Study On The Hybrid Celestial-inertial Guidance Method Of Ballistic Missile

In order to improve the accuracy of missile shooting,this dissertation studies separation of guidance instrumentation error and correction method of stellar inertial combined guidance.In view of the action machanism of various initial errors and inertial guidance instrument errors in the process of missile flight,the relationships between the initial errors,the error coefficients of inertial navigation tools,star sensitive error of platform system,the strapdown system and misalignment angle are established respectively.And the calculation method of position and velocity environment function under inertial navigation systems is given.The observation equations of the star sensor are obtained from the output of the star sensor in practical and ideal conditions respectively.Finally,the calculation model of the composite guidance environment function matris is obtained.this chapter is the basis of subsequent researches.This chapter first reviews the basic principles of principal component mathod,support vector machine mathod and trajectory reconstruction mathod.the method and parameter setting of the three methods to identify the error coefficient of guidance tools is studied.The error model of the platform system is identified and the identification results are obtained under the condition of starlight information and no starlight information.The telemetry-tracking deviation of position and velocity are fitted.The identification accuracy of the three methods is compared.The identification results are reduced to the full trajectory.The fitting residuals of the three methods are obtained.The results show that SVM has better performance than the other two methods.Strapdown celestial-inertial composite guidance correction method is based on the star sensitive output contained in the information contained in the missile state correction.This chapter first derives the error identification correction method based on the strapdown star system and the misalignment angle and the error coefficient.And then according to the principle of statistics to derive the best correction coefficient method.Two kinds of correction methods are simulated and Monte Carlo shooting.The correction effect of the two methods is similar,and both of them can correct the deviation of missile placement effectively.This dissertation's studies are capable of providing theoretical bases for improving the precision of the error coefficient identification of ballistic missile,and enhancing fighting efficiency for strategic missile.