Realization оf Inertial Navigation System on Flight Computer for Unmanned Aerial Vehicle

 

 

Nada Asanović

Ivana Trajkovski

Vladimir Vukmirica

Stojan Stanojković

 

This paper presents a realized design of a flight computer for unmaned aerial vehicle (UAV) and the implementation of an inertial navigation system (INS) in it. Inertial navigation systems usually consist of the inertial measuring unit (IMU) with three mutually perpendicular gyroscopes and accelerometers that represent three input axes to the system and the navigation algorithm. The input values for the navigation algorithm are signals of gyroscopes and accelerometers. The paper describes all flight computer components such as an inertial measurement unit (IMU), a GPS, a servo switch controller (SSC), a supply and controller board as well as software applications with the emphasis on the navigation algorithm. The procedures for each component testing as well as for inertial navigation testing are presented. The realization of a UAV flight computer with the implemented INS is a significant achievement in this kind of technology.

 

Key words: unmanned aerial vehicle, navigation system, inertial system, gyroscope, accelerometer, flight computer for unmanned aerial vehicle..