Performance O Ptimization Design And Development Of The Strap-down Attiude Reference System Base On Mems

The attitude reference system is an essential avionics system for military and civil aircraft,guided weapons,etc.The output stability and accuracy of the attitude reference system directly affect the attitude control of the aircraft.Modern aircraft require a small azimuth reference system as a backup for the main inertial navigation equipment,while future advanced aircraft require the attitude reference system to develop toward small size,low weight,and high integration.This project uses Micro Chip's PIC32 MX series 32-bit MCU as the main control unit,and designs the MEMS inertial device based attitude reference system to meet the needs of modern aircraft and the future development direction of aircraft.The improved flight performance of advanced aircraft has significant engineering application value and practical significance,and its potential application prospects and benefits are very significant.The main work of the thesis is as follows:First of all,this paper introduces the basic theory and working principle of strap-down inertial navigation,including the definition of coordinate system commonly used in inertial system,the attitude angle and coordinate transformation of carrier,and the classification of strap-down navigation algorithm.Among them,the quaternion algorithm used in this paper is mainly studied.Secondly,this paper combines the characteristics of miniaturization and high integration of the strap-down reference system to establish the overall design scheme of the system.The PIC32MZ2048 EFM is the main controller,and the accelerometer,gyroscope,barometer and GPS module are used as the measurement unit,through EAGLE and The MPLAB X IDE integrated development environment designed the Strap-down Attitude Reference System.Finally,the environmental adaptability study was carried out for the designed strapdown attitude reference system to verify the feasibility of the system design.