考虑星敏安装误差的弹道导弹捷联星光/惯性复合制导-星光导航专栏

doi:10.7527/S1000-6893.2019.23603

Abstract

Abstract: Strapdown stellar -inertial guidance of ballistic missile is a composite guidance method based on inertial guidance supplemented by starlight correction, which can significantly improve the guidance accuracy of missile. Since the star sensor is strapdown mounted on the missile body, the installation error will affect the accuracy of stellar meas-urement and the precision of composite guidance. Thus a composite guidance method for on-line identification and correcting the star sensor installation error is proposed. The relationship between the observed amount of star sensor and platform misalignment angle and star sensor installation error is established. After the active segment of the missile is shut down, six observations are obtained by measuring three independent stars. The misalignment angle and star sensor installation error can be estimated by the least square method. Finally, optimal correction factor determination equation of stellar-inertial composite guidance is improved, and the influence of star sensor installation error is corrected directly. The simulation results show that the proposed approach can estimate the plat-form misalignment angle and the star sensor installation error effectively. The precision of strapdown stellar -inertial composite guidance is improved.

Key words: installation error of star sensor, platform misalignment angle, online identification, strapdown celestial-inertial composite guidance, optimal correction coefficient

CLC Number:

V448

References

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Strapdown stellar-inertial composite guidance method for ballistic missile considering the star sensor installation error

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