Helicopter MI 8 technical characteristics. Russian aviation. Combat use in Afghanistan

The first version of the Mi-8 helicopter with a four-bladed rotor was tested in 1962. In October 1963, the second version with a five-bladed main rotor began to be tested, which at the end of 1965 was accepted into mass production.

Mi-8 is equipped with an anti-icing system that works both in automatic and manual modes... The external suspension system of the helicopter allows you to transport cargo weighing up to 3000 kg. If one of the engines fails in flight, the other engine automatically reaches increased power, while level flight is performed without lowering the altitude. The Mi-8 is equipped with an autopilot that ensures roll, pitch and yaw stabilization, as well as a constant flight altitude. Navigation and flight instruments and radio equipment, which the helicopter is equipped with, make it possible to fly at any time of the day and in adverse weather conditions.

The helicopter is mainly used in transport (Mi-8T) and passenger versions. In the passenger version, the Mi-8P is equipped to carry 28 passengers. By special order, in Kazan, a version with a "luxury" cabin, designed for seven passengers, can be manufactured. Orders for B. Yeltsin, N. Nazarbayev, M. Gorbachev and others were completed. The military version of the Mi-8T has pylons for the suspension of weapons (NUR, bombs). The next military modification of the Mi-8TV has reinforced pylons for the suspension of a large number of weapons, as well as a machine gun mount in the bow of the cockpit. By rearranging the PB to the left side, its efficiency was increased.

The Mi-8MT is the latest modification of the helicopter, which was the logical completion of the transition from a transport helicopter to a transport-combat helicopter. Installed more modern TVZ-117 MT engines with additional gas turbine AI-9V and a dustproof device at the entrance to the air intakes. To combat surface-to-air missiles, there are systems for dispersing hot gases from engines, shooting false heat targets and generating pulsed infrared signals. In 1979-1988. the Mi-8MT helicopter took part in the military conflict in Afghanistan.

Helicopter modifications:

Mi-8T (Hip-C)- the main military transport modification.
Mi-8TV- an upgraded version with enhanced armament.
Mi-8TVK- export version of the Mi-8TV with 6 Malyutka ATGM.
Mi-9- a flying command helicopter based on the Mi-8T.
Mi-8SMV- EW and RER helicopter.
Mi-8PPA- a modernized version of the Mi-8SMV in the role of a liaison helicopter and an electronic warfare helicopter.
Mi-8MT- transport and combat helicopter based on the Mi-8TV (1991).

Tactical specifications helicopter Mi-8:

The year of adoption is 1966.
The main rotor diameter is 21.29 m.
The tail rotor diameter is 3.91 m.
Length - 18.22 m.
Height - 5.65 m.
Weight, kg
- empty - 7260,
- normal takeoff - 11100,
- maximum takeoff - 12200.
Domestic fuel - 1450 + 1420 kg.
Engine type - 2 GTE Klimov TV2-117A (TV3-117MT).
Power - 2 х 1710 hp (2 x 3065 HP)
Maximum speed- 260 km / h
Cruising speed - 225 km / h.
Practical range - 1200 km.
The operating range is 465 km.
Service ceiling - 4500 m.
Static ceiling - 1900 m.
Crew - 2-3 people.

28 passengers or 32 soldiers or 12 stretchers with accompanying persons or 4000 kg of cargo in the cabin or 3000 kg of suspension.

Based on site materials

In the late 1950s, abroad and in our country, work began on the creation of second-generation helicopters with turboshaft engines, and in May 1960. the cost center began the development of a new multipurpose helicopter to replace the well-proven multipurpose helicopters Mi-4 ... The first experienced helicopter AT 8 , with one GTE AI-24V designs by S.P. Izotov and a four-bladed 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 AT 8, with two gas turbine engines TB2-117 capacity for 1267kW, made its first flight on September 17, 1962, successfully passed flight tests and from 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 regulation of the operation of engines, ensuring their synchronization and maintaining the speed of rotation of the main rotor within the specified limits. Compared to a helicopter Mi-4 the new helicopter had better flight characteristics and twice the payload. By helicopter Mi-8 in 1964-1969. 7 international records were set, most of which were female, set by female pilots L.G. Isaeva, N.A. Kollets and T.V. Russiyan, and unsurpassed to date.

Helicopters Mi-8 are the most widespread transport helicopters in the world, second only to light multipurpose and transport Bell UH-1 "Iroquois" and "Huey" ... More than 8000 helicopters were produced in total Mi-8 at the Kazan Helicopter Plant and the Aviation Plant in Ulan-Ude, of which more than 2000 have been exported to more than 40 countries of the world, 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 are:

Mi-8P- passenger helicopter with gas turbine engine TV2-117A capacity for 1267kW, with a cabin for 28 passengers and square windows;
Mi-VPS "Salon"- a passenger helicopter with a superior cabin for 11 passengers with an eight-seater common seat on the starboard side and two seats and a rotating seat on the left side, improved interior trim and ventilation system and a toilet; also produced in versions with a saloon for 9 and 7 passengers;
Mi-8T- transport helicopter with gas turbine engine TV3-117MT capacity for 1454 kW, for the carriage of goods weighing 4000kg in the cockpit, or 3000kg on an external sling, or 24 passengers in the outboard seats, or 12 patients on a stretcher with an accompanying person; It is distinguished by small round cockpit windows and equipment; in military versions, it is equipped with pylons with holders for weapons.
Mi-8TG- modification of the Mi-8T helicopter with a gas turbine engine TV2-117TG capacity for 1103kW, developed in 1987, the world's first helicopter to use liquefied petroleum gas along with aviation fuel;
Mi-8TV- an amphibious 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-mounted weapons holders from six blocks of 32 NAR each, and on guide rails up to six ATGMs AT-2 with semi-automatic control; It was also produced in an export version with six ATGMs AT-3 with manual control... Over 250 helicopters Mi-8TB and MT were converted into Mi-17 .
Mi-8MT- modernized airborne transport helicopter with gas turbine engine TV3-117MT capacity for 1454kW, with dust protection devices, auxiliary power unit 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 ; produced in versions Mi-8AM and MI-8MTV with various equipment and weapons and in the variant Mi-8MTB-1A for civilian use;
Mi-8PP- helicopter-producer of active jamming with a container and with cross-shaped dipole antennas on the sides of the fuselage; a number of modifications were also built for conducting 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 a load of mass in it 5-6.5t, and on the external sling - loads weighing 5t... In 1980. two helicopters Mi-8MT were modernized in Mi-18 with an enlarged cab, new fiberglass blades and retractable tricycle landing gear, and in 1982. flight tests have been completed, which have confirmed an increase in carrying capacity with an increase in speed and range of flight 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; suspension of bombs with caliber is possible 50-500kg on beam holders BDZ-57KRVM; in the bow can be placed a mobile unit with a machine gun caliber 12.7mm, in the openings of sliding doors up to 8 pivot mounts with machine guns caliber 7.62mm, and on the holders - 4 cannon containers UPK-23-250 with guns GSh-23L caliber 23mm what the helicopter does Mi-8MTV-2 the most heavily armed in the world. To dissipate the heat flux of the gas turbine engine, screen-exhaust devices are installed, and to protect against missiles with an IR system, a passive jamming system is installed on the helicopter consisting of 4 ACO-2B cassettes on the tail boom and 6 cassettes on the fuselage; Each cassette contains 32 IR decoys PPI-26-1 and generators of pulsed IR signals. The helicopter is equipped with armor plates covering the floor, front and rear parts of the cockpit and the hydraulic panel. The helicopter can be equipped with radar and radio equipment for long-distance navigation communications;
Mi-8AMTSh- option combat helicopter Mi-8AMT, with a complex of supersonic ATGM "Storm"; exhibited at the Farnborough Aerospace Show in September 1996.

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

The fuselage of the helicopter is of frame construction, 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. The glazing of the cockpit provides good visibility, the right and left sliding blisters are equipped with emergency release mechanisms. In the central part there is a cab with dimensions of 5.34 x 2.25 x 1.8m in a transport version with a cargo hatch with doors increasing the length of the cab to 7.82m, and a central sliding door with dimensions of 0.62 x 1.4m with an emergency release mechanism; there are mooring units and an electric winch on the floor of the cargo compartment, and an electric winch boom is installed above the door. The cargo compartment is designed for the carriage of goods weighing up to 4 tons and is equipped with folding seats for 24 passengers, as well as nodes for attaching 12 stretchers. In the passenger version, the cabin has dimensions of 6.36 x 2.05 x 1.7m and 28 seats, two on each side with a pitch of 0.74m and a passage of 0.3m; in the rear part of the cab on the right is a wardrobe, and in the rear part 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 a working skin, equipped with nodes for attaching a controlled stabilizer and a tail support.

A stabilizer with a size of 2.7m and an area of 2m 2 with a NACA 0012 single-spar structure, with a set of ribs and duralumin and canvas sheathing.

The chassis is tricycle, non-retractable, the front support is self-orienting, with two wheels measuring 535 x 185mm, the main supports are shaped-type with liquid-gas two-chamber shock absorbers and wheels with dimensions of 865 x 280mm. The tail support consists of two struts, a shock absorber and a support heel; track of the chassis is 4.5m, the base of the chassis is 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-hardened steel hinges on a vibration table, a tail section, a steel tip and a steel 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 signaling system about damage to the spar and an electric thermal anti-icing device. ...

Tail rotor with a diameter of 3.9 m, three-bladed, pushing, with a cardan-type hub and all-metal rectangular blades 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. V.Ya. Klimov with a takeoff power of 1250 kW at Mi-8T or TVZ-117MT - 1435 kW each for Mi-8MT, AMT and MTB installed on top of the fuselage and closed by a common hood with opening doors. 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 motors are equipped with dust protection devices.

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

The transmission consists of a main, intermediate and tail gearboxes, brake shafts, and a main rotor. The main gearbox VR-8A is three-stage, provides power transmission from engines with a rotational speed of the output shafts of 12000 rpm to the main rotor with a rotational speed of 192 rpm, the tail rotor - 1124 rpm and the fan - 6021 rpm for cooling , engine oil coolers and main gearbox; the total capacity of the oil system is 60 kg.

Redundant control, with rigid and cable wiring. And hydraulic boosters driven from the main and backup hydraulic systems. The AP-34B four-channel autopilot provides stabilization of the helicopter in flight in terms of 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 redundant one, with a pressure of 6.5 MPa, supplies only hydraulic boosters.

Equipment. The heating and ventilation system supplies heated or cold air to the cockpits and passengers, the anti-icing system protects the rotor and tail rotor blades, front cockpit windows and engine air intakes from icing.

The equipment for instrument flight in complex meteorological conditions, day and night, includes two ARB-ZK artificial horizons, two NV speed indicators, a combined heading system GMK-1A, an ARK-9 or ARK-U2 automatic radio compass, and a RV-3 radio altimeter.

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

At the request of the customer, an external cargo 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. On military versions, a 12.7 or 7.62mm machine gun is used in a bow 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 of guide rails. Containers with machine guns or cannons can also be suspended on the pylons, and machine guns and grenade launchers can be installed in the blisters and side openings of the cargo compartment on pivots.

EI Ruzhitsky "Helicopters", 1997

Technical details Mi-8T

Power point: 2 x GTE TV2-117A capacity for 1250kW, rotor diameter: 21.29m, fuselage length: 18.17m, height: 4.38m, fuselage width: 2.5m, takeoff weight: 12000kg, empty weight: 6625kg, maximum speed: 250km / h, cruising speed: 225km / h, dynamic ceiling: 4500m, range of flight:

A number of original technical solutions were used in the design of the helicopter: large-sized duralumin stampings, glue-welded joints, and an automatic engine control system. Compared to the Mi-4, the new helicopter had better flight characteristics and twice the payload. The first experimental V-8 with one AI-24V engine and a four-blade propeller from the Mi-4 took off for the first time on June 24, 1961 (test pilot B.V. Zemskov). On August 2, 1962, test pilot N.V. Lyoshin tore off the V-8A prototype with two TV2-117 and a five-blade propeller from the ground, and on September 17 its first free flight took place.

In May 1964, the assembly of the new passenger V-8AP in the version of the government cabin was completed. It almost did not differ from the V-8AT and served as the basis for testing the modernized AP-34B autopilot and the main rotor revolution synchronizer. V-8AP was shown to the leaders of the party and government. In September of the same year, the second stage ("B") of the joint state testing program began with flights on the V-8AP. Having successfully completed the program of state tests, the V-8AP was converted in the spring of 1965 at the pilot production plant No. 329 into a comfortable version for carrying 28 passengers. By this time, the experienced V-8AP helicopter was practically perfected, the resource of most of its units reached 500 hours. recognized as one of the most successful middle class helicopters. The helicopter was just as successfully demonstrated a few months later at an industrial exhibition in Copenhagen. Subsequently, Mi-8 helicopters took part in all major international air shows and exhibitions almost every year, adequately representing the domestic aviation industry in different parts of the world.

Serial production of the Mi-8 began in March 1965 at the aircraft plant No. 387 in Kazan. At the end of the year, the first serial samples... By 1969, the Mi-8 had completely replaced the Mi-4 on the assembly line. In 1970, the Ulan-Udensky plant also began its production.

A single-rotor Mi-8 helicopter with a five-bladed three-articulated main rotor and a three-bladed tail rotor. The landing gear is tricycle, non-retractable, with a self-orienting front strut fixed in flight. There is a tail support to protect the tail rotor. The Mi-8P helicopter differs from the Mi-8T transport helicopter with rectangular windows and the absence of a Doppler ground speed and drift angle DIV-1 on the tail boom. The main Mi-8P version has 28 soft passenger seats. The 28-seat layout of the passenger compartment became the main one on the production Mi-8P. It was only in 1968 that it underwent a slight revision. The rear fuselage compartment was changed - the luggage compartment was located in it. The passenger compartment has lengthened by more than a meter. The rear doors were made smaller, and a rear entrance door with a gangway was installed in them. The Mi-8P could also be used as an ambulance or transport helicopter for the transportation of small cargo inside the cabin and large cargo on an external sling. Several years later, on the basis of the Mi-8P and its later modifications, variants with a passenger cabin for 20, 24 and 26 seats were created. The Mi-8P can be used as an ambulance and transport (small cargo inside the cabin, large cargo on an external sling).

In 1968, the rear fuselage was redesigned. The luggage compartment was located there. The passenger compartment has lengthened by more than a meter. The rear doors have become smaller, and a rear entrance door with a gangway has been installed in them.

In 1962-1991, about 5200 Mi-8 helicopters (3700 in Ulan-Ude) were manufactured at two factories. About 2800 of them were exported to 40 countries of the world. Half of the released helicopters are still in operation. In 1964-1967, 7 international records were set on the Mi-8 (most of them were female crews).

Modifications:

B-8A is the second prototype. Notable for two engines and a five-blade propeller.
V-8AP is the fourth prototype. Made in 1964 in the version of the government salon. In 1965, it was converted into a passenger version.
Mi-8APS, Mi-8AP-2, Mi-8AP-4 - enhanced comfort options ("salons"). They differ in the engine. TV2-117AG. Produced in Ulan-Ude.
Mi-8M - modernized for 40 passenger seats (project). It featured an elongated fuselage and TV3-117 engines. Developed in 1964-1971.
Mi-8PA - with forced TV2-117F engines (1700 hp). Certified in Japan in 1980.
Mi-8PS - Salon "for 7, 9 or 11 passengers (respectively Mi-8PS-7, Mi-8PS-9, Mi-8PS-11).
Mi-8S - (the second with this designation) - "salon" based on the Mi-8T. Developed in 1969.

Modification: Mi-8P
Main rotor diameter, m: 21.29
Tail rotor diameter, m: 3.91
Length, m: 18.17
Height, m: 5.65
Weight, kg
- empty: 6800
-normal takeoff: 11100
-maximum takeoff: 12000
Engine type: 2 х GTD TV2-117A
-power, kW: 2 x 1257
Maximum speed, km / h: 250
Cruising speed, km / h: 225
Practical range, km: 480
Practical ceiling, m: 4500
Static ceiling, m: 1900
Crew, pers: 2-3
Payload: up to 28 passengers or 12 stretchers with accompanying persons or 4000 kg of cargo in the cabin or 3000 kg of suspension.

Experienced helicopter V-8A - the second prototype.

The third prototype B-8A in flight.

Experienced helicopter V-8AP is the fourth prototype. 1964 g.

Experienced V-8AP helicopter.

Mi-8P of the first series in flight.

Helicopter Mi-8P. On the background is the Mi-8T.

Mi-8P sits on the site near the Peter and Paul Fortress. St. Petersburg.

A Mi-8P helicopter at the site near the Peter and Paul Fortress.

Mi-8P of Altai Airlines.

Mi-8P of the U Teir company in the parking lot.

Mi-8P is landing.

Government Mi-8PS.

Mi-8P cockpit.

Main rotor The main rotor is designed to create a lifting
forces and traction forces, to ensure longitudinal and
lateral control of the helicopter. Main rotor
consists of five blades and a rotor hub,
mounted on the shaft of the main gearbox VR-14. For
changes in the magnitude and direction of the bearing force
the screw serves as a swash plate.

Main rotor

CARRIER PROPELLER BLADE
Blade
all-metal
constructions
rectangular in plan with a chord of 520 mm.
It has

Main rotor

CARRIER BLADE (FIG. 1)
All-metal blade, the main element
the structure is a spar (a hollow beam with an internal constant
outline).
The spar is made by machining a hollow billet,
extruded from AVT1 aluminum alloy, the spar is hardened for
increasing the resource by work hardening with steel balls on a vibrating table.
Each section of the blade (there are 21 of them in total) has a sheathing of sheet aviation (0.3
mm), glued with honeycomb filler (aluminum foil 0.04 mm), with
lateral ribs (0.4 mm air) and tail stringer (from
PCB). The compartments are glued to the spar, installed between the compartments
liners.
The steel tip is glued to the spar with its cheeks and secured by nine
bolts.
The blade has an anti-icing system electrical connector and
contour fire. Each blade is equipped with an alarm system
damage to the spar.

Main rotor

Rice. 1

Main rotor

The side member damage signaling system consists of
(fig. 2):
- two plugs at the ends of the spar;
- air pressure indicator, including
bellows sensitive element;
- charging valve with spool and key cap.
The bellows is charged with helium with a pressure of 1.05 ... 1.1 kgf / cm2.
The inner cavity of the side member is filled with air under
pressure exceeding the start pressure
signaling device for 0.15 kgf / sq. cm. Air entering the enclosure
signaling device, compresses the bellows and retracts the cylindrical
red cap inside. In case of appearance on the spar
cracks or other damage the air pressure decreases,
the bellows expands and pushes the cap over the line
visual overview of the transparent cap.

Main rotor

Rice. 2

Main rotor

The end part of the blade is a fairing with a front removable
part for the approach to the fastening of balancing weights and to the contour
fire. The balancing weight consists of a set of metal plates. For
of lateral balancing of the blade, a counterweight is inserted into the toe of the spar
(eight bars of 40 cm and weighing 1 kg). Rotating
the centrifugal forces of the blades are absorbed by the screw stop,
installed inside the spar at the end of the blade.

Main rotor

To mount the blades, use
special device.

10. Main rotor

CARRIER SCREW BUSHING (FIG. 3):
The sleeve is designed to transmit rotation
blades from the main gearbox, as well as for
perception and transmission to the fuselage
aerodynamic forces arising on
main rotor. Attaching the blades to the body
bushings are carried out by
horizontal, vertical and axial
hinges.

11. Main rotor

Rice. 3

12. Main rotor

The main parts of the main rotor hub are (Fig. 4):
- Frame;
- Staples;
- Trunnions and housings of axial hinges;
- Levers for turning the blade.
To limit the overhang of the blade when the carrier is inoperative
screw and at low speeds, a centrifugal
overhang stop mechanism .. Vibration damping
blades relative to vertical hinges
carried out using hydraulic dampers. Everything
the bushing hinges are filled with oil, the grade of which depends
on the outside temperature.

13. Main rotor

Rice. 4

14. Main rotor

MAIN DETAILS OF THE CARRIER SCREW BUSHING (FIG. 5):
Spacing of horizontal hinges "b" ...................... 220 mm
Spacing of vertical hinges "b" ...................... 507 mm
Offset of the middle of the eyelet horiz. hinge "a" ................. 45 mm
Swing angle (upward from the plane of rotation) .......... 25 ° ± 30`
Overhang angle (downward from the plane of rotation):
- when focusing on
bracket ........................ 4 ° -20` ... 4 ° + 10`
- when resting on the pawl of the centrifugal limiter ...... 1 ° 40` ± 20`
Rotation angle relative to the vertical hinge:
- forward in rotation ........ 13 ° ± 15`
- back against rotation .... 11 ° ± 10`
Sleeve weight (dry) ............................................. ........................ 610.5 kg

15. Main rotor

Rice. 5

16. Main rotor

HYDRO DAMPER (FIG. 6)
Vibration damping of blades relative to vertical hinges
carried out using hydraulic dampers. Damper piston
has eight bypass valves to dissipate vibration energy.
The valves bypass fluid from the cylinder cavity with increased pressure to
cavity low pressure when the pressure difference between the cavities is reached
20 kgf / sq. Cm. The valves are installed so that four of them allow fluid to pass through
one direction and four in the other. The damper cover has
a tide in which a three-ball compensation valve is installed. Valve
communicated with the inlet fitting (elbow), to which through a flexible hose
liquid is supplied from the expansion tank.

17. Main rotor

Rice. 6

18. Main rotor

MAINTENANCE:
Oil filling into the horizontal hinge is made through the holes closed by the threaded
traffic jams. The oil is drained through the lower drain holes.
Oil filling into the vertical hinge is carried out directly into the glass through the filler
hole with plug.
The oil used in the horizontal and vertical joints is hypoid (oil mixture 2/3
TSgip and 1/3 AMG-10 (in winter)).
The axial joint consists of a trunnion and a body. The axial hinge housing has closed
plugs for filling and draining oil. Used oil - MS-20 (summer), MS-14
(in winter).

19. Main rotor

Swashplate (fig. 7):
The swash plate is designed to change the value and
direction of the resultant thrust force of the main rotor.
The change in the resultant value is carried out
change common step main rotor (by changing the angles
installations simultaneously for all five blades on the same
magnitude. The direction of the resultant changes by
the corresponding inclination of the plane of rotation of the plate of the machine
skew, resulting in a cyclic change in angles
installation of each blade.
The main parts and assemblies of the swashplate are:
slide guide, slide, slide bracket, cardan, plate,
rods of rotation of blades, longitudinal control rocker, rocker
transverse control and a collective pitch lever with support.

20. Main rotor

Rice. 7

21. Main rotor

BASIC DATA OF THE SKEWING AUTOMATOR:
Slider full stroke ............................................... ...................... 47 ± 1 mm
The minimum clearance between the end of the slide and the guide
.................................................. .................................................. .. 0.3 ... 0.5 mm
Swashplate tilt with handle neutral
longitudinal-transverse control:
- forward................................................ .. 1 ° 30 "± 6"
- to the left ................................................ ..... at 0 ° 30` ± 6`
Lubrication of bearings of moving joints ................... CIATIM-201

22. Main rotor

Main details
and machine nodes
skews are:
guide
slider, slider,
slider bracket,
cardan, plate,
leash and traction
turning the blades,
longitudinal and
transverse
control, lever
common step with support.

Approved by the UUZ MGA USSR

as a teaching aid

for secondary specialized educational institutions

civil aviation

Moscow "M A SH I N O S T RONIA

INTRODUCTION

Helicopter Mi-8 belongs to the family of single-rotor helicopters with gas turbine engines, created at the Design Bureau of the General Designer, Dr. technical sciences, laureate of the Lenin Prize Mikhail Leontievich Mil. The first of this / family was the Mi-6 helicopter, created in 1957.The Mi-8 helicopter was created in 1961, passed state tests

Rice. 1. Helicopter Mi-8

in 1963-1965, entered service in 1966 (Fig. 1). By weight category helicopter Mi-v belongs to the 1st class of helicopters.

When designing the Mi-8, the latest world achievements in science and technology in the field of helicopter construction were taken into account, therefore, in terms of flight properties, efficiency, etc., it was significantly superior to other helicopters.

On the Mi-8 helicopter on April 19, 1964, the crew under the command of test pilot V.P. Koloshenko set two absolute world records of that time: ST on the basis of 2000 km - 201.834 km / h.

The Mi-8 helicopter was demonstrated in front of representatives of foreign states and companies in Vnukovo in May 1965, as well as, since 1965, in Paris at the International Salon aeronautics and space. He stands at the level of the best modern foreign samples and is recognized as competitive in the world market. The Mi-8 helicopter was widely used in the USSR, it is exported to all countries of the socialist camp and to many capitalist countries of Europe, Asia and Africa.

In 1967, on a Mi-8 helicopter, a female crew led by I. Kopets set a number of world records: range along a closed route - 2082.224 km, speed based on 500 km - 273.507 km / h, speed based on 1000 km - 258.666 km / h, speeds based on 2000 km —235.119 km / h.

In September 1969, the female crew of I. Kopets set a new world record for flight range - 2263 km.

The helicopter is available in passenger and transport versions. The passenger version of the Mi-8 helicopter is designed for interregional and local transportation of passengers, baggage, mail and small-sized cargo. It is designed for 28 passengers. Passengers are accommodated in soft, comfortable seats. The helicopter in the "saloon" version is even more comfortable. The passenger version of the helicopter can be easily converted into a transport, ambulance version, as well as into a transport version with an increased range and with an external load suspension. The transport version of the helicopter is designed for the carriage of goods or for official transportation on folding seats for 24 passengers. The transport version of the helicopter, just like the passenger one, can be easily converted into a sanitary one, with loads on an external sling, and into a transport one with an increased range (ferry).

The maximum take-off weight of the helicopter is 12,000 kg, the normal weight is 11,100 kg. Maximum speed 250 km / h, cruising speed - 220 km / h.

The ceiling of the helicopter for a normal weight is 4500 m, for a maximum weight of 4000 m.

The helicopter is equipped with two turboprop engines TV2-P7A, designed by S.P. Izotov, with a takeoff power of 1500 hp each. with. each, as well as a five-bladed main rotor with a diameter of 21.288 m.

The helicopter is economical, highly reliable, easy to maintain and operate, has an air conditioning, heating and ventilation system, a low vibration level and a spacious pilot cabin with good overview... The helicopter is equipped with an AP-34B four-channel autopilot, which provides
stabilization of the helicopter in pitch, roll, heading and flight altitude. The helicopter is equipped with a rotor speed stabilizer, has modern systems, electrical, radio and navigation equipment that allows it to operate by helicopter and in difficult atmospheric conditions, including
icing conditions.

■ The Mi-8 was preceded by the heaviest helicopters in the world with Mi-6 and Mi-10 gas turbine engines.

The Mi-6 helicopter was the first winged helicopter with gas turbine engines in the Soviet Union (Fig. 2). It was created in 1957, and its serial production began in 1958.

The Mi-6 helicopter has been widely used in our country, it is exported to many countries of the socialist la-hero and to some capitalist countries.

From 1957 to 1964 the Mi-6 helicopter set thirteen world records in speed, range and lifting of commercial cargo to a height. World speed records based on 100, 500 and 1000 km are 340, 315 and 300 km / h, respectively, and

Rice. 2. Helicopter Mi-6

also the speed of 300 km / h on the basis of 1000 m with a commercial load of 1000 and 2000 kg, set by the crew under the command of test pilot V. Galitsky, are still being held.

Also, the world speed record is still held on the basis of 1000 km - 284.354 km / h with a commercial load of 5000 kg, set by test pilot V.P. Koloshenko, and a world altitude record of 4885 m with a commercial load of 10 000 kg, set by the pilot - tester R. Kaprelyan.

The maximum take-off weight of the helicopter is 42.5 tons, the maximum speed is 300 km / h, the ceiling is 4500 m. The helicopter has two gas turbine engine D-25V designed by P.A. with. each, a five-bladed main rotor with a diameter of 35 m and a wing.

The helicopter can carry cargo both inside the cabin, weighing up to 12,000 kg, and on an external sling, weighing up to 8,000 kg.

The helicopter has electrical and radio equipment, is equipped with a full set of flight and navigation instruments, engine control devices and individual systems that allow piloting and solving aeronautical tasks during a helicopter flight during the day, at night and in adverse weather conditions.

On the basis of the Mi-6 helicopter, the Mi-10 helicopter was created in 1960 (Fig. 3). This is a "flying crane" with a high chassis for transporting bulky cargo on an external suspension.

ke. The helicopter can land directly over the cargo placed on a special platform. The hydraulic gripper system fixes the platform to four standard ball mountings and within 2-3 minutes the cargo is prepared for transportation. These four standard ball mountings can be installed on all sorts of containers, mobile workshops or all kinds of self-propelled equipment, then these goods can be transported without standard platforms.

Rice. 3. Helicopter Mi-10

On May 26, 1965, on the Mi-10 helicopter, the crew under the leadership of the master of sports V.P. Koloshenko set an absolute world record for lifting commercial cargo to a height: a load of 5000 kg was lifted to a height of 7151 m. On May 28, 1965, a test pilot tator G. Alferov raised a commercial load of 25 105 kg to a height of 2840 m, thereby setting two absolute world records: a maximum height of 2840 m was reached with a load of 25 000 kg and a maximum load of 25 105 kg was raised to a height of 2000 m. the records are still unsurpassed.

The Mi-10 helicopter was demonstrated in front of representatives of foreign countries and companies in Vnukovo in May 1965, as well as several times in Paris at the International Salon of Aeronautics and Space.

The maximum take-off weight of the Mi-10 "is 43,070 kg, the maximum payload is 12 tons. The flight range with a load of 12 tons is 250 km, the maximum range for refueling the main and additional tanks is 630 km. Cruising speed with a platform without loads is 220 km / h, and with a load - 180 km / h.

Inside the cargo compartment and in special passenger containers under the fuselage of the helicopter, 100-120 people can be transported over a distance of 250 km. The cabin can accommodate 28 people.

The Mi-10 helicopter, like the Mi-6 helicopter, has two D-25V engines and a five-bladed main rotor with a diameter of 35 m.

Rice. 4. Helicopter Mi-2 ■ -

The helicopter is designed for flights in difficult weather conditions day and night, therefore it is equipped with modern navigation equipment, an autopilot To anti-icing system. The cockpit is equipped with a heating and ventilation system, and an oxygen unit is provided for high-altitude flights.

Simultaneously with the Mi-8 helicopter in 1961, the Mi-2 helicopter with two GTD-350 turboprop engines designed by S. P. Izotov was designed on the basis of the Mi-1 helicopter (Fig. 4). The Mi-2 helicopter has a multipurpose application. Its passenger version has a comfortable cabin for 8 passengers, a low vibration level, and good sound insulation. The agricultural version of the Mi-2 helicopter accommodates up to 900 kg of pesticides in the form of powder or liquid in two tanks. In the sleigh? The container can accommodate four bed patients and a health worker. In the transport version, it can carry up to 800 kg of cargo inside the cab. The maximum take-off weight of the helicopter is 3550 kg. The flight range when refueling the main fuel tank (600 l) is 300 km for the passenger version, and when refueling additional outboard tanks

(2X238 l) —600 km. The maximum speed at an altitude of 500 m for the passenger version is 210 km / h, and for the agricultural one - 140 km / h.

Ceiling (helicopter 4000 m. Minimum vertical speed in autorotation mode 8-8.5 m / s. The helicopter can fly without descent on one engine, which ensures the reliability of the flight.

Rice. 5. Helicopter Mi-10 "K

The Mi-2 helicopter has a three-bladed all-metal propeller with a diameter of 14.5 m and a two-bladed tail rotor. The control has a hydraulic system, a stabilizer of the main rotor revolutions. On the helicopter, the possibility of ground resonance is excluded by using two-chamber shock-absorbing landing gear struts and hydraulic dampers of vertical hinges. The equipment allows helicopter flights in difficult weather conditions and at night.

Due to the presence of gas turbine engines, a high culture of design and the use of new materials, the helicopter has a large weight return, high efficiency I and is not inferior in all respects the best examples abroad | helicopters.

On the Mi-2 helicopter in May 1963, test pilot BA Anopsshy and the leading engineer of the State Research Institute of Civil Aviation L. L. Ba ~ badjanova set a world speed record for helicopters of the 5th weight category; on the basis of 100 km, the average speed was obtained - 54.337 km / h.

In 1965, on the basis of the Mi-10 helicopter, a lightweight Mi-YK helicopter with a conventional landing gear (short-legged) was created (Fig. 5). This is a "flying crane" for construction and installation work. Due to the lightweight design, the load

the lift capacity of this helicopter is 2-3 tons higher than the lift capacity of the Mi-10 helicopter. The Mi-YUK helicopter has an additional canopy and separate controls located under the fuselage of the helicopter for the possibility of performing assembly and construction works directly to the pilot himself without the assistance of an operator or flight director; thereby increasing productivity and efficiency of work.

Rice. 6. Rotor K & -22

In the near future, the new heaviest helicopter in the world, the V-12, will go into operation. The helicopter is equipped with four gas turbine engines designed by P. A. Solovyov with a capacity of 6500 hp each. with. each. On February 22, 1969, on this helicopter flight, the crew under the leadership of the ship's commander, test pilot V.P. Koloshenko, set five absolute world records in one flight: the maximum load of 31,030 kg was raised to an altitude of 2000 m, and also reached a height of 2951 m with commercial cargo of 15, 20, 25 and 30 tons.

In August 1969, on a B-12 helicopter, test pilot V.P. Koloshenko lifted a commercial cargo of 40204.5 kg to an altitude of 2250 m, thereby setting three world records: an altitude of 2250 m with a commercial cargo ”35 and 40 thousand . kg and a record of the maximum carrying capacity of 40204.5 kg at an altitude of 2000 m.

The design bureau, headed by the Lenin Prize laureate, Doctor of Technical Sciences Nikolai Ilyich Kamovshch, also designs helicopters with gas turbine engines. A heavy combined helicopter-propeller-wing aircraft Ka-22 was built here (Fig. 6). It is a heavy flying vehicle with two powerful 5900 hp gas turbine engines. with. each spaced apart along the transverse axis on the wings. Each motor drives two propellers: ° Dyno to create lift, the other to pull

to create a forward flight. In vertical flight modes, the rotor transmission is switched on - the vehicle takes off and lands vertically, it can hang. To obtain a translational movement, the transmission of the pulling screws is simultaneously turned on - the apparatus receives a translational movement. The wings begin to create lift, which increases with increasing speed, while the main rotor is unloaded.

Management of such aircraft in forward flight it is carried out like a conventional aircraft. The rotorcraft has a number of advantages over the helicopter. In view of the fact that the rotorcraft flies at positive angles of attack, its resistance is less than that of a helicopter, less fuel consumption and greater flight range.

At the end of 1961, on the K a-22 rotorcraft, the crew under the leadership of test pilot D. Efremov set a world speed record for the class of these machines (tiltrotors) based on 15-25 km, which was 356.3 km / h. In the same year, on this helicopter, the same crew set world records for lifting commercial cargo of 1000, 2000, 5000, 10,000 and 15,000 kg to a height of 2588 m and a world record for lifting the maximum load to an altitude of 2000 m - 16485 kg ... Until now, these records remain with our country.

Chapter I BRIEF CHARACTERISTICS OF THE MI-8 HELICOPTER

DESIGN FEATURES

The Mi-8 helicopter is designed and built according to the classic single-rotor configuration with a tail rotor. More than 90% of all helicopters in the world are currently being built according to this scheme. The helicopter is equipped with two TV2-117A turboprop engines with a take-off power of 1500 hp. with. each. The Mi-8 helicopter is produced in two main versions: transport (Mi-8T) and passenger (Mi-8P).

The transport version of the helicopter is designed for the transportation of wheeled vehicles, cargo, engineering equipment, official transportation of 24 passengers, sick people, as well as for carrying out various works in hard-to-reach areas. The maximum payload of the helicopter is 4000 kg. In the cargo compartment, due to the payload, an additional fuel tank is installed to increase the flight range to 910 km, or two tanks to increase the range to 1160 km (ferry version).

The cargo compartment is 5.15 m long, 7.5 m long with flaps, 2.34 m wide, 1.82 m high. parts of the cargo compartment on special ladders. On the left side of the fuselage there is a sliding door for entering the cargo compartment and for loading small-sized cargo with the doors closed.

The transport version of the helicopter can easily be converted into an ambulance, designed to transport 12 patients on a stretcher and an accompanying medical worker.

The helicopter is equipped with a pendulum external suspension system, which allows transporting bulky cargo weighing up to 3000 kg, as well as an onboard boom with an electric winch, which provides lifting (or lowering) cargo weighing up to 200 kg or one person when the helicopter is hovering near the ground ...

24 25 26 27

Rice. 7. Layout diagram tr.

1 - the right handle of the longitudinal-transverse control; 2 -wiper; 3 - cockpit glazing; 4 - the hatch cover for the exit to the engines; 5 — oil tank; 6~ engine; 7 — hood; 8— -fan installation; 9— oil cooler; 10— right pilot's seat; 11— right stick "step-gas"; 12 - autopilot control panel; 13 - the main rotor torus-mosaic handle; 14 - rotor brake control cable; 15 - rods of separate engine control; 16 - traction of longitudinal control; 17 - foot control rod; 18 - common pitch control thrust; 19 - lateral control rod; 20 21 - left handle "step-gas"; 22 - the left handle of the longitudinal-transverse control; 23 - instrument panel of the left pilot; 24 - the left side panel of the left electrical panel; 25 — left electrical panel; 26— left panel; 27— engine stop levers; 28— the left and right panels of the gas station; 29— middle panel; 30 - right panel; 31 - right electric power supply; 32 - right side panel; 33 - dashboard of the right pilot; 34 - main rotor hub; 35 -Automatic swash; 36 - main gearbox; 37 —Hydropa-nel; 38— control rods; 39— sub-gear frame; 40— a container of a service fuel tank; 41— the tail shaft of the transmission; 41 - whip antenna of the command radio station; 43 - compartment for placing radio equipment; 44 - beam antennas for communication radio

of anport helicopter M.Y-8T:

stations; 45— flashing beacon; 46— main rotor blade; 47—
stabilizer; 48-- intermediate gearbox; 49— tail rotor;
50 - tail gearbox; 51 - end beam; 52 -taillight
XC-39; 53 - the end shaft of the transmission; 54 - removable fairing -, 55 —
tail support; 56— tail boom; 57 - radio height antennas
measure RV-UM;58— fan damper control handle;
59 - signal flares cassettes; 60 - box KUL-2 of electric control
trolley winch; 61 - cockpit entrance door; 62 - battery -
tori; 63 - emergency hatch; 64 —Window for connecting the sleeve con-
director: 65— winch LPG-2; 66— ladders; 67— folding seat;
68— PUL-1 control panel for winch control; 69— folding seats; 70—
boxes for onboard tools; 71 - cargo flap; 72 - head -
naya leg of the chassis; 73 - left outboard fuel tank; 74 —Aero-
navigation light BANO-45; 75 — central part of the fuselage "a;
76— sliding entrance door; 77— external suspension device
cargo; 78 - cargo boom; 79 - the place where the batteries are installed;
80 81 -Sliding bl-
erased; 82 - seat of the left pilot; 83 - levers of separate control
engines; 84— front leg of the chassis; 55 - - LDPE tube; 86—
beam antenna of ARK-9 radio compass; 87— right foot pedal
management

Rice. 8. Layout of the MI-8P passenger helicopter:

1 - right foot control pedals; 2 - right handle longitudinally
transverse control; 3 -wiper; 4 - glazing
bins; 5 — hatch cover for the exit to the engines; 6— oil tank; 7 - move
gatel; 8 -hood; 9 - fan installation; 10— oil cooler;
11 - main rotor hub; 12— swashplate; 13 - head -
ny gearbox; 14 —Hydropanel; 15 - control rods;
16 - under-gear frame; 17 —Container of consumable fuel
tank; 18 - the tail shaft of the transmission; 19 - rod antenna
command radio station; 20— radio equipment compartment
niya; 21— beam antenna of a communication radio station; 22— flashing
Lighthouse; 23 - main rotor blade; 24 -stabilizer; 25 —Between-
precise gearbox; 26 - tail rotor; 27 - tail gearbox;
28 - end beam; 29 - tail light XC-39; 30 - end shaft
transmissions; 31— removable fairing; 32— tail support; 33— needles
steel beam; 34 —Antenna of the RV-UM radio altimeter; 35 - upper
rear entrance door leaf; 36 - the central part of the fuselage;
37 - folding ladder; 38 - the main leg of the chassis; 39 - left hanging
fuel tank; 40 - aeronautical light BANO-45; 41 —Passage-

fat chair; 42 —Sliding entrance door; 43 - sliding blister; 44 - niches for accumulators; 45 —The output antenna of the communication radio station; 46— left pilot's seat; 47 — levers of separate control, motors; 48 - the front leg of the chassis; 49 - LDPE tube; 50— beam antenna of ARK-9 radio compass; 51— left pilot's dashboard; 52— left side panel of the upper electric control panel; 53— left electrical panel; 54— left panel; 55— engine stop levers; 56 - the left and right panels of the gas station; 57 - middle panel; 58 - right panel; 59 - right electrical panel; 60 - right side panel; 61— dashboard of the right pilot .; 62— right pilot's seat; 63 - right stick "step-gas"; 64 - autopilot control panel; 65 - main rotor brake knob; 66 - rotor brake control cable; 67, 68 - rods of separate engine control; 69— longitudinal control thrust; 70— foot control thrust; 71 - common pitch control thrust; 72 - traction of transverse control; 73 - left foot control pedals; 74— left stick "step-gas"; 75— left longitudinal-transverse control knob

The helicopter crew consists of three people: two pilots and a flight mechanic (or a conductor). The left and right pilot seats are located side by side, with a folding seat for the flight engineer or conductor located behind the pilot seats in the cockpit aisle (Fig. 7). ■

In the passenger version, the helicopter is designed to carry 28 passengers with luggage (15 kg for each passenger), mail and small-sized cargo. The helicopter cockpit is comfortable, heat and sound insulation is used to reduce noise. To maintain a normal temperature in the cockpit and the required air composition, the helicopter is equipped with an air conditioning, ventilation and heating system. There is a wardrobe and a luggage compartment. Passengers boarding is carried out through a sliding door located on the left side in the front of the fuselage and through a hinged gangway of the rear entrance door.

The passenger version of the helicopter can be easily re-equipped in airfield conditions into a transport and sanitary one. Under the finishing of the passenger cabin, there are nodes for fastening small-sized cargo and for installing racks and straps on which the stretcher is fixed. The passenger version of the helicopter can be re-equipped for the transportation of bulky cargo on an external sling.

Both the transport and passenger versions of the helicopter have electrical, radio, instrumentation and special equipment designed to perform flights day and night, in simple and difficult meteorological conditions in the range of ambient temperatures from plus 40 to 50 minutes. ° WITH(fig. 8).