Abstract:

The micro electro mechanical systems (MEMS) inertial navigation system (INS) of an aircraft has low measure accuracy, so that the navigation error rapidly drifts. For this shortage, an aircraft dynamics (AD)aided MEMS INS method is proposed. The method is based on the AD model and the dynamic error model, using realtime dynamic calculation information to build Kalman filter to estimate and correct MEMS INS error. Further more, considering the improved algorithm when integrating INS/global positioning system (GPS) navigation, an arithmetic is proposed which evaluates aircraft dynamic error by making use of GPS information and the predictive filter. Finally, the hardwareintheloop simulation test result shows that the aircraft dynamicsaided system can effectively reduce INS system error and improve the MEMS INS output accuracy.