Aviation weapons of the Mi 8 helicopter. Russian Aviation

At the end of the 1950s, work began abroad and here on the creation of second-generation helicopters with turboshaft engines, and in May 1960. at the Moscow Helicopter Plant the development of a new multi-purpose helicopter began to replace the multi-purpose helicopters that have proven themselves in operation Mi-4 . The first experimental helicopter V-8 , with one gas turbine engine AI-24V designs by S.P. Izotov and a four-blade main rotor from a helicopter Mi-4 , designed to carry 25 passengers, made its first flight in June 1961, and on July 9 it was first demonstrated at an air festival at the Tushino airfield in Moscow; several helicopters were built.

The main attention was paid to the development of a twin-engine helicopter with a new five-bladed main rotor, developed on the basis of modified all-metal helicopter blades Mi-4 , and a new rigid tail rotor. Second experimental helicopter V-8, with two gas turbine engines TB2-117 power by 1267kW, made its first flight on September 17, 1962, successfully passed flight tests and since 1965. began mass production at the helicopter plant in Kazan under the designation Mi-8. A number of original technical solutions were used in the design of the helicopter: large-sized duralumin stampings and glue-welded joints, new system external suspension, automatic system regulating the operation of engines, ensuring their synchronization and maintaining the rotor speed within specified limits. Compared to a helicopter Mi-4 the new helicopter had higher flight characteristics and twice the payload capacity. By helicopter Mi-8 in 1964-1969 7 international records were set, most of which were women's, set by pilots L.G. Isaeva, N.A. Kolets and T.V. Russiyan, and unsurpassed to this day.

Helicopters Mi-8 are the most common transport helicopters in the world, second only to light multi-purpose and transport Bell UH-1 "Iroquois" And "Huey" . In total, more than 8,000 helicopters were produced Mi-8 at the Kazan Helicopter Plant and the Aviation Plant in Ulan-Ude, of which more than 2,000 were exported to more than 40 countries, where half of them are still in operation.

Helicopters Mi-8 were produced in more than 30 different civil and military modifications, among which the main ones:

• Mi-8P- passenger helicopter with gas turbine engine TV2-117A power by 1267kW, with a cabin for 28 passengers and square windows;
• Mi-VPS "Salon"- a passenger helicopter with a high-comfort cabin for 11 passengers with an eight-seat common seat on the right side and two seats and a rotating seat on the left side, improved interior trim and a ventilation system and a toilet; also produced in versions with a cabin for 9 and 7 passengers;
• Mi-8T- transport helicopter with gas turbine engine TV3-117MT power by 1454 kW, for transportation of goods weighing 4000kg in the cabin, or 3000kg on an external sling, or 24 passengers on the side seats, or 12 patients on stretchers with accompanying persons; It is distinguished by small round cabin windows and equipment; in military versions it is equipped with pylons with holders for weapons.
• Mi-8TG- modification of the Mi-8T helicopter with gas turbine engine TV2-117TG power by 1103kW, developed in 1987, the world's first helicopter that uses liquefied petroleum gas along with aviation fuel;
• Mi-8TV- a landing transport helicopter for the armed forces with reinforced truss pylons with four holders for blocks of 32 NAR caliber 57mm or other weapons and a mobile installation with a machine gun caliber 12.7mm in the bow, it is possible to install triple holders for weapons from six blocks of 32 NAR, and on guide rails up to six ATGMs AT-2 with semi-automatic control; also produced in an export version with six ATGMs AT-3 with manual control. More than 250 helicopters Mi-8TB And M.T. were converted into Mi-17 .
• Mi-8MT- modernized airborne transport helicopter with gas turbine engine TV3-117MT power by 1454kW, with dust protection devices, auxiliary power plant AI-9V and a tail rotor mounted on the left to increase efficiency; the helicopter is a transitional model to an improved helicopter Mi-17 ; was produced in variants Mi-8AM And MI-8MTV with various equipment and weapons and in the variant Mi-8MTB-1A for civil use;
• Mi-8PP- active jamming helicopter with a container and cross-shaped dipole antennas on the sides of the fuselage; A number of modifications were also built for electronic warfare, relaying, etc.
• Mi-9- a helicopter to provide communication with additional antennas on the tail boom;
• Mi-18 - military transport helicopter, helicopter modification Mi-8T with a cabin length increased by 1 m, which made it possible to accommodate more than 38 soldiers or cargo weighing 5-6.5t, and on the external sling - loads weighing 5t. In 1980 two helicopters Mi-8MT have been modernized to Mi-18 with an enlarged cabin, new fiberglass blades and a retractable tricycle landing gear, and in 1982. passed flight tests that confirmed an increase in payload capacity with an increase in speed and flight range by 10-15%;
• Mi-8MTV-2 And 3 - the latest military transport modifications, intended for use in airborne transport, ambulance, rescue and combat versions, with weapons from four blocks B8V20-A 20 NAR each S-8, the firing of which is controlled by the PUS-36-71 sight; it is possible to mount aerial bombs with caliber 50-500kg on beam holders BDZ-57KRVM; in the bow there can be placed a mobile installation with a machine gun caliber 12.7mm, in the sliding door openings there are up to 8 pivot installations with machine guns of caliber 7.62mm, and on the holders - 4 gun containers UPK-23-250 with guns GSh-23L caliber 23mm what does a helicopter do Mi-8MTV-2 the most heavily armed in the world. To dissipate the heat flow of the gas turbine engine, screen-exhaust devices are installed, and to protect against guidance missiles with an IR system, the helicopter is equipped with a passive jamming system consisting of 4 ACO-2B cassettes on the tail boom and 6 cassettes on the fuselage; Each cassette contains 32 PPI-26-1 IR decoys and pulsed IR signal generators. The helicopter is equipped with armor plates covering the floor, front and rear parts of the cockpit and hydraulic panel. The helicopter can be equipped with radar and long-range navigation radio equipment;
• Mi-8AMTSH- option combat helicopter Mi-8AMT, with a complex of supersonic ATGMs "Storm"; demonstrated at the Farnborough Aerospace Exhibition in September 1996.

DESIGN. The helicopter is made according to a single-rotor design with a tail rotor, two gas turbine engines and a tricycle landing gear.

The helicopter fuselage has a frame structure and consists of the nose and central parts, tail and end beams. In the bow there is a three-seat crew cabin, consisting of two pilots and a flight mechanic. Cabin glazing provides good review, the right and left sliding blisters are equipped with emergency release mechanisms. In the central part there is a cabin with dimensions of 5.34 x 2.25 x 1.8 m in the transport version with a cargo hatch with doors that increase the length of the cabin to 7.82 m, and a central sliding door with dimensions of 0.62 x 1.4 m with an emergency release mechanism; mooring units and an electric winch are located on the floor of the cargo compartment, and an electric winch boom is installed above the door. The cargo compartment is designed to transport cargo weighing up to 4 tons and is equipped with folding seats for 24 passengers, as well as attachment points for 12 stretchers. In the passenger version, the cabin has dimensions of 6.36 x 2.05 x 1.7 m and 28 seats, two installed on each side with a pitch of 0.74 m and a passage of 0.3 m; in the rear of the cabin there is a wardrobe on the right, and in the rear of the doors there is an opening for the rear entrance door, consisting of doors and a ladder.

The tail boom is of a riveted beam-stringer type with working skin, equipped with units for attaching a controlled stabilizer and a tail support.

Stabilizer with a size of 2.7 m and an area of ​​2 m 2 with a NACA 0012 profile of a single-spar design, with a set of ribs and duralumin and fabric covering.

The chassis is tricycle, non-retractable, the front support is self-orienting, with two wheels measuring 535 x 185 mm, the main supports are of a shaped type with liquid-gas double-chamber shock absorbers and wheels measuring 865 x 280 mm. The tail support consists of two struts, a shock absorber and a support heel; chassis track 4.5m, chassis base 4.26m.

Main rotor with hinged blades, hydraulic dampers and pendulum vibration dampers, installed with a forward inclination of 4° 30". All-metal blades consist of a pressed spar made of AVT-1 aluminum alloy, hardened by work hardening with steel hinges on a vibration stand, a tail section, a steel tip and tip The blades have a rectangular shape in plan with a chord of 0.52 m and NACA 230 profiles with a relative thickness of 12% to 11.38% and a geometric twist of 5%, the peripheral speed of the blade tips is 217 m/s, the blades are equipped with a visual alarm system for spar damage and an electrothermal anti-icing device. .

The tail rotor with a diameter of 3.9 m is three-blade, pushing, with a cardan-type hub and all-metal blades of rectangular shape in plan, with a chord of 0.26 m and a NACA 230M profile.

The power plant consists of two turboshaft gas turbine engines with a free turbine TV2-117AT of the St. Petersburg NPO named after. V.Ya.Klimov with a take-off power of 1250 kW per Mi-8T or TVZ-117MT - 1435 kW per Mi-8MT, AMT And MTB, installed on top of the fuselage and closed by a common hood with opening flaps. The engine has a nine-stage axial compressor, an annular combustion chamber and a two-stage turbine. Engine length 2.835m, width 0.547m, height 0.745m, weight 330kg. The engines are equipped with dust protection devices.

The fuel system consists of a consumable fuel tank with a capacity of 445 l, a left external tank of 745 or 1140 l, a right external tank of 680 or 1030 l, an additional tank of 915 l in the cargo compartment.

The transmission consists of main, intermediate and tail gearboxes, brake shafts, and a main rotor. The VR-8A three-stage main gearbox provides power transfer from engines with an output shaft rotation speed of 12,000 rpm to the main rotor with a rotation speed of 192 rpm, the tail rotor - 1,124 rpm and the fan - 6,021 rpm for cooling , engine oil coolers and main gearbox; The total capacity of the oil system is 60 kg.

The control is duplicated, with rigid and cable wiring and hydraulic boosters driven from the main and backup hydraulic systems. The AP-34B four-channel autopilot ensures stabilization of the helicopter in flight in roll, heading, pitch and altitude. The main hydraulic system with a working pressure of 4.5 MPa provides power to all hydraulic units, and the backup one, with a pressure of 6.5 MPa, provides power only to the hydraulic boosters.

Equipment. The heating and ventilation system supplies heated or cold air to the crew and passenger cabins; the anti-icing system protects the main and tail rotor blades, the front windows of the cockpit and engine air intakes from icing.

Equipment for instrument flights in difficult meteorological conditions day and night includes two attitude indicators EPIRB-ZK, two NV rotation speed indicators, a combined exchange rate system GMK-1A, automatic radio compass ARK-9 or ARK-U2, radio altimeter RV-3.

Communication equipment includes VHF command radios R-860 and R-828, HF radios R-842 and Karat, and an aircraft intercom SPU-7. On Mi-8T there is RI-65 voice communication equipment to notify the crew about emergency situations in flight. On military variants Mi-8MT an IR jamming station "Linden", a screen-exhaust device for suppressing IR radiation from engines, containers with LC, and an armored cockpit were installed.

At the request of the customer, an external load suspension system is installed: cable for 3000 kg and articulated-pendulum for 2500 kg and a winch with a lifting capacity of 150 kg.

Armament. Military versions use a machine gun with a caliber of 12.7 or 7.62 mm in the nose mobile installation, built-in holders on shaped pylons on the sides of the fuselage for installing up to six NAR units with up to six ATGMs placed on top on guide rails. Containers with machine guns or cannons can also be suspended on pylons, and machine guns and grenade launchers can be mounted on pins in the blisters and side openings of the cargo compartment.

E.I.Ruzhitsky "Helicopters", 1997

Technical data Mi-8T

Power point: 2 x GTD TV2-117A power by 1250kW, main rotor diameter: 21.29m, fuselage length: 18.17m, height: 4.38m, fuselage width: 2.5m, take-off weight: 12000kg, empty weight: 6625kg, maximum speed: 250km/h, cruising speed: 225km/h, dynamic ceiling: 4500m, flight range:

GENERAL CHARACTERISTICS OF THE MI-8T HELICOPTER

1. GENERAL INFORMATION ABOUT THE HELICOPTER

The Mi-8 helicopter is designed to transport various cargoes inside the cargo compartment and on an external sling, mail, passengers, as well as for carrying out construction, installation and other work in hard-to-reach areas.

Rice. 1.1. Mi-8 helicopter (general view)

The helicopter (Fig. 1.1) is designed using a single-rotor design with a five-blade main rotor and a three-blade tail rotor. The helicopter is equipped with two TV2-117A turboprop engines with a take-off power of 1,500 hp. each, which ensures high flight safety, since flight is possible even if one of the engines fails.

The helicopter is operated in two main versions: the passenger Mi-8P and the transport Mi-8T. The passenger version of the helicopter is designed for interregional and local transportation of passengers, baggage, mail and small-sized cargo. It is designed to carry 28 passengers. The transport option provides for the transportation of cargo weighing up to 4000 kg or passengers in the amount of 24 people. At the request of the customer, the passenger cabin of the helicopter can be converted into a cabin with increased comfort for 11 passengers.

The passenger and transport versions of the helicopter can be converted into an ambulance version and into a version for operation with an external sling.

The ambulance version of the helicopter allows you to transport 12 bedridden patients and an accompanying medical worker. In the version for working with external sling, large cargo weighing up to 3000 kg is transported outside the fuselage.

For long-range helicopter flights, it is possible to install one or two additional fuel tanks in the cargo compartment.

Existing versions of the helicopter are equipped with an electric winch, which allows, using an onboard boom, to lift (lower) loads weighing up to 150 kg on board the helicopter, and also, if there is a pulley system, to pull wheeled loads weighing up to 3000 kg into the cargo compartment.

The helicopter crew consists of two pilots and a flight mechanic.

When creating a helicopter special attention attention was paid to high reliability, efficiency, ease of maintenance and operation.

Safety of flights on the Mi-8 helicopter is ensured by:

The installation of two TV2-117A(AG) engines on the helicopter, the reliability of the operation of these engines and the VR-8A main gearbox;

The ability to fly in the event of failure of one of the engines, as well as switch to autorotation mode (self-rotation of the main rotor) in the event of failure of both engines;

The presence of compartments that isolate the engines and the main gearbox using fire partitions;

Installation of a reliable fire protection system that ensures extinguishing a fire in the event of its occurrence, both simultaneously in all compartments and in each compartment separately;

Installation of backup units in the main systems and equipment of the helicopter;

Reliable and effective anti-icing devices for the main and tail rotor blades, engine air intakes and cockpit windshields, which allows flight in icing conditions;

Installation of equipment that ensures simple and reliable piloting and landing of a helicopter in various meteorological conditions;

Drive of the main units of the systems from the main gearbox, ensuring the operability of the systems in the event of engine failure:

The ability to quickly leave the helicopter after landing by passengers and crew in emergency situations.

2. BASIC HELICOPTER DATA

Flight data

(transport and passenger options)

Take-off weight (normal), kg.................. 11100

Maximum speed flight (instrument), km/h, 250

Static ceiling, m........................ 700

Instrument cruise speed at altitude
500 m, km/h ……………………………………………220

Economic flight speed (instrument), km/h. 120

fuel 1450 kg, km................................ 365

option with fuel filling 2160 kg, km. . .620

Flight range (at an altitude of 500 m) in ferry
option with fuel filling 2870 kg, km... 850

Flight range (at an altitude of 500 m) with refueling
fuel 2025 kg (outboard tanks of increased
capacity), km................................................... ..575

Flight range (at an altitude of 500 m) in ferry
version with fuel filling 2735 kg (outboard tanks

increased capacity), km.... 805

Flight range (at an altitude of 500 m) in ferry
version with fuel refueling 3445 kg (outboard tanks

increased capacity), km.... 1035

Note. Flight range is calculated taking into account 30 minutes of fuel remaining after landing

Geometric data

Helicopter length, m:

without main and tail rotors................... 18.3

with rotating main and tail rotors ...25,244

Helicopter height, m:

without tail rotor................................... 4.73

with rotating tail rotor................ 5.654

Distance from the tip of the main rotor blade to
tail boom when parked, m.................. 0.45

Distance from ground to lowest point fuselage

(clearance), m................................................... ...... 0.445

Area of ​​horizontal tail, m 2 ..... 2

Helicopter parking angle................. 3°42"

Fuselage

Cargo compartment length, m:

without cargo doors........................ 5.34

with cargo doors at 1 m from the floor 7.82

Cargo compartment width, m:

on the floor................................................ ... 2.06

for heating ducts........................ 2.14

maximum........................................ 2.25

Cargo compartment height, m.................. 1.8

Distance between power floor beams, m ... 1.52

Escape hatch size, m…………………… 0.7 X1

Loading ramp track, m.................. 1.5±0.2

Passenger cabin length, m............ 6.36

Passenger cabin width (floor), m... 2.05

Passenger cabin height, m ​​1.8

Seat pitch, m................................................... .... 0.74

Passage width between seats, m... 0.3

Wardrobe dimensions (width, height, depth), m 0.9 X1.8 X 0.7
» sliding door (width, height), m. 0.8 X1.4
» opening, along the rear entrance door in the passenger

option (width, height), m.......... 0.8 X1>3

Size of emergency hatches in passenger compartment

option, m........................................ 0, 46 X0.7

Crew cabin size, m................... 2.15 X2.05 X1.7

Adjustment data

Angle of installation of the main rotor blades (according to the rotor pitch indicator):

minimum................................................. 1°

maximum........................................ 14°±30"

Deflection angle of the trimmer plates of the propeller blades -2 ±3°

» installation of tail rotor blades (at r=0.7) *:

minimum (left pedal all the way) ................... 7"30"±30"

maximum (right pedal all the way)………….. +21°±25"

* r- relative radius

Weight and centering data

Take-off weight, kg:

maximum for transport option…….. 11100

» with a load on an external sling …………… 11100

transport option........................... 4000

on external sling......................... 3000

passenger version (person).......... 28

Empty helicopter weight, kg:

passenger version........................... 7370

transport »................................ 6835

Weight of service load, including:

crew weight, kg................................... 270

» oil, kg................................................... ............. 70

weight of products, kg................................................... 10

» fuel, kg................................................... .......... 1450 - 3445

» commercial load, kg........................ 0 - 4000

Empty helicopter alignment, mm:

transport option........................................ +133

passenger » ..................................... +20

Acceptable alignments for a loaded helicopter, mm:

front................................................... ............. +370

rear................................................... .................... -95

3. AERODYNAMIC AND GEOMETRIC CHARACTERISTICS OF THE HELICOPTER

According to the aerodynamic design, the Mi-8 helicopter is a fuselage with a five-bladed main rotor, three-bladed tail rotor and fixed landing gear.

The main rotor blades are rectangular in plan with a chord equal to 0.52 m. The rectangular plan is considered aerodynamically worse than others, but it is easy to manufacture. The presence of trimmer plates on the blades allows you to change their torque characteristics.

The blade profile is the most important geometric characteristic of the rotor. The helicopter has different profiles along the length of the blade, which significantly improves not only the aerodynamic characteristics of the main rotor, but also the flight properties of the helicopter. From the 1st to the 3rd section, the NACA-230-12 profile is used, and from the 4th to the 22nd - the NACA-230-12M profile (modified) *. The NACA-230-12M airfoil has Mkr = 0.72 at an angle of attack of zero lift. With increasing angles of attack a° (Fig. 1.2), Mkr decreases even at the most favorable angle of attack, at which the lift coefficient C y = 0.6, Mkr = 0.64. In this case, the critical speed in the standard atmosphere above sea level will be:

V KP == a Mkr = 341 0.64 = 218 m/s, where a is the speed of sound.

Consequently, at the ends of the blades it is possible to create a speed of less than 218 m/s, at which shock waves and wave resistance will not appear. At the optimal rotor speed of 192 rpm, the peripheral speed of the blade tips will be:

U = wr = 2 prn / 60 = 213.26 m/s, where w is the angular velocity;

r is the radius of the circle described by the tip of the blade.

Rice. 1.2. Change in the lift coefficient C y from the angles of attack a° and the M number of the NACA-230-12M profile

This shows that the peripheral speed is close to the critical speed, but does not exceed it. The helicopter main rotor blades have a negative geometric twist, varying according to a linear law from 5° at the 4th section to 0° at the 22nd section. In the area between the 1st and 4th sections there is no twist and the installation angle of the blade sections in this area is 5°. Twisting the blade by such a large amount significantly improved its aerodynamic properties and the flight characteristics of the helicopter, and therefore the lift force is more evenly distributed along the length of the blade.

* The compartment from the 3rd to the 4th section is transitional. Main rotor blade profile - see fig. 7.5.

The propeller blades have variable both absolute and relative profile thickness. The relative thickness of the profile c is 13% in the butt, in the area from r = 0.23 to 7 = 0.268 - 12%, and in the area from r = 0.305 to the end of the blade - 11.38%. Reducing the thickness of the blade towards its end improves the aerodynamic properties of the propeller as a whole by increasing the critical speed and Mkr of the end parts of the blade. Reducing the thickness of the blade towards the end leads to a decrease drag and reducing the required torque.

The main rotor of a helicopter has a relatively large fill factor - 0.0777. This coefficient makes it possible to create greater thrust with a moderate propeller diameter and thereby keep the blades in flight at small installation angles, at which the angles of attack are closer to the most advantageous ones in all flight modes. This made it possible to increase the efficiency of the propeller and delay stalling at higher speeds.

Rice. 1.3. Helicopter rotor polarity in hovering mode: 1 - without ground influence; 2 - with the influence of the earth.

The aerodynamic characteristics of a helicopter main rotor are presented in the form of its polar (Fig. 1.3), which shows the dependence of the thrust coefficient Cp and the torque coefficient tcr on the total pitch of the main rotor<р. По поляре видно, что чем больше общий шаг несуще­го винта, тем больше коэффициент крутящего момента, а следовательно, больше коэффициент тяги. При наличии «воздушной подушки» тяга несущего винта будет больше, чем без нее при том же шаге винта и коэффициенте кру­тящего момента.

The tail rotor blades are rectangular in plan with the NACA-230M profile and do not have geometric twist. The presence of a combined horizontal joint of the “cardan” type and a flapping compensator at the tail rotor hub allows for a more even redistribution of the lift force over the surface swept by the propeller in flight.

The helicopter fuselage is aerodynamically asymmetrical. This can be seen from the curves of changes in the coefficients of fuselage lift C 9f and drag coefficient C depending on the angles of attack a f (Fig. 1.4). The lift coefficient of the fuselage is zero at an angle of attack slightly greater than 1, therefore the lift force will be positive at angles of attack greater than G, and negative at angles of attack less than 1. The minimum value of the fuselage drag coefficient C will be at an angle of attack equal to zero. Due to the fact that at angles of attack greater or less than zero the coefficient C f increases, it is advantageous to fly at angles of attack of the fuselage close to zero. For this purpose, a forward tilt angle of 4.5° is provided for the main rotor shaft.

A fuselage without a stabilizer is statically unstable, since an increase in the angle of attack of the fuselage leads to an increase in the coefficient of longitudinal moment, and, consequently, the longitudinal moment acting on pitching up and tending to further increase the angle of attack of the fuselage. The presence of a stabilizer on the tail boom of the fuselage provides longitudinal stability to the latter only at small installation angles from +5 to -5° and in the range of small angles of attack of the fuselage from -15 to + 10°. At large angles of installation of the stabilizer and large angles of attack of the fuselage, which corresponds to flight in autorotation mode, the fuselage is statically unstable. This is explained by the disruption of flow from the stabilizer. Due to the helicopter having good controllability and sufficient control margins in all flight modes, it uses a stabilizer that is not controllable in flight with an installation angle of 6°.

Rice. 1.4. Dependence of the lift coefficient Suf and drag coefficient Схф of the fuselage on the angle of attack a° of the fuselage

In the transverse direction, the fuselage is stable only at large negative angles of attack -20° in the range of gliding angles from -2 to + 6°. This is due to the fact that an increase in the sliding angles leads to an increase in the roll moment coefficient, and consequently, the lateral moment, which tends to further increase the sliding angle.

In terms of direction, the fuselage is unstable at almost all angles of attack at small sliding angles from -10 to +10°; at angles greater than these, the stability characteristics improve. At sliding angles of 10°< b < - 10° фюзеляж нейтрален, а при скольжении больше 20° он приобретает путевую устойчивость.

If we consider the helicopter as a whole, although it has sufficient dynamic stability, it does not cause any great difficulties when piloting even without an autopilot. The Mi-8 helicopter is generally rated with satisfactory stability characteristics, and with the automatic stabilization systems turned on, these characteristics have improved significantly, the helicopter is given dynamic stability in all axes and therefore piloting is significantly easier.

4. HELICOPTER LAYOUT

The Mi-8 helicopter (Fig. 1.5) consists of the following main parts and systems: fuselage, takeoff and landing devices, power plant, transmission, main and tail rotors, helicopter control, hydraulic system, avionics and electronic equipment, cabin heating and ventilation systems , air conditioning systems, air and anti-icing systems, devices for external load suspension, rigging, mooring and household equipment. The helicopter fuselage includes a nose 2 and central 23 parts, a tail 10 and end 12 beams. In the bow, which is the cockpit, there are pilot seats, instrument panels, electric consoles, an AP-34B autopilot, and command control levers. The glazed cockpit provides good visibility; the right 3 and left 24 blisters are equipped with emergency release mechanisms.

In the forward part of the fuselage there are niches for installing containers with batteries, airfield power plug connectors, air pressure receiver tubes, two taxi and landing lights and a hatch with a cover 4 for access to the power plant. The forward part of the fuselage is separated from the central part by connecting frame No. 5N, in the wall of which there is a doorway. A folding flight mechanic's seat is installed in the door opening. At the front, on the wall of frame No. 5N, there are shelves for radio and electrical equipment, at the rear there are containers for two batteries, a box and an electric winch control panel.

In the central part of the fuselage there is a cargo compartment, to enter which there is a sliding door 22 on the left, equipped with an emergency release mechanism. A side boom is attached to the outside of the upper front corner of the sliding door opening. In the cargo compartment, folding seats are installed along the right and left sides. On the floor of the cargo compartment there are mooring units and an electric winch. Above the cargo compartment there are engines, a fan, a main gearbox with a swashplate and a main rotor, a hydraulic panel and a consumable fuel tank.

Shock absorbers and struts of the main 6, 20 and front landing gear, and outboard fuel tanks 7, 21 are attached to the fuselage components from the outside. A kerosene heater is located in front of the right outboard fuel tank.

The cargo compartment ends in a rear compartment with cargo doors. In the upper part of the rear compartment there is a radio compartment in which panels for radio and electrical equipment are installed. There is a hatch to enter the radio compartment and tail boom from the cargo compartment. Cargo doors cover the opening in the cargo compartment, designed for rolling in and out of wheeled vehicles, loading and unloading large cargo.

In the passenger version, 28 passenger seats are attached to special profiles located along the floor of the central part of the fuselage. On the starboard side in the rear of the cabin there is a wardrobe. The right side panel has six rectangular windows, the left - five. The rear side windows are built into the emergency hatch covers. The cargo doors in the passenger version are shortened, the luggage compartment is located on the inside of the left door, and the boxes for containers with batteries are located in the right door. There is an opening in the cargo doors for the rear entrance door, consisting of a door and a ladder.

Rice. 1.5 Layout diagram of the helicopter.

1-front chassis leg; 2-nose fuselage; 3, 24-sliding blisters; 4-engine exit hatch cover; 5, 21 main landing gear legs; 6-hood heater KO-50; 7, 12-outboard fuel tanks; 8-hoods; 9-gear frame; 10-central part of the fuselage; 11-hatch cover in the right cargo door; 12, 19-load doors; 13-tail boom; 14-stabilizer; 15-end beam; 16-fairing; 17-tail support; 18-ladders; 20-sash flap; 23-sliding door; 25-emergency hatch-window.

The tail boom is attached to the central part of the fuselage, to the nodes of which the tail support and the uncontrolled stabilizer are attached. The tail shaft of the transmission runs inside the tail boom in its upper part. An end beam is attached to the tail boom, inside of which an intermediate gearbox is installed and the end part of the transmission tail shaft passes through. A tail gearbox is attached to the end beam on top, on the shaft of which a tail rotor is mounted.

The helicopter has a non-retractable tricycle landing gear. Each landing gear is equipped with liquid-gas shock absorbers. The wheels of the front strut are self-orienting, the wheels of the main struts are equipped with shoe brakes, for the control of which the helicopter is equipped with an air system.

The power plant includes two TV2-117A engines and systems that ensure their operation.

To transmit power from the engines to the main and tail rotors, as well as to drive a number of units, a transmission is used, consisting of main, intermediate and tail gearboxes, a tail shaft, a fan drive shaft and a main rotor brake. Each engine and main gearbox has its own autonomous oil system, made according to a direct single-circuit closed circuit with forced oil circulation. To cool the engine oil coolers and main gearbox, starter generators, alternators, air compressor and hydraulic pumps, the helicopter is equipped with a cooling system consisting of a high-pressure fan and air ducts.

The engines, main gearbox, fan and panel with hydraulic units are covered by the hood. When the hood covers are open, free access to the units of the power plant, transmission and hydraulic system is provided, while the open hood covers of the engines and main gearbox are working platforms for performing maintenance of helicopter systems.

The helicopter is equipped with means of passive and active fire protection. Longitudinal and transverse fire partitions divide the engine compartment into three compartments: the left engine, the right engine, and the main gearbox. The active fire-fighting system supplies extinguishing agent from four cylinders to the burning compartment.

The main rotor of a helicopter consists of a hub and five blades. The bushing has horizontal, vertical and axial hinges and is equipped with hydraulic dampers and centrifugal blade overhang limiters. The all-metal construction blades have a visual spar damage alarm system and an electrothermal anti-icing device.

The tail rotor is a pusher, pitch variable in flight. It consists of a cardan-type hub and three all-metal blades equipped with an electrothermal anti-icing device.

The helicopter's dual control consists of longitudinal-transverse control, directional control, combined "Pitch-throttle" control and main rotor brake control. In addition, there is separate control of engine power and engine shutdown. Changing the overall pitch of the main rotor and longitudinal-transverse control of the helicopter are carried out using a swashplate.

To ensure control of the helicopter, the system of longitudinal, transverse, directional control and collective pitch control includes irreversible hydraulic boosters, for powering which the helicopter has a main and backup hydraulic systems.

The four-channel AP-34B autopilot installed on the Mi-8 helicopter ensures stabilization of the helicopter in flight in roll, heading, pitch and altitude.

To maintain normal temperature conditions and clean air in the cabins, the helicopter is equipped with a heating and ventilation system that supplies heated or cold air to the crew and passenger cabins. When operating a helicopter in areas with a hot climate, instead of a kerosene heater, two onboard freon air conditioners can be installed.

The helicopter's anti-icing system protects the main and tail rotor blades, the two front windows of the cockpit and the engine air intakes from icing.

The anti-icing device for the propeller blades and cockpit windows is electrothermal, and the engine air intakes are air-thermal.

The aviation and radio-electronic equipment installed on the helicopter ensures flights day and night in simple and difficult weather conditions.

Mi-8 - Soviet/Russian multi-role helicopter, developed by the Mil Design Bureau in the early 1960s. It is the most popular twin-engine helicopter in the world, and is also included in the list of the most popular helicopters in the history of aviation. Widely used in many countries around the world to perform a variety of civil and military tasks. MI-8 helicopters, as a rule, have a dual purpose, as indicated in the type certificate.

Mi-8AMTSh helicopter - video

In Russia, helicopters with military purposes can only be sold by the Rosoboronexport Joint Stock Company, part of the Rostec corporation. All other helicopters that are on sale are for civilian purposes only.

The development of a promising medium-sized multi-purpose helicopter under the designation B-8, designed to replace the existing model of the Mi-4 helicopter, began at the Mil Design Bureau in the second half of the 50s. First of all, the new machine had to use ergonomics as rationally as possible, so the layout of the helicopter changed radically, which became a carriage type with a longitudinally elongated fuselage. The cockpit was located in the front of the fuselage, the engine (one on the first prototype) was located above the fuselage. The rest of the space was occupied by either the cargo compartment or the passenger compartment, depending on the modification of the helicopter.

The first B-8 prototype flew on July 9, 1961, it had one AI-24 turboprop engine; the second prototype of the V-8A - September 17, 1962, it already had two TV2-117 turboshaft engines, which were already installed on production vehicles. After a number of modifications, the Mi-8 was put into production in 1965 and adopted by the Soviet Air Force in 1967 and proved to be such a successful machine that purchases of the Mi-8 for the Russian Air Force continue to this day. The Mi-8 is used in more than 50 countries, including India, China and Iran.

The modernization of the Mi-8 helicopter, completed in 1980, led to the creation of an improved version of this machine - the Mi-8MT (product "88", when supplied for export - Mi-17), which is distinguished by an improved power plant (2 TV3-117 engines ) and the presence of an auxiliary power unit. Mi-17s are not so widespread and are used in about 20 countries around the world.

In 1991, production began of a new civilian transport modification of the Mi-8AMT (the export version is called Mi-171E), and in the late 1990s, the military transport and assault modification of the Mi-8AMTSh (Mi-171Sh).

In 2014, the 3,500th helicopter of the Mi-17 family was delivered to the customer.

Design

Single-rotor helicopter with 5-bladed main rotor and 3-bladed tail rotor. The fastening of the main rotor blades is hinged (vertical, horizontal and axial hinges), and the tail rotor blades are combined (horizontal and axial), cardan type. The main rotor blades are all-metal, consisting of a hollow spar pressed from an aluminum alloy, to the trailing edge of which 21 compartments with a honeycomb core of aluminum foil are glued, forming a profile. All main rotor blades are equipped with a pneumatic spar damage alarm. In the main mode, the main rotor rotates at a speed of 192 min−1, the steering rotor - 1124 min−1.

Transmission

Similar to the Mi-4 helicopter. The main transmission units are:

— Main gearbox VR-14 (for Mi-8MT) or VR-8A (for Mi-8T)
— Intermediate gearbox;
— Tail gearbox;
— Transmission tail shaft;
— Fan drive shaft;
— Main rotor brake.

Fuselage

It is the main power body of the helicopter and is an all-metal semi-monocoque of variable cross-section with a smooth working skin. The fuselage has three structural connectors and includes:

— bow part;
- central part;
— tail boom;
- end beam with fairing.

Chassis

Three-legged, non-retractable, with a self-orienting front strut in flight. To prevent the tail rotor from touching the ground, there is a tail support.

External suspension system

Allows you to transport cargo weighing up to 3000 kg (5000 kg). The Mi-8 is equipped with a four-channel autopilot AP-34B, which provides stabilization of roll and pitch, direction, and flight altitude (±50m). In the passenger version, up to 18 seats can be installed in the cabin; in the transport version, folding benches for 24 seats are used.

Control system

Designed to control the helicopter relative to three axes, carried out by changing the magnitude and direction of the main rotor thrust force and changing the tail rotor thrust force. To control the helicopter, hydraulic boosters are used - three KAU-30B (combined control unit) to control the main rotor and one RA-60B (steering unit) to control the tail rotor. The Mi-8MTV has four KAU-115M. The hydraulic system is designed to supply working fluid:

— helicopter control units (RA-60B tail rotor control, KAU-30B general pitch main rotor, two KAU-30B longitudinal and lateral control);
- hydraulic cylinders for controlling the STEP-GAZ clutch, a variable stop in the longitudinal control of the helicopter (controlling the afterburner of engines for helicopters of the MT modification) are activated by separate electromagnetic valves GA-192.

The hydraulic system consists of a main and a backup one, the pressure in each is created by a separate NSh-39M pump installed on the main gearbox. The pressure is regulated within 45±3 ... 65+8-2 kgf/cm2 by GA-77V pump unloading machines, supported by hydraulic accumulators - two in the main system and one in the backup one.

Fuel system

Designed to accommodate the required amount of fuel on board the helicopter and its uninterrupted supply to the engine control pumps at all modes and altitudes, as well as to supply fuel to the KO-50 kerosene heater.

Fire protection system (FPS)

Designed to detect, signal and extinguish fire in protected compartments:

— left and right engines;
— kerosene heater KO-50;
— main gearbox and AI-9V engine.

Anti-icing system (AIS)

Designed to protect the main and tail rotor blades, two front windows of the cockpit, engine inlet devices, and engine dust protection devices (DPD) from icing. Heating of the propeller blades and cockpit windows is electrothermal. The heating of the air intake fairings and engine inlet devices is air-thermal, and the heating of the ROM is mixed (some of the components are heated with hot air, and the other part is electrically heated). PIC works both automatically and manual modes. The NV RV blades, front windows and ROM are powered by an AC mains voltage of 208 volts. Hot air from the compressor is used to heat the engine input device and the ROM.

Air system

Designed to brake the wheels of the main landing gear and recharge the wheel chambers from on-board cylinders in off-airfield conditions using a special device.

The heating and ventilation system is designed for:

— supplying heated or atmospheric air to the cockpit and cargo compartment to maintain normal temperature conditions in them;
— blowing the front windows and cockpit blisters;
— heating of the drain valve of the drainage tank.

A kerosene heater KO-50 is used to heat the air.

Oxygen equipment

Designed to supply oxygen to the crew during flights at altitudes up to 6000 m, as well as to the wounded and sick during flights at any altitudes.

Power system

DC power sources:

— two GS-18 starter-generators installed on each of the engines;
— six rechargeable batteries 12САМ-28.

AC Power Sources:

— Single-phase alternating current with a voltage of 208 V and a frequency of 400 Hz is supplied by the SGO-30U generator installed on the main gearbox. (To power the heating elements of propellers and windshields). Also, from SGO-30U, through a single-phase transformer TS/1-2, radio and navigation equipment is powered, and from it - transformer Tr-115/36, which supplies engine and transmission control devices with a single-phase voltage of 36 V, and through transformer 115/7.5 - power supply rotor outline lights. If the SGO-30U fails, the heating elements of the blades are turned off, the rest of the equipment automatically switches to power from the PO-750A converter.
— Three-phase alternating current voltage 36 V for powering gyroscopic devices is provided by one of two PT-500Ts converters (main or backup).

Navigation and flight instruments and radio equipment in all modifications of the helicopter allow flights at any time of the day in normal and adverse weather conditions.

Power point

It consists of two TV2-117 turboshaft engines (TVZ-117MT modification “MT”, TV3-117VM modification Mi-8MTV). If one of the engines fails in flight, the other engine automatically switches to increased power, while horizontal flight is performed without reducing altitude.

Helicopters of various modifications differ very significantly in the composition of their equipment. Early helicopters (Mi-8, Mi-8T, Mi-8TV, Mi-8P, Mi-8PS, Mi-8SMV(PPA, R) are equipped with two TV2-117A engines with a take-off power of 1500 hp, with a 10-stage compressor and starting from the GS-18TO starter-generator installed on each engine. When starting the first engine, its starter-generator is powered by six on-board 12CAM-28 batteries (starter aviation monoblock with a capacity of 28 Ah) with a voltage of 24 V, the second engine - from the starter-generator. already running engine and three batteries. When the GS-18TO engines are running, they supply a voltage of 27 volts to the main power supply system. Four batteries are installed in the pilot’s cabin under the shelves of electrical and radio equipment, two on each side, the remaining two behind the pilot’s cabin in the cargo compartment, in the passenger version in the rear part behind the cabin partition. Despite their relatively small capacity, they are capable of providing 5 engine starts in a row on the ground and in the air at altitudes of up to 3000 m, while delivering a current of 600-800 amperes; when the engines are running, they are charged from DC generators. current and automatically turn off when the rated capacity is reached or turn on when the voltage drops in the on-board network (in case of generator failure) using differential minimum relays DMR-600T, a generator operation monitoring system.

Helicopters of later series (Mi-8MT, Mi-17, etc.) have been significantly modernized. The engines were replaced with more powerful ones (takeoff power - 2200 hp) TV3-117 with a 12-speed compressor and air start; an AI-9V APU was installed to supply air to the engine air starters. Basic AC Power System:

— Sources of three-phase current with a voltage of 208 V and a frequency of 400 Hz; 2 generators SGS-40PU, located on the main gearbox.

The first generator powers:

— rectifier devices VU No. 1;
— elements of POS screws;
— transformer TS-310S04B (power 1 kW) for powering a three-phase 36 V network;

The second generator powers:

— rectifier devices VU No. 2 and No. 3;
— heated windows and dust protection device (ROD) of engines;
— transformer TS/1-2 for powering a single-phase 115 V network;
— after TS/1-2 with a voltage of 115 V, two transformers Tr115/36 are also powered, (main and spare) supplying single-phase alternating current 36 V to the instruments for monitoring the operation of engines and transmissions.

Two converters serve as backup sources for alternating current: PO-500A and PT-200Ts. If generator No. 1 fails, the TS310S04B switches to generator No. 2; if both generators or the generator itself fail, the PT-200Ts converter starts. If generator No. 2 fails, TS/1-2 switches to generator No. 1; if both generators or the generator itself fail, the PO-500A converter starts. Also, if generator No. 2 fails, VU-6A No. 3 switches to generator No. 1.

DC System (Secondary): DC Power Sources:

— main sources - three rectifier devices, rectifier devices VU-6A;
— STG-3 starter-generator, which can supply a voltage of 27 volts with a power of 3 kW to the on-board network for 30 minutes when the APU is running;
— 2 rechargeable batteries 12САМ-28 or 20NKBN-28 (for starting the APU and emergency power supply to the network).

Modifications

Passenger

Passenger helicopter with 28 seats. Equipped with GTD TV2-117A engines with a power of 1267 kW/1700 hp. The passenger cabin has a length of 6.36 m, a width of 2.34 m, a height of 1.80 m, and rectangular windows.

Modification of Mi-8P with GTD TV2-117F engines.

A passenger helicopter with a high-comfort cabin: two large leather chairs near a table, a sofa, and a telephone on the table; there is a small buffet, a wardrobe compartment and a toilet, enlarged rectangular portholes, as well as a ladder door.

A passenger helicopter built by order of the Ministry of Defense specifically for transporting international inspection teams to monitor arms limitation measures. It has a slightly more modest interior than the Mi-8PS.

Mi-172- a helicopter created on the structural basis of the Mi-8MTV-1 multi-purpose helicopter. At the beginning of 2017, it is the only helicopter from the Mi-8 family certified for commercial passenger transportation.

Transport

Landing transport helicopter for 24 paratroopers with weapons (in the ambulance version, 12 wounded on stretchers with one accompanying person). GTD TVZ-117MT engines with a power of 1454 kW/1950 hp are installed. The helicopter is also designed to transport cargo weighing 4000 kg in the cabin or 3000 kg on an external sling. Cargo compartment: length 5.34 m, width 2.34 m, height 1.80 m. In the military version, equipped with pylons for hanging weapons.

Export version of the Mi-8T for the Syrian Air Force, modified for dry climate conditions.

Multipurpose

- “Transport, armed.” Adopted by the Soviet Army in 1968. Reinforced truss pylons with four holders for thirty-two blocks of 57 mm caliber rockets and a movable 12.7 mm machine gun mount in the forward part of the fuselage are installed. The helicopter can also carry other weapons: blocks of thirty-two rocket launchers. AT-2 ATGM with semi-automatic control. AT-3 ATGM with manual control, etc. It was distinguished by the armored cockpit, gearbox and engine hoods, and armored glass in the cockpit (mostly frontal).

Helicopter with TV2-117AG engines.

Aerial minelayer for ground forces. The VMR-1 minelayer was installed. Could set from 64 (in the first modifications) to 200 minutes.

A modification of the air minelayer for ground forces, designed for laying small-sized non-retrievable anti-personnel mines.

Modification of the Mi-8T helicopter with GTD TV2-117TG engines with a power of 1103 kW/1500 hp, running on aviation condensed fuel.

Upgraded airborne transport helicopter. Equipped with high-power GTD TVZ-117MT engines with a power of 1454 kW/1950 hp. with dust protection devices and an AI-9V auxiliary power unit and a left-mounted tail rotor for increased efficiency. It has an infrared jamming station "Linden", screens for exhaust devices to suppress thermal radiation from engines and containers with decoys, a machine gun (12.7 or 7.62 mm caliber) in the nose mobile installation, holders on the sides of the fuselage for installing up to six NAR units placed on top on the guides on rails up to six ATGMs. Machine gun containers are also suspended on the pylons; machine guns and grenade launchers can be located in the blisters and side openings of the troop compartment. The helicopter is a transitional model to the improved Mi-17 helicopter.

Mi-17- export version of the Mi-8MT.

Mi-8MTV or Mi-8MTV-1- a modernized high-altitude transport helicopter with TV3-117VM, TV3-117VM series 02, VK-2500-03 engines. Dynamic ceiling increased to 6000 m. Developed in 1985-1987. and launched into mass production in Kazan in 1988. Has only civilian use.

Mi-17-1V- export version of the Mi-8MTV-1.

Mi-8MTV-2

Mi-8MTV-2 and Mi-8MTV-3 later modifications of military transport helicopters of the MT version. Designed for use in airborne transport, ambulance, rescue and strike versions. These are some of the most heavily armed helicopters in the world. In the MTV-2 version, the helicopter could be equipped with four B8V20-A blocks of twenty S-8 NARs; it was possible to suspend aerial bombs of 50-500 kg caliber on beam holders BDZ-57KRVM: a mobile installation with a 12.7 mm machine gun could be placed in the forward part of the fuselage , in the sliding door openings - up to 8 pivot installations with machine guns; 7.62 mm caliber, and on the external mounts there are 4 UPK-23-250 gun containers with GSh-23L cannons of 23 mm caliber. To protect against missiles with an infrared seeker, ASO-2B cassettes with PPI-26-1 infrared decoy targets are installed. The helicopter's cockpit has armor plates covering the floor, front and rear parts of the compartment.

Mi-8MTO- night.

Mi-8MTKO- option with lighting equipment adapted for the use of aerobatic night vision systems.

Mi-17-1V- export version of the Mi-8MTV.

Mi-8AMT(export designation - Mi-171E) - variant of the Mi-8MTV with minor changes, produced at the Ulan-Ude Aviation Plant (since 1991). There are various modifications: passenger. transport, search and rescue, VIP salon, etc. Has only civilian use.

Mi-171- modification of the Mi-8AMT helicopter, has a certificate issued by the Interstate Aviation Committee. Has only civilian use.

Mi-171A2

Mi-171A1- a modification of the Mi-8AMT helicopter that complies with the US Rotorcraft Airworthiness Standards FAR-29. Has only civilian use.

Mi-17KF- modification of the Mi-8MTV-5 with Honeywell avionics. Developed by the Mil Design Bureau jointly with Kazan Helicopter Plant for the Canadian company Kelowna Flightcraft. First flight August 3, 1997.

Mi-8MSB- own Ukrainian modification not certified in Russia with TV3-117VMA-SBM1V 4E series engines, a passenger transport version for civil aviation.

Mi-8MSB-V- own Ukrainian modification, not certified in Russia, with TV3-117VMA-SBM1V 4E series engines, for the Air Force (adopted into service in April 2014, by the end of 2014 3 units were transferred to the troops) and for export.

Special purpose

Mi-8TECH-24- flying technical and operational part. It was equipped with plumbing, electrical, inspection and testing and other equipment used in the operation and repair of helicopter equipment.

Refueler and fuel transporter.

Trawl towing.

Special sea rescue.

Mi-8SPA- a search and rescue helicopter to search for astronauts and aircraft crews in the event of splashdown.

Forest fire modification, equipped with a massive water discharge system and a water cannon.

Staff helicopter with round windows.

Staff helicopter with square windows.

Special command post to conduct large-scale complex search and rescue operations.

Or the Mi-8R - a reconnaissance aircraft designed for visual observation and photography in the front line.

Artillery spotter.

Mi-8TAKR- a helicopter with a television surveillance system.

Radiation-chemical reconnaissance.

Modification with a combined power plant consisting of turboshaft engines driving the main rotor and a traction turbojet.

Mi-8MT "Flying Crane"- features a crane operator cabin in place of the cargo doors.

Mi-8MT "Meteo"- flying weather station. In 1990, 12 Mi-8MTs were converted.

Mi-8MTA- short-range tactical reconnaissance helicopter.

Mi-8MTS- radiation reconnaissance helicopters. Developed in 1986.

Mi-8MTT- a helicopter for searching for descending spacecraft.

Mi-8MTL- reconnaissance aircraft with the ability to simultaneously use thermal imaging reconnaissance and radio interception with precise definition target coordinates.

Mi-8MTF- aerial reconnaissance officer. Developed in 1984.

Mi-8MTF (II)- smoke screen producer. Developed in 1987.

Mi-8MTYU- It was built in a single copy. Designed to detect landers, small surface targets, with a radar antenna in the nose. Used by the Ukrainian Air Force.

Mi-8AMT-1- a luxury lounge (VIP lounge) for the government air squad of the President of the Russian Federation.

Mi-8AMTSH-VA- version for performing tasks of the Russian Ministry of Defense in the Arctic. Mi-8AMTSh-VA, created on the basis of the latest modification of the military transport helicopter Mi-8AMTSH-V, which is distinguished by new Klimov VK-2500-03 gas turbine engines, a more powerful TA-14 auxiliary power unit and an updated set of avionics, is additionally equipped with a heating the main units of the power plant. To operate above the water surface, the helicopter is equipped with an air conditioning system for sea rescue suits (MSS), in which the crew works.

Air command posts

Mi-8VKP or Mi-8VzPU- air command post.

Airborne command post for division commanders, serial modification.

Mi-9- air command post for motorized rifle commanders and tank divisions. Equipped with special equipment and additional antennas on the tail boom. Created in 1977 on the basis of the Mi-8T.

Mi-9R- an air command post for commanders of missile divisions of the Strategic Missile Forces. Equipped automated complex communications. Created in 1987 on the basis of the Mi-8T.

Medical

Air hospital (medical bisector). Created on the basis of the Mi-8T in 1978.

Mi-8MTB- armored air hospital. Created on the basis of the Mi-8MT.

Mi-8MTVM- medical modification of the Mi-8MTV.

Mi-8MTV-3G- an air hospital based on the Mi-8MTV-3.

Mi-8MTV-MPS- medical search and rescue helicopter based on the Mi-8MTV.

Mi-8MTD- search and rescue helicopter. Designed to search for astronauts and aircraft crews in distress.

Mi-8MTN- a helicopter providing medical assistance to astronauts. Developed in 1979.

Mi-17G- export version of the air hospital.

Mi-17-1VA "Ambulatory"- export version of the Mi-8MTV in a sanitary version. Shown at the Paris Air Show in 1989, equipped with more powerful TV3-117VM engines.

Jammers

Mi-8SMV- the first modification of the Mi-8 helicopter as an electronic warfare helicopter. The Mi-8SMVb modification, created in 1971, was intended to protect front-line aviation from damage by enemy anti-aircraft missile systems. A helicopter version of the Smalta-V (Smalta-3) electronic warfare system with a control panel was installed in the cargo compartment, and transceiver antennas were mounted on board the fuselage.

An electronic warfare (electronic warfare) helicopter, created in 1974. According to some sources, it is equipped with the “Pole” complex, but in the 70-80s. EW complexes were usually called by the names of plants; perhaps this option is simply confused with early versions of the Mi-8PPA. Intended for jamming ground detection, guidance and target designation radars. The suppression stations placed on the helicopter also made it possible to use the Mi-8PP as a radio reconnaissance aircraft. The helicopter is easily distinguished by its containers and cross-shaped dipole antennas on the sides of the fuselage.

Mi-8PPA- an electronic warfare helicopter equipped with the Azalea and Fasol stations, according to some sources - modified in 1980-1982. version of Mi-8PP.

Mi-8MTPR-1- jammer based on Mi-8MTV-5-1. The modification differs from the serial Mi-8MTV-5-1 in the absence of a ramp and armor plates on the cockpit, a narrowed left sliding door and the absence of part of the windows, and an additional antenna on the tail boom. The helicopter is equipped with the Rychag-AV electronic warfare system.

Military transport

Mi-8MTV-5

Mi-8AMTSH(export designation - Mi-171Sh) and Mi-8MTV-5(export designation - Mi-17V-5) - modern multi-purpose military transport helicopters designed for transporting personnel, as well as cargo inside the cabin and on an external sling. They can be equipped with a set of weapons equivalent to the Mi-24, a complex of armor protection for the crew, and can be adapted for the use of night vision technology. These helicopters were created taking into account a comprehensive analysis of the experience of using Russian helicopter technology in combat operations in various “hot spots”. In November 2015, the military should receive the first Arctic version (Mi-8AMTSH-VA) “Terminator”, which was created on the basis of the latest modification of the Mi-8AMTSH-V helicopter. It is equipped with new VK-2500-03 gas turbine engines, a more powerful TA-14 auxiliary power unit and updated avionics. The helicopter was created taking into account the specifics of use in conditions of low temperatures (from minus 40-50 degrees Celsius and below) and limited visibility when flying, including during the polar night. An experimental batch of 5 helicopters was ordered in February 2014. At the same time, the military announced that their total need for Terminators could reach 100 units.

Protection: electronic device, steel armor plates, LC ejection machine, jammer, protected fuel tanks.

Features: winching up to 4 people at a time, ramp, IR search light, night vision goggles, IR camera.

Armament S-8 missiles in blocks, Attack (ATGM).

Mi-8AMTSH

Mi-8AMTSH-1- modification of the Mi-8AMTSh, equipped with a weapons complex in combination with a luxury salon (VIP salon)

Mi-8MNP-2- modification of the Mi-8AMTSh for the Russian Border Guard Service. 6 helicopters were converted.

Performance characteristics of the Mi-8AMT

— Chief designer: M. L. Mil
— First flight: July 9, 1961
— Start of operation: 1965
— Units produced: > 12,000 (all modifications)

Cost of Mi-8

— about 252 million rubles. or from $14.75 million to ~$17.5 million (Mi-17V-5, export)
— Mi-8AMTSH (for government customers): ~200 (as of 2010) – 250 million rubles. (as of 2012)

Mi-8 crew

— 3 people

Mi-8 capacity

— 27 people

Dimensions of Mi-8

— Length (with rotating screws): 25.31 m
— Height (with rotating tail rotor): 5.54 m
— Main rotor diameter: 21.3 m

Weight of Mi-8

— Empty weight: 6913 kg
— Normal take-off weight: 11,100 kg
— Maximum take-off weight: 13,000 kg

Mi-8 engines

— 2 × TV3-117VM
— Engine power (at takeoff mode): 2 × 2000 l. With
— Aviation fuel consumption, t/hour - 0.72

Speed ​​of Mi-8

— Maximum speed: 250 km/h
— Cruising speed: 230 km/h

Dynamic ceiling Mi-8

Practical range of the Mi-8

Mi-8 flight range

— with additional fuel tanks: 1300 km
— with maximum aviation fuel reserve: 800 km
— at maximum load: 550 km

Photo of Mi-8

Mi-8 helicopters are the most common transport helicopters in the world, second only to the light multi-role and transport Bell UH-1 "Iroquois" and "Huey". In total, more than 8,000 Mi-8 helicopters were produced at the Kazan Helicopter Plant and the Aviation Plant in Ulan-Ude, of which more than 2,000 were exported to more than 40 countries, where half of them are still in operation.

At the end of the 1950s, work began abroad and here on the creation of second-generation helicopters with turboshaft engines, and in May 1960. At the Moscow Helicopter Plant, the development of a new multi-purpose helicopter began to replace the Mi-4 multi-purpose helicopters, which have proven themselves in operation. The first experimental B-8 helicopter, with one AI-24V gas turbine engine designed by S.P. Izotov and a four-blade main rotor from the Mi-4 helicopter, designed to carry 25 passengers, made its first flight in June 1961, and on July 9 it was first demonstrated at an air festival at the Tushino airfield in Moscow; several helicopters were built.

The main attention was paid to the development of a twin-engine helicopter with a new five-bladed main rotor, developed on the basis of modified all-metal blades of the Mi-4 helicopter, and a new rigid tail rotor. The second experimental B-8 helicopter, with two TB2-117 gas turbine engines with a power of 1267 kW each, made its first flight on September 17, 1962, successfully passed flight tests and since 1965. began mass production at the helicopter plant in Kazan under the designation Mi-8. A number of original technical solutions were used in the design of the helicopter: large-sized duralumin stampings and glue-welded joints, a new external suspension system, an automatic engine control system that ensures their synchronization and maintaining the rotor rotation speed within specified limits. Compared to the Mi-4 helicopter, the new helicopter had higher flight characteristics and twice the payload capacity. On Mi-8 helicopters in 1964-1969. 7 international records were set, most of which were women's, set by pilots L.G. Isaeva, N.A. Kolets and T.V. Russiyan, and unsurpassed to this day.

Mi-8 helicopters are the most common transport helicopters in the world, second only to the light multi-role and transport Bell UH-1 "Iroquois" and "Huey". In total, more than 8,000 Mi-8 helicopters were produced at the Kazan Helicopter Plant and the Aviation Plant in Ulan-Ude, of which more than 2,000 were exported to more than 40 countries, where half of them are still in operation.

Mi-8 helicopters were produced in more than 30 different civil and military modifications, including the main ones:

Mi-8P- a passenger helicopter with a TV2-117A gas turbine engine with a power of 1267 kW, with a cabin for 28 passengers and square windows;

Mi-VPS "Salon" - a passenger helicopter with a high-comfort cabin for 11 passengers with an eight-seat common seat on the right side and two seats and a rotating seat on the left side, improved interior trim and a ventilation system and toilet; also produced in versions with a cabin for 9 and 7 passengers;

Mi-8T- a transport helicopter with a TV3-117MT gas turbine engine with a power of 1454 kW, for transporting cargo weighing 4000 kg in the cabin, or 3000 kg on an external sling, or 24 passengers on the side seats, or 12 patients on stretchers with accompanying persons; It is distinguished by small round cabin windows and equipment; in military versions it is equipped with pylons with holders for weapons.

Mi-8TG- a modification of the Mi-8T helicopter with a TV2-117TG gas turbine engine with a power of 1103 kW, developed in 1987, the world’s first helicopter that uses liquefied petroleum gas along with aviation fuel;

Mi-8TV- a landing transport helicopter for the armed forces with reinforced truss pylons with four holders for blocks of 32 NAR of 57 mm caliber or other weapons and a mobile installation with a machine gun of 12.7 mm caliber in the bow, it is possible to install triple holders for weapons from six blocks of 32 NAR, and on guide rails up to six AT-2 ATGMs with semi-automatic control; It was also produced in an export version with six AT-3 ATGMs with manual control. More than 250 Mi-8TB and MT helicopters were converted to Mi-17.

Mi-8MT- a modernized landing transport helicopter with a TV3-117MT gas turbine engine with a power of 1454 kW, with dust protection devices, an AI-9V auxiliary power unit and a tail rotor mounted on the left to increase efficiency; the helicopter is a transitional model to the improved Mi-17 helicopter; produced in the Mi-8AM and MI-8MTV variants with various equipment and weapons and in the Mi-8MTB-1A variant for civilian use;

Mi-8PP- active jamming helicopter with a container and cross-shaped dipole antennas on the sides of the fuselage; A number of modifications were also built for electronic warfare, relaying, etc.

Mi-9- a helicopter to provide communication with additional antennas on the tail boom;

Mi-18- a military transport helicopter, a modification of the Mi-8T helicopter with a cabin length increased by 1 m, which made it possible to accommodate more than 38 soldiers or cargo weighing 5-6.5 tons, and cargo weighing 5 tons on an external sling. In 1980 two Mi-8MT helicopters were modernized into the Mi-18 with an enlarged cabin, new fiberglass blades and a retractable tricycle landing gear, and in 1982. passed flight tests that confirmed an increase in payload capacity with an increase in speed and flight range by 10-15%;

Mi-8MTV-2 and 3 - the latest military transport modifications, intended for use in airborne transport, ambulance, rescue and combat versions, with armament from four B8V20-A blocks of 20 S-8 NARs, the fire of which is controlled by the PUS-36-71 sight; it is possible to suspend aerial bombs with a caliber of 50-500 kg on beam holders BDZ-57KRVM; in the bow, a mobile installation with a 12.7mm caliber machine gun can be placed, in the sliding door openings up to 8 pivot installations with 7.62mm caliber machine guns, and on the holders - 4 UPK-23-250 gun containers with GSh-23L cannons of 23mm caliber, which makes The Mi-8MTV-2 helicopter is the most heavily armed in the world. To dissipate the heat flow of the gas turbine engine, screen-exhaust devices are installed, and to protect against guidance missiles with an IR system, the helicopter is equipped with a passive jamming system consisting of 4 ACO-2B cassettes on the tail boom and 6 cassettes on the fuselage; Each cassette contains 32 PPI-26-1 IR decoys and pulsed IR signal generators. The helicopter is equipped with armor plates covering the floor, front and rear parts of the cockpit and hydraulic panel. The helicopter can be equipped with radar and long-range navigation radio equipment;

Mi-8AT. Soon after the start of serial production, helicopters began to be equipped with improved TV2-117A engines. Since 1973, vehicles supplied to southern countries have been equipped with engines designed for operation in high temperatures air. At the end of the 1970s, they created a forced TV2-117F engine with an emergency power of 1700 hp. With. It was used on the Mi-8PA, which successfully passed certification in Japan in 1980. In the 1980s, production Mi-8s, instead of the TV2-117A, were equipped with the more durable TV2-117AG with a graphite seal in the turbocharger supports. This modification was again given the designation Mi-8AT. It still serves as the basis for the development of various, mainly civilian, options. Mi-8AT helicopters equipped with cheap TV2-117AG are widely used in lowland areas with moderate temperatures air.

Mi-8AMTSH- a transport-assault helicopter developed at the Ulan-Ude plant. The car is made on the basis of the military transport "eight". The helicopter is equipped with armor protection for the crew members (the bottom and front part of the pilot's cabin are covered with armor, between the cabin and the cargo compartment; in the cargo compartment, an armor plate is installed under the gunner's position); the suspended weapons are placed on six suspension units, the rear hemisphere is covered by a remotely controlled PKT machine gun.

The “highlight” that distinguishes the AMTSh from previous versions of the G8 is the inclusion of the Ataka or Sturm ATGM and the Igla air-to-air missile in its armament. The Mi-8AMTSh helicopter was first shown at the Farnborough exhibition '97-99, and it was also demonstrated at MAKS '97. The Mi-8AMTSh may be of interest, first of all, to countries that have transport Mi-8s in service, but do not have specialized combat helicopters; China, for example. Considering that upgrading the Mi-8 to Mi-8AMTSh is cheaper than upgrading to modern level The Mi-24, and the Mi-8 itself can be used more flexibly compared to “crocodiles”; direct competition between the two helicopters is also possible. At the Farnborough exhibition '99 the helicopter was named "Terminator".

Mi-8MTKO. After carrying out the proposed modernization, it additionally provides the solution to the following tasks:

 24/7 (day and night) combat use the entire range of helicopter weapons using a gyro-stabilized optical-electronic system;

 increasing the accuracy of the use of unguided weapons through the use of a laser rangefinder;

 round-the-clock performance of reconnaissance and search and rescue missions with precise determination of target coordinates and automatic transmission of data to the ground control point;

 high-precision navigation and a new system for displaying navigation and flight information;

 round-the-clock guidance and adjustment of artillery fire;

 performing flights at night at an altitude of 50 m using night vision goggles;

 independent search and landing at night on unlit and unmarked areas without the use of landing lights;

 semi-automatic (director) and automatic flight along a programmed route

Information and control field of the cabin.

For the helicopter, a new cockpit information and control field has been developed based on IV-86-1 multifunctional color liquid crystal displays with a horizontal screen layout, a push-button frame and a screen size of 8 x 6 inches. The new cockpit information and control field increases information content by 2-2.5 times and increases the safety of flights near the ground day and night.

The helicopter uses a new progressive layout of instrument panels and cabin lighting. In-cab lighting and indicators are adapted to the use of third-generation night vision goggles. The new concept of in-cabin lighting creates a favorable light climate in the cockpit both when flying with or without night vision goggles, day or night. The new layout of the cockpit has improved the visibility of the space behind the cockpit.

Equipment composition:

Gyro-stabilized optical-electronic system (GOES).

The gyro-stabilized two-channel (thermal imager + laser rangefinder) or three-channel (thermal imager + low-level television camera of the third generation + laser rangefinder) optical-electronic system GOES-321 (GOES-331) provides:

 round-the-clock review and aiming with thermal imaging and television (from a low-level camera) images displayed on indicators;

 control of the line of sight is carried out over a wide range (n 230 degrees in azimuth and from +60 to -150 degrees in elevation);

 gyrostabilization of the line of sight with an accuracy of up to 20 arc minutes;

 capture and automatic tracking of a target using a teletracking machine;

 operation of the thermal imager in a wide (20 x 13.3 degrees) and narrow (5 x 3.3 degrees) field of view;

 determination of the range to the target using a laser rangefinder with an accuracy of up to 5 m at a distance of up to 5 km.

Complex of navigation and electronic display.

The KNEI-8 navigation and electronic display complex provides solutions to the following tasks:

 display of information from the GOES system on indicators;

 calculation, display on the indicator and recording in non-volatile memory of the coordinates of the detected target and automatic transmission data to the ground command post;

 automatic calculation and display, in the form of a moving mark, of firing corrections for the use of the entire range of standard helicopter weapons;

 calculation and display of permitted weapon ranges;

 bringing the helicopter to a target with pre-known coordinates and automatic orientation of the GOES line of sight to it;

 calculating the current coordinates of the helicopter location (TCM);

 correction of calculated TCMV using information from satellite navigation systems GLONASS, NAVSTAR;

 calculation and presentation on indicators of the necessary flight parameters to reach a given point at a given time;

 calculation and presentation on indicators of the necessary flight parameters along the route;

 calculation and issuance of control signals to the autopilot for automatic flight along the route;

 storage of a navigation database in non-volatile memory;

 prompt change of the navigation database on the ground and in flight;

 display of flight and navigation information, emergency, warning and notification signals on indicators;

 calculation and display on indicators of information about the achievement of control flight parameters and operational tolerance limits;

 calculation of the engineering and navigation flight plan;

 registration of the image from the indicator to the VCR.

Aerobatic night vision goggles of the III generation.

GEO ONV-1 The highly sensitive photocathode based on gallium arsenide, used in GEO ONV-1 night vision goggles, can significantly improve observation in low light conditions. High image quality under starry sky conditions is achieved through the use of third-generation electro-optical converters (EOCs), on the basis of which night vision goggles have been developed.

Features of the system.

 III generation image intensifier technology.

 Stereoscopic vision in a wide angle field.

 Ease of mounting on a helmet and adjustment to the pilot’s eyes, realized by four possible movements of the monoculars.

 Comfortable work with glasses, ensured by large exit pupils of the eyepieces and their distance from structural elements.

 Fast undocking.

 Easy to move to non-working position.

 Built-in standalone source power supply and on-board network.

Application:

 Terrain observation and helicopter control during night flights.

 Helicopter takeoff and landing on unequipped sites at night.

 Search for people and equipment.

DESIGN. The helicopter is made according to a single-rotor design with a tail rotor, two gas turbine engines and a tricycle landing gear.

Fuselage helicopter frame structure, consists of bow and central parts, tail and end beams. In the bow there is a three-seat crew cabin, consisting of two pilots and a flight mechanic. The cabin glazing provides good visibility; the right and left sliding blisters are equipped with emergency release mechanisms. In the central part there is a cabin with dimensions of 5.34 x 2.25 x 1.8 m in the transport version with a cargo hatch with doors that increase the length of the cabin to 7.82 m, and a central sliding door with dimensions of 0.62 x 1.4 m with an emergency release mechanism; mooring units and an electric winch are located on the floor of the cargo compartment, and an electric winch boom is installed above the door. The cargo compartment is designed to transport cargo weighing up to 4 tons and is equipped with folding seats for 24 passengers, as well as attachment points for 12 stretchers. In the passenger version, the cabin has dimensions of 6.36 x 2.05 x 1.7 m and 28 seats, two installed on each side with a pitch of 0.74 m and a passage of 0.3 m; in the rear of the cabin there is a wardrobe on the right, and in the rear of the doors there is an opening for the rear entrance door, consisting of doors and a ladder.

The tail boom is of a riveted beam-stringer type with working skin, equipped with units for attaching a controlled stabilizer and a tail support.

Stabilizer 2.7 m in size and 2 m2 in area with a NACA 0012 profile of a single-spar design, with a set of ribs and duralumin and fabric covering.

Chassis three-support, non-retractable, self-orienting front support, with two wheels measuring 535 x 185 mm, main supports of a shaped type with liquid-gas double-chamber shock absorbers and wheels measuring 865 x 280 mm. The tail support consists of two struts, a shock absorber and a support heel; chassis track 4.5m, chassis base 4.26m.

Carrier a propeller with hinged blades, hydraulic dampers and pendulum vibration dampers, installed with a forward inclination of 4° 30". All-metal blades consist of a pressed spar made of AVT-1 aluminum alloy, hardened by work hardening with steel hinges on a vibration stand, a tail section, a steel tip and an ending. The blades have a rectangular shape in plan with a chord of 0.52 m and NACA 230 profiles with a relative thickness from 12% to 11.38% and a geometric twist of 5%, the peripheral speed of the blade tips is 217 m/s, the blades are equipped with a visual alarm system for spar damage and an electrothermal anti-icing device.

Tail rotor with a diameter of 3.9 m, three-bladed, pushing, with a cardan-type bushing and all-metal rectangular blades in plan, with a chord of 0.26 m and a NACA 230M profile.

Power point consists of two turboshaft gas turbine engines with a free turbine TV2-117AT of the St. Petersburg NPO named after. V.Ya.Klimov take-off power of 1250 kW each on the Mi-8T or TVZ-117MT - 1435 kW each on the Mi-8MT, AMT and MTB, installed on top of the fuselage and closed by a common hood with opening flaps. The engine has a nine-stage axial compressor, an annular combustion chamber and a two-stage turbine. Engine length 2.835m, width 0.547m, height 0.745m, weight 330kg. The engines are equipped with dust protection devices.

Fuel the system consists of a consumable fuel tank with a capacity of 445 l, a left external tank of 745 or 1140 l, a right external tank of 680 or 1030 l, and an additional tank of 915 l in the cargo compartment.

Transmission consists of main, intermediate and tail gearboxes, brake shafts, and main rotor. The VR-8A three-stage main gearbox provides power transfer from engines with an output shaft rotation speed of 12,000 rpm to the main rotor with a rotation speed of 192 rpm, the tail rotor - 1,124 rpm and the fan - 6,021 rpm for cooling , engine oil coolers and main gearbox; The total capacity of the oil system is 60 kg.

Control duplicated, with rigid and cable wiring and hydraulic boosters driven from the main and backup hydraulic systems. The AP-34B four-channel autopilot ensures stabilization of the helicopter in flight in roll, heading, pitch and altitude. The main hydraulic system with a working pressure of 4.5 MPa provides power to all hydraulic units, and the backup one, with a pressure of 6.5 MPa, provides power only to the hydraulic boosters.

Equipment. The heating and ventilation system supplies heated or cold air to the crew and passenger cabins; the anti-icing system protects the main and tail rotor blades, the front windows of the cockpit and engine air intakes from icing.

Equipment for instrument flights in difficult meteorological conditions day and night includes two ARB-ZK attitude indicators, two NV rotation speed indicators, a GMK-1A combined heading system, an ARK-9 or ARK-U2 automatic radio compass, and an RV-3 radio altimeter.

Communication equipment includes VHF command radios R-860 and R-828, HF radios R-842 and Karat, and an aircraft intercom SPU-7. The Mi-8T has RI-65 voice communication equipment to notify the crew about in-flight emergencies. Military versions of the Mi-8MT are equipped with a Lipa IR jamming station, a screen-exhaust device for suppressing IR radiation from engines, containers with LC, and an armored cockpit.

At the request of the customer, an external load suspension system is installed: cable for 3000 kg and articulated-pendulum for 2500 kg and a winch with a lifting capacity of 150 kg.

Armament. Military versions use a machine gun with a caliber of 12.7 or 7.62 mm in the nose mobile installation, built-in holders on shaped pylons on the sides of the fuselage for installing up to six NAR units with up to six ATGMs placed on top on guide rails. Containers with machine guns or cannons can also be suspended on pylons, and machine guns and grenade launchers can be mounted on pins in the blisters and side openings of the cargo compartment.

Russian Civilization

Mi-8 (V-8, product “80”, according to NATO: Mi-8 Hip- “hip”) is a Soviet/Russian multi-purpose helicopter created by the Mil Design Bureau in the early 1960s. This car is the most popular twin-engine helicopter in the world, and is also included in the list of the most popular helicopters in history. Widely used in many countries around the world to perform most civil and military tasks.

Story

The first B-8 prototype flew on July 9, 1961; second prototype B-8A - September 17, 1962. After a number of modifications, the Mi-8 was adopted by the Soviet Air Force in 1967 and proved to be such a successful machine that purchases of the Mi-8 for the Russian Air Force continue in our time. The Mi-8 is operated in more than 50 countries, including India, China and Iran.

The modernization of the Mi-8 helicopter, which ended in 1980, led to the creation of an improved version of this machine - the Mi-8MT (product “88”, which received the designation Mi-17 when exported), which is distinguished by an improved power plant (2 TV3- 117), as well as the presence of an auxiliary power unit. The Mi-17 is not so widespread and is used in about 20 countries around the world.

In 1991, production of the new civilian transport modification Mi-8AMT (the export version is called Mi-171E) began, and in the late 1990s, the military transport and assault modification Mi-8AMTSh (Mi-171Sh).

In 2014, the 3,500th helicopter of the Mi-17 family was delivered to the customer.

Design

Single-rotor helicopter with 5-bladed main rotor and 3-bladed tail rotor. The fastening of the main rotor blades is hinged (vertical, horizontal and axial hinges), and the tail rotor blades are combined (horizontal and axial), cardan type. The transmission of the Mi-8 helicopter is the same as that of the Mi-4 helicopter. The main rotor blades are all-metal, consisting of a hollow spar pressed from an aluminum alloy, to the trailing edge of which 24 compartments (on some versions 23) with a honeycomb core of aluminum foil are glued, forming a profile. All main rotor blades are equipped with a pneumatic spar damage alarm. The Mi-8 is equipped with an electric anti-icing blade system, which operates in both automatic and manual modes, and is powered by an alternating voltage of 208 volts. If one of the engines fails in flight, the other engine automatically switches to increased power, while horizontal flight is performed without reducing altitude. In the main mode, the main rotor rotates at a speed of 192 min-1, the steering rotor - 1445 min-1. The helicopter control system uses hydraulic boosters - three KAU-30B (combined control unit) to control the main rotor and one RA-60B (steering unit) to control the tail rotor.

The landing gear is tricycle, non-retractable, with a self-orienting front strut in flight. To prevent the tail rotor from touching the ground, there is a tail support. The helicopter's external suspension system makes it possible to transport cargo weighing up to 3 tons. The Mi-8 is equipped with a four-channel autopilot AP-34, which provides stabilization of roll, pitch and direction, as well as flight altitude (+...-50m). In the passenger version, the helicopter cabin can accommodate up to 18 seats; in the transport version, it is equipped with folding benches for 24 seats. To maintain a comfortable temperature in the cockpit and cargo compartment, the helicopter is equipped with a heating system, using a KO-50 kerosene heater, and ventilation. Navigation and flight instruments and radio equipment in all modifications of the helicopter allow flights at any time of the day in any weather.

Helicopters of different modifications differ quite significantly in the composition of their equipment. Early helicopters (Mi-8, Mi-8T) are equipped with two TV2-117 engines with a power of 1500 hp, with a 10-stage compressor and starting from a GS-18TO starter-generator installed on each engine. When starting the first engine, its starter-generator is powered by six on-board 12CAM28 batteries (monoblock aviation starter with a capacity of 28 Ah) with a voltage of 24 V, the second engine is powered by a starter-generator of an already running engine, and three batteries. When the GS-18TO engines are running, they supply a voltage of 27 volts to the main power supply system. Four batteries are installed in the pilot's cabin under the shelves of electrical and radio equipment, two on each side, the remaining two behind the pilot's cabin in the cargo compartment, in the passenger version in the rear part behind the cabin partition. Despite their relatively small capacity, they are capable of providing 5 engine starts in a row on the ground and in the air at altitudes of up to 3 km, while delivering a current of 600-800 amperes; when the engines are running, they are charged from DC generators and automatically turn off when the rated capacity is reached or turn on in the event of a voltage drop in the on-board network (if generators fail) using differential minimum relays DMR-600T, a generator operation monitoring system.

A three-phase voltage of 36 V for powering gyroscopic devices is provided by one of two PT-500Ts converters (main or backup), a single-phase current of 208 V with a frequency of 400 Hz to power the heating elements of propellers and windshields is provided by the SGO-30U generator installed on the main gearbox. Also from SGO-30U through a single-phase transformer TS/1-2, which powers radio and navigation equipment, and from it - transformer Tr-115/36, which supplies engine and transmission control devices with a single-phase voltage of 36 V, and through transformer 115/7.5 - power supply for main rotor contour lights. If the SGO-30U fails, the heating elements of the blades are turned off, the rest of the equipment automatically switches to power from the PO-750A converter.

Helicopters of later series (Mi-8MT, Mi-17, etc.) have been significantly modernized. The engines were replaced with more powerful (2250 hp) TV3-117 with a 12-speed compressor and air starting; to supply air to the air starters of the engines, an AI-9V APU was installed, the STG-3 starter-generator of which can supply a voltage of 27 to the on-board network when the APU is running volts with a power of 3 kW for 30 minutes. The main power supply system with a voltage of 208 V and a frequency of 400 Hz is powered by two SGS-40PU generators located on the main gearbox. In the 27 V system, two 12SAM-28 batteries are installed for starting the APU and emergency power supply, and three VU-6A rectifier devices are installed for the main power supply when the engines are running. The first generator powers VU No. 1, propeller heating elements and transformer TS310S04B (power 1 kW) for supplying a three-phase 36 V network, from the right generator - VU No. 2 and No. 3, heated glass and dust protection device (ROM) of engines, transformer TS/1 -2.

If generator No. 1 fails, the TS310S04B automatically switches to generator No. 2; if both generators or the transformer itself fail, the PT-200Ts converter starts up. If generator No. 2 fails, TS/1-2 switches to generator No. 1; if both generators or the transformer itself fail, the PO-500A converter starts up. Also, if generator No. 2 fails, VU-6A No. 3 switches to generator No. 1.

The helicopter has two hydraulic systems - the main one and the backup one, the pressure in each is created by a separate NSh-39M pump installed on the main gearbox. The pressure is adjustable within 45+-3 ... 65+8-2 kgf/sq.cm. GA-77V automatic pump unloading machines are supported by hydraulic accumulators - two in the main system and one in the backup system. Hydraulic supply to consumers - RA-60B tail rotor control, KAU-30B general pitch main rotor, two KAU-30B longitudinal and lateral controls, a movable stop in the tail rotor control system and the "Step-Gas" handle clutch - is switched on by separate electromagnetic valves GA192.

Modifications

Experienced

V-8 - The first prototype with one gas turbine engine (gas turbine engine) AI-24V (single-shaft turboprop engine with a 10-stage axial compressor, an annular combustion chamber and a three-stage turbine) designed by A. G. Ivchenko. The first flight took place on June 24, 1961.

-V-8A - Second prototype with two TV2-117 gas turbine engines (aviation turboshaft engine)

V-8AT - The third prototype.

V-8AP - The fourth prototype.

Passenger

Mi-8P - passenger helicopter has 28 seats. Equipped with rectangular portholes.

Mi-8PA - modification of Mi-8P with GTD TV2-117F engines (designed to operate in difficult climatic conditions)

Transport

Mi-8T is a transport and landing helicopter designed for the Air Force.

Mi-8TS is an export version of the Mi-8T created specifically for the Syrian Air Force, modified for dry climate conditions.

Multipurpose

Mi-8TV - “Transport, armed.” has been in service with the USSR Air Force since 1968. It is distinguished by the installation of guides for 4 9M14M “Malyutka” ATGMs, an A-12.7 machine gun, armoring of the cockpit, gearbox and engine hoods, armored glass of the cockpit (mainly frontal).

Mi-8AT is a helicopter with TV2-117AG engines.

Mi-8AV is an aerial minelayer for ground forces. Equipped with a VMR-1 minelayer. Which could set from 64 (in the first modifications) to 200 minutes.

Mi-8AD is a modification of an air minelayer for ground forces, designed to lay small-sized non-retrievable anti-personnel mines.

Mi-8MT - modification with TV3-117 engines.

Mi-8MTV or Mi-8MTV-1 - modification with TV3-117VM, TV3-117VM series 02, VK-2500-03 engines. Serial production began in Kazan in 1988.

Mi-8MTV-5 - the shape of the nose section has been replaced (“dolphin nose”). Since the end of 2013, it has been equipped with the Test-1 BUR product instead of SARPP-12DM (SARPP-12D1M).

Mi-8MTKO is a variant with lighting equipment adapted for the use of a night vision flight system.

Mi-17-1V - variant of the Mi-8MTV intended for export

Mi-8AMT (export designation - Mi-171E) - a variant of the Mi-8MTV with minor changes, produced at the aircraft plant in Ulan-Ude (since 1991). There are different modifications: passenger, transport, search and rescue, VIP salon, etc.

Mi-171 is a modification of the Mi-8AMT helicopter, has a certificate issued by the Interstate Aviation Committee.

Mi-171A1 is a modification of the Mi-8AMT helicopter that complies with the US Rotorcraft Airworthiness Standards FAR-29.

Mi-17KF is a modification of the Mi-8MTV-5 with Honeywell avionics. The Mil Design Bureau was created jointly with KVZ by order of the Canadian company Kelowna Flightcraft. The first flight was made on August 3, 1997.

Mi-8TG - modification of Mi-8P with polyfuel gas turbine engines TV2-117G (Improved version of TV2-117A with additional graphite bearing seals. TV2-117A engines are upgraded to TV2-117AG during repairs)

Mi-14 is a multi-purpose amphibious helicopter.

Mi-18 is an extended version of the Mi-8MT. Not mass produced.

Mi-8MSB - Ukrainian modification with TV3-117VMA-SBM1V 4E series engines, for the Air Force (adopted into service in April 2014) and for export.

Mi-8TECH-24 - flying technical and operational unit. Equipped with plumbing, electrical, testing and other equipment used during the operation and repair of helicopter equipment.

Mi-8TZ - tanker and fuel transporter.

Mi-8BT - trawl towing vehicle.

Mi-8SP is a special sea rescue aircraft.

Mi-8SPA is a search and rescue helicopter for searching for cosmonauts and crews of other aircraft in the event of splashdown.

Mi-8TL is a forest fire modification equipped with a massive water discharge system and a water cannon.

Mi-8S is a command helicopter equipped with round windows.

Mi-8PS is a command helicopter equipped with square windows.

Mi-8KP is a specialized command post for conducting large-scale integrated search and rescue operations.

Mi-8GR or Mi-8R is a reconnaissance helicopter designed for visual observation and photography in the front line.

Mi-8K - artillery spotter.

Mi-8TAKR is a helicopter with a television surveillance system.

Mi-8VD is a radiation-chemical reconnaissance helicopter.

Mi-8S is a modification of a helicopter with a combined power plant of turboshaft engines driving the main rotor and a traction turbojet.

Mi-8MTL is a reconnaissance aircraft with the ability to simultaneously use thermal imaging reconnaissance and radio interception with precise determination of target coordinates.

Mi-8MTYU - Was designed in a single copy. Designed specifically for detecting landers and small surface targets; a radar antenna is located in the nose. Used by the Ukrainian Air Force.

Mi-AMT-1 - equipped with a luxury cabin (VIP cabin) for the government air squad of the President of the Russian Federation

Air command posts

Mi-8VKP or Mi-8VzPU - air command post.

Mi-8IV or Mi-9 - an air command post intended for division commanders, a serial modification.

Mi-9 is an air command post for commanders of motorized rifle and tank divisions. Equipped with an automated communication complex. Designed in 1987 on the basis of the Mi-8MT.

Mi-9R is an air command post created specifically for commanders of missile divisions of the Strategic Missile Forces. Equipped with an automated communication complex. Designed in 1987 on the basis of the Mi-8MT.

Medical

Mi-8MB - air hospital. Designed on the basis of the Mi-8T.

Mi-8MTB - armored air hospital. Created on the basis of the Mi-8MT.

Mi-8MTVM - medical modification of the Mi-8MTV.

Mi-8MTV-MPS is a medical search and rescue helicopter created on the basis of the Mi-8MTV.

Mi-17G is an air hospital version created for export.

Mi-17-1VA "Ambulatory" - a sanitary variant of the Mi-8MTV designed for export.

Jammers

Mi-8SMV is a jammer equipped with a Smalta-V (Smalta-helicopter) jamming station.

Mi-8PP is an electronic warfare (electronic warfare) helicopter, according to some sources it is equipped with the “Pole” complex, but in the 70-80s. EW complexes were usually called by the names of plants; it is quite possible that this option is simply confused with early versions of the Mi-8PPA.

The Mi-8PPA is an electronic warfare helicopter equipped with the Azalia and Fasol stations; according to some sources, it is a modified version of the Mi-8PP.

Mi-8MTP - jammer.

Mi-8MTPB - jammer.

Mi-8MTPI - jammer.

Mi-8MTPSh - jammer.

Mi-8MTD - jammer.

Mi-8MTR1 - jammer.

Mi-8MTR2 - jammer.

Mi-8MTS - jammer.

Mi-8MTSh1 - jammer.

Mi-8MTSh2 - jammer.

Mi-8MTSh3 - jammer.

Mi-8MTYA - jammer.

Mi-8MT1S - jammer.

Agricultural

Mi-8ATS is an agricultural version of the helicopter with fertilizer spraying devices. Designed on the basis of the Mi-8T.

Mi-8MTSkh - agricultural helicopter. Developed on the basis of the Mi-8MT.

Drums

Mi-8AMTSh (export designation - Mi-171Sh) is a transport and attack helicopter, equipped with a set of weapons equivalent to the Mi-24, a complex of armor protection for the crew and adapted for the use of night vision equipment. At the Farnborough Air Show 99 it was designated "Terminator". Since the end of 2011, it has been equipped with an on-board recording device “Test-1” instead of SARPP-12. Since the end of 2013, it has been equipped with the Test-1 BUR product with an expanded list of recorded parameters (40 analog and 28 one-time).
Protection: electronic device, steel armor plates, LC ejection machine (False target - a device, structure, formation or means that imitates a real protected object according to signal characteristics, movement parameters (if the object is moving) and other signs essential for recognition and intended to distract electronic weapons from the actual target (protected object)), jammer, protected fuel tanks.

Features: winch lowering up to 4 people at a time, ramp, IR search light, night vision goggles, infrared camera.

Armament S-8 missiles in blocks, Attack missiles.

Mi-8AMTSh-1 - modification of the Mi-8AMTSh, equipped with a weapons complex in combination with a luxury salon (VIP salon)

TTX Mi-8

	V-8			Mi-18
Year of construction	1961	1965	1965	1975	1980	1987	1991	1991	2014
Crew, people	3	3	3	3	3	3	3	3
Number of passengers (paratroopers)	18	28	24	24	30	24	27	26
Length (with rotating screws), m.		25,31	25,31	25,31	25,31	25,31	25,31	25,31	25,31
Height (with rotating tail rotor), m		5,54	5,54	5,54	5,54	5,54	5,54	5,54	5,54
Main rotor diameter, m	21	21,3	21,3	21,3	21,3	21,3	21,3	21,3	21,3
Empty weight, kg	5726	7000	6934	7200	7550	7381	6913	7514
Normal take-off weight, kg	-	11570	11100	11100	11500	11100	11100	11878
Maximum take-off weight, kg	-	12000	12000	13000	13000	13000	13000	no data	12500
Engines	1 x AI-24V	2 x TV2-117	2 x TV2-117	2 x TV3-117MT	2 x TV3-117MT	2 x TV3-117VM	2 x TV3-117VM	2 x TV3-117VM	2 x TV3-117VMA-SBM1V 4E
Engine power (takeoff mode)	1 x 1900 l. With.	2 x 1500 l. With.	2 x 1500 l. With.	2 x 1900 l. With.	2 x 1900 l. With.	2 x 2000 l. With.	2 x 2000 l. With.	2 x 2000 l. With.	2 x 1500 l. With.
Maximum speed, km/h	-	250	260	250	270	250	250	250	260
Cruising speed, km/h	-	225	225	220	240	240	230	230	225
Dynamic ceiling, m	-	4200	4500	5000	5550	6000	6000	6000	9150
Practical range, km	-	425	480	520	580	590	570	715	600

Flight range, km:
-with additional fuel tanks 1300
-with a maximum aviation fuel reserve of 800
-at maximum load 550
-Aviation fuel consumption, t/hour 0.72

Combat use of MI-8

Six-Day War (1967) - at least 3 Egyptian Mi-8s are destroyed by Israeli aircraft at airfields.
-Ethiopian-Somali War (1977-1978)
-Afghan War (1979-1989) - the 40th Army lost 174 Mi-8 helicopters; the losses of helicopters of the border troops, SAVO and the Afghan army are unknown. During the Afghan conflict, there was a recorded case of an Mi-8 being shot down with an old English Lee-Enfield rifle ("drill").
-Georgian-Abkhazian war (1992-1993)
-Iran-Iraq War (1980-1988) - 6 Iraqi Mi-8s were shot down in the air by Iranian fighters. The total losses of Iraqi helicopters are unknown.
-Paquisha War (1981) - one Peruvian Mi-8 helicopter was shot down by FAL rifle fire
-War in Karabakh
-First Chechen war (1994-1996)
-Ethiopian-Eritrean conflict (1998-2000)
-Invasion of militants into the Republic of Dagestan (1999) - Russian army lost at least three Mi-8s.
-Kargil War (1999)
-NATO operation against Yugoslavia (1999) In 1999, a Serbian Mi-8 shot down a reconnaissance UAV with a machine gun. In 2000, a similar incident occurred.
-Second Chechen War (1999)
-War in Afghanistan (since 2001)
-Iraq War
-Bhutan Operation against Assamese Resistance 2003
-Armed conflict in South Ossetia (2008)
-Civil war in Syria (since 2011)
-Armed conflict in eastern Ukraine (2014)

Operated:

Used in more than 50 countries around the world

Russia - 534 in 2010, 34 Mi-8 (22 Mi-8AMTSh and the rest Mi-8AMT and Mi-8MTV) were put into service at the air bases of Budennovsk and Korenovsk (10 Mi-8). 53 Mi-8AMTSh in 2013
-Azerbaijan
-Algeria
-Argentina - in 2010-11 a contract was signed for six Mi-171Es for flights from the coast of Argentina to Antarctica
-Armenia - as of 2014, 3 m-17v were also purchased
-Angola
-Afghanistan - an agreement was concluded for the supply of 21 military transport Mi-17V5.
-Bangladesh
-Brazil - in 2011, three Mi-171A1 were manufactured for ATLAS airline.
-Belarus
-Bulgaria
-Bosnia and Herzegovina
-Burkina Faso
-Butane
-Venezuela - 20 Mi-17s (in service with the country's air force), 6 Mi-17s have been ordered.
-Hungary
-Vietnam
-Ghana
-Guyana
-Germany
-Georgia - in 2011, there were 17 units in service. Mi-8T
-Djibouti
-Zambia
-Egypt
-India - a large number of Mi-8 and Mi-17 helicopters are in operation, the delivery of another 80 helicopters, Mi-17V-5, is planned.
-Indonesia - 6 Mi-17-B5 were delivered in July 2008 under an agreement concluded in 2005.
-Iraq - in 2010, the United States placed an order for the Iraqi Air Force for 80 Mi-17 helicopters (of which 46 were used), by 2012 68 were delivered.
-Iran - 5 Mi-171s have been ordered, of which 2 have already been delivered.
-Kazakhstan
-Cameroon - in 2013, an agreement was concluded for the supply of a batch of Mi-17.
-Canada
-Kenya
-Cyprus
-Kyrgyzstan
-China
-North Korea
-Colombia
-Cuba - in 2011, there were 2 units in service. Mi-8R and 8 pcs. Mi-17
-Latvia - as of 2011, there were 4 units in service. Mi-17
-Libya
-Lithuania - in 2011, there were nine Mi-8s in service
- Macedonia
-Mexico
-Moldova
-Mongolia
-Myanmar
-Nepal
-Nigeria
-Nicaragua - as of 2011, 16 pcs. Mi-17 is in service
-UAE
-UN
-Pakistan
-Transnistria
-Poland
-Peru - In 2010, 6 Mi-171E and Mi-171Sh were acquired.
-Romania - 25 units delivered in 1968. Mi-8T and 14 pcs. Mi-8PS, in 1985 - 3 more units. Mi-17; in the 1990s, two more Mi-17s were acquired for the police, one Mi-17-1V and one Mi-17-1VA; in 2001 they were withdrawn from army service (put in storage and transferred to the Ministry of Internal Affairs).
-Syria
-Serbia
-Slovakia
-Sudan - 6 units were purchased in 2012, in 2013 a contract was concluded for the supply of 16 Mi-8 transport vehicles. Sudan Police - 1 Mi-17V-5 (w/n 101, serial number 736M07)
-USA - 70 Mi-17V5 units purchased for missions in Afghanistan.
-Sierra Leone
-Tajikistan
-Turkmenistan
-Turkey - 19 units were ordered in 1993 and delivered in 1995. Mi-17-1B for the gendarmerie, in 2007 one helicopter crashed due to technical reasons
-Ukraine
-Uzbekistan
-Finland
-Chad
-Montenegro
-Czech Republic
-Croatia
-Sri Lanka
-Ecuador
-Eritrea
-Estonia
-South Korea. Police of the Republic of Korea - 3 Mi-172, as of the beginning of 2014.
-SOUTH AFRICA
-South Sudan