A configuration method for the
information fusion of a plurality of
optical flow sensors and an inertial navigation device is disclosed, which comprises the following five steps of: 1, establishing a linear disturbance kinematical equation aiming at an aircraft needing to be installed with
optical flow sensors; 2, arranging the
optical flow sensors on the aircraft in all directions and at a plurality of points; 3, establishing the measurement equation of the optical flow sensors according to the installation position and direction of each optical flow sensor on the aircraft; 4, estimating the flight state of the aircraft by utilizing EKF, that is,
extended Kalman filter method and UKF, that is, unscented
Kalman filter method respectively; and 5, realizing the specific flight mission of the aircraft by the estimated state information. In the configuration method for the
information fusion of a plurality of optical flow sensors and an inertial navigation device, a plurality of optical flow sensors and an inertial navigation device are used; and the optical flow sensors and the inertial navigation device are light in weight, small in volume, low in
power consumption, convenient to install and arrange on the aircraft, and unable to radiate
electromagnetic signal outwards, thereby enhancing the concealment of the aircraft. The configuration method for the
information fusion of a plurality of optical flow sensors and an inertial navigation device has practical value and wide application prospect in the technical fields of measurement and
estimation for the attitude,
flight speed and height of aircraft.