búsqueda y rescate posee una grúa eléctrica con capacidad de 120 Kg. (264 lb.). El gancho de carga soporta hasta 800 Kg. (1763 lb.)

  The M.L.Mil Mi-2, first flown in September 1961, was designed in the USSR by the Mikhail L. Mil bureau. Development of the two prototypes continued in the USSR until the helicopter had completed its initial State trials programme. Then, in accordance with an agreement signed in January 1964, further development, production and marketing of the Mi-2 were assigned exclusively to the Polish aircraft industry, which flew its own first example of the Mi-2 on 4 November 1965.

Series production began in 1965, and Swidnik has since built more than 5250 for various civil and military operators; the majority of these have been exported. Among the operators of the Mi-2 are the air forces of Bulgaria, Czechoslovakia, Germany, Hungary, Iraq, North Korea, Libya, Poland (Mi-2CH, Mi2T, Mi-2URN, Mi-2URP and Mi-2US and other variants), Syria and the USSR, and civil operators in European and various developing countries. Production of the Mi-2B (see separate entry) accounts for ``a few per cent'' of the overall total.

During the course of production the Mi-2 has undergone continuous improvement and upgrading, with versions for new applications being developed to meet specific customers requirements. The principal civil versions being produced recently were as follows:

• Convertible passenger/cargo transport;
• Ambulance and rescue versions (Mi-2R);
• Agricultural version, for dusting or conventional and ultra-low-volume spraying. In service in Bulgaria, Czechoslovakia, Egypt, Iraq, Poland and USSR;  
• Freighter version, with external cargo sling and electric hoist;
• Training version.
• Aerial photography versions, able to carry photographic, photogrammetric, thermal imaging or TV cameras for oblique or vertical pictures.

The following armed military variants have been produced:

• Mi-2URN: As Mi-2US, but with four Mars 2 launchers (each with 16 S-5 57mm unguided rockets) instead of pylon mounted gun pods. PKV gunsight in cockpit for aiming of all weapons. In service since 1973. 

• Mi-2URP: Anti-tank version, with cabin-side outriggers for four 9M14M Malyutka (AT-3 `Sagger') wire-guided missiles. Four additional missiles carried in cargo compartment. In service since 1976; later version can carry four 9M32 Strela 2 missiles.

• Mi-2US: Gunship version, equipped with 23mm NS-23KM cannon on port side of fuselage, two 7.62mm gun pods on each side pylon, and two other 7.62mm PK type movable machine guns in rear cabin.

The following details apply specifically to the basic Mi-2, except where indicated:

TYPE : Twin-turbine general purpose light helicopter.

ROTOR SYSTEM: Three-blade main rotor fitted with hydraulic blade vibration dampers. All-metal blades, of NACA 230-12M section. Flapping, drag and pitch hinges on each blade. Main rotor blades and those of two-blade tail rotor each consist of an extruded duralumin spar with bonded honeycomb trailing-edge pockets. Anti-flutter weights on leading-edges, balancing plates on trailing-edges. Hydraulic boosters for longitudinal, lateral and collective pitch controls. Coil spring counterbalance mechanism in main and tail rotor systems. Pitch change centrifugal loads on tail rotor carried by ribbon type steel torsion elements. Rotors do not fold. Electric blade de-icing system for main and tail rotors. Rotor brake fitted. Freewheel units permit disengagement of a failed engine and also autorotation.

FUSELAGE : Conventional semi-monocoque structure of pod and boom type, made up of three main assemblies: the nose (including cockpit), central section, and tailboom. Construction is of sheet duralumin, bonded and spot welded or riveted to longerons and  frames. Main load bearing joints are of steel alloy.

TAIL UNIT : Variable incidence horizontal stabiliser controlled by collective pitch lever.

LANDING GEAR : Non-retractable tricycle type, plus tailskid. Twin-wheel nose unit. Single wheel on each main unit. Oleo-pneumatic shock absorbers in all units, including tailskid. Main shock absorbers designed to cope with both normal operating loads and possible ground resonance. Mainwheel tyres size 600x180, pressure 4.41 bars (64 lb/sq in). Nosewheel tyres size 400x125, pressure 3.45 bars (50 lb/sq in). Pneumatic brakes on mainwheels. Metal ski landing gear optional.

POWER PLANT : Two 298 kW (400 shp) Polish built Isotov GTD-350 turboshafts, mounted side by side above cabin. Fuel in single rubber tank, capacity 600 litres (158.5 US gallons; 131 Imp gallons), under cabin floor. Provision for carrying a 238 litre (63 US gallon; 52.4 Imp gallon) external tank on each side of cabin. Refuelling point in starboard side of fuselage. Oil capacity 25 litres (6.6 US gallons; 5.4 Imp gallons). Engine air intake de-icing by engine bleed air.

ACCOMMODATION : Normal accommodation for one pilot on flight deck (port side). Seats for up to eight passengers in air-conditioned cabin, comprising back to back bench seats for three persons each, with two optional extra starboard side seats at the rear, one behind the other. All passenger seats are removable for carrying up to 700kg (1543 lb) of internal freight. Access to cabin via forward hinged doors on each side at front of cabin and aft on port side. Pilot's sliding window jettisonable in emergency. Ambulance version has accommodation for four stretchers and a medical attendant, or two stretchers and two sitting casualties. Side by side seats and dual controls in pilot training version. Cabin heating, ventilation and air-conditioning standard. Electric de-icing of windscreen.

SYSTEMS: Cabin heating, by engine bleed air, and ventilation; heat exchangers warm atmospheric air for ventilation system during cold weather. Hydraulic system, pressure 65 bars (940 lb/sq in), for cyclic and collective pitch control boosters. Hydraulic fluid flow rate 7.5 litres (1.98 US gallons; 1.65 Imp gallons)/min. Vented reservoir, with gravity feed. Pneumatic system, pressure 49 bars (710 lb/sq in), for mainwheel brakes. AC electrical system, with two STG-3 3kW engine driven starter/generators and 208V 16kVA three-phase alternator. 24V DC system, with two 28Ah lead-acid batteries.

AVIONICS : Standard items include two transceivers (MF/HF), gyro compass, radio compass, radio altimeter, intercom system and blind-flying panel. Nose and tail warning radar fitted to some military versions.

EQUIPMENT: Agricultural version carries a hopper on each side of the fuselage (total capacity 1000 litres; 264 US gallons; 220 Imp gallons of liquid or 750 kg; 1650 lb of dry chemical) and either a spraybar to the rear of the cabin on each side or a distributor for dry chemicals under each hopper. Swath width covered by the spraying version is 40-45m (130-150 ft). As a search and rescue aircraft, an electric hoist, capacity 120kg (264 lb), is fitted. In the freight role an underfuselage hook can be fitted for suspended loads of up to 800kg (1763 lb). Illustrations in the Polish press have shown a version equipped for laying smokescreens. Diesel oil from external tanks on each side of the cabin is injected into large-diameter pipes extending backward and downward from the upper part of the rotor pylon. These pipes do not touch the engine exhausts but are warmed sufficiently to convert the diesel oil into dense white smoke. Electrically operated wiper for pilot's windscreen. Fire extinguishing system, for engine bays and main gearbox compartment, is generally similar to, but simpler than, the Freon system fitted to the Soviet M.L.Mil Mi-8, and can be actuated automatically or manually.

JANE'S ALL THE WORLDS AIRCRAFT 1991/1992

Characteristics
Características

Information
Información

Characteristics
Características

Information
Información

1961

  2 Isotov
GTD-350P

1 / 8

400 SHP each

2400 Kg

3280 Ft

3550 Kg

6560 Ft

 102 Kts

13125 Ft

113 Kts

237 NM

Dimensions / Dimensiones

37,40 Ft
11,40 m

47,57 Ft
14,50 m

12,30 Ft
3,75 m

8,85 ft
2,70 m