Ae1252-nol

Aircraft systems and Instruments AE 1252 By Prof . N.Muthusamy Department of Aeronautical Engg

FLIGHT CONTROL SYSTEMS

PRIMARY FLIGHT CONTROL SRUFACES 4. ELEVATOR 5. AILERON 6. RUDDER SECONDARY FLIGHT CONTROL SYSTEMS. 1. TABS 2. FLAPS 3. SPOILERS 4. SPEED BRAKES

PURPOSE 1.TO ENABLE THE PILOT TO EXERCISE CONTROL OVER THE AIRCRAFT DURING ALLL PORTIONS OF FLIGHT. 2.IT ALLOWS TO MANOEUVRES IN PITCH,ROLL AND YAW. METHODS: 1. PUSH-PULL CONTROL ROD SYSTEM 2. CABLE AND PULLY SYSTEM

FLIGHT CONTROL SYSTEM COMPONENTS: 1. 2. 3. 4. 5. 6. 7. 8.

CABLES PULLEYS TURNBUCKLES PUSH PULL RODS BELL CRANKS QUANDRANTS. TORQUE TUBES CABLE GURARDS

FLY BY WIRE (FBW) IT IS ONE IN WHICH WIRE CARRYING ELECTRICAL SIGNALS FROM THE FLIGHT CONTROLS BY REPLACING MECHANICAL LINKAGES.

ADVANTAGES OF FBW: 1. WEIGHT SAVING 2. REDUCED MAINTENANCE TIMES 3. LESS SPACE 4. IMPROVED HANDLING

AUTOPILOT SYSTEM ACTIVE CONTROL TECHNOLOGY: AUTOPILOT IS A SYSTEM OF AUTOMATIC CONTROLS WHICH HOLDS THE ARICRAFT ON ANY SELECTED MAGNETIC HEADING AND RETURNS THE ARICRAFT TO THAT HEADING WHEN IT IS DISPLACED FROM IT.

PURPOSE: TO REDUCE THE WROK STRAIN AND FATIQUE OF CONTROLLING THE AIRCRAFT IN FLIGHT BY THE PILOT.

COMPONENTS: 1. GYROS (TO SENSE WHAT AIRPLANE IS DOING) 2. SERVOS (TO MOVE CONTROL SURFACES) 3. AMPLIFIER (TO INCREASE THE STRENGTH OF GYRO SIGNALS TO OPERATE SERVOS) THREE CHANNELS. 1. RUDDER CHANNELS 2. AILERON CHANNES. 3. ELEVATOR CHANNELS

COMMUNICATION SYSTEMS 1. H F 2. VHF 3. UHF NAVIGATIONAL AIDS 1. VOR (VHR OMNIRANGE) 2. DME (DISTANCE MEASURING EQUIPMENT) 3. ADF (AUTOMATIC DIRECTION FINDING)

INSTRUMENT LANDING SYSTEM 1. RUNWAY LOCALISER 2. GLIDESLOPE SIGNAL 3. MARKER BEACONS MIRCROWAVE LANDING SYSTEMS (MLS): MLS OPERATES IN THE FREQUANCY BAND OF 5031MHZ-5190.7MHZ. IT HAS WIDE FIEL D VIEW OF 40 DEGRESS IN AZIMUTH AND UPTO 20 DEGREES ELEVATION. THE COVERAGE IS UPTO 20NM FOR NORMAL APPROACH.

NON DIRECTIONAL BEACON (NDB) NDB IS GROUND BASED .IT IS NON-DIRECTIONAL BECAUSE NO PARTICULAR DIRECTION IS FAVOURED. THE NDB RADIATES IDENTICAL ELECTROMAGNETIC ENERGY IN ALL DIRECTIONS. FREQ RANGE 200-415KHZ.

AIRCRAFT SYSTEM HYDRAULIC SYSTEM HAS TWO MAJOR PARTS: 1. POWER SECTION WHICH PROVIDES FLUID FLOW AND REGULATES 2. ACTUATING SECTION WHICH OPERATES FLAPS, LANDING GEAR ETC

MAIN COMPONENTS: 1. RESERVOIR 2. HAND PUMP 3. ENGINE DRIVEN PUMP (EDP) 4. CHECK VALVE 5. ACCUMULATOR 6. BRAKE 7. PRESSURE GUAGE 8. FLAP 9. LANDING GEAR CYLINDER 10. RELIEF VALVE 11. FILTER

PNEUMATIC SYSTEM AIRCRAFT PNEUMATIC SYSTEM USED PRIMARILY AS EMERGENCY SOURCES OF PRESSURE. The AIR WHICH IS CLEAR AND DRY ARE STORED IN HIGH PRESSURE BOTTLE.

LANDING GEAR THE LANDING GEARO AN AIRPLANE PERFORMS VERY IMPORTANT FUCTIONS.IT SUPPORTS FOR LANDING AND TAKE OFF.IT ALSO DAMPENS VIBRATIONS WHILE LANDING.

CLASSIFICATION: 1.UNABSORBING LANDING GEAR 2. SHOCK ABSORBING LANDING GEAR SHOCK ABSORBING LANDING GEAR:

SHOCK ABSORBING LANDING GEAR DISSIPATES THE IMPACT OF ENERGY OF LANDING. THIS IS ACHIEVED BY FORCING THE FLUID THROUGH A RESTRICTED PASSAGE.

TWO TYPES OF SHOCK ABSORBING LANDING GEAR: SPRING –OLEO STRUTS: IT CONSISTS OF PISTON TYPE STRUCTURE AND A HEAVY COILED SPRING. AIR OLEO STRUT: DURING COMPRESSION OF THE STRUT AT LANDING AN ORIFICE PROVIDES A RESTRICTION OF AIR FLOW.

RETRACTABLE GEAR: IT WAS DEVELOPED TO ELIMINATE THE DRAG. THE RETRACTION IS NORMALLLY ACCOMPLISHED WITH HYDRAULIC POWER.EMERGENCY SYSTEM IS PROVIDED TO ENSURE THAT THE LANDING SYSTEM FAILURE. THE LANDING GEAR OF AN AIRPLANE IS OF PRIMARY IMPORTANCE IN THE OPERATION OF AN AIRCRAFT.

SHIMMY DAMPERS: 1.IT IS A HYDRAULIC SNUBBING UNIT THAT REDUCES THE TENDENCY OF THE NOSE TO OSCILLATE FROM SIDE TO SIDE. 2.SHIMMY DAMPERS ARE USUALLY CONSTRUCTED IN ONE OF TWO GENERAL DISIGNS a) PISTON TYPE b) VANE TPYES

LUBRICATION SYSTEM: 1.IT CARRIES HEAT FROM THE ENGINE 2.IT PROVIDES CUSHOING BETWEEN MOVING PARTS 3.IT REDUCES FRICTION BETWEEN MOVING PARTS 4.IT ACTS AS A HEAT EXCHANGER BY HEATING FUEL 5.DUE TO FLOWABILITY IT CARRIES PARTICLS 6.IT PROVIDES FILTERING AND MAGNETICS DETECTOR 7.IT ACTS AS SEAL BETWEEN AND PISTON AND CYLINDER 8.OIL BREATHER PROVIDES TO REMOVE VAPOUR 9.WARNING LIGHT ENSURES SAFE OPERTATION

TYPES OF LUBRICATION SYSTEM: 1.PRESSURE RELIEF VALVE SYSTEM 2.FULL FLOW SYSTEM 3.TOTAL LOSS SYSTEM

JET ENGINE IGNITION AND STARTING: 1.MUST BE ABLE TO ROTATE COMPRESSOR AND TURBINE AT A SPEED AT WHICH ADEQUATE AIR PASSESS INTO THE COMBUSTION TO MIX WITH FUEL 2.IGNITION OF FUEL AIR MIXTURE IN THE COMBUTION TO OCCUR IGNITION SYSTEM COMPONENTS: 1.EXCITER BOX 2.IGNITION LEAD 3.LEAD

STARTING SYSTEM FOR GAS TURBINE: 1.AIR TURBINE STARTERS(PNEUMATIC) a) LOW PRESSURE b) HIGH PRESSURE 2.ELECTRIC STARTERS 3.FUEL AIR COMBUSTION STARTERS

AUXILIARY SYSTEMS: 1.IT IS REQUIRED FOR SAFE OPERATION OF AIRCRAFT 2.IT IS PROVIDED FOR EMERGENGY SYSTEMS NOT ESSENTIAL FOR ACTUAL OPERATION ARE CALLED AUXILIARY SYSTEMS. 1.ICE AND RAIN PROTECTION 2.FIRE WARNING AND FIRE EXTINGUISHERS 3.WATER AND WASTE SYSTEM 4.WARNING SYSTEMS 5.AUXILIARY POWER UNITS(APU)

TYPES OF FIRE AND OVERHEAT SYSTEMS 1.THERMAL SWITCHES 2.THEROMCOUPLES 3.TUBULAR DETECTORS

SMOKE AND FLAME DETECTORS TYPES: 1.LIGHT DETECTION 2.LIGHT REFRACTION DETECTOR 3.IONIZATION TYPE SMOKE DETECTOR 4.SOLID STATE TYPE CLASSIFICATION OF FIRE EXTINGUISHING SYSTEM: 1.CONVENTIONAL SYSTEM 2.HIGH RATE OF DISCHARGE SYSTEM

ICE PROTECTION SYSTEM: AIRCRAFT OPERATES AT ALL WEATHER CONDITIONS WHERE IS LIKELY TO BE FORMED . AN ANTI-ICING SYSTEM PREVENTS THE FORMATION OF ICE ON THE AIRPLANE AND THE DEICING SYSTEM REMOVES THE ICE THAT HAS ALREADY FORMED . PARTS THAT ICE LIKELY TO BE FORMED: 1.WINDSHILED 2.WING LEADING EDGE 3.PROPELLERS 4.ENGING AIR INLETS 5.TAIL AIRFOIL LEADING EDGE 6.PITOT TUBES 7.WATER DRAINS

PNEUMATIC –MECH DEICING SYSTEM: INFLATABLE RUBBER BOOTS FORMED AT THE LEADING EDGE OF WING,STRUTS AND STABLISHERS. ANTI-ICING : 1.THERMAL ANTI-ICING SYSTEM 2.PROBE ANTI-ICING WIND SHIELD ICE CONTROL 1.HEATING WINDSHIELD a) BY HEATING ELEMENT b) BLOWING HOT AIR BETWEEN SHEILDS 2.BY SPRAYING FLUID ON THE WINDSHIELD SURFACE

RAIN REMOVAL SYSTEMS: TO HAVE CLEAR VIEW OF THE AIRPORT WHEN TAXING AND ALLOW THE PILOT TO SEE APPROACH PATHS WHEN TAKING OFF OR LANDING. 1.REPELLANT SYSTEM 2.PNEUMATIC RAIN REMOVAL SYSTEM

CABIN COOLING SYSTEMS: AIRCRAT COOLING SYSTEMS ALSO CALLED AIRCONDTIONING SYSTEM ARE USED TO REDUCE THE TEMPERATURE INSIDE FOR COMFORT OF CREW AND PASSENGER. TWO METHODS USED TO REDUCE THE TEMPERATURE : 1.VAPOUR CYCLE MACHING 2.AIRCYCLE MACHINE

CABIN PRESSURISATION SYSTEM: TO MAINTAIN A COMFORTABLE ENVIRONMENT FOR OCCUPANTS AT HIGH ALTITUDE. TO MAKE IT COMFORTABLE ,THE CABIN MUST NORMALLY BE PRESSURIED TO MAINTAIN THE CABIN AIR PRESSURE AT THE LEVEL REACHED AT NOT HIGHER THAN 8000FT.THIS ENABLES CREW AND PASSENGER TO FUNCTION WITHOUT THE USE OF SUPPLLEMENTARY OXYGEN AND WITH ADJUSTMENT OF THE CABIN AIR TEMP,ALLOWS THAM TO BE IN A SHIRSLEEVE ENVIRONMENT.

OXYGEN SYSTEMS: TYPE OF OXYGEN SYSTEMS CLASSIFIED ACCORDING TO THE SOURCE OF SUPPLY 1.STORED GAS 2.CHEMICAL OR SOLID STATE 3.LIQUID OXYGEN

INSTRUMENTS INSTRUMENTS ARE CLASSIFIED ACCORDING TO THE FUNCION . THREE PRINCIPLE CATEGORIES: 1.POWER PLANT INSTRUMENTS 2.FLIGHT AND NAVIGATIONAL INSTRUMENTS 3.SYSTEMS INTRUMENTS.

PURPOSE OF INTRUMENTS: 1.SAFETY OF AIRCRAFT ,CREW AND PASSENGER DEPENDS ON THE PROPER INSTALLATION AND CORRECT OPERATION OF INSTRUMENTS 2.POWER PLANT INSTRUMENTS FOREWARN THE PILOT ABOUT ENGINE FAILURE. 3.FLIGHT INSTRUMENTS INDICATE ANY IRRUGULARITY OF FLIGHT ATTITUDE OR DIRECTION .

POWER PLANT INSTRUMENTS:] 1.OIL PRESSURE INDICATOR 2.OIL TEMPERATURE INDICATOR 3.ENGINE PRESSURE RATIO GAUGE 4.FUEL QUANTITY INDICATOR 5.TACHO METER 6.EXHAUST GAS TEMPERATURE(EGT) 7.MANIFOLD PRESSURE GAUGE(PISTON ENGINE)

FLIGHT INSTRUMENTS: 1.ALTIMETER 2.AIRSPEED INDICATOR 3.ANGLE OF ATTACK INDICATOR 4.MACH METER 5.VERTICAL SPEED INDICATOR(RATE OF CLIMB INDICATOR) 6.HEADING INDICATOR 7.HORIZONTAL SITUATION INDICATOR 8.TURN AND BANK INDICATOR(TBI) 9.ACCELEROMETER 10.MAGNETIC COMPASS