A Generic Inertial Navigation System Model for Computer Simulation Studies

Abstract : A number of Inertial Navigation System (INS) models ranging from simple forced harmonic oscillator models to three-gyro, three-accelerometer systems were studied to ascertain a compromise between accuracy and computation time on the one hand and model complexity suitable for use in avionics system models for effectiveness studies on the other. INS position and orientation errors for various cruise and acceleration conditions were predicted by these models and the results shown graphically. The importance of various INS characteristics has been determined and the effects of the relevant error sources have been isolated and their propagation in time plotted.