My HAL Project

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JAYPEE UNIVERSITY OF ENGINEERING AND TECHNOLOGY

PROJECT REPORT

ON

Actuator Systems

SUMMER TRAINING REPORT

DURATION: 1stJuly 2014-31stJuly 2014

Hindustan Aeronautics Limited (H.A.L), Lucknow

Submitted To: Submitted By:

Mr. Amiya Kumar Sahoo Sir PUSHKIN SAXENA

Training & Placement In charge Er. No. 111659

Mechanical Engg. Dept. Mechanical (E-2)


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DECLARATION

I hereby declare that project work is an authentic record of my own work carried out at

HINDUSTAN AERONAUTICS LIMITED (H.A.L), LUCKNOW under the guidance of

Mr. Chaturbhuj Bhuma, (Sr. Manager- Training), during 1stJULY to 31stJULY, 2014.

Certified that the above statement made by the student is correct to the best of our knowledge

and belief.

Pushkin Saxena

111659

J.U.E.T, Guna


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ACKNOWLEDGEMENT

With deep sense of gratitude, first & foremost I express my profound thanks to Mr.

Chaturbhuj Bhuma, Sr. Manager- Training for giving me this very opportunity to do my summer

training in the Instrument factory of H.A.L. Lucknow during the summer session- 2014.

I would like to express my gratitude to Mr. Ram Awtar, Head of Instrument factory, our

training guide for the valuable guidance , inspiration & enouragenment.

Last but not the least, I also wish to acknowledge my indebteness to the staff of H.A.L.

without whose co-operation, this training would not have not been successful.

The training at H.A.L. Lucknow was full of responsiveness & it gave me the rare

opportunity to correlate the theoretical knowledge with the practical one.

Being well known company of India & abroad, it gave me the opportunity to learn the

work carried out here, got a glimpse of new environment & hard work of industrial unit.

Pushkin Saxena

111659

J.U.E.T, Guna


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CONTENT

Page No.

1. Preface 6

2. About H.A.L. 7

3. Organizational Growth of HAL 10

4. Our Products 11

5. Airplane parts definitions 12

6. Major products of the H.A.L. Division 19

7. H.A.L. Accessories DivisionLucknow 20

8. Instrument Factory 22

9. Gyroscope 25

10. Actuator 29

11. Flight Data Recorder 32

12. Advanced Light Helicopter (ALH) 33

13. Conclusion 36

14. References 37


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List of Figures

Fig No. Description Page No.

1. Airplane Parts 12

2. Aircraft yaw motion 15

3. Aircraft roll motion 17

4. Gyroscope 25


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1. PREFACE

Last few years have witnessed major changes in economic environment of our country.

The industrial and economical policies have been liberalized .Indian industries have become

globally competitive, giving boost to the young and small enterprises and thus arises the need of

an efficient research and development department.

I had done my part of training in INSTRUMENT DEPARTMENT of HAL LUCKNOW.

The project I had worked on ALH department, SU30 department. There I had learned a lot of

things about Helicopter and Fighter plane.

This all, for me, was a memorable experience.


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2. ABOUT US

Hindustan Aeronautics Limited (HAL) came into existence on1st October 1964. The

Company was formed by the merger of Hindustan Aircraft Limited with Aeronautics India

Limited and Aircraft Manufacturing Depot, Kanpur.

The Company traces its roots to the pioneering efforts of an industrialist with

extraordinary vision, the late Seth Walchand Hirachand, who set up Hindustan Aircraft Limited

at Bangalore in association with the erstwhile princely State of Mysore in December 1940. The

Government of India became a shareholder in March 1941 and took over the Management in

1942.

Today, HAL has 19 Production Units and 9 Research and Design Canters in 7 locations

in India. The Company has an impressive product track record - 12 types of aircraft

manufactured with in-house R & D and 14types produced under license. HAL has manufactured

over 3550 aircraft, 3600enginesand overhauled over 8150aircraft and 27300 engines.

HAL has been successful in numerous R & D programs developed for both Defense and

Civil Aviation sectors. HAL has made substantial progress in its current projects:


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Dhruv, which is Advanced Light Helicopter (ALH)

Tejas - Light Combat Aircraft (LCA)

Intermediate Jet Trainer (IJT)

Various military and civil upgrades.

Dhruv was delivered to the Indian Army, Navy, Air Force and the Coast Guard in

March 2002, in the very first year of its production, a unique achievement.

HAL has played a significant role for India's space programs by participating in the manufacture

of structures for Satellite Launch Vehicles like

PSLV (Polar Satellite Launch Vehicle)

GSLV (Geo-synchronous Satellite Launch Vehicle)

IRS (Indian Remote Satellite)

INSAT (Indian National Satellite)

HAL has formed the following Joint Ventures (JVs):

BAeHAL Software Limited

Indo-Russian Aviation Limited (IRAL)

Snecma HAL Aerospace Pvt Ltd

SAMTEL HAL Display System Limited

HALBIT Avionics Pvt Ltd

HAL-Edgewood Technologies Pvt Ltd

INFOTECH HAL Ltd

Apart from these seven, other major diversification projects are Industrial Marine Gas

Turbine and Airport Services. Several Co-production and Joint Ventures with international

participation are under consideration.


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HAL's supplies / services are mainly to Indian Defence Services, Coast Guards and Border

Security Forces. Transport Aircraft and Helicopters have also been supplied to Airlines as well

as State Governments of India. The Company has also achieved a foothold in export in more

than 30 countries, having demonstrated its quality and price competitiveness.

HAL has won several International & National Awards for achievements in R&D,

Technology, Managerial Performance, Exports, Energy Conservation, Quality and Fulfillment

of Social Responsibilities.

HAL was awarded the INTERNATIONAL GOLD MEDAL AWARD for Corporate

Achievement in Quality and Efficiency at the International Summit (Global Rating

Leaders 2003), London, UK by M/s Global Rating and UK in conjunctionwith the

International Information and Marketing Centre(IIMC).


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Su 30 MKI

Twin-seater, Multi-role, Long range Fighter / Bomber / Air

Superiority Aircraft

MiG-27 M

Single-seater Tactical Fighter / Bomber with variable sweep wings

MiG-21 VARIANTS

Single-seater Front line Tactical Interceptor / Fighter Aircraft

JAGUAR

Stabilized Inertial Platform with Dry-tuned Gyroscopes

and Accelerometers


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5. AIRPLANE PARTS DEFINITIONS

And their functions

Fig-1

This page shows the parts of an airplane and their functions. Airplanes are transportation devices

which are designed to move people and cargo from one place to another. Airplanes come in

manydifferent shapes and sizes depending on the mission of the aircraft. The airplane shown on

this slide is a turbine-powered airliner which has been chosen as a representative aircraft.
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For any airplane to fly, you must lift the weight of the airplane itself, the fuel, the

passengers, and the cargo. The wings generate most of the lift to hold the plane in the air. To

generate lift, the airplane must be pushed through the air. The jet engines, which are located

beneath the wings, provide thethrust to push the airplane forward through the air. The air resists

the motion in the form of aerodynamic drag.Some airplanes usepropellers for the propulsion

system instead of jets.

To control and maneuver the aircraft, smaller wings are located at the tail of the plane.

The tail usually has a fixed horizontal piece (called the horizontal stabilizer) and a fixed vertical

piece (called the vertical stabilizer). The stabilizers' job is to provide stability for the aircraft, to

keep it flying straight. The vertical stabilizer keeps the nose of the plane from swinging from

side to side, while the horizontal stabilizer prevents an up-and-down motion of the nose. (On theWright brother's first aircraft, the horizontalstabilizer was placed in front of the wings. Such a

configuration is called a canard after the French word for "duck").

At the rear of the wings and stabilizers are small moving sections that are attached to the

fixed sections by hinges. In the figure, these moving sections are colored brown. Changing the

rear portion of a wing will change the amount of force that the wing produces. The ability to

change forces gives us a means of controlling and maneuvering the airplane. The hinged part of

the vertical stabilizer is called the rudder; it is used to deflect the tail to the left and right as

viewed from the front of the fuselage. The hinged part of the horizontal stabilizer is called the

elevator; it is used to deflect the tail up and down. The outboard hinged part of the wing is called

theaileron; it is used to roll the wings from side to side. Most airliners can also be rolled from

side to side by using thespoilers. Spoilers are small plates that are used to disrupt the flow over

the wing and to change the amount of force by decreasing the lift when the spoiler is deployed.

The wings have additional hinged, rear sections near the body that are calledflaps. Flaps

are deployed downward on takeoff and landing to increase the amount of force produced by the

wing. On some aircraft, the front part of the wing will also deflect. Slats are used at takeoff and

landing to produce additional force. Thespoilers are also used during landing to slow the plane

down and to counteract the flaps when the aircraft is on the ground. The next time you fly on an

airplane, notice how the wing shape changes during takeoff and landing.
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Thefuselage or body of the airplane, holds all the pieces together. The pilots sit in the

cockpit at the front of the fuselage. Passengers and cargo are carried in the rear of the fuselage.

Some aircraft carry fuel in the fuselage; others carry the fuel in the wings.

As mentioned above, the aircraft configuration in the figure was chosen only as anexample. Individual aircraft may be configured quite differently from this airliner. The Wright

Brothers 1903 Flyer had pusher propellers and the elevators at the front of the aircraft. Fighter

aircraft often have the jet engines buried inside the fuselage instead of in pods hung beneath the

wings. Many fighter aircraft also combine the horizontal stabilizer and elevator into a single

stipulator surface. There are many possible aircraft configurations, but any configuration must

provide for thefour forces needed for flight.
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Aircraft Yaw Motion

Fig-2

In flight, any aircraft will rotate about itscenter of gravity,a point which is the average location

of the mass of the aircraft. We can define a three dimensional coordinate system through the

center of gravity with each axis of this coordinate system perpendicular to the other two axes.

We can then define the orientation of the aircraft by the amount of rotation of the parts of the

aircraft along these principal axes. The yaw axis is perpendicular to the wings and lies in the
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plane of the aircraft centerline. A yaw motion is a side to side movement of the nose of the

aircraft as shown in the animation.

The yawing motion is being caused by the deflection of the rudder of this aircraft. The

rudder is a hinged section at the rear of the vertical stabilizer.

As described on theshape effects slide, changing the angle of deflection at the rear of an

airfoil changes the amount of lift generated by the foil. For the vertical stabilizer and rudder, the

orientation of the airfoil causes a side force to be generated. With greater deflection of the rudder

to the left, the side force increases to the right. With greater deflection to the right, the side force

increases to the left. The lift generated by the rudder acts through the center of pressure of the

rudder and vertical stabilizer and is located at some distance from the center of gravity of the

aircraft. The change in side force created by deflecting the rudder generates a torque about the

center of gravity which causes the airplane to rotate. The pilot uses this ability to keep the nose

of the aircraft pointed in the direction of travel.

On allaircraft, the vertical stabilizer and rudder create asymmetric airfoil. This produces

no side force when the rudder is aligned with the stabilizer and allows the combination to

produce either positive or negative side force, depending on the deflection of the rudder. Some

fighter planes have two vertical stabilizers and rudders because of the need to control the planewith multiple, very powerful engines.
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Aircraft Roll Motion

Fig-3

In flight, any aircraft will rotate about itscenter of gravity,a point which is the average location

of the mass of the aircraft. We can define a three dimensional coordinate system through the

center of gravity with each axis of this coordinate system perpendicular to the other two axes.

We can then define the orientation of the aircraft by the amount of rotation of the parts of the

aircraft along these principal axes. The roll axis lies along the aircraft centerline. A roll motion is

an up and down movement of the wings of the aircraft as shown in the animation .
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The rolling motion is being caused by the deflection of theailerons of this aircraft. The

aileron is a hinged section at the rear of each wing. The ailerons work in opposition; when the

right aileron goes up, the left aileron goes down.

As described on theshape effects slide, changing the angle of deflection at the rear of an

airfoil will change the amount of lift generated by the foil. With greater downward deflection,

the lift will increase in the upward direction; with greater upward deflection, the lift will decrease

in the upward direction. Since the ailerons work in pairs, the lift on one wing increases as the lift

on the opposite wing decreases. Because the forces are not equal, there is a net twist, or torque

about the center of gravity and the aircraft rotates about the roll axis. The pilot can use this

ability tobank the aircraft which causes the airplane to turn.

On this page we have demonstrated an aircraft roll induced by movement of the ailerons,

but there are other ways to produce a rolling motion on an aircraft. The Wright brothers used a

method called wing warping. Their wings were wired together in such a way that the outer

panels of each wing could be twisted relative to the inner panel. The twisting changed the local

angle of attack of sections of the wing which changed the lift being generated by that section.

Unequal forces on the wings caused the aircraft to roll. Many modern airliners use aspoiler to

roll the aircraft. A spoiler is a plate that is raised between the leading and trailing edges of the

wing. The spoiler effectively changes the shape of the airfoil, disrupts the flow over the wing,and causes a section of the wing to decrease its lift. This produces an unbalanced force with the

other wing, which causes the roll. Airliners use spoilers because spoilers can react more quickly

than ailerons and require less force to activate, but they always decrease the total amount of lift

for the aircraft. It's an interesting trade! You can tell whether an airliner is using spoilers or

ailerons by noticing where the moving part is located. At the trailing edge, it's an aileron;

between the leading and trailing edges, it's a spoiler. (Now you can dazzle the person sitting next

to you on the plane!
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6. MAJOR PRODUCTS OF THE H.A.L. DIVISION

The major products of the Division are:

Undercarriage systems

Wheels and Brake systems

Hydraulic Systems

Aircraft and Engine Fuel Systems

Panel Instruments (Barometric and gyroscopic)

Electric Power Generation and Control systems

Environmental control systems.

Flight Control Actuators

Ground Support Equipment and test Rigs.

Main Customers:

Indian Air Force, Army, Navy, Coast Guard, BSF

Defence R&D Laboratories and Deptt of Space;

Civil Aviation, State Govt., Ordnance Factories, Corporate Sectors;

Flying Academies & Educational Institutions;

Airlines, Air Taxi, Air Cargo;

Overseas customers for civil and military applications.

Collaborators and Licensors.


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7. HAL ACCESSORIES DIVISION - LUCKNOW

Hindustan Aeronautics Limited

Accessories Division

Lucknow 226 016

India

The Division was established in 1970 with the primary objective of manufacturing

systems and accessories for various aircraft, helicopters and engines with a view to attain self-

sufficiency in this field in the country. The Division started with the manufacture of hydro-

mechanical accessories and instruments under license for Marut and Kiran aircraft. This was

followed by license manufacture of accessories for MiG-21 aircraft, Cheetah/Chetak helicopters,

Dornier and other defense applications. Additionally repair and overhaul of Lucknow

manufactured accessories as well as those fitted on directly purchased aircraft, such as Mirage

and Sea Harrier was undertaken. At present, it is manufacturing, repairing and overhauling more

than 800 different types of systems and accessories under license. The range of items cover units

for hydraulics, engine fuel system, environment control system, pressurization system,


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gyroscopic instruments, barometric instruments, electrical system items, undercarriages, and

electronic items. The number of licensors exceeds twenty.

From inception, the Division has laid emphasis on developing indigenous capability

through design and development of various systems and accessories. This capability has

culminated in indigenous design and development of a variety of systems and accessories for the

Light Combat Aircraft (LCA), Advanced Light Helicopter (all versions i.e. Army, Air force,

Navy & Civil) and Intermediate Jet Trainer (IJT-36). The Division has also developed and has

made successful strides into the area of Microprocessor based control systems. Design and

Development capabilities include Environmental Control Systems & Pneumatics, Fuel

Management, Engine Fuel Control & aircraft fuel systems, Microprocessor based Controllers,

Hydraulic System & Power Controls, Wheels and Brakes, Cockpit instruments and sensors,Gyroscopes, Electrical Power Control Protection, Navigation and Display, Land Navigation,

Ground support equipment, Dedicated Test rigs, and Computerized test equipment. The Division

has diversified in other defence applications like tanks and armored vehicles for Army, and took

commercial applications of Hydraulic items, Gyroscopic Equipment, Special Purpose Test

Equipment & Ground Support Equipment.

The Division has also made steady progress in the area of Exports. The range of products

and services available for exports include:

1. Rotables and spares of Jaguar International and Cheetah (Lama), Chetak (Alouette)

Helicopters;

2. Ground Support Equipment for MiG 23, 27, 29 Mirage-2000, Jaguar, LCA, Su-30, Sea-

Harrier, Dornier DO-228, Avro HS-748, Cheetah, Chetak, MI-17, and ALH.

3. Repair and Overhaul of aircraft accessories of MiG series, Jaguar International, Cheetah(Lama), Chetak (Alouette) and Dornier.

The Division today has a prime name in the aviation world and a number of international

companies are interested to join hands with it for future projects.


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H.A.L. accessory division, Luknow is divided into three main factories namely

1. Mechanical Factory

2. Instrument Factory

3.FuelFactory

8. INSTRUMENT FACTORY

This factory deals with the testing and assembly of electronics instruments used in

aircraft e.g. Altimeter, RMI, Gyro-magnetic compass, black box etc.

This INSTRUMENT FACTORY is further divided into four units which are as follows:

CLEAN ROOMS

ASSEMBLY AND TEST SHOP 2 & 3

ELECTRO ROTATING MACHINES

GROUND LAND NAVIGATION SYSTEM SHOP (G.L.N.S Shop)

Clean room

In Clean room those subunits are assembled and tested that are sensitive to dust,

temperature and humidity. All these parameters are kept under control because these can have

adverse effect on their functional efficiency.

The required specification for the instruments assembled and tested are different .so Clean

room is further subdivided into three units. The following chart is given for the classification of

clean room.


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STANDARD CLEAN ROOM CONDITIONS:

ROOMITEM Temp

Limits

C

Humidity

R/H %

Dust Count

Particle size 0.5

m/ft3

AIRCRAFT

ROOM

1

ROOM

2

ROOM

3

Gyroscopic

Instruments of

Russian Origin

Barometric

Instruments,

Accelerometers,

RPM Indicator of

Western Origin

Gyroscopic

Instruments of

Western Origin

15 to 25

C

15 to 25

C

15 to 25

C

45 -55

45 -55

45 -55


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Assembly and test shop 2 & 3

The major products of H.A.L. are fighter aircrafts. An aircraft comprises of many small

units or accessories, which play significant role in their successful flight. Any fault, may lead to

a catastrophic end. Here comes the role of assembly and test unit .it forms an integral part of any

manufacturing unit. The main instrument were KCN-2 compass system, flight data recorder,

gyro magnetic compass, fuel gauging system, radio magnetic indicator, milli voltmeter

temperature indicator.

Electromagnetic rotating shop (E.R.M)

In the E.R.M department of the instrument factory the assembly and testing of the dc

Starter Generators, AC Generator system, Constant speed alternator, Regulators, Inverter, of theRussian and French origin. These products are basically those products which takes the principle

of the electromagnetic rotating which can be elaborated as follows i.e., electrical energy is

converted into mechanical energy or vice versa. These products are of mig-21 & mig-27 aircrafts

which is of Russian origin and jaguar aircraft is of France origin.

Ground land navigation system shop (G.L.N.S)

Ground land navigation system shop is one of the most different & unique shop. As in this

shop it manufacture the only ground land navigation system in world. As due the different

applicability of the gyros therefore these gyro own


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s have been placed in the road transportation system which is used in ground e.g. trucks, cars.

The instrument which uses the property of any type of gyro and is installed in road transportation

system is known as ground land navigation system. The Gyro land navigation system is an

electronic navigation device used for guiding any army vehicle to its destination point. The

principle objective of system is not only to ease the in more precise and quicker manner whether

in plains, hills

or sand dunes, where there are no special remarks. In the G.L.N.S shop it assembles and test the

ground land navigation system of Vijayanta tank.

9. Gyroscope

A gyroscope is a device for measuring or maintainingorientation,based on the principles

of momentum. The device is a spinningwheel or disk whoseaxle is free to take any orientation.

This orientation changes much less in response to a given externaltorque than it would without

the large angular momentum associated with the gyroscope's high rate of spin. Since external

torque is minimized by mounting the device in gimbals, its orientation remains nearly fixed,

regardless of any motion of the platform on which it is mounted. Gyroscope works in situations

when using magnetic compass is not possible at all (as in Hubble telescope). Due to higher

precision it is used to maintain direction in tunnel mining.

Fig-4
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Description

Within mechanical systems or devices, a conventional gyroscope is a mechanism

comprising arotorjournal to spin about oneaxis,thejournals of the rotor being mounted in an

innergimbals or ring, the inner gimbals being journal for oscillation in an outer gimbals which

in turn is journal for oscillation relative to a support. The outer gimbals or ring is mounted so as

to pivot about an axis in its own plane determined by the support. The outer gimbals possesses

one degree of rotational freedom and its axis possesses none. The inner gimbals are mounted in

the outer gimbals so as to pivot about an axis in its own plane that is alwaysperpendicular to the

pivotal axis of the outer gimbals.

The axle of the spinning wheel defines the spin axis. The inner gimbals possess two

degrees of rotational freedom and its axis possesses one. The rotor is journal to spin about an

axis which is always perpendicular to the axis of the inner gimbals. So, the rotor possesses three

degrees of rotational freedom and its axis possesses two. The wheel responds to a force applied

about the input axis by a reaction force about the output axis.

The behavior of a gyroscope can be most easily appreciated by consideration of the front

wheel of a bicycle. If the wheel is leaned away from the vertical so that the top of the wheel

moves to the left, the forward rim of the wheel also turns to the left. In other words, rotation on

one axis of the turning wheel produces rotation of the third axis.

A gyroscope flywheel will roll or resist about the output axis depending upon whether the

output gimbals are of a free- or fixed- configuration. Examples of some free-output-gimbals

devices would be the attitude reference gyroscopes used to sense or measure thepitch, roll and

yaw attitude angles in a spacecraft or aircraft. The center of gravity of the rotor can be in a fixed

position. The rotor simultaneously spins about one axis and is capable of oscillating about the

two other axes, and thus, except for its inherent resistance due to rotor spin, it is free to turn in

any direction about the fixed point. Some gyroscopes have mechanical equivalents substituted

for one or more of the elements, e.g., the spinning rotor may be suspended in a fluid, instead of

being pivotally mounted in gimbals. A control moment gyroscope (CMG) is an example of a

fixed-output-gimbals device that is used on spacecraft to hold or maintain a desired attitude angle
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or pointing direction using the gyroscopic resistance force. In some special cases, the outer

gimbals (or its equivalent) may be omitted so that the rotor has only two degrees of freedom. In

other cases, the center of gravity of the rotor may be offset from the axis of oscillation, and thus

the center of gravity of the rotor and the center of suspension of the rotor may not coincide.

Properties

A gyroscope exhibits a number of behaviors including precession and mutation.

Gyroscopes can be used to construct gyrocompasses which complement or replace magnetic

compasses (in ships,aircraft andspacecraft,vehicles in general), to assist in stability (bicycle,

Hubble Space Telescope, ships,vehicles in general) or be used as part of an inertial guidance

system. Gyroscopic effects are used in toys like tops, yo-yos, and Powerballs. Many other

rotating devices, such asflywheels,behave gyroscopically although the gyroscopic effect is not

used.

The fundamental equation describing the behavior of the gyroscope is:

Where the vectors and L are, respectively, thetorque on the gyroscope and itsangular

momentum, the scalar I is its moment of inertia, the vector is its angular velocity, and the

vector is its angular acceleration. It follows from this that a torque applied perpendicular to

the axis of rotation, and therefore perpendicular to L, results in a rotation about an axis

perpendicular to both and L. This motion is called precession. The angular velocity of

precession Pis given by thecross product:

Precession can be demonstrated by placing a spinning gyroscope with its axis horizontal

and supported loosely (frictionless toward precession) at one end. Instead of falling, as might be

expected, the gyroscope appears to defy gravity by remaining with its axis horizontal, when the

other end of the axis is left unsupported and the free end of the axis slowly describes a circle in a

horizontal plane, the resulting precession turning. This effect is explained by the above
http://en.wikipedia.org/wiki/Precessionhttp://en.wikipedia.org/wiki/Nutationhttp://en.wikipedia.org/wiki/Gyrocompasshttp://en.wikipedia.org/wiki/Shiphttp://en.wikipedia.org/wiki/Aircrafthttp://en.wikipedia.org/wiki/Spacecrafthttp://en.wikipedia.org/wiki/Vehiclehttp://en.wikipedia.org/wiki/Bicyclehttp://en.wikipedia.org/wiki/Hubble_Space_Telescopehttp://en.wikipedia.org/wiki/Shiphttp://en.wikipedia.org/wiki/Vehiclehttp://en.wikipedia.org/wiki/Inertial_guidance_systemhttp://en.wikipedia.org/wiki/Inertial_guidance_systemhttp://en.wikipedia.org/wiki/Tophttp://en.wikipedia.org/wiki/Yo-yohttp://en.wikipedia.org/wiki/Powerball_%28toy%29http://en.wikipedia.org/wiki/Powerball_%28toy%29http://en.wikipedia.org/wiki/Powerball_%28toy%29http://en.wikipedia.org/wiki/Flywheelhttp://en.wikipedia.org/wiki/Torquehttp://en.wikipedia.org/wiki/Angular_momentumhttp://en.wikipedia.org/wiki/Angular_momentumhttp://en.wikipedia.org/wiki/Moment_of_inertiahttp://en.wikipedia.org/wiki/Precessionhttp://en.wikipedia.org/wiki/Cross_producthttp://en.wikipedia.org/wiki/Cross_producthttp://en.wikipedia.org/wiki/Precessionhttp://en.wikipedia.org/wiki/Moment_of_inertiahttp://en.wikipedia.org/wiki/Angular_momentumhttp://en.wikipedia.org/wiki/Angular_momentumhttp://en.wikipedia.org/wiki/Torquehttp://en.wikipedia.org/wiki/Flywheelhttp://en.wikipedia.org/wiki/Powerball_%28toy%29http://en.wikipedia.org/wiki/Yo-yohttp://en.wikipedia.org/wiki/Tophttp://en.wikipedia.org/wiki/Inertial_guidance_systemhttp://en.wikipedia.org/wiki/Inertial_guidance_systemhttp://en.wikipedia.org/wiki/Vehiclehttp://en.wikipedia.org/wiki/Shiphttp://en.wikipedia.org/wiki/Hubble_Space_Telescopehttp://en.wikipedia.org/wiki/Bicyclehttp://en.wikipedia.org/wiki/Vehiclehttp://en.wikipedia.org/wiki/Spacecrafthttp://en.wikipedia.org/wiki/Aircrafthttp://en.wikipedia.org/wiki/Shiphttp://en.wikipedia.org/wiki/Gyrocompasshttp://en.wikipedia.org/wiki/Nutationhttp://en.wikipedia.org/wiki/Precession


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equations. The torque on the gyroscope is supplied by a couple of forces: gravity acting

downwards on the device's center of mass, and an equal force acting upwards to support one end

of the device. The rotation resulting from this torque is not downwards, as might be intuitively

expected, causing the device to fall, but perpendicular to both the gravitational torque (horizontal

and perpendicular to the axis of rotation) and the axis of rotation (horizontal and outwards from

the point of support), i.e. about a vertical axis, causing the device to rotate slowly about the

supporting point. Under a constant torque of magnitude , the gyroscope's speed of precession P

is inversely proportional to L, the magnitude of its angular momentum:

where is the angle between the vectors Pand L. Thus if the gyroscope's spin slows down (for

example, due to friction), its angular momentum decreases and so the rate of precession

increases. This continues until the device is unable to rotate fast enough to support its own

weight, when it stops processing and falls off its support, mostly because friction against

precession cause another precession that goes to cause the fall.

By convention, these three vectors, torque, spin, and precession, are all oriented with

respect to each other according to theright-hand rule.

To easily ascertain the direction of gyro effect, simply remember that a rolling wheel

tends, when entering a corner, to turn over to the inside.
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10. Actuator

A linear actuator is a device that applies force in a linear manner, as opposed to

rotationally like an electric motor. There are various methods of achieving this linear motion.

Some actually convert rotational motion into linear motion.

Types

Mechanical actuators

Mechanical actuators typically convert rotary motion of a control knob or handle into

linear displacement via screws and/or gears to which the knob or handle is attached. A jackscrew

or car jack is a familiar mechanical actuator. Another family of actuators are based on the

segmented spindle.Rotation of the jack handle is converted mechanically into the linear motion

of the jack head. Mechanical actuators are also frequently used in the field of lasers and optics to

manipulate the position of linear stages, rotary stages, mirror mounts, monometers and other

positioning instruments. For accurate and repeatable positioning, index marks may be used on

control knobs. Some actuators even include an encoder and digital position readout.[1]These are

similar to the adjustment knobs used on micrometers except that their purpose is position

adjustment rather than position measurement.

Hydraulic actuators

Hydraulic actuators orhydraulic cylinders typically involve a hollow cylinder having a

piston inserted in it. The two sides of the piston are alternately pressurized/de-pressurized to

achieve controlled precise linear displacement of the piston and in turn the entity connected to

the piston. The physical linear displacement is only along the axis of the piston/cylinder. This

design is based on the principles of hydraulics. A familiar example of a manually operated

hydraulic actuator is a hydraulic car jack. Typically though, the term "hydraulic actuator" refers

to a device controlled by ahydraulic pump.
http://en.wikipedia.org/wiki/Linearhttp://en.wikipedia.org/wiki/Jackscrewhttp://en.wikipedia.org/wiki/Segmented_spindlehttp://en.wikipedia.org/wiki/Linear_stagehttp://en.wikipedia.org/wiki/Rotary_stagehttp://en.wikipedia.org/wiki/Mirror_mounthttp://en.wikipedia.org/wiki/Goniometer_%28positioning%29http://c/Documents%20and%20Settings/sourab/Desktop/hal/Linear_actuator.htm%23cite_note-0http://c/Documents%20and%20Settings/sourab/Desktop/hal/Linear_actuator.htm%23cite_note-0http://c/Documents%20and%20Settings/sourab/Desktop/hal/Linear_actuator.htm%23cite_note-0http://en.wikipedia.org/wiki/Micrometerhttp://en.wikipedia.org/wiki/Hydraulic_cylinderhttp://en.wikipedia.org/wiki/Hydraulicshttp://en.wikipedia.org/wiki/Hydraulic_pumphttp://en.wikipedia.org/wiki/Hydraulic_pumphttp://en.wikipedia.org/wiki/Hydraulicshttp://en.wikipedia.org/wiki/Hydraulic_cylinderhttp://en.wikipedia.org/wiki/Micrometerhttp://c/Documents%20and%20Settings/sourab/Desktop/hal/Linear_actuator.htm%23cite_note-0http://en.wikipedia.org/wiki/Goniometer_%28positioning%29http://en.wikipedia.org/wiki/Mirror_mounthttp://en.wikipedia.org/wiki/Rotary_stagehttp://en.wikipedia.org/wiki/Linear_stagehttp://en.wikipedia.org/wiki/Segmented_spindlehttp://en.wikipedia.org/wiki/Jackscrewhttp://en.wikipedia.org/wiki/Linear


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Piezoelectric actuators

The piezoelectric effect is a property of certain materials in which application of a

voltage to the material causes it to expand. Very high voltages correspond to only tiny

expansions. As a result, piezoelectric actuators can achieve extremely fine positioning resolution,

but also have a very short range of motion. In addition, piezoelectric materials exhibithysteresis

which makes it difficult to control their expansion in a repeatable manner.

Electro-mechanical actuators

Electro-mechanical actuators are similar to mechanical actuators except that the control

knob or handle is replaced with an electric motor. Rotary motion of the motor is converted to

linear displacement of the actuator. There are many designs of modern linear actuators and every

company that manufactures them tends to have their own proprietary method. The following is a

generalized description of a very simple electro-mechanical linear actuator.

Linear Actuator

VL13A4Aircraft

Jaguar

The linear actuator VL13A4 is destined to operate the elevator trim. This actuator is

assembled with two motors and a differential planet gear arrangement which converts the rotary

motion of motor to linear motion. As the motors are bidirectional it shows the progressive

working in both the directions. For normal working of the unit only, one motor is energized at a

time. The second motor is called the sub motor which works in case of failure of main motor.
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Specifications

Nominal Load : 20 Dan

Maximum Load : 40 Dan

Operating Voltage : 18V to 29V

Stroke Length : 44+/-1.25mm

Motor RPM : 25000

Rated current : 0.85 Amp

Power : 5.2 Watt

Trim Actuator

AircraftALH

A set of trim / force feel system (FFS) consists of four actuators namely collective, pitch,

roll and yaw actuator corresponding to the four body axis of the helicopter. These actuators are

electromechanical units interfaced with the mechanical as well as with automatic flight control

system. The conventional mechanical control leakages in pitch, roll, collective and yaw axis are

fitted with one corresponding trim.

Functions

1.) Engagement/disengagement of anchor point by means of an electrically

operated clutch. This anchor point can be displaced either automatically or

mechanically.

2.) Artificial force feel about the anchor point generating a predetermined feel

force. The artificial feel is proportional to the displacement in pitch, roll and

collective trim actuator as they are spring based. The force feel is a constant

friction in the yaw axis.

3.) Pilot controlled displacement of the anchor point by means of an electrical

motor (manual trim function) or by declutching the artificial feels.


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4.) Automatic displacement of the anchor point so as to maintain the series

actuators around there center position (auto trim) .

11.Flight Data Recorder

Purpose and working:

System records automatically 6 continuously changing parameters which are:

Altitude

Engine speed

Aircraft speed

Vertical acceleration

Horizontal acceleration

Turn Angle of stabilizer

Five single command signal, Eight single command signals superimposed on Three

continuously variable parameters, and timer line to indicate the time on black and white aero

photo film and preserves it in normal and crash conditions for study and analysis of flight

conditions.

Working:

In this, mechanical motion is converted into electrical signals and then it is converted in

to optical signals,. There is a fixed mirror in the vibrator which moves accordingly to the moving

light beam. The light beam is moved under the effect of a permanent magnetic field and flux and

shifts the light beam accordingly. Now the mirror will move and thus light will move and thus

further the photographic film is printed.


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12. ADVANCED LIGHT HELICOPTER (ALH)

Advanced Light Helicopter is a multirole, multi-mission helicopter designed &

developed by HAL. The design of this 5.5-ton class, twin-engine helicopter incorporates several

state of the art technologies. Extensive use of composites high cruise speed, long range &

endurance, excellent high altitude performance and capability to operate in hot & humid

environment are the key design features. ALH has been designed for both civil & military

applications in large variety of roles overland & sea.

Performance:-

Maximum cruise speed at maximum load: 250 km/hr.

Maximum rate of climb: 10 m/sec

Range with 20 min reserve: 650 km

Endurance: 4 hrs.

Hover in ground effect: 1500 m

Hover out of ground effect: 1000m

Leading Particulars:-

Overall length: 15.87 m

Overall height : 4.91 m

Width : 3.19 m

Empty weight : 2500 kg

Fuel capacity : 1100 kg

Maximum take-off weight : 5500 kg

Maximum under slung weight : 1500 kg

Maximum height : 25000 HT


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Roles:-

Military Role (unarmed):-

Heliborne attack

Reconnaissance

Logistics support

Casualty evacuation

Air observation post

Military Role (Armed):-

Anti-tank

Close air support

Anti-submarine warfare

Anti-surface vessel warfare

Civil Role:-

Commuter / VIP

Search & rescue

Disaster relief

Air ambulance


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Salient Features:-

Ergonomically designed cockpit

Extensive use if composites, reduced radar signature

Large cabin volume

Ballistic damage tolerant

Greater system redundancy

Provision for weapons hard points

Twin engine with full authority digital electronic control

Adequate safety margin for single engine operation

Four axes automatic flying control system

Crash worthy crew seats, under floor & fuel tank

Hinge less main rotor & bearing less tail rotor

Excellent handling qualities at low as well as high speeds

Low maintenance cost & high fuel efficiency


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13. CONCLUSION

Finally we may conclude that HAL Accessories Division, Lucknow is a Government

undertaking, which is entitled to perform the making of the accessories used in the fighter

aircraft.

Although the whole assembly of the aircraft is not done in HAL Lucknow but there are

plans to launch Sukhois full assembly in HAL Lucknow

Thus HAL Lucknow would be entitled to work on latest technology of Sukhoi aircraft in

the coming future.


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14. References

1. http://www.grc.nasa.gov/WWW/K-12/airplane/airplane.html

2. http://www.alibaba.com/countrysearch/IN-suppliers/Alternator_Manufacturers.html

3. http://en.wikipedia.org/wiki/Gyroscope

4. http://www.aircraftspruce.com/menus/ps/oxygensystems.html

5. en.wikipedia.org/wiki/Actuator

6. en.wikipedia.org/wiki/Voltage regulator
http://www.grc.nasa.gov/WWW/K-12/airplane/airplane.htmlhttp://www.grc.nasa.gov/WWW/K-12/airplane/airplane.htmlhttp://www.alibaba.com/countrysearch/IN-suppliers/Alternator_Manufacturers.htmlhttp://www.alibaba.com/countrysearch/IN-suppliers/Alternator_Manufacturers.htmlhttp://en.wikipedia.org/wiki/Gyroscopehttp://en.wikipedia.org/wiki/Gyroscopehttp://www.aircraftspruce.com/menus/ps/oxygensystems.htmlhttp://www.aircraftspruce.com/menus/ps/oxygensystems.htmlhttp://www.aircraftspruce.com/menus/ps/oxygensystems.htmlhttp://en.wikipedia.org/wiki/Gyroscopehttp://www.alibaba.com/countrysearch/IN-suppliers/Alternator_Manufacturers.htmlhttp://www.grc.nasa.gov/WWW/K-12/airplane/airplane.html


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Hindustan Aeronautics Limited

Accessories Division

Lucknow-226 016

India