Strapdown stellar-inertial guidance of ballistic missiles is a composite guidance method based on inertial guidance supplemented by starlight correction. It can significantly improve the guidance accuracy of missiles. However, since the star sensor is strapdown mounted on the missile body, installation errors will inevitably affect the accuracy of stellar measurement and the precision of composite guidance. Therefore, a composite guidance method for on-line identification and correction of the star sensor installation errors is proposed. The relationship among the observations of the star sensor, the platform misalignment angle, and the 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 the star sensor installation error can be estimated by the least square method. The optimal correction factor determination equation of the stellar-inertial composite guidance is improved, and the influence of the star sensor installation error is directly eliminated. The simulation results show the effectiveness of the proposed approach in estimating the platform misalignment angle and the star sensor installation error, thus improving the precision of the strapdown stellar-inertial composite guidance.
ZHAO Yi
,
ZHANG Hongbo
,
TANG Guojian
. Strapdown stellar-inertial composite guidance method for ballistic missiles considering star sensor installation errors[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020
, 41(8)
: 623603
-623603
.
DOI: 10.7257/S1000-6893.2019.23603
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