Optimized Inertial Navigation System with Kalman Filter based altitude determination for aircraft in GPS Deprived Regions

The project provides solution for existing GPS based navigational issues, the proposed prototype navigation system consists of an inertial measurement unit based navigation called as inertial navigation system with barometric pressure sensor which is fused with the Global Positioning System data and that are optimized using Kalman filter to mitigate the uncertainty in the estimated values and provide accurate data of Pitch, Yaw, Roll, Heading, Altitude with Latitude and Longitude coordinates of the aircraft in an on-board Electronic Flight Instrument System to ensure safe navigation. The project would ensure high navigation solution integrity even in an environment with poor or no GPS/Satellite navigation signal that will ensure aircraft navigation even without the assistance of GPS signals.