Research On Strapped Stellar/SINS Composite Guidance Method Of Ballistic Missle

This paper takes the ballistic missile Strapped Stellar/SINS Composite Guidance System as the application background.In order to eliminate the larger initial error conditions of the precise guidance requirements for the purpose of research,make the preliminary design of a new triple nav-star Strapped Stellar/SINS Composite Guidance System.Research has been carried out the key technology and the installation errors of star sensor are combined to generate a real navigation star map database catalog.To identify the installation errors of star sensor,this paper established SINS/CNS the initial error,instrument error coefficient of inertial navigation devices and loss model angle calculation method,gives two kinds of position / velocity error function under SINS/CNS environment,as well as in the installation does not consider the star sensor observation equation error under the condition of actual and ideal output obtained star sensor.The alignment of the principle through the derivation of non-collinear two vectors,this paper proposes the use of three stars of the SINS/CNS scheme is derived on the two navigation stars scheme consider star sensor measurement equation of star sensor installation error conditions,the optimal correction coefficient method to attain the highest point precision,different star sensor measurement and generate different installation errors of star sensor measuring star process under the conditions to do the simulation analysis,to verify the correctness of the star sensor installation error identification method.According to the real star catalog database generation navigation requirements,this paper first compares the various objects catalog commonly used in academic research,the final selection of the Hipparcos catalogue as generated on board guide catalog of original catalogue,and the Hipparcos catalogue for a simple quantitative analysis of different stars and the sky distribution analysis,and from the nebula cluster the characteristics of the latest release of RNGC;and then the star information from the international celestial reference system to launch inertial coordinate matrix,makes a detailed analysis on the distribution of stars in launch inertial system;according to the influence of different objects on Star selection process in SINS/CNS,put forward different methods of avoiding fast objects.At the end of the SINS/CNS process of the whole trajectory simulation,obtained the triple guide star program under the new star sensor installation error correction can improve missile accuracy conclusion.This research can provide a research idea for the larger initial error correction of inertial navigation,and provide a theoretical basis for improving the accuracy of SINS/CNS in our country.