Research On GPS/SAR/INS Integrated Guidance Methold Of SSM

In recent years, with the development of aerospace technology, the new-style guidance technology makes the guidance precision of SSM get improved observably. In Paper, the scheme, model and algorithm of GPS/SAR/INS integrated guidance for SSM have been studied, the main contents include the followings:1. With the past, the advantages and disadvantages of various commonly used navigation system is proposed to apply to a combination of guided missile terminal guidance program that is based inertial navigation system, respectively, and synthetic aperture radar satellite navigation, supplemented by the combination.And designed the method of muti-sensor information fusion, including INS/GPS Kalman filter, INS/SAR Kalman filter and INS/GPS/SAR federal filter.2. According to the terminal flight of"PershingⅡ"type missiles, an appropriate terminal-trajectory has been designed. And introduce the theory and algorithm of INS; The principle of determining position and speed measurement of GPS; The model and principle of determining position of SAR.3. Introduce the basic theories of Kalman filter and information fusion, mainly do research on the basic formula of discrete Kalman filter and the necessary technical processing. At last, discuss the muti-sensor information fusion technology, and according to the main contents of this paper, the structure and algorithm of federal Kalman filter have been analyzed and researched.4. The performance of differenet guidance program was simulated by Matlab/Simulink. The results of simulation show that the accumulated error of single INS increased with time rapidly, the INS/GPS and INS/SAR have better position, velocity and attitude accuracy respectively, and the INS/GPS/SAR integrated guidance methold has better position ,velocity and attitude accuracy.