The document is a training report submitted by Rahul Kumar about indigenization at Hindustan Aeronautics Limited (HAL) in Lucknow, India. It provides details about several aircraft and helicopters developed through HAL's indigenization efforts, such as the Light Combat Aircraft (LCA), HAWK advanced jet trainer, and Cheetah/Chetak helicopters. It also describes HAL's objectives in pursuing indigenization to increase self-reliance and reduce dependence on foreign suppliers.

1. HINDUSTAN AERONAUTICS LIMITED,
LUCKNOW, UP
Training Report
INDIGENISATION
Submitted by RAHUL KUMAR
6/28/2018
In this Reportwe are going to learn about Indigenization system of HAL and
also about the indigenised aircrafts made by India through HAL

2. pg. II
DR. A. P. J. ABDUL KALAM TECHNICAL UNIVERSITY,
SITAPUR ROAD, LUCKNOW
CERTIFICATE
This to certify that Mr. RAHUL KUMAR , RollNo. 1547340054,
B.TECHFinal Year student of MechanicalEngineering had undergone
an Industrial Training at “HINDUSTAN AERONAUTICS LIMITED”,
LUCKNOW, effect 01-06-2018_30-06-2018. He has appearedin the
Industrial Training viva-vice as partial fulfillment of requirement for
the awardof the degree in “BachelorofTechnology” in the Mechanical
Engineering of A.K.T.U, Lucknow during academic year2018-2019.
Mr. Pankaj Kumar
H.O.D
(ME Deptt.)

3. pg. III
Declaration
I here by declare that this project work is an authentic record of my own work carried out
at Hindustan Aeronautics Limited, Lucknow as requirement of four weeks training
project for the award of degree which held between 1 June 2018 - 30 June 2018.
Rahul Kumar
MechanicalEngg.
GCRG,
BKT,
Lucknow
Certified that the abovestatement made by the student is correctto the
best of our knowledgeand belief.
SIGNATURE

4. pg. IV
Preface and Acknowledgement
I did a vocational training at HAL from Lucknow division which is the accessories
division of HAL, an aircraft manufacturing company which is India’s largest aircraft
manufacturing company. HAL is the 40th aircraft manufacturing company which is
ranked in the global level. HAL contains three types of industries- Mechanical Industry,
Fuel Industry, and Instrument Industry. I have experienced all the three industries during
my industrial visit. This training report is a part of my 4-year undergraduation
program which is being done in the GCRG Institute, BKT, Lucknow affiliated to AKTU .
During my training I have learned much about different sectors of industries and also
about the Aircraft systems by different faculties who are all masters in their sectors who
had used their crucial time to make us understand everything about HAL’s functioning
through presentations and lectures.
I would like to thank Abhishek Sir-manager at training department HAL, S. P. Singh Sir-
chief manager at training department HAL for guiding us at different levels during
training and making of this report and also for giving me this golden opportunity to be
part of HAL environment for a month. I would also like to thank all the faculties and staff
members of HAL who helped us during training. I would also like to thank my mates
during the session who helped in sorting queries.

5. pg. V
About HAL
Hindustan Aeronautics Limited (HAL) is an Indian state-
owned aerospace and defence company headquartered in Bangalore, India. It
is governed under the management of the Indian Ministry of Defence.
The government-owned corporation is primarily involved in the operations
of the aerospaceand is currently involved in the design, fabrication and
assembly of aircraft, jet engines, helicopters and their spare parts. It has
several facilities spread across India
including Nasik, Korwa, Kanpur, Koraput, Lucknow, Bangalore and Hydera
bad. HAL HF-24 Marut fighter-bomber was the first fighter aircraft made in
India.
The history and growth of the Hindustan Aeronautics Limited is
synonymous with the growth of Aeronautical industry in India for more
than 77 years.
The Company which had its origin as the Hindustan Aircraft Limited was
incorporated on 23 Dec 1940 at Bangalore by Shri Walchand
Hirachand a farsighted visionary in association with the Government of
Mysore with an Authorised Capital of Rs.4 crores (Paid up capital Rs.40
lakhs) and with the aim of manufacturing aircraft in India. In March
1941, the Government of India became one of the shareholders in the
Company holding 1/3 of its paid-up capital and subsequently took over
its management in 1942. In collaboration with the Inter Continental
Aircraft Company of USA, Hindustan Aircraft Company commenced its
business of manufacturing of Harlow Trainer, Curtiss Hawk Fighter and
Vultee Bomber Aircraft.

6. pg. VI
Organization Chart

7. pg. VII
Table of Contents
Contents
DR. A. P. J. ABDUL KALAM TECHNICAL UNIVERSITY,.............................................. II
What is Indigenization ........................................................................................................ VIII
AIRCRAFTS ........................................................................................................................ X
LCA..................................................................................................................................... X
Airframe...................................................................................................................... XII
Avionics ..................................................................................................................... XIII
HAWK............................................................................................................................... XV
AMCA.............................................................................................................................. XVII
Marut and HAL Tejas............................................................................................... XIX
Overview................................................................................................................... XIX
Propulsion.................................................................................................................. XX
Stealth and radar signature ....................................................................................... XX
Avionics and equipment ........................................................................................... XXI
Radar and sensors ................................................................................................... XXI
Cockpit..................................................................................................................... XXII
Projected Specifications.............................................................................................. XXII
Differences for FGFA.............................................................................................. XXIII
Specifications (PAK FA and FGFA – projected) ........................................................ XXIV
CHETAK......................................................................................................................... XXXI

8. pg. VIII
What is Indigenization
Indigenization is the act of making something more native; transformation of some
service, idea, etc. to suit a local culture, especially through the use of more indigenous
people in administration, employment, etc.
The term is primarily used by anthropologists to describe what happens when locals take
something from the outside and make it their own (e.g. Africanization, Americanization).
In world politics, indigenization is the process in which non-Western cultures redefine
their native land for better use in agriculture and mass marketing. Due to imperialism and
the impetus to modernize, many countries and cultures invoked Western values and
ideals of liberalism, democracy and independence in the past. But now, along with
experiencing their own share of cultural confidence, they desire to revert to their
traditional cultures and values.
However, the word indigenization is also used in almost the opposite sense, it means: to
increase local participation in or ownership of, to indigenize foreign-owned companies,
or to adapt (beliefs, customs, etc.) to local ways.
The word indigenization first appeared in a paper about studies conducted in India
about Christian missionaries. The word was used to describe the process of making
Churches indigenous in southern India. From there, it spread to The Economist where it
was used to describe managerial positions and to a book by John Spencer, named English
Language in West Africa, where it was used to describe the adoption of English.
Indigenization is often used to describe the adoption of colonial culture in Africa because
of the effects of colonialism by Europe in the 19th and early 20th century.

9. pg. IX
OBJECTIVES OF INDIGENISATION
In order to attain a progressively higher level of self-reliance, HAL has a policy of
carrying out concerted effort on indigenization of components, accessories and systems
required for manufacturing as well as repair & overhaul of aircraft, engine and
equipment. Indigenization with the primary objective of achieving Make in India and
lowering dependence on foreign countries especially for critical items is one of the key
thrust areas of HAL.
The major objectives of Indigenization and categories of items taken up for
indigenization at HAL are as follows:
 ltems which have become obsolete, or with delayed supply / no supply from OEMs and
thereby holding up production.
 ltems that are going to be obsolete.
 High value items which are leading to high FE expenditure.
 ltems being procured in high volume and in overall leading to high FE expenditure.
 All items especially the Class 'C' items where the technical details / drawings are
available.
 Class 'C' items where the technical details are not available but can be easily indigenized.
 ltems which are proprietary in nature and can create production hold up

10. pg. X
Some Indigenized aircrafts &
helicopters
AIRCRAFTS
LCA
Series Production Phase
Tejas is a single engined, light weight, highly agile, multi-role supersonic fighter. It has
quadruplex digital fly-by-wire Flight Control System (FCS) with associated advanced
flight control laws. The aircraft with delta wing is designed for ‘air combat’ and
‘offensive air support’ with ‘reconnaissance’ and ‘anti-ship’ as its secondary roles.
Extensive use of advanced composites in the airframe gives a high strength to weight
ratio, long fatigue life and low radar signatures. Aeronautical Development Agency is the
designated project manager for the development of LCA.

11. pg. XI
Performance
Specification Measurement
Length 13.2 m
Span 8.2 m
Height 4.4 m
Max Take of Weight 13.5 t
Payload 5.3 t
Speed 1.6 M
Radius of Action 300 km
Takeoff distance 1700 m
Landing distance 1300 m
Service Ceiling 16 km
Power Plant
 GE 404F2/J-IN20 (1 in no.) (General Electric)
 Turbofan engine
 Max. Thrust : 5618 kgf
The HAL Tejas is an Indian single-seat, single-jet engine, multirole light
fighter designed by the Aeronautical Development Agency (ADA) and Hindustan
Aeronautics Limited (HAL) for the Indian Air Force and Navy. It came from the Light
Combat Aircraft (LCA) programme, which began in the 1980s to replace India's
ageing MiG-21 fighters. In 2003, the LCA was officially named "Tejas".
Tejas has a tail-less compound delta-wing configuration with a single dorsal fin. This
provides for high maneuverability. Its wing root leading edge has a sweep of 50°, the
outer wing leading edge has a sweep of 62.5°, and trailing edge forward has a sweep of
4°. It integrates technologies such as relaxed static stability, fly-by-wire flight control
system, multi-mode radar, integrated digital avionics system, composite material
structures, and a flat rated engine. It is the smallest and lightest in its class of
contemporary supersonic combat aircraft.
The Tejas is the second supersonic fighter developed by Hindustan Aeronautics Limited
(HAL) after the HAL HF-24 Marut. As of 2016 the Tejas Mark 1 is in production for the
Indian Air Force (IAF) and the naval version is undergoing flight tests for Indian Navy
(IN). The projected requirement for the IAF is 200 single-seat fighters and 20 twin-seat
trainers, while the IN expects to operate 40 single-seat fighters. The first Tejas IAF
unit, No. 45 Squadron IAF Flying Daggers was formed on 1 July 2016 with two aircraft.
Initially being stationed at Bangalore, the first squadron will be placed at its home base at
Sulur, Tamil Nadu.[12]
The Minister of State for Defence, Subhash Bhamre, reported to parliament that the
indigenous content of the Tejas is 59.7% by value and 75.5% by number of line
replaceable units.

12. pg. XII
The maximum payload capability of Tejas is 4,000 kg (8,818 lb).All weapons are carried
on one or more of seven hardpoints with total capacity of greater than 4,000 kg: three
stations under each wing and one on the under-fuselage centreline. An eighth offset
station beneath the port-side intake trunk can carry a variety of pods
like FLIR, IRST, laser rangefinder/designator, as can the centreline under-fuselage
station and inboard pairs of wing stations. Auxiliary fuel tanks of 800 and 1,200 litres can
be carried under the fuselage to extend range. An aerial refuelling probe on the starboard
side of the forward fuselage can further extend range and endurance. RAFAEL's Derby
fire-and-forget missile will serve as the Tejas' initial medium range air-air
armament.The Brahmos NG supersonic cruise missile is being developed for the Tejas.
Airframe
Composites in the LCA
Tejas is constructed of aluminium-lithium alloys, carbon-fibre composites, and titanium
alloys.Composite materials make up 45% of the airframe by weight and 95% by surface
area. Upper and lower wing skins are manufactured from a single piece of carbon-fibre
reinforced polymer. Wing spars and ribs are also made out of carbon composites. The

13. pg. XIII
percentage of carbon composites in the airframe by weight rose from 30% in the
technology demonstrators to 42% in the prototype vehicles. The construction
of elevons, tailfin, rudder, air brakes and landing gear doors use co-cured and co-bonded
manufacturing techniques. The radome is made out of Kevlar, while the fin tip is made
out of glass-fibre reinforced plastic. Composite materials are used to make an aircraft
both lighter and stronger at the same time compared to an all-metal design, and the LCA's
percentage employment of carbon-fibre composites is one of the highest among
contemporary aircraft of its class.
Avionics
The Tejas has a night vision goggles (NVG)-compatible "glass cockpit", dominated by an
CSIR-CSIO domestically-developed head-up display (HUD), three 5 in x 5 in multi-
function displays, two Smart Standby Display Units (SSDU), and a "get-you-home"
panel providing the pilot with essential flight information in case of an emergency. The
displays provide information on key flight systems and controls on a need-to-know basis,
along with basic flight and tactical data. The pilot interacts with onboard systems through
a multifunctional keyboard and several selection panels. The CSIO-developed HUD,
Elbit-furnished DASHhelmet-mounted display and sight (HMDS), and hands-on-throttle-
and-stick (HOTAS) controls reduce pilot workload and increase situation awareness by
allowing access to navigation and weapon-aiming information with minimal need to
spend time "head down" in the cockpit.
The first 20 production Tejas Mk 1 equipped with hybrid version of the EL/M-2032
radar. It features look-up/look-down/shoot-down modes, low/medium/high pulse
repetition frequencies (PRF), platform motion compensation, doppler beam-
sharpening, moving target indication(MTI), Doppler filtering, constant false alarm
rate (CFAR) detection, range-Doppler ambiguity resolution, scan conversion, and online
diagnostics to identify faulty processor modules. The Tejas Mk 1A will be equipped with
an improved version of the EL/M-2052 AESA radar being developed jointly by Elta and
HAL.
Flight controls
Since the Tejas is a relaxed static stability design, it is equipped with a quadruplex digital
fly-by-wire flight control system to ease pilot handling. The Tejas aerodynamic
configuration is based on a pure delta-wing layout with shoulder-mounted wings.
Its control surfacesare all hydraulically actuated. The wing's outer leading edge
incorporates three-section slats, while the inboard sections have additional slats to
generate vortex lift over the inner wing and high-energy air-flow along the tail fin to
enhance high-AoA stability and prevent departure from controlled flight. The wing
trailing edge is occupied by two-segment elevons to provide pitch and roll control. The
only empennage-mounted control surfaces are the single-piece rudder and two airbrakes

14. pg. XIV
located in the upper rear part of the fuselage, one each on either side of the fin.
A Tejas conducting an inverted pass
Propulsion
Early on, it was decided to equip prototype aircraft with the General Electric F404-GE-
F2J3 afterburning turbofan engine while a program to develop a domestic powerplant led
by the Gas Turbine Research Establishment was launched. In 1998, after Indian nuclear
tests, US sanctions blocked sales of the F404, leading to a greater emphasis on the
domestic Kaveri. In 2004, General Electric was awarded a US$105 million contract for
17 uprated F404-GE-IN20 engines to power the eight pre-production LSP aircraft and
two naval prototypes;deliveries began in 2006. In 2007, a follow-on order for 24 F404-
IN20 engines to power the first operational Tejas squadron was issued.
A General Electric F404 engine during ground testing

15. pg. XV
HAWK
Hawk- Advanced Jet Trainer
The Hawk is a tandem-seat Aircraft for ground attack, flying training and weapon
training. It has a low wing and an all-metal structure and is powered by an Adour Mk 871
turbofan engine. The Aircraft has an integrated navigation /attack system and radio and
inertial navigation systems. The Aircraft is cleared for instrument (IFR) flying and for
Solo Instrument flying from the front cockpit only.
Basic Data
Dimensions Wing Data Weight Fuel Capacity Power Plant
Length: 12.43
m
Area (Gross): 16.70
m2
Maximum
Takeoff: 9100 kg
Internal : 360 Imp
Galls
Rolls Royce Adour MK 871
Turbofan
Wing Span:
9.940 m
Height: 3.98
m
Sweep (at quarter
chord): 21º 31’ 55”
Basic Mass
(Empty): 4,440 Kg
Ext. Drop Tanks: 2
x 130 Imp Galls
Static Thrust at sea level: 1 x 25.5
kN (5730 lbf) at sea level ISA

16. pg. XVI
Flying Characteristics
 The aircraft has excellent flying characteristics with good stability and response to
controls about all three axes
 The aircraft is cleared for a wide range of aerobatic manoeuvres and exhibits very good
resistance to departure even outside the normal flight envelope
 At incidences up to the stall, the aircraft is stable about all axes for all flap configurations
 Recovery from any stall is immediate on moving the control column forward
 The Hawk Mk.132 wing has a moderate amount of fixed droop to the leading edge to aid
sustained turn performance in the speed range 0.4 to 0.7 M
 The aircraft is spin-resistant, but is cleared for deliberate upright spinning in the basic
aircraft configuration with or without the gunpod
 The aircraft is currently cleared for take-off and landing with a crosswind component of
30 knots (55 km/hr)
 For solo flying the front cockpit is used
 The aircraft has an inverted flight (negative g) capability of 30 secs
 The aircraft may be flown at night, either dual or solo, without any additional flight
limitations
Performance
Maximum Level Speed Service
Radius of action with max. pay
load
At Sea Level:
0.84 Mach
Ceiling: 13533 m (13.53
km)
Lo-Lo-Lo: 267 km (267000 m)
At 30000 ft: 0.85 Mach Take-off run: 664 m Hi-Hi-Hi: 754 km (754000 m)

17. pg. XVII
Maximum Level Speed Service
Radius of action with max. pay
load
Landing run: 799 m
International Co-Operation
The Division has made a breakthrough on Exports by bagging the biggestever export contract from Airbus
Industries France,for the supplyof Forward Passenger Doors for A320/A321.
The Division’s performance in the supplyof export packages has been credited with “No rejection “and “No
Delay “at mostcompetitive prices.
Aircraft Division, HAL is an Established Exporter To
BOEING, USA
 Boeing 777 Uplock Box
 F/A 18 Gun Bay Door
 F/A 18 Wire Harness
 P-8I Weapon Bay Door
AIRBUS, FRANCE
 A320 Forward Passenger Doors
IAI, ISRAEL
 Boeing 737-300 Cargo Conversion Door & Kits
 G-150 Rear Fuselage
AMCA
The HAL Advanced Medium Combat Aircraft (AMCA) is an Indian programme of a fifth-
generation fighter aircraft. It is being developed by an aerospace industry team which
consists of the Aeronautical Development Agency (ADA) as the design firm with
manufacturing carried out by Hindustan Aeronautics Limited (HAL) as the primary contractor
and main assembly firm.[1]
It is a single-seat, twin-engine, stealth all weather multirole
fighter aircraft. Feasibility study on AMCA and the preliminary design stage have been
completed. The project awaits approval to begin design and development stage. The first
flight is scheduled to occur in 2025.

18. pg. XVIII
Role Stealth multirole fighter
National origin India
Manufacturer Hindustan Aeronautics Limited
Designer Aeronautical Development Agency
Defence Research and Development
Organisation
Status Under development
Primary users Indian Air Force
Indian Navy

19. pg. XIX
It is a multirole combat aircraft designed for air superiority, ground attack,
bombing, intercepting, strike and other types of roles. It combines supercruise, stealt,
advanced AESA radar, supermaneuverability and advanced avionics to overcome and
suppress previous generation fighter aircraft along with many ground and maritime defences.
It will complement HAL Tejas, Sukhoi/HAL FGFA, the Su-30MKI, and Rafale in the air force
service and HAL Naval Tejas and Mikoyan MiG-29K in the naval service. The AMCA is
intended to be the successor to the SEPECAT Jaguar, Dassault Mirage 2000 and Mikoyan
MiG-27 in the Indian Air Force. The aircraft, along with its naval variants, is intended to
provide the bulk of the manned tactical airpower of the Indian Air Force and Navy over the
coming decades. AMCA would be the third supersonic jet of Indian origin after the HAL
Marut and HAL Tejas.
Overview
The AMCA is a multirole fighter aircraft, with shoulder mounted diamond shaped trapezoidal
wings, a profile with substantial area-ruling to reduce drag at transonic speeds, and an all-
moving Canard-Vertical V-tail with large fuselage mounted Tail-wing.[2]
Flight control surfaces
include leading and trailing-edge flaps, ailerons, rudders on the canted vertical stabilizers,
and all-moving tailplanes; these surfaces also serve as Air brakes. The cockpit features a
single seat configuration which is placed high, near the air intakes and wings of the aircraft to
provide good visibility to the pilot with a single bubble canopy construction.[2]
The aircraft
features a tricycle landing gear configuration with a nose landing gear leg and two main
landing gear legs. The weapons bay is placed on the underside of the fuselage between the
nose and main landing gear. The AMCA is designed to produce a very small radar cross-
section, to accomplish this it features serpentine shaped air-intakes to reduce radar
exposure to the fan blade which increases stealth, uses an internal weapons bayand
features the use of composites and other materials.[2]
The flight control surfaces are
controlled by a central management computer system. Raising the wing flaps and aileronson
one side and lowering them on the other provides roll.[citation needed]
A leading-edge root extension (LERX), which is a small fillet, is situated on the front section
of the intake and wings of the aircraft. It has a typically roughly rectangular shape, running
forward from the leading edge of the wing root to a point along the fuselage. Also, the AMCA
has an In-flight refueling (IFR) probe that retracts beside the cockpit during normal
operation.[2]
Airframe
Stressed ducts in s-shape are locked with airframe with the loaded bulkheads which are
made of composite materials spanning the aircraft from air intake to engine shafts.[2]
The
radome which holds radar is made of advance composite and construction, which result in
allowing only the operating frequencies of the mated radar to transmit from the dome, while
blocking other radars.[2]
Flight surfaces and controls
Since the AMCA is a relaxed static stability design, it is equipped with a quadruplex
digital fly-by-optics flight control system to ease pilot handling. The AMCA's aerodynamic
configuration is based on a diamond shaped trapezoidal-wing layout with shoulder-mounted
wings. Its control surfaces are electro hydraulically actuated and digitally controlled using
fiber-optic cables. The wing's outer leading edge incorporates three-section slats, while the
inboard sections have additional slats to generate vortex lift over the inner wing and high-
energy air-flow along the tail fin to enhance high-angle of attack stability and prevent
departure from controlled flight. The wing trailing edge is occupied by two-segmented

20. pg. XX
elevons to provide pitch and roll control. The only empennage-mounted control surfaces are
the Pelikan tail with single-piece rudder which includes two airbrakes located in the upper
rear part of the Pelikan tail, one each on either side of the tail. The AMCA feature a highly
evolved integrated control laws for flight, propulsion, braking, nose-wheel steering and fuel
management and adaptive neural networks for fault detection, identification and control law
reconfiguration. Flights controls of the aircraft are both highly integrated and independent of
each other which includes flight controls, engine controls, brake and landing controls, and
other systems this is possible due the active controls gears systems (ACGS).[2]
The digital FBW system of the aircraft employs an advance next-generation distributed digital
flight control computer (DDFCC) made by ADE comprising four computing channels, each
with its own independent power supply and all housed in differently placed LRU.[73]
The
DFCC receives signals from a variety of sensors and pilot control stick inputs, and processes
these through the appropriate channels to excite and control the elevons, rudder and leading
edge slat hydraulic actuators. DFCC provides raising the wing flaps and ailerons on one side
and lowering them on the other provided roll. The Pelikan-tail fins are angled at 27 degrees
from the vertical. Pitch is mainly provided by rotating these pelikan-tail fins in opposite
directions so their front edges moved together or apart. Yaw is primarily supplied by rotating
the tail fins in the same direction. The AMCA is designed for superior high Angle of
attack (AoA) performance. Deflecting the wing flaps down and ailerons up on both sides
simultaneously provided for Aerodynamic braking.[2]
Propulsion
AMCA is a twin-engined aircraft which is powered by two GTRE K 9 + or K 10 engine which
are successor to the troubled Kaveri engine. The K 10 Program is a joint venture partnership
with a foreign engine manufacturer. K 10 program engine will be final production standard
Kaveri engine and shall have less weight and more reheat thrust along with certain other
changes to meet the original design intent. Both the engines are designed by ADA and
developed by GTRE. Full scale development of the K 9 and K 10 engine would be completed
by 2019.while AMCA Test Demonstrator would be powered by an existing 90 kN thrust
engine.
The K 9 + and K 10 engines are designed to supercruise with a speed of Mach 1.82 with
both engines.The aircraft is projected to have a maximum speed of over Mach 2.5, with a
maximum takeoff weight of 60,000 lb (29,000 kg).
Stealth and radar signature
The AMCA is designed to be difficult to detect by radar and other electronic measures due to
various features to reduce radar cross-section include airframe shaping such as planform
alignment of edges, fixed-geometry serpentine inlets that prevent line-of-sight of the engine
faces from any exterior view, use of radar-absorbent material (RAM), and attention to detail
such as hinges and pilot helmets that could provide a radar return. Efforts have been made
to minimise radio emissions and both the infrared signature and acoustic signature as well as
reduced visibility to the naked eye. Alignment of wings, tail, flaps and other edges increases
radar and visually stealthe.
Radar absorbing structures and radome, body conformal antennae surface hard aperture,
flush air data sensors and frequency selective surface (FSS) radome are used to reduce
radar detection. Stealth ability is enhanced by the use of microelectromechanical
systems (MEMS) and nanoelectromechanical systems (NEMS) during the construction of the
airframe and in the airframe and instruments. AMCA's design prevents detection of the
aircraft from L band, C band and X band radars.[2]
The aircraft's thrust vectoring nozzle
reduces infrared emissions to mitigate the threat of infrared homing surface-to-air or air-to-air

21. pg. XXI
missiles. Additional measures to reduce the infrared signature include special paint
and active cooling of leading edges to manage the heat build up from supersonic flight.
Armament and standards
Image of Astra
The AMCA features an internal weapons bay, but a non-stealthy version with external pylons
is also planned. The aircraft is planned to be equipped with beyond visual range missiles,
close combat missiles, standoff weapons, precision weapons and laser guided bombs.[79]
Avionics and equipment
The aircraft's avionics suite will IRST and advance situational oriented electronic
warfare systems and all aspect radar warning receiver(RWR), Self-Protection
Jammer(SPJ), CMOS, laser warning receiver (LWR), missile warning suite.
Defence Electronics Application Laboratory (DEAL) has designed and developed a next-
generation network-centric aircraft management system (including weapons) including
various features such as data fusion, Cooperative Engagement Capability, decision aids,
integrated modular avionics, and intern signature control with sharpening for low
observability. The aircraft will use integrated modular avionicsfor real time computing, and
the fibre optic cables used on the aircraft feature photonic crystal fibres technology for faster
exchange of data. Unlike the HAL's previous fighter aircraft, the Tejas, which has a digital
flight-control computer and hydraulic controllers, the AMCA has a distributed processing
system employing fast processors and smart subsystems and will be electronically controlled
via a "central computational system connected internally and externally on an optic-fibre
channel by means of a multi-port connectivity switching module". This results in using
the IEEE-1394B-STD a departure from MIL-STD-1553B databus standard.[82]
Radar and sensors
AMCA would be equipped with an AESA radar mounted on a mechanically steerable
mount.[2]
An onboard condition monitoring system is planned to be included in the AMCA.[83]

22. pg. XXII
Cockpit
The AMCA's cockpit features a panoramic active-matrix display, with the switches, bezels
and keypads replaced with a single large multi-functional touch screen interface supported
by voice commands (Also the cockpit will be fully made by composite or glass) .[72]
Projected Specifications
Data from Jane's All the World's Aircraft
General characteristics
 Crew: 1 to 2
 Length: 17.2 m (56 ft 5.25 in)
 Wingspan: ()
 Height: 4.8 m (16 ft 9 in)
 Wing area: 39.9 m² (429.5 ft²)
 Empty weight: 17,273 kg (38,090 lb)
 Max. takeoff weight: 29,465 kg (64,959 lb)
 Powerplant: 2 × Undecided[5]
afterburning turbofan
Performance
 Maximum speed: 2,655 km/h (1,650 mph)
 Range: 1,750 nmi (3,241 km, 2,014 mi)
 Ferry range: 2,875 nmi (5,324 km, 3,308 mi)
 Service ceiling: 18,044 m (59,200 ft)
 Rate of climb: 13,716 m/min (45,000 ft/min)
 Wing loading: 738 kg/m² (151.26 lb/ft²)
Armament
 Guns: 23 mm GSh-23 cannon
 Hardpoints: 3 under each wing, 2 tandem pairs under-fuselage for a total of 10
 Missiles: BrahMos NG[33]
SU-30 MKI
The Sukhoi/HAL Fifth Generation Fighter Aircraft (FGFA) or Perspective Multi-role
Fighter (PMF) was a fifth-generationfighter aircraft planned for India and Russia. It was a
derivative project of the Russian Sukhoi Su-57 for the Russian Air Force. The FGFA was the
earlier designation for the Indian version, while the combined project is called the
Perspective Multi-Role Fighter (PMF). India withdrew from the FGFA programme in 2018.
The completed FGFA was to include a total of 43 improvements over the Su-57, including
stealth, supercruise, advanced sensors, networking and combat avionics.[7][8]
The Indian
version would have have been a two-seater with pilot and co-pilot/weapon systems
operator (WSO).

23. pg. XXIII
Twin-seater, Multi-role, Long range Fighter / Bomber / Air Superiority Aircraft.
Although there is no reliable information about the PAK FA and FGFA specifications yet, it is
known from interviews with people in the Russian Air Force that it will be stealthy, have the
ability to supercruise, be outfitted with the next generation of air-to-air, air-to-surface, and air-
to-ship missiles, and incorporate an AESA (active electronically scanned array) radar. The
PAK FA/FGFA will use on its first flights 2 Saturn 117 engines (about 147.1 kN thrust each).
The 117 is an advanced version of the AL-31F, but built with the experience gained in the
AL-41F programme. The AL-41F powered the Mikoyan MFI fighter (Mikoyan Project 1.44).
Later versions of the PAK FA will use a completely new engine (107 kN thrust each, 176 kN
in full afterburner), developed by NPO Saturn or FGUP MMPP Salyut.
Three Russian companies will compete to provide the engines with the final version to be
delivered in 2015–2016.
Russian expertise in titanium structures will be complemented by India's experience in
composites like in the fuselage. HAL is to be contributing largely to composites, cockpits and
avionics according to company statements made in September 2008. HAL is working to
enter into a joint development mechanism with Russia for the evolution of the FGFA engine
as an upward derivative of the AL-37. Speaking to Flight International, United Aircraft chief
Mikhail Pogosyan said India is giving engineering inputs covering latest airframe design, Hi-
Tech software development and other systems.
By August 2014, the United Aircraft Corporation (UAC) had completed the front end
engineering design for the FGFA for which a contract had been signed with India's HAL in
2010. Preparation of contract for full-scale development is in progress.
Differences for FGFA
The FGFA will be predominantly armed with weapons of Indian origin such as the Astra,
a beyond-visual-range missile (BVR) being developed by India. Although in keeping with the
Russian BVR doctrine of using a variety of different missiles for versatility and
unpredictability to countermeasures, the aircraft is expected to have compatibility with
various missile types. The FGFA may include systems developed by third parties.

24. pg. XXIV
The completed joint Indian/Russian versions of the operational fighters will differ from the
current flying prototypes through the addition of stealth, supercruise, sensors, networking,
and combat avionics for a total of 43 improvements.
Russia agreed to the demand of the Indian Air force that it must be a two-seater fighter. The
Indian version will be a two-seater with a pilot and weapon systems operator.[39]
Specifications (PAK FA and FGFA – projected)
Most of these figures are for the Sukhoi T-50 prototype and not the finished HAL FGFA.
Data from Aviation News, Aviation Week, Air International
General characteristics
 Crew: 2
 Length: 19.8 m (65.0 ft)
 Wingspan: 13.95 m (45.8 ft)
 Height: 4.74 m (15.6 ft)
 Wing area: 78.8 m2
(848.1 ft2
)
 Empty weight: 18,000 kg (39,680 lb)
 Loaded weight: 25,000 kg (55,115 lb) typical mission weight, 29,270 kg (64,530 lb) at
full load
 Max. takeoff weight: 35,000 kg (77,160 lb)
 Fuel capacity: 10,300 kg (22,700 lb)
 Powerplant: 2 × NPO Saturn izdeliye 117 (AL-41F1) for initial production, izdeliye 30 for
later production thrust vectoring turbofan
 Dry thrust: 93.1 kN / 110 kN (21,000 lbf / 24,300 lbf) each
 Thrust with afterburner: 147 kN / 176 kN (33,067 lbf / 39,600 lbf) each
Performance
 Maximum speed:
 At altitude: Mach 2.3 (2,440 km/h, 1,520 mph)
 Supercruise: Mach 1.6 (1,700 km/h, 1,060 mph)
 Range: 3,500 km (2,175 mi) subsonic
 1,500 km (930 mi) supersonic
 Ferry range: 5,500 km (3,420 mi) with one in-flight refueling
 Service ceiling: 20,000 m (65,000 ft)
 Wing loading: 317–444 kg/m2
(65–91 lb/ft2
)
 Thrust/weight:
 Saturn 117: 1.02 (1.19 at typical mission weight)
 izdeliye 30: 1.23 (1.41 at typical mission weight)
 Maximum g-load: +9.0 g
Armament
 Guns: 1 × 30 mm internal cannon
 Hardpoints: 6 internal, 6 on wings
Avionics
 Sh121 multi-functional integrated radio electronic system (MIRES)

25. pg. XXV
 N079 AESA radar
 L402 Himalayas ECM suite built by KNIRTI institute
 101KS Atoll electro-optical suite
 101KS-O: Laser-based counter-measures against infrared missiles
 101KS-V: IRST for airborne targets
 101KS-U: Ultraviolet warning sensors
 101KS-N: Targeting pod
FGFA
Fifth Generation Fighter Aircraft
It is the future aircraft. The proposed FGFA will have air combat superiority, high tactical
capability, group action capability in the regions even with poor communication support.
The aircraft will have advanced features like
 Increased Stealth
 Supersonic cruise
 Data link and network centric warfare capability.
FGFA will be co-developed with Russians. Sukhoi Design Bureau (SDB) has been
selected as the Russian agency for this development project.

26. pg. XXVI
HELICOPTERS
LCH
Light Combat Helicopter (LCH) was proposed to meet IAF’s requirement of a dedicated
light helicopter for combat operations. LCH has maximum possible commonality with
ALH. LCH with a narrow fuselage has pilot and co-pilot/gunner in tandem configuration
incorporating a number of stealth features, Armour protection, Night attack capability
and crash worthy landing gear for better survivability.
The major features of LCH are:
 Glass Cockpit
 Crashworthy bottom structure
 Crashworthy fixed tricycle type with tail wheel landing gear
 Canted flat panels for low Radar Cross Section
 Integrated Dynamic System
 Hinge less Main Rotor / Bearing less Tail Rotor
 Anti-Resonance Isolation System
 Integrated Architecture and Display System (IADS)
 IR Suppressor
 Counter Measuring Dispensing System (CMDS)
 EO pod, Helmet Mounted Display System & EW suite
 20mm Gun, 70mm Rocket & Missiles
 Air to Air Missiles (ATAM)
 Air to Ground Missiles (ATGM)
TechnicalParameters

27. pg. XXVII
 MTOW : 5800 Kg
 Max. speed : 268 Kmph
 Range : 550 Km
 Service Ceiling : 6.5 km
 Oblique climb rate : 12 m/s
PowerPlant
 SHAKTI engine (2 no.)
 Power is 1032 kW
DHRUV
Advanced Light Helicopter (ALH- DHRUV)
The indigenously designed and developed Advanced Light Helicopter (ALH-DHRUV) is
a twin engine, multi-role, multi-mission new generation helicopter in the 5.5 ton weight
class. The basic Helicopter is produced in skid version and wheeled version. Dhruv is
“type –Certified” for Military operations by the Centre for Military Airworthiness
Certification (CEMILAC) and civil operations by the Directorate General of Civil
Aviation (DGCA).
Certification of the utility military variant was completed in 2002 and that of the civil
variant was completed in 2004. The deliveries of production series helicopters
commenced from 2001-02 onwards. A total of 228 Helicopters have been produced by
March 2017 including 216 for the Indian Armed Forces.

28. pg. XXVIII
The major variants of Dhruv are classified as Dhruv Mk-I, Mk-II, Mk-III & Mk-IV. The
major features are furnished below:
Variant Power Plant / Major Systems Roles
ALH Mk.
I
- TM-333-2B2 engine
- Conventional cockpit
Utility
ALH Mk.
II
- TM-333-2B2 engine
- Integrated Architecture Display system
(Glass cockpit)
Utility
ALH
Mk.III
- Shakti engine
- IADS with Digital Moving Map
- Electronic Warfare Suite
- Electro Optical pod
- Counter Measure Dispensing system
- Infra Red Suppressor
- Health & Usage Monitoring system
- Solid State Digital Video Recorder
(SSDVR)
- Engine Particle Separator
Utility roles of Defence Services suited for high altitude
operations
ALH Mk.
IV
ALH Mk.III with weapon systems
and mission sensors like
- Turret Gun
- Rocket
- Air-to-Air Missile
- Air-to-Ground Missile
- Helmet Pointing System
- Data Link
- Infra Red Jammer
- Obstacle Avoidance System
Armed variant for Attack, Close Air Support and High
altitude operations.
Technical Parameters
ALH Mk-III ALH Mk-IV
Length 15.9 m 15.9 m
Width 13.2 m 13.2 m
Height 4.98 m 4.98 m
Max Take Off Weight 5500 kg 5800 kg
Never Exceed Speed (VNE) 292 Km/h 245 Km/h
Range 630 km 590 km
Endurance 3.65hr 3.8 hr
PAX 12 + 2
Power Plant
 TM 333 – 2B2 (For Dhruv Mk-I and Mk-II) & ARDIDEN 1H1 (Shakti) (for Dhruv Mk
III & Mk IV).

29. pg. XXIX
TM 333 - 2B2 SHAKT
- Dry wt. 167.5 kg 205 kg
- Max. Power 801 kW 1032 kW
- Specific Fuel Consumption 0.323 kg/kw hr 0.300 kg/kw hr
Shakti Engine (For Dhruv Mk-III & Mk-IV)
 12 % Higher power than TM 333 2B2 engine
 Dual centrifugal compressor assembly
 Single crystal blades
 Dual channel FADEC
Roles of Dhruv
 Passenger / Commuter Role
 VIP Travel
 Causality Evacuation
 Under Slung Load
 Rapid Deployment of Forces
 Logistic Air Support
 Search and Rescue
 Training
Features of Dhruv
 Composite Hinge less Interchangeable Main Rotor Blades
 Composite Bearing less Tail Rotor Blades
 Composite Air Frame
 Glass Cockpit & AFCS
 Chaff & Flare Dispenser
 Helmet Pointing System (HPS)
 Health & Usage Monitoring System
 Digital Video Recording System
 VOR/ILS/DME
 EO Pod with FLIR, LRF & LP
 IR Suppressor
 FADEC
 Integrated Self Protection Suite
 Digital Moving Map
 On Board Inert Gas Generation System
Weapon fitment on ALH Mk-IV
 20 mm Turret Gun
 70 mm Rocket
 Air to Air Missile

30. pg. XXX
The HAL Rudra, also known as ALH-WSI, is an armed version of HAL Dhruv. Rudra
is equipped with Forward Looking Infrared(FLIR) and Thermal Imaging Sights Interface,
a 20 mm turret gun, 70 mm rocket pods, anti-tank guided missiles and air-to-air missiles.
RUDRA
Rudra is the Weaponised version of the Advanced Light Helicopter (Dhruv) designed and
developed by Hindustan Aeronautics Limited (HAL) to meet the requirements of Indian
Army & Air Force. The multi role helicopter of 5.8 Ton class is powered by two Shakti
Engines
Roles:
 Anti-tank
 Scout
 Fire support
 Armed reconnaissance and surveillance
 Escort
 EW platform
Salient Features:
 Excellent hover performance
 Designed for high rate of climb performance
 Adequate safety margins in the event of single engine failure
 Ideal for operations from unprepared surfaces and slopes
 Designed to perform cost effective operations due to better fuel efficiency and low
maintenance cost

31. pg. XXXI
Weapons:
 20 mm Turret Gun
 70 mm Rocket System
 Air to Air Missile
Mission Sensors:
 Electronic Warfare (EW) Suite
 Helmet Pointing System (HPS)
 Electro Optical (EO)-Pod.
 Video and Data Recorder (VDR)
 Flare and Chaff Dispenser (FCD)
CHETAK
HAL, Helicopter Division started manufacturing of helicopters in 1962, by entering an
agreement with M/s SUD-AVIATION (Presently M/s AIRBUS (Former
EUROCOPTER), France) for production of Aloutte III helicopters (Chetak). The first
Chetak (Aloutte III) in ‘Fly Away’ condition delivered in 1965.
The Chetak Helicopter is a two ton class helicopter. The seven seater Chetak helicopter
is versatile, multi role, multi purpose, and spacious.
The helicopter is powered by Artouste - III B turbo shaft engine.
The helicopter is suitable for commuting, cargo / material transport, casualty evacuation,
Search & Rescue (SAR), Aerial Survey & Patrolling, Emergency Medical Services, Off-
shore operations and Under slung operations.

32. pg. XXXII
Till date, HAL has produced and sold more than 350 of these versatile Helicopters which
are in service both in India and abroad. Recently, HAL has received orders for Chetak
helicopters from MOD Namibia & MoD Suriname.
Technical Parameters
Length 12.84 m
Width 2.59 m
Height 2.97 m
MTOW 2200 kg
Cruise Speed 185 Km/h
Range 500 km
Endurance 3.00 hr
No. of Passengers 5 + 2

33. pg. XXXIII
Conclusion
This training lend me in many ways and I got knowledge in many areas which I never
imagined before this training.
HAL is planning to launch different aircrafts having more advanced features.
Their aim is to become the topmost aircraft manufacturing company in the global
ranking and also their fighter aircrafts or helicopters would be exported in an enormous
number.
Hope they’ll achieve their aim in future and glow our countries name more in the global
list.

34. pg. XXXIV
References
The contents are gathered from-
 Class lectures
 Presentations of the faculties
 HAL website-http://hal-india.co.in
 Wikipedia
 And other sites