Abstract:

The integrated navigation technology of aircraft motion model (AMM) with medium and low accuracy strapdown inertial navigation system (SINS) is studied. Considering the uncertainty of the system equation caused by inaccurate aerodynamic coefficient and the uncertainty of the observation equation as well as the noise, the extended H∞ filter (EHF) algorithm is proposed, which is abided by the minmax principle. The simulation, which is tested on a small fixedwing UAV in both time and frequency domain, shows that for the SINS/AMM integrated navigation system, EHF performs better than the extended Kalman filter (EKF) in robustness and EHF brings approximately a 35% increasing in precision.