Research On Ariborne SINS/SAR Integrated Navigation Based On Atmospheric Altitude

Airborne SINS/SAR integrated system is obtained by using high resolution SAR image, and theairplane prior to storage in the atlas of the digital image, given the airplane current positioninformation after image matching, the two complement each other, and then and inertial navigationsystem information fusion can effectively improve the navigation accuracy.Flying altitude is an important flight parameters of aerospace vehicles and essential informationof air vehicle realizing normal safe driving, accurate navigation and control, effective reconnaissanceand attack and so on. But considering the instability of altitude channel of inertial navigation system,and the defects of SAR image matching can only getting latitude and longitude information, notobtaining altitude information.Therefore, this paper studies the atmospheric altitude auxiliary airborne SINS/SAR integratednavigation method, the corresponding atmospheric altitude and inertial navigation system highlychannel information fusion method and modeling methods based on the combination of atmosphericaltitude, and it have very important theoretical significance and application value of national defense.Based on the full analysis of the barometric altimeter measurement error characteristics, toeffectively enhance inertia/atmospheric high damping system performance in the transonic, divebombing and other non stationary high dynamic flight phase, and carry out inertia/atmosphericdamping parameter design and theoretical study, this Paper proposes the working pattern adjustmentand dynamic parameter adjustment scheme which based on the classical control theory, thus providethe theoretical basis for improving the performance of inertia/atmospheric altitude channelinformation fusion in transonic and other flight phases.Meanwhile this Paper combines the existing inertia/atmospheric high damping basic designmethod, analyzes and establishes the inertia/atmospheric damping system complementary filter model,and contrasts with inertia/atmospheric combination kalman system model theoretically. At the sametime this Paper also puts forward inertial navigation system in transonic section pressure altimeter andGPS information two step fusion method, in order to eliminate pressure altitude value violent change,through the establishment of pressure altimeter/GPS/inertial navigation system integrated navigationsystem state equation and measurement equation, and ultimately obtain the optimal estimation ofinertial altitude channel state.After analyze SAR’s error sources and error form, it proposes a quasi real-time integrated navigation filtering scheme and algorithm, effectively solve the SINS/SAR integrated navigationsystem of measuring hysteresis effect. In the meantime, puts forward atmospheric altitude aidedSINS/SAR combination adaptive filtering scheme and algorithm to solve the measuring hysteresiseffect of SINS/SAR integrated navigation system, and using adaptive filtering algorithm in thephenomenon of altitude error appearing mutation in the atmospheric system transonic and other flyingstages, in order to improve and promote the comprehensive performance of integrated navigationsystem effectively.Finally, based on the overall scheme of atmospheric altitude auxiliary airborne SINS/SARintegrated navigation system, it researches airborne SINS/SAR integrated navigation datavisualization simulation based on FlightGear, and also designs and realizes the atmospheric altitudeauxiliary airborne SINS/SAR integrated navigation simulation system, to provide support for therealization of subsequent atmospheric altitude auxiliary airborne SINS/SAR integrated navigationsystem engineering.