This presentation provides an overview of electronics control systems used in aircraft, including those manufactured by Hindustan Aeronautics Limited (HAL). It discusses the history of HAL and describes some of the systems and products manufactured at HAL's Lucknow facility. It then explains the four forces of flight and describes electronic control systems like the SU-30's avionics, the electronic flight instrument system, full authority digital engine control (FADEC), and limited authority spark advance regulator (LASAR). The presentation emphasizes that these electronic systems improve aircraft and engine performance, safety, and efficiency.

1. Presentation On Electronics Control System
In Aircrafts
PREPARED BY:
PRASHANT KUMAR
EC(4th Year)
1

2. ABOUT HAL
2

3. HISTORY OF HAL
 > Hindustan Aeronautics Limited (HAL) came
into existence on 1st October 1964. The
Company was formed by the merger of
Hindustan Aircraft Limited with Aeronautics
India Limited and Aircraft Manufacturing
Depot, Kanpur
 Late Mr. Seth Walchand Hirachand 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.
3

4. HAL LUCKNOW
 Established in 1970 with the primary
objective of manufacturing systems and
accessories for various aircraft and engines
and attain self sufficiency in this area
 Presently turning out over 1100 different
types of accessories
 Started with manufacturing various Systems
and Accessories-Hydraulics, Engine Fuel
System, Air-conditioning and Pressurization,
Gyro & Barometric Instruments, Electrical
System items, Undercarriages, Electronic
items all under one roof to meet the
requirements of the aircraft, helicopters and
engines being produced by HAL
4

5. PRODUCTS OF HAL
LUCKNOW
 Instruments Sensors, Gyros
 Flight instruments, electrical indicators, Fuel Gauge probes, Gyros,
sensors and Switches
 Electrical power generation and control AC/DC Generator, Control
and protection units, inverters, Transformers Rectifier units, AC/DC
Electrical system, Actuators.
 Land navigation systems
 Microprocessor controller
 Under carriage, wheels and breaks
 Hydraulic system and power control
 Pumps, Accumulators, Actuators, Electro-Selectors, Bootstrap
Reservoirs and various types.
 Environmental control system
 Pneumatics and oxygen system, cold air unit, water Extractors,
valves.
 Ejection system-Ejection Seats, Release Units
 Engine fuel control systems
 Booster pumps, main and Reheat Fuel systems, Nozzle Actuators
5

6. The Four Forces of Flight
6
The four forces act on the
airplane in flight and also work
against each other.

7. THE FOUR FOURCES
7

8. WHAT IS WEIGHT ???
8

9. WHAT IS LIFT ???
9

10. HOW LIFT IS GENERATED??
 Newton’s Laws of Motion and
Bernoulli’s Principle are used to
explain lift.
 Bernoulli – Bernoulli’s Principle
states that, as air speeds up, its
pressure goes down.
 He focused his studies on the
curvature of the wing, and the
differing air pressure over the top
and bottom of the wing.
 Newton – Newton’s Third Law states
that for every action there is an
equal and opposite reaction.
 He focused his studies on the
deflection of air or fluid on an object
and its reaction. (Newton’s 3rd Law)
 To explain the lift phenomena we
have to understand the meaning of
Aerofoil structure
10

11. AEROFOIL
11
An Aerofoil is a device that gets a
reaction from air moving over its
surface. When it is moved through the
air it produces lift. Wings, horizontal
and vertical tail surfaces and propellers
are all examples of aerofoil

12. SIMPLIFIED AIRCRAFT MOTION
UNBALANCED FORCES
12

13. 13

14. VARIOUS MOTIONS AROUND THE
AXES
14
• Yawing along vertical axis–
side to side motion
• Pitching along lateral axis –
up and down motion (nose up
and nose down)
• Rolling along longitudinal axis
– rolling motion

15. AIRFRAME UNITS
15

16. AVIONICS OF AIRCRAFT
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.
16

17. SUKHOI-30
17

18. SUKHOI SU-30
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.
18

19. SUKHOI SU-30
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.
19

20. Electronic Flight Instrument System
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
A basic EFIS might have all these facilities in the one
unit.
20

21. Electronic Flight Instrument System
Two Primary Flight
Displays
(PFD) for EFIS functions
(EADI/EHSI)
Two Primary Flight
Displays
(PFD) for EFIS functions
(EADI/EHSI)
Two Multi Function
Displays
(MFD) for Navigation and
aircraft system synoptic.
Control panels for system settings
One Engine & Warning
Display
(EWD) for Engine
Instruments and
Crew Alerting System,
Checklists/
Procedures management
and
permanent data.
21

22. DISPLAY UNITS:
1-Primary Flight Display
* 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, attitude, vertical speed and yaw.
* The PFD is designed to improve a pilot's situational awareness by
integrating this information into a single display instead of six different
analog instruments.
* LCD units generate less heat than CRTs; an advantage in a
congested instrument panel. They are also lighter, and occupy a lower
volume.
22

23. The Multi Function Display (MFD)-
1-The MFD (multi-function display) displays navigational and weather
information from multiple systems.
2- . MFDs are most frequently designed as "chart-centric", where the
aircrew can overlay different information over a map or chart.
3- MFDs can also display information about aircraft systems, such as
fuel and electrical systems (see EICAS, below).
23

24. Engine indications and crew alerting system (EICAS) /
electronic centralized aircraft monitoring (ECAM):
1- EICAS (Engine Indications and Crew Alerting System) displays
information about the aircraft's systems, including its fuel, electrical
and propulsion systems (engines).
2- EICAS improves situational awareness by allowing the aircrew to
view complex information in a graphical format and also by alerting the
crew to unusual or hazardous situations.
Control Panels :
 The pilots are provided with controls, with which they select display
range and mode (for example, map or compass rose) and enter data
(such as selected heading).
Where inputs by the pilot are used by other
equipment, data buses broadcast the pilot's selections so
that the pilot only needs to enter the selection once.
24

25. Advantages Of EFIS-
1-Offers versatality.
2- Flexibility afforded by software modifications.
3- Minimizes costs.
4- EFIS system can be updated with new software to
extend its capabilities.
5- Degree of redundancy is available.
25

26. Full Authority Digital Engine Control (FADEC):
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
26

27. ~ Provides optimum engine efficiency.
~ Provides efficient engine operation.
~ Controls engine starting & restarting.
~ Controls fuel flow.
~ Manages the power efficiently.
~ Manages the wind conditions, runway length.
FUNCTIONS OF FADEC:
27

28. Advantages of FADEC:
~ Better fuel efficiency.
~ Automatic engine protection against out-of-tolerance
operations.
~ Safer as the multiple channel FADEC computer provides
redundancy in case of failure.
~ Provides semi-automatic engine starting.
~ Better systems integration with engine and aircraft systems.
~ Can provide engine long-term health monitoring and
diagnostics.
Disadvantages of FADEC:
~ If a total FADEC failure occurs, the engine fails.
~ High system development and validation effort due to the
complexity.
28

29. Limited Authority Spark Advance Regulator:
~ FIRST microprocessor based engine control system approved
the FAA for general aviation piston aircraft.
~ To establish and command the optimum ignition timing and
spark energy to produce maximum torque from the engine.
~ LASAR has an inherent mechanical magneto backup system.
29

30. Benefits Of LASAR:
~Better engine starting with three times more spark energy
and higher output voltage.
~Smoother transition in ignition timing from engine start to
idle .
~Faster Rate of Climb.
~Increased spark plug life.
~EGT reduced by 150°F on average.
~Up to 12% Reduced Fuel Consumption.
~Up to 8% Increased Horsepower.
30

31. FLY SAFE……………….!!!!!
31

32. THANK YOU
..32

33. Any Query !!
33