Author: Wg Cdr Rajagopal

Future Air Navigation System Global Navigation Satellite Systems FANS A1 provides communication, navigation and surveillance system Provides positive control over oceans & polar regions GNSS and Data link are used to provide efficient air-ground communications Automatic Dependent Surveillance Automatic dependent surveillance automatically sends data ATS unit receives the communication using VHF and UHF frequencies FANS-B2 FANS B2 is an improved system of FANS Provides unique digital link address for all aircrafts CPDLC CPDLC Data link messages have a fixed format Messages are activated by pilot or controllers CPDLC messages are…

Head Up Display Components of Head Up Display HUD presents flight information and guidance in a pilot’s visual line of sight In critical phases of flight, like take off or landing the system is very useful Head Up Display system consists of four components Display controller to control various modes Display guidance computer to generate symbology Overhead unit which is a projector Combiner which is a glass screen to reflect displays to pilot Ambient light sensor controls brightness and adjusts display brightness Display brightness is adjusted as per lighting in…

Inertial Reference System Introduction to Inertial Reference System Inertial reference system is a stand alone system providing accurate position Ring laser gyro and computers with high computing power are used in IRS Acceleration in pitch, roll and yaw axis is measured and integrated To compare, INS measures accelerations in East West and North South Inertial reference system is a strap down system Gyroscopes and accelerometers are fixed to airframe Reduction in moving parts increase accuracy and maintainability Sagnac Effect Ring laser gyro uses Sagnac effect of laser source to measure…

Inertial Navigation System Introduction to Inertial Navigation Systems INS is an accurate navigational aid for pilots The instrument is independent of any ground installation INS is capable of world-wide operations Advanced form of deduced reckoning is used in INS Inertial Navigation System comprises of three parts inertial navigation unit Mode selector unit Control and display unit Principle of Inertial Navigation Systems Accelerometers and Integrators are the core of Inertial Navigation Systems High grade accelerometers provide acceleration or deceleration Acceleration Integrators integrates acceleration to obtain velocity Velocity integrators further integrates velocity…

Aircraft Magnetism Introduction to Aircraft Magnetism Compass north is the north indicated by an aircraft’s compass needle Compass north deviates from magnetic north due to deviation Aircraft magnetism induces deviation error in the compass Ferrous metals and electrical fields cause aircraft magnetism Deviation is the angular difference between compass and magnetic north Compass swing procedure enables us to correct deviation in our compass Deviation Compass Swing Compass swing is used to calculate, correct and record residual error Aircraft’s compass is compared with datum compass outside the aircraft Deviation on cardinal…

Gyro Magnetic Compass Introduction to Gyro Magnetic Compass Remote indicating compass reduces limitations of direct reading compass In accurate headings during acceleration and turns High deviation due to magnetic sensing element situated in the cockpit Magnetic headings cannot be provided to other instrument Gyro magnetic compass has a directional gyro monitored by compass Drift of gyroscope is corrected by magnetic detector Gyro has a slow precession rate of 3 degrees per minute Slow precession rate damps flux valve errors of magnetic detector Construction of Gyro Magnetic Compass Gyro Magnetic compass…