Suitable for semi-strapdown inertial measurement and navigation algorithms high speed rotation of the flying object

The present invention relates to an inertial measurement and navigation algorithm, in particular semi-strapdown inertial measurement and navigation algorithm in the high speed rotation of the flying object. The invention solves half strapdown inertial measurement system measured the movement of information not accurately reflect the problem of high-speed rotating motion information flying object. Suitable for semi-strapdown inertial measurement and navigation algorithm for the high speed rotation of the flying object, the algorithm is the following steps are implemented: 1) real-time measured three-dimensional than the force; real-time measuring three-dimensional angular rate; 2) updated in real time is calculated based to attitude matrix n lines, based opposite n-based three-dimensional acceleration, based relative n-dimensional velocity system, system to the n-dimensional position of the system, based opposite n D attitude system; 3) to solve a three-dimensional than the force; 4) Solution a three-dimensional angular velocity; 5) to solve the three-dimensional acceleration; 6) to solve a three-dimensional velocity; 7) solving three-dimensional position; 8) for solving three-dimensional attitude. The present invention is suitable for measuring high-speed rotary motion information of the flying object.