This document provides information about Hindustan Aeronautics Limited (HAL), an Indian state-owned aerospace and defense company. It discusses HAL's history, facilities, products, collaborations, and the electronic systems used in its aircrafts. Specifically, it details the electronic flight instrument system (EFIS), sensors that measure altitude, airspeed, and heading, fuel measurement techniques, and digital engine control systems like FADEC used in HAL aircrafts such as the Sukhoi Su-30.

1. A PRESENTATION ON
INDUSTRIAL TRAINING AT
LUCKNOW

2. 2
Type State-owned enterprise
Industry Aerospace and defence
Founded
1940 (in 1964,
company took on
current name)
Headquarters
Bangalore, Karnataka,
India
Chairman Ashok Nayar
Products
Aerospace equipment
Military aircraft
Communication &
Navigation equipment
Space systems
Revenue
US$2.35 billion (FY
2007)
Employees 30,000

3. 3
THE MISSION
“To become a global player in the aerospace industry”
> Hindustan Aeronautics Limited is the largest PSU under the
Department of Defense Production and is a Navaratana Company.
> HAL is one of the largest aerospace companies in Asia with its
annual turnover to be running above US$ 2 billion.
> It has several facilities throughout India including
Nasik, Korwa, Kanpur, Koraput, Lucknow, Bangalore
and Hyderabad.

4. 4
DIVISIONS OF HAL

5. COLLABORATIONS WITH COMPANIES
5
Airbus
Boeing
Sukhoi Aviation Corporation
Israel Aircraft Industries
RSK MiG
BAE Systems
Rolls-Royce plc
Dassault Aviation
Dornier Flugzeugwerke
Indian Aeronautical Development Agency
Indian Space Research Organisation.

6.  Established as Hindustan Aircraft Limited in Bangalore in
1940 by the late Seth Walchand Hirachand .
 Hindustan Aeronautics Limited came into existence on 1st
October 1964 by the merger of Hindustan Aircraft Limited
with Aeronautics India Limited and Aircraft Manufacturing
Depot, Kanpur.
 The Gov. of India became a share holder in March 1941 and
took over the management in 1942.
 Today H.A.L has 19 production units and 10 Research and
Design Centers in 8 location of India.
6

7. 7
 Electronic control system is used to install and
maintain the sensors which measure and report
flight and engine parameters.
1-SU-30.
2-Electronic flight instrumentation system.
3-Full Authority Digital Electronics Control
(FADEC).
4-Limited Authority Spark Advance Regulator.
5-Fuel Measurement Techniques.

8. 8

9. 9
The Sukhoi Su-30 is an air
superiority fighter jointly developed
by Russia's Sukhoi Aviation
Corporation and India's Hindustan
Aeronautics Limited (HAL).
Sukhoi Su-30 is a heavy, all-weather,
long-range fighter.
The Su-30 is a highly integrated
twin-finned aircraft.
The Su-30 is a multirole fighter.

10. 10
The aircraft is fitted with a satellite
navigation system (GPS compatible),
which permits it to make flights in all
weather, day and night.
SU-30 is equipped with a modern digital
weapons control system as well as anti-jamming
features.
The Su-30 is capable of accomplishing a
wide variety of combat mission at
significant distance from the home base, in
any weather conditions.

11.  An electronic flight instrument system is a flight deck
instrument display system in aircrafts.
 Which the display technology used in electronic
rather than electromechanical.
 EFIS consists of PFD,MFD,EICAS.
An EFIS installation will have the following
components:
 1-Display
 2-Controls
 3-Data Processors
11

12. 12
Two Multi Function
Displays
(MFD) for Navigation
and
aircraft system
synoptic.
Two Primary Flight
Displays
(PFD) for EFIS functions
(EADI/EHSI)
Two Primary Flight
Displays
(PFD) for EFIS functions
(EADI/EHSI)
Control panels for system
settings
One Engine & Warning
Display
(EWD) for Engine
Instruments and
Crew Alerting System,
Checklists/
Procedures
management and
permanent data.

13. 1-Primary Flight Display / Instrument System
* On the flight deck, the display units are the most obvious parts
of an EFIS system.
* The PFD displays all information critical to flight,
including calibrated airspeed, altitude, heading, vertical speed
and yaw.
* The altitude of the aircraft may be measured using
microelectronic sensors.
13

14.  Information on altitude and airspeed is provided by sensors
that measure static and ram air pressure.
 Aircraft heading may be determined using a magnetic
direction-sensing device such as a magnetometer or a
magnetic flux valve.
 An air data computer (ADC) combines those air pressure
and temperature sensors with a computer processor that is
capable of calculating pressure altitude, indicated airspeed,
vertical speed, and true airspeed.
14

15.  Precision Barometer and altimeter is used.
 The sensor Pressure and Temperature outputs are digitized by
a high resolution 24-bit ADC.
 The Altitude value is calculated by a specific patented
algorithm according to the pressure and temperature data.
 Easy command-based data acquisition interface and
programmable interrupt control is available.
 Pressure output can be resolved with output in fractions of a
Pascal, and Altitude can be resolved in 0.1 meter.
15

16.  Tri-Axial External Magnetometer (XMAG) is used.
 The XMAG is used to measure the magnetic field in
the area of its installation.
 In-production device is a solid-state sensor designed
to fit within the normal location of a flux-gate sensor
on an aircraft.
 It provides automatic ground and airborne calibration
when used with an Athena unit.
16

17.  Instrument used in an aircraft to display the craft's
airspeed, typically in knots, to the pilot.
 Airspeed indicators work by measuring the difference
between static pressure, captured through one or
more static ports; and stagnation pressure due to "ram
air", captured through a pitot tube.
 The static ports are located on the exterior of the
aircraft, at a location chosen to detect the prevailing
atmospheric pressure as accurately as possible.
17

18. 18

19.  The MFD (multi-function display) displays
navigational and weather information from multiple
systems.
 MFDs are most frequently designed as "chart-centric",
where the aircrew can overlay different
information over a map or chart.
 MFDs can also display information about aircraft
systems, such as fuel and electrical systems.
19

20. 20

21.  The conception of a modern fuel gauge is based on
another way of processing of capacitance change.
 The principle lays in transfer of the capacitance
change to the change of pulse width.
 The subsequent measurement by means of pulses is
done a defined width in 16-bit scalar of a general
microprocessor system and figuring the measured
values in the analog and digital form.
21

22.  Full Authority Digital
Engine (or Electronics) Control
(FADEC) is a system consisting of
a digital computer, called
an electronic engine controller (EEC) or engine
control unit(ECU), and its related accessories that
control all aspects of aircraft engine performance.
 FADEC works by receiving multiple input variables
of the current flight condition including air density,
throttle lever position, engine temperatures, engine
pressures, and many other parameters.
22

23. 23

24. 24