| In Inertial Guidance method, the error angle of the platform caused by initial errors and platform tool errors will lead to landing errors. Based on the starlight vector, the Inertial-Stellar Integrated Guidance method can improve the landing accuracy by correcting the landing errors. Trajectory conversion is a method that can evaluate the full trajectory deviation from the short range test information. At the hypothesis that the error-coefficients in the air and on the ground are consistent, the full trajectory deviation can be calculated by using the short rang multi source information which can identify the short range error-coefficient. This paper mainly analyzed the error-coefficient identification of Single-Star Platform Inertial-Stellar Integrated Guidance method and the landing errors conversion method.Firstly, models of initial errors and inertial guidance tool errors are discussed. Functions on the relationship between the error angle of the platform and the two errors are established. Secondly, by deducing the environment function matrix, a new method to verify it is also put forward in this paper. The simulation results indicate that the remote heterodyne error calculated by the environment function matrix can satisfy the accuracy requirement. Then, the error-coefficient identification results based on the short range ballistic multi source information in apparent-velocity and apparent-position is compared. Lastly, a landing errors conversion and accuracy evaluation have been done. Star sensor measure information is simulated and platform drift error in the landing errors is corrected. The final results indicate that the Inertial-Stellar Guidance method can highly improve the missile landing accuracy.The research in this paper is closely combined with the accuracy engineering of one of our country's new missile. The work and achievement can provide theoretical and technical support to the research and development of our country's strategic missiles. |
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