[AVIATION] Ultra Light Helicopter Ak1-3 Specs Rev1.2 (Copter Ua

Ultra light Helicopter AK1-3

14/10/04

Tech Specs Rev 1.2

TABLE OF CONTENTS

1. GENERAL PROVISIONS

1.1. HELICOPTER REQUIREMENTS

1.2. HELICOPTER CERTIFICATION

1.3. MATERIALS AND PRODUCTION TECHNIQUE

1.4. SUPERVISION AND TESTING METHODS

1.5. HELICOPTER PROOFING

1.6. STENCILLING AND INSCRIPTIONS ON THE HELICOPTER

2. A BRIEF DESCRIPTION OF THE HELICOPTER

2.1 CONSTRUCTIONS AND LAYOUT DIAGRAM

2.2. HELICOPTER TYPE AND DESIGNATION

2.3. ENGINE TYPE AND QUANTITY

2.4. DEVELOPER AND MODEL

2.5. CREW PERSONNEL AND HELICOPTER’S TRANSPORTING CAPABILITIES

2.6. OUTER COATING

3. MAIN FEATURES

3.1. ESTIMATED WEIGHTS

З.2. REGULATION CURVES

3.3. CENTERING CHARACTERISTICS

3.4. FLIGHT CHARACTERISTICS

3.5. GEOMETRICAL DIMENSIONS

3.6. ENGINE INFORMATION

3.7. GEOMETRICAL ADJECTIVES OF THE ROTORS

3.8. ALTITUDE RANGES, OPERATING TEMPERATURE RANGES, AND

WEATHER CONDITIONS

3.9. LIFETIME

4. BRIEF DESCRIPTION OF THE HELICOPTER’S CONSTRUCTION

4.1. GENERAL PROVISIONS

4.2. MATERIALS USED

4.3. FRAMEWORK

4.4. COCKPIT

4.5. TAIL BOOM

4.6. UNDERCARRIAGE

4.7. ROTOR

4.8. ANTI-TORQUE ROTOR

5. PROPULSION AND TRANSMISSION

5.1. GENERAL INFORMATON

5.2. ENGINE

5.3. TRANSMISSION

5.4. NOISE LEVEL

6. CONTROLLING SYSTEM

Ultra light Helicopter AK1-3

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Tech Specs Rev 1.2

6.1. GENERAL PROVISIONS

6.2. WOBBLE PLATE

6.3. CONTROLS

7. POWER-SUPPLY SYSTEM

7.1. GENERAL PROVISIONS

7.2. 12V AND 27V DIRECT-CURRENT SYSTEM

7.3. 36V THREE-PHASE ALTERNATE CURRENT SYSTEM

8 FUEL SYSTEM

8.1. GENERAL PROVISIONS

9. HEATING AND EVAPORATION SYSTEM

9.1. GENERAL CHARACTERISTICS

10. GENERAL PROCESS TECHNOLOGY CHARACTERISTICS

Ultra light Helicopter AK1-3

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Tech Specs Rev 1.2

GENERAL PROVISIONS

PTER REQUIREMENTS

The AK1-3 helicopter complies with the requirements of AP 27 Normal Category

Rotary Wing Flight Suitability Norms, which comply with the FAA flight suitability

standards for civil aircraft (FAR-27).

1.2. HELICOPTER CERTIFICATION

AK1-3 helicopter is registered for certification with the State Aircraft Department of

Ukraine.

АК1-3 complies with the requirements of the certification basis for the helicopter

developed according to:

- AP-27 normal category flight suitability norms;

- noise abatement requirements as laid down in Chapter 3 of Appendix 16 of the

International Civil Aircraft Convention (Chicago 1944), volume 1, Aviation Noise,

3rd edition 1933; and the requirements of Part 3 of Aviation Rules (AP-36).

1.3. MATERIALS AND PRODUCTION TECHNIQUE

In producing the helicopter, the materials and techniques applied comply with the

existing aviation standards and other reference documents.

1.4. SUPERVISION AND TESTING METHODS

The supervision and testing during manufacturing are carried out according to the

existing reference documents.

1.5. HELICOPTER PROOFING

The helicopter's inner and outer surface proofing is carried out according to the

existing reference documents.

1.6. STENCILLING AND INSCRIPTIONS ON THE HELICOPTER

All inscriptions on the helicopter’s outer surface, stenciling and inscriptions in the cockpit

and on the controls are in Russian. Under the customer’s wishes, stenciling and

inscriptions can be done in a foreign language.

Ultra light Helicopter AK1-3

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A BRIEF DESCRIPTION OF THE HELICOPTER

2.1 CONSTRUCTIONS AND LAY-OUT DIAGRAM

2.1.1. The AK1-3 helicopter (Fig. 2.1) is a fabricated structure with a 3-bladed rotor and a

2-bladed anti-torque rotor.

2.2. HELICOPTER TYPE AND DESIGNATION

2.2.1. The helicopter falls into the normal category of light aircraft, and is designated to

fulfill the following tasks:

- Patrolling (power lines, canals, pipelines, highways, hard-to-reach border regions);

- Agriculture (pollination, spraying, sowing, animal watch);

- Forest and wild animal protection;

- Advertising;

- Searching;

- Aerial inspection (aerial photography, geological and fishing exploration);

- Flying lessons for both military and civilian students;

- Participation in aviation sports competitions.

2.3 ENGINE TYPE AND QUANTITY

2.3.1. The helicopter uses one piston liquid-cooled engine produced by the Japanese

Subaru, EJ-25 model, which is installed behind the cockpit.

2.4. DEVELOPER AND MODEL

2.4.1 The developer is Аэрокоптер Ltd., Ukraine.

Model: AK1-3 helicopter.

2.5. CREW PERSONNEL AND HELICOPTER’S TRANSPORTING CAPABILITIES

2.5.1. Depending on its mission, the helicopter crew may include one or two persons:

- A pilot;

- An observer (operator, trainee).

2.5.2. The helicopter is capable of transporting one passenger.

2.6 OUTER COATING

Coating and proofing of the helicopter’s outer surfaces, engine, and components are

carried out according to the existing norms and guarantee successful exploitation under

different climatic conditions.

Ultra light Helicopter AK1-3

Figure 2.1. General View of the Helicopter

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Tech Specs Rev 1.2

Ultra light Helicopter AK1-3

14/10/04

Tech Specs Rev 1.2

MAIN FEATURES

3.1. ESTIMATED WEIGHTS

3.1.1. Maximum takeoff weight 650 kg

3.1.2. Maximum weight of loaded helicopter without fuel 590 kg

3.1.3. Maximum payload weight (including pilot and fuel) 270 kg

3.1.5. Empty helicopter weight 380 kg

3.1.6. Helicopter equipment weight, including:

- crew parachutes (2) 20 kg

- crew (2 persons) 160 kg

- protective helmets (2) 2.3 kg

- engine oil 3 kg

- unusable fuel 0,5 kg

З.2. REGULATION CURVES

Table 3.1

REGULATING DATA

Deflection

Deflecting

# Item

degrees mm

Note

direction

1.

2.

3.

Slope angle of rotor axis

Angle of rotor pitch

Forward

Left

Right

min

max

Forward

Backward

Right

Left

0

0

0

0

14°

5°±20′

4°±20′

4°±20′

4°±20′

+20°±20′

+5°±20′

-10°±20′

60±2

-- -- --

-- --

--

130

110

110

110

Crosshead

traverse

24±1mm

--

Slope angles of wobble

plate and control rod

traverses that correspond to

them

4. Angle of incidence of anti-torque rotor

a) with right pedal stopped

b) with both pedals in

neutral

c) with left pedal stopped

5. Deflection of pedals from

neutral

-- -- --

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6. Control rod labor not more

than 3 kg.

=

--

7. Foot pedals labor with anti-torque rotor attached not

more than 7 kg.

--

Labor -- --

measurements are

taken in the

middle part

of rods and

footboards

-- --

with TNV

8. Labor for the Lead/Gas

shift, with normal shifting

from one extreme position

to the other taking no less

than 20 seconds, not more

than 5 kg.

> +15°.

-- -- --

3.3. CENTERING CHARACTERISTICS

3.3.1 Centering capacity during takeoff, flight, and landing:

- noseheaviness, before the rotor axis 38 mm

- bowheaviness, behind the rotor axis 59 mm

3.3.2. Longitudinal centering for an empty helicopter 173mm

3.4. FLIGHT CHARACTERISTICS

3.4.1. Maximum ground airspeed 186 km/h

3.4.2. Ground cruising airspeed 160 km/h

3.4.3. Rotation speed around vertical axis during hovering < 45 degrees/s

3.4.4. Static ceiling for hovering 1500 m

3.4.5. Maximum ground climbing capacity 8 m/s

3.4.6. Minimal vertical descent rate while floating in

autorotation regime at VDesc90 km/h 7,4 m/s

3.4.7. Flight duration at Н=0 - 500 m with 5 % necessary fuel supply 3 hrs

3.4.8. Practical ground range ability with 5 % necessary fuel supply 450 km

3.4.9. Maximum exploitation load range +0.5…+2.5

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3.5. GEOMETRICAL DIMENSIONS

3.5.1. Tail unit

Keel area 0.267 m2 Stabilizer area 0.15 m23.5.2. Cockpit

Internal dimensions:

- length 1.5 m

- width 1.4 m

- height 1.2 m

Entrance door 0.95х1 m

3.5.3. Undercarriage

- length 1.8 m

- distance between skids 1.6 m

3.6. ENGINE INFORMATION

3.6.1. Engine quantity, type, and marking:

one horizontal piston four-cylinder four-act liquid-cooled engine Subaru EJ-25.

3.6.2. General characteristics of Subaru EJ-25:

Engine working volume 2500 cm3 Engine power 165 horsepower

(121 kW)

Engine dry weight 110 kg

Overall dimensions of the engine:

- length 0.8 m

- height 0.7 m

- width 0.5 m

3.6.3. Subaru EJ-25 operating limitations:

Continuous working time in regime - unlimited

3.6.4. Engine mounting units:

- three shock-absorbing pads, of which two are

on the engine mounting, and one near the flywheel.

3.7. GEOMETRICAL ADJECTIVES OF THE ROTORS

3.7.1. Geometrical adjectives of the rotor

- rotor diameter 6.84 m

- blade number 3

- carrier blade chord 0.17 m

- blade profile NACA 63012/63015

- outline blade shape rectangular

- peripheral velocity of blade tip 205 m/s

- duty factor 0.0475

3.7.2. Geometrical adjectives of the anti-torque rotor

- rotor diameter 1.28 m

- blade number 2

Ultra light Helicopter AK1-3

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- carrier blade chord 0.115 mm

- blade profile NACA 63012

- peripheral velocity of blade tip 186.3 m/s

- duty factor 0.1144

3.8. ALTITUDE RANGES, OPERATING TEMPERATURE RANGES, AND

WEATHER CONDITIONS

3.8.1. Temperature range: –30…+30°С

3.8.2. Altitude range (limited by the absence of oxygen equipment) 0…3000 m

3.8.3. The helicopter is designated for use under normal weather conditions in daylight

according to visual flight rules in any latitudes.

3.9. LIFETIME

The overall technical lifetime (design life) of the helicopter is 2,000 flight hours.

The passing of design life is warranted by revisions and checkups that are included

in regular technical service.

Ultra light Helicopter AK1-3

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BRIEF DESCRIPTION OF THE HELICOPTER’S CONSTRUCTION

4.1. GENERAL PROVISIONS

АК1-3 (Fig. 4.1.) is a modular construction using different construction materials. In

manufacturing the details and units we have considered the experience of similar

production, technical documentation, and aviation building norms.

4.1. Legend:

Несущий винт Rotor

Лопасть несущего винта Rotor blade

Несущий вал Drive shaft

Хвостовое оперение Tail unit

Хвостовая балка Tail boom

Автомат перекоса Wobble plate

Главный редуктор Propulsion

reduction gear

Ременная передача Belting

Кабина Cockpit

Шасси Undercarriage

Радиатор Radiator

Топливный бак Fuel tank

Лопасть рулевого винта Anti-torque

rotor blade

Двигатель Engine

Рама Framework

Figure 4.1. LAYOUT DIAGRAM

4.2. MATERIALS USED

The bulk of materials used in manufacturing the helicopter is presented in Table 4.1.

Protective coating includes blueing, anodization, and painting.

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Table 4.1

CONSTRUCTION MATERIALS

Name of component Material

Glass fiber cloth Т-25 Rotor blades

Organic fiber art.56313

Anti-torque rotor blades Glue VК-41 TU1 596-67-80

Brass L63 GOST 931-70

Alloy POS-80 GOST 1499-91

Building agent EDT-69N

Styrofoam Rohacell 51

Framework

Undercarriage

Wobble plate

Cockpit

Steel 30HGSA GOST 4543-86

Steel 30HGSA GOST 4543-86

Alloy D-16Т GOST 4784-97, PТ 7-1

Alloy D-16Т GOST 4784-97, textolite,

titanium VТ 3-1 GOST 19807-91

Glass fiber cloth Т-10-80 GOST 19170-73

Carbonic cloth

Glass thread

Lorit 287, 285, Styrofoam

Acrylic plastic

Steel 30HGSA GOST 4543-86, titanium VТ 3-1 GOST 19807-91,

alloy D-16Т GOST 4784-97, steel 08Х15N5D2ТS (VNS-2), rubber

7-В-14 ТU 38405-395-78

Steel 30HGSA GOST 4543-86, VТ 3-1, D-16Т, bulk graphite zytel

polyamide ТU 6-05-988-93, , steel 08Х15N5D2ТS (VNS-2), glass

fiber cloth Т-25, building agent EDT-69N

16 mm plywood, glass fiber cloth Т-10

Carbonic cloth

Lorit 287, 285

Tail boom

Anti-torque rotor hub

Rotor hub

Floor

4.3. FRAMEWORK

The framework (Fig. 4.2) is a welded construction made of pipes, and serves as a base for

different components of the helicopter.

Overall dimensions: 1133х720х878 mm

Ultra light Helicopter AK1-3

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Legend:

Труба

Pipe

Figure 4.2. FRAMEWORK

4.4. COCKPIT

The cockpit (Fig. 4.3) is designed for the crew, the controls, and the equipment.

In the fore-part of the pilots’ cockpit is a control panel with monitoring, В передней

части кабины пилотов расположена приборная панель с комплектом контрольно-измерительных, aviation, and radio equipment. In the control panel’s base is the cockpit

heater. On the cockpit’s ceiling are the headset holders; on the back panel is a n internal

lighting lamp.

The cockpit’s floor is a load-bearing element in itself, holding on it: pilots’ seats,

controls, control panel; and under it, elements of the control system for the rotor and the

anti-torque rotor, elements of electric system, heating and ventilating systems.

The cockpit’s glass paneling provides f good field of vision ahead, ahead down, left,

right, and up.

The crew seats are not adjustable, since the field of vision is good in any position. The

seats are also equipped with safety belts. Shoulder and lap belts are designed for reliable

fixation of crew members during all stages of the flight.

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4.5.

l panel

paneling

Figure 4.3 COCKPIT

TAIL BOOM

The tail boom (Fig. 4.3) is a cylindrical riveted construction made out of plate.

1. Pipe 5. Fork

2. Light indication 6. Frame

3. Hatch 7. Support fork

4. Strut fork

Figure 4.4. TAIL BOOM

Ultra light Helicopter AK1-3

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The tail boom holds:

- helicopter’s light indication;

- four hatches (to access the main units of the tail boom);

- strut fork (the strut keeps the tail boom horizontal);

- fork attaching the tail boom to the V-belt drive;

- nine frames (for main units of the rotor control, and also as a wireframe for the pipe);

- fork for support and attachment of stabilizer.

The helicopter’s stabilizer provides the necessary characteristics of directional stability

and controllability in the main flight regimes for saving the necessary resources of

directional control. The vertical empennage provides for yaw stability and relieves the

rotor at high speeds.

4.6. UNDERCARRIAGE

The helicopter’s undercarriage (Fig.4.5.) are skid-equipped.

1. Skids

2. Tubular spring

3. Rolling device fitting point

4. Footboard

Figure 4.5. UNDERCARRIAGE

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The skids are made of jointless pipes.

For softening the impact during incorrect landing, the helicopter is equipped with springs

made of bent pipes. The skids are equipped with holders for the detachable rolling device

for land transportation of the helicopter within airports or hangars.

To make getting into the cockpit more comfortable, the footboards are attached to the

fore springs.

4.7. ROTOR

The rotor (Fig. 4.6.) moves the helicopter.

There are three blades of rectangular shape made of composite materials with nonlinear

twist and variable in width symmetric profile.

The blades are torsion-attached. Steel detail package VNS-2 serves as a torsion bar.

1. Torsion bar

2. Blade

Figure 4.6. ROTOR

Ultra light Helicopter AK1-3

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Torsion rotor hub (Pic 4.7.) successfully solves the problem of reliability of the blade

fitting point, is easily manufactured, requires no service, and has a good weight

characteristic. The hub details are corrosive-resistant.

745821119

3

6

10

1.рукав в сборе 6. Штырь

2. Тарелка нижняя 7. диск

3. Тарелка верхняя 8.сфера

4. Корпус 9. ось

5. Ось 10. болт

11. пружина

Pic 4.7. Torsion rotor hub

Ultra light Helicopter AK1-3

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Tech Specs Rev 1.2

13

910

1

6

7

3411

8

1252

1. Casing 8. Body

2. Ear 9. Bolt

3. Hub 10. Plate

4. Nut 11. Hub

5. Fork 12. Rest

6. Torsion bar 13. Plate

7. Torsion bar fork

Pic.4.8. ARM

4.8. ANTI-TORQUE ROTOR

The two-blade anti-torque rotor serves as a balance for the reactionary torque of the rotor

and provides controllability. It is attached to a generic horizontal joint. The blades are

made of composite materials.

The hub (Fig. 4.9) is made of aluminum alloys and steels.

The parameters of anti-toque rotor and transmission provide the necessary speeds of rotation

around the vertical axis.

Ultra light Helicopter AK1-3

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Tech Specs Rev 1.2

3

10

12

5

9

1

2

8

4

11 11

4

2

10

76

12

1. Body 7. Torsion pack

2. Socket 8. Hub

3. Fork 9. Washer

4. Hub 10. Hub

5. Nut 11. Hub

6. Baffle 12. Hub

Figure 4.9. ANTI-TORQUE ROTOR HUB

8

Ultra light Helicopter AK1-3

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PROPULSION AND TRANSMISSION

5.1. GENERAL INFORMATON

The helicopter’s propulsion is mainly produced by the engine.

The helicopter features a piston engine Subaru EJ-25, which is horizontal, four-cylinder,

opposed, four-act, and liquid-cooled. Its working volume is 2500 cm3, power – 165

horsepower (121 kW). The engine has a sixteen-valve gas-distributing mechanism with

a distribution shaft in each of the two cylinder heads.

The engine is flexibly affixed to the framework. It is positioned in such a way, that with

a specified centering it provides easy access to the devices which demand frequent

service.

The helicopter’s transmission (Fig. 5.1) provides the power transfer from the engine to

the rotors, with rotary speed being the most advantageous for both rotors. Transmission

is also responsible for the concrete direction of rotors and the power transfer for other

devices and mechanisms.

Главный редуктор Propulsion reduction

gear

Ременная передача Belting

Обгонная роликовая муфта Free-wheel roller

clutch

Пластинчатая муфта Plate clutch

Промежуточная опора Pillow block

Трансмиссионный вал Transmission shaft

Пластинчатая муфта Plate clutch

Рулевой редуктор Steering reduction gear

Двигатель Engine

Резиновая муфта Rubber clutch

Fig. 5.1. TRANSMISSION LAYOUT

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5.2. ENGINE

5.2.1. The engine’s design philosophy:

- pyramidal combustors with spark-plug in the center and four valves (2 exhaust,

2 admission ones) for one cylinder;

- valve-levers are equipped with gap hydro-compensators;

- distribution shafts (in the left and right heads) are activated by one cogged belt,

which also activates the cooling system pump situated in the left engine half-block.

The cogged belt’s tension is regulated automatically;

- the supporting crankshaft is positioned in the five main-bearings;

- the cylinder block is made of aluminum alloy through pressure die casting and

is equipped with dry cast-iron liners mounted into the floor of the block.

5.2.2. Cooling system.

The propulsion cooling system is liquid-based. The cooling system radiator is

situated in the lower part of the frame and forcibly cooled by the airflow created by

two electric fans with step-by-step activation, mounted on the fan baffle above the

radiator. For air supply from the approach flow, there is a fresh-air intake.

5.2.3. Engine starting system

The engine starting system is regular. The engine is equipped with an electric starter,

a starter relay, and a starter button. The engine is started from a storage battery with

the capacity of 60 Å/hr.

The storage battery is charged by a 12 V 70 Å generator, whicj includes a voltage

control box and an electronic rectifier.

5.3. TRANSMISSION

5.3.1. The belting is responsible for power transfer through the flexible rubber clutch and

the free-wheel roller clutch from the engine to the reduction gear drive shaft. The belt

is a V-belt. There are seven belts.

5.3.2. The propulsion reduction gear is single, transmitting the rotational moment from the

engine to the rotor shaft. The transmission is conical, with a circular cog. The

propulsion reduction gear has one entrance.

The power is transmitted from the engine through the belting and the free-wheel

clutch to the control shaft and the rotor shaft. The control shaft, through the flexible

plate clutch, transfers the power to the transmission shaft, mounted on three pillow

blocks. The transmission shaft, through the plate clutch, transfers the tension to the

steering reduction gear.

The reduction gear uses bubbling oiling. The oil is filled through the filler neck,

which is closed with a breather lid. Oil level monitoring is done with the help of the

level indicator. To control the oil temperature, there is an oil-temperature sensor in

the propulsion reduction gear, with indication appearing on the pilot’s control panel.

Ultra light Helicopter AK1-3

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5.3.3.

5.3.4.

The steering reduction gear is designated for rotating the anti-torque rotor. It has a

90° transmission. It has two conical cog-wheels with circular cogs, which are

mounted on the frictionless bearings. The reduction gear case is made of aluminum

alloy, and is attached to the tail boom’s mainframe. The anti-torque rotor collective

pitch control system is mounted on the takeoff shaft of the steering reduction gear.

The anti-torque axis shaft transmits power from the propulsion reduction gear to the

steering reduction gear. The shaft consists of a pipe with plate clutches mounted on

one end. It has three fulcrums, which include closed frictionless bearings in rubber

casings. The units’ mounting is done with the help of frames positioned in the tail

boom.

5.4. NOISE LEVEL

The noise level produced by the helicopter is in compliance with the ICAO and

environmental norms. Appendix 16 of the International Civil Aircraft Convention,

Aviation Noise, vol. 1, chapter 3.

Ultra light Helicopter AK1-3

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CONTROLLING SYSTEM

6.1. GENERAL PROVISIONS

To change the helicopter’s flight configuration and counteract external disturbance, the

helicopter uses an unassisted control system, with the help of which the pilot, operating

the rotor and the anti-torque rotor, provides the helicopter’s necessary position.

The control system is mechanical (Fig. 6.1).

The control linkages are rigid in the circular and collective pitch channels, and mixed in

the itinerary channel.

6.2. WOBBLE PLATE

The wobble plate is the most responsible device in the controlling system.

The wobble plate is a mechanism which provides simultaneous angle of pitch change for

all blades and circular pitch change depending on the blades’ azimuthal location.

Moving the wobble plate along the rotor’s rotational axis, with the control levers turning

the blades to the same value, makes the blades’ angle of pitch change.

Tilting the wobble plate relative to the rotor’s rotational axis does the blades’ circular

pitch change. Rotating a tilted plate leads to displacement of the rotor thrusts, which

connect the plate with the blade control levers, making the plates rotate relative to their

longitudinal axes, which changes the azimuth pitch.

The wobble plate consists of rotating and nonrotating movable rings. It is mounted to the

rotor shaft with a spherical joint, which slides along the shaft.

6.3. CONTROLS

The controls are situated in the cockpit and are divided into the main and auxiliary ones.

The main controls include the circular pitch knob, the rotor collective pitch lever, and the

airway control pedal.

The auxiliary controls include the cockpit heater door control knobs.

The engine power correction twist-knob is mounted on the rotor collective pitch lever.

The change in collective pitch automatically changes the throttle plate position, which

means the engine power correction twist-knob does not have to be used in flight.

Ultra light Helicopter AK1-3

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Figure

6.1

CONTROL

SYSTEM

LAYO

UT

Ultra light Helicopter AK1-3

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Tech Specs Rev 1.2

Legend:

Трос управления рулевым винтом Anti-torque rotor control cable

Качалка Walking beam

Втулка рулевого винта Anti-torque rotor hub

Редуктор рулевой Steering reduction gear

Автомат перекоса Wobble plate

Тяга Rotor thrust

Ручка управления общим шагом Collective pitch control knob

Блок роликов Roller block

Кронштейн ручки управления Circular pitch control knob holder

циклическим шагом

Узел натяжения троса Cable tension node

Педали Pedals

Качалка Walking beam

Ultra light Helicopter AK1-3

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POWER-SUPPLY SYSTEM

7.1. GENERAL PROVISIONS

The helicopter’s power-supply system (Fig. 7.1) is centralized and provides energy for

the helicopter’s equipment. It includes the 12V and 27V direct-current system and the

36V three-phase alternate current system.

7.2. 12V AND 27V DIRECT-CURRENT SYSTEM

The direct-current system includes:

- a 12V, 60 Å/hr acid storage battery;

- a 12V 70Å generator;

- a PN-27 transducer.

7.3. 36V THREE-PHASE ALTERNATE CURRENT SYSTEM

The 36V 400 Hz three-phase alternate current system includes a PT-3-36-400 static

transducer.

Figure 7.1. ELECTRIC CIRCUIT DIAGRAM

Ultra light Helicopter AK1-3

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Tech Specs Rev 1.2

Legend:

Электромеханизм прижимного ролика Clamping roller electric mechanism

Стеклоочиститель Screen wiper

Лампа освещения кабины Cockpit lighting lamp

Электрический двигатель отопителя Heater electric engine

Генератор Generator

Стартер Starter

Реле старт Start relay

Двигатель Engine

Лампа Lamp

Блок навигационных огней Navigation lights block

Контроллер Control unit

Кнопка пуска Start button

Вентиляторы системы охлаждения Cooling system fans

Топливный насос Fuel pump

Указатель шага Pitch indicator

Тахометр НВ и двигателя Anti-torque rotor and engine tachometer

Датчик оборотов НВ ATR rotation sensor

Гарнитуры Headsets

Тангента Flap

Антенна Aerial

Датчик

шага Pitch sensor

Датчик засорения Blockage sensor

Радиостанция «Бриз» Breeze radio station

Пульт Control panel

Сигнальное табло Annunciation panel

Блок световой сигнализации Annunciation unit

Датчик температуры главного редуктора Propulsion reduction gear temperature sensor

Ultra light Helicopter AK1-3

14/10/04

Tech Specs Rev 1.2

FUEL SYSTEM

8.1. GENERAL PROVISIONS

The fuel system (Fig. 8.1) is designed for storing fuel in the helicopter and supplying the

engine with it. The fuel used is high-octane petroleum of no less than 95 quality. Fuel

tank capacity is 80 liters. The fuel is supplied from the tank to the engine through two

fuel pumps. The fuel quantity in the tank is monitored by a fuel gauge, which has an

indicator in the middle of the control panel. Monitoring of the pumps is done through

annunciation panels.

Monitoring the engine fuel supply is done with the help of pressure indicator, which is

situated on the control panel.

Figure 8.1 FUEL SYSTEM DIAGRAM

Ultra light Helicopter AK1-3

14/10/04

Tech Specs Rev 1.2

Legend:

Указатель количества топлива

Топливный бак

Аварийный остаток

Топливные фильтры

Отказ дублирующего насоса

Дублирующий топливный насос

Основной топливный насос

Отказ основного насоса

Обратный клапан

Обратка

Фильтр топлива

Хомут

Указатель давления топлива

Двигатель

Fuel quantity indicator

Fuel tank

Emergency resource

Fuel filters

Backup pump failure

Backup fuel pump

Main fuel pump

Main pump failure

Check valve

Feedback

Fuel filter

Clamp

Fuel pressure indicator

Engine

Ultra light Helicopter AK1-3

14/10/04

Tech Specs Rev 1.2

HEATING AND EVAPORATION SYSTEM

9.1. GENERAL CHARACTERISTICS

The heating and evaporation system (Fig. 9.1) provides hot or atmospheric air supply into

the cockpit, and also for air-cooling the glass paneling. In heating regime, the air is taken

from the atmosphere or the cockpit and into the heating unit, which is situated under the

control panel and covered by boards. The heating unit includes:

- a liquid-based radiator;

- an electric fan;

- a plastic casing;

- plastic air ducts.

The supply of hot liquid to the heating unit’s radiator from the helicopter’s evaporation

system is done by metal pipelines. Choke and liquid supply controls are situated on the

lower electric panel in the cockpit. The choke regulates air supply from the atmosphere or

the cockpit. In the back part of the cockpit there are ventilation slits.

Figure 9.1 HEATING AND EVAPORATION SYSTEM DIAGRAM

Ultra light Helicopter AK1-3

14/10/04

Tech Specs Rev 1.2

Legend:

Горячий воздух Hot air

Заслонка Choke

Атмосферный воздух Atmospheric air

Рычаг управления положением заслонки Choke control lever

Кабинный воздух Cockpit air

Подача охлаждённой жидкости от

двигателя/к двигателю Cool liquid supply to/from the engine

Перекрывной кран Shutoff valve

Вентиляционные щели Ventilation slits

Ultra light Helicopter AK1-3

14/10/04

Tech Specs Rev 1.2

GENERAL PROCESS TECHNOLOGY CHARACTERISTICS

10.1. Process technology development is basic in preparing the AK1-3 helicopter for

production.

In developing process technology the source information was considered: design

drawings of details, technical precision requirements, surface roughness parameter,

and other quality requirements, such as yield. Technological processes were developed

with regard to their regulation. This includes estimate and norm-setting in completing

the work process; estimating the work category; estimating the material consumption

norm.

10.1.1. Technological processes in part cutting

Before developing the technological processes for part cutting, each specific part’s

construction and function in a unit (mechanism) was examined, and manufacturability

analyses were carried out. Design drawings of details contain all the data necessary for

full understanding of the detail’s manufacture and control, and comply with the

existing standards.

10.1.2. Technological processes in part assembly

The technological processes of part assembly were based on assembly drawings,

inspection specifications, and reference materials.

The assembly diagrams based on assembly drawings make the work process easier.

There are subassembly diagrams for the elements which are dismounted unsorted and

are parts of the article. And the parts dismounted separately are directly a part of the

general assembly. The technological processes of part cutting and assembly are

presented as flow-sheets and operational sheets.